GLOBAL TRANSPORTATION SYSTEM AND METHOD FOR PLACING A PAYLOAD INTO A CIRCULAR ORBIT
20220055778 · 2022-02-24
Inventors
Cpc classification
B64G5/00
PERFORMING OPERATIONS; TRANSPORTING
B64G1/10
PERFORMING OPERATIONS; TRANSPORTING
B64G99/00
PERFORMING OPERATIONS; TRANSPORTING
International classification
B64G99/00
PERFORMING OPERATIONS; TRANSPORTING
B64G1/10
PERFORMING OPERATIONS; TRANSPORTING
B64G1/24
PERFORMING OPERATIONS; TRANSPORTING
Abstract
The disclosure relates to space science and space transportation, in particular, to the area of commercial exploitation of outer space, and, namely—to the structure of multiple-mission geospatial transportation complex and method of operation thereof, based on the principle of non-rocket ‘planet surface to planned circular orbit’ payload insertion. A general planetary geospatial transportation complex, according to a first variant includes a general planetary vehicle encircling the planet along the line of the planet surface cross-section by the plane parallel to plane of the equator, fastened, on launch overpass of specified altitude, and represents a linear bearing structure encircling the planet, comprising pressure hull with the special endless linear flywheels, equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives. For a general planetary geospatial transportation complex, it is distinctive that the present intended use is to solve the set of geospatial problems in industrial-scale volumes, for instance, for the purpose of relocation of ecologically harmful portion of earth-based manufacturing into near space and non-rocket space industrialization, as well as stabilization of the global climate.
Claims
1. A general planetary geospatial transportation complex, comprising: a general planetary vehicle encircling a planet along a line of a planet surface cross-section by a plane parallel to a plane of an equator, fastened on a launch overpass of an altitude h, m, defined by a ratio:
10.sup.−7≤h/R≤10.sup.−4, (1) where R, m,—a radius of the planet in a plane of arranging the launch overpass, and representing a linear bearing structure encircling the planet and having a length L.sub.0, m, comprising a pressure hull with at least two vacuum channels, ringing around the planet, in a first one of which a first endless planet-encircling linear flywheel is located, and in a second one—a second endless planet-encircling linear flywheel is located; wherein the first linear flywheel and the second linear flywheel are contactlessly positioned in relation to walls of the corresponding vacuum channels and equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives of the first flywheel and the second flywheel, respectively, configured to accelerate linear flywheels to a velocity of V.sub.0, m/sec, defined by a ratio:
1.1≤V.sub.0/V.sub.eh≤5, (2) where V.sub.eh, m/sec,—a first cosmic velocity at the altitude h, m; a linear bearing structure being equipped with transportation compartments and configured to be elongated without uniformity loss, defined by a ratio:
1.01≤L.sub.H/L.sub.0≤1.25, (3) where L.sub.H, m,—length of linear bearing structure at circular orbit of the altitude H, m, and the linear flywheels having masses m.sub.1 and m.sub.2, kg, defined by a ratio:
0.1≤m.sub.1/m.sub.2≤10; and (4) wherein drives of the linear flywheels are connected with a power supply source via control and communication systems.
2. A general planetary geospatial transportation complex, comprising: a general planetary vehicle encircling a planet along a line of a planet surface cross-section by a plane parallel to a plane of an equator, fastened in liquid of a planetary ocean at a launch depth h.sub.v, m, defined by a ratio:
10.sup.−7≤h.sub.v/R.sub.v≤10.sup.−4, (5) where R.sub.v, m,—a radius of the planet in a plane of arranging the general planetary vehicle in the liquid of the planetary ocean, and representing a linear bearing structure encircling the planet and having a length L.sub.0, m, comprising a pressure hull with at least two vacuum channels, ringing around the planet, in a first one of which a first endless planet-encircling linear flywheel is located, and in a second one—a second endless planet-encircling linear flywheel is located; wherein the first and the second linear flywheels are contactlessly positioned in relation to walls of the corresponding vacuum channels and equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives of the first flywheel and the second flywheel, respectively, configured to accelerate the linear flywheels to velocity of V.sub.0, m/sec, defined by a ratio:
1.1≤V.sub.0/V.sub.vh≤5, (6) where V.sub.vh, m/sec,—a first cosmic velocity at a launch depth h.sub.v, m; wherein a linear bearing structure is equipped with transportation compartments and configured to be elongated without uniformity loss, defined by a ratio (3):
1.01≤L.sub.H/L.sub.0≤1.25; wherein the linear flywheels have masses m.sub.1 and m.sub.2, kg, defined by a ratio (4):
0.1≤m.sub.1/m.sub.2≤10; wherein the general planetary vehicle is performed with a launch density ρ.sub.1v, kg/m.sup.3, defined by the ratio:
0.5≤ρ.sub.2/ρ.sub.1v≤2, (7) where ρ.sub.2, kg/m.sup.3,—a density of the liquid of the planetary ocean at the launch depth h.sub.v, m; and wherein drives of the linear flywheels are connected with a power supply source via control and communication systems.
3. A general planetary geospatial transportation complex, comprising: a general planetary vehicle encircling a planet along a line of a planet surface cross-section by a plane parallel to a plane of an equator, fastened in a gaseous environment of a planetary atmosphere at a launch altitude h.sub.l, m, defined by a ratio:
10.sup.−7≤h.sub.l/R.sub.l≤10.sup.−2, (8) where R.sub.l, m,—a radius of the planet in a plane of arranging the general planetary vehicle in the gaseous environment of the planetary atmosphere, and representing a linear bearing structure encircling the planet and having a length L.sub.0, m, comprising a pressure hull with at least two vacuum channels, ringing around the planet, in a first one of which a first endless planet-encircling linear flywheel is located, and in a second one—a second endless planet-encircling linear flywheel is located; wherein the first linear flywheel and the second linear flywheel are contactlessly positioned in relation to walls of the corresponding vacuum channels and equipped with systems of magnetic and/or electromagnetic suspension and linear electromagnetic drives of the first flywheel and the second flywheel, respectively, configured to accelerate the linear flywheels to a velocity of V.sub.0, m/sec, defined by a ratio:
1.1≤V.sub.0/V.sub.lh≤5, (9) where V.sub.lh, m/sec,—a first cosmic velocity at a launch altitude h.sub.l, m; wherein a linear bearing structure is equipped with transportation compartments and configured to be elongated without uniformity loss, defined by a ratio (3):
1.01≤L.sub.H/L.sub.0≤1.25; wherein the linear flywheels have masses m.sub.1 and m.sub.2, kg, defined by a ratio (4):
0.1≤m.sub.1/m.sub.2≤10; wherein the general planetary vehicle is performed with a launch density ρ.sub.1l, kg/m.sup.3, defined by a ratio:
0.1≤ρ.sub.3/ρ.sub.1l≤2, (10) where ρ.sub.3, kg/m.sup.3,—a density of the gaseous environment of the planetary atmosphere at a launch altitude h.sub.l, m; and wherein drives of the linear flywheels are connected with a power supply source via control and communication systems.
4. The general planetary geospatial transportation complex according to claim 1, wherein the transportation compartments are both inside a body of the linear bearing structure, or are fastened outside thereupon.
5. The general planetary geospatial transportation complex according to claim 1, wherein the general planetary vehicle is equipped by a linear ballast system, covering the planet and uniformly loaded along its entire length with a liquid and/or gaseous ballast.
6. The general planetary geospatial transportation complex according to claim 1, wherein the linear bearing structure of the general planetary vehicle is made from elastically deformable material with a modulus of elasticity E, Pa, within a range of:
10.sup.8≤E≤5×10.sup.11 (11).
7. The general planetary geospatial transportation complex according to claim 1, wherein the linear bearing structure is embodied as telescopically interconnected units.
8. The general planetary geospatial transportation complex according to claim 1, wherein the linear bearing structure is embodied as units interconnected by bellows.
9. The general planetary geospatial transportation complex according to claim 2, wherein the launch density ρ.sub.1v, kg/m.sup.3, of the general planetary vehicle is secured by a pontoon fastening the linear bearing structure in the liquid of the ocean at the depth h.sub.v, m.
10. The general planetary geospatial transportation complex according to claim 3, wherein the launch density ρ.sub.1l, kg/m.sup.3, of the general planetary vehicle is secured by balloons fastening the linear bearing structure in the gaseous environment of the atmosphere at the altitude h.sub.l, m.
11. The general planetary geospatial transportation complex according to claim 1, further comprising fixing locks of the linear bearing structure at the launch altitude h, m, or h.sub.v, m, or h.sub.l, m, respectively in the overpass which is an elevated structure, in a liquid of an ocean or in a gaseous environment of a planetary atmosphere, along the entire length L.sub.0, m.
12. A method for planet surface to circular orbit payload insertion, the method comprising: (a) using a general planetary geospatial transportation complex comprising a general planetary vehicle encircling a planet along a line of a planet surface cross-section by a plane parallel to a plane of an equator; (b) holding general planetary vehicle, along its entire length L.sub.0, m, on a launch overpass of an altitude h, m, and/or a liquid of an ocean at a launch depth h.sub.v, m, and/or in a gaseous environment of a planetary atmosphere at a launch altitude h.sub.l, m, by fixing locks of a linear bearing structure in initial launch position; (c) placing payload of total mass m.sub.3, kg, uniformly along the entire length L.sub.0, m, of the linear bearing structure in transportation compartments; (d) accelerating at least one linear flywheel at least by 10% in a co-rotational direction to a velocity of V.sub.0, m/sec, exceeding a first cosmic velocity V.sub.eh, m/sec, at the altitude h, m, of the launch overpass, and/or V.sub.vh, m/sec,—the first cosmic velocity in the liquid of the ocean at the launch depth h.sub.v, m, and/or V.sub.lh, m/sec,—the first cosmic velocity being in the gaseous environment of the planetary atmosphere at the launch altitude h.sub.l, m; (e) executing a launch of the general planetary vehicle via detachment thereof along its entire length L.sub.0, m, of the fixing locks of the linear bearing structure; (f) lifting of a payload of a total mass m.sub.3, kg, with use of the linear bearing structure of the general planetary vehicle on a planned circular orbit of the altitude H, m, centrifugally, due to action of at least one linear flywheel; (g) achieving circumferential velocity of the linear bearing structure of the general planetary vehicle around the planet in the co-rotational direction, equal to the first cosmic velocity V.sub.1H, m/sec, on the planned circular orbit of the altitude H, m, above the surface of the planet, via deceleration of a first of the at least one linear flywheel and transmission of energy, produced due to deceleration thereof, to acceleration of a second of the at least one linear flywheel in a counter direction; (h) shutting down solenoid actions of both of the first and the second of the at least one linear flywheel on the planned circular orbit of the altitude H, m, above the surface of the planet and unloading of the transportation compartments of the general planetary vehicle; (i) returning of the general planetary vehicle into an initial launch position by lowering an altitude of deployment of the linear bearing structure of the general planetary vehicle from a circular orbit of the altitude H, m, over the planet surface, to a value h, m, or h.sub.v, m, or h.sub.l, m, respectively in the overpass, in the liquid of the ocean or in the gaseous environment of the planetary atmosphere, via the deceleration of one of the linear flywheels and the acceleration of another of the at least one linear flywheel in the counter direction to receive zero circumferential velocity by the linear bearing structure of the general planetary vehicle in relation to the planet; and (j) clamping the general planetary vehicle into the initial launch position, upon its return, with use of the fixing locks of the linear bearing structure along its entire length L.sub.0, m.
13. The method according to claim 12, wherein linear force N.sub.1, N/m, of the acceleration and/or the deceleration of the first and the second linear flywheels is applied uniformly along entire length thereof via linear electromagnetic drives.
14. The method according to claim 12, wherein during operation of general planetary vehicle, along the entire length of its linear flywheels, linear force N.sub.1, N/m, of the acceleration and/or the deceleration, is regulated with regard to a rated value of a linear force N.sub.0, N/m, within a range determined by a ratio:
0.9≤N.sub.1/N.sub.0≤1.1 (12).
15. The method according to claim 12, further comprising uniformly loading, as part of the payload, in an amount of 0.1-10% of its mass m.sub.3, kg, a liquid and/or a gaseous ballast along the entire length L.sub.0, m, of the linear bearing structure.
16. The method according to claim 12, using as ballast, ecologically friendly to Planet Earth substances and materials including at least one of: water and/or compressed, and/or liquid air and/or oxygen, and/or nitrogen.
17. The method according to claim 12, further comprising restoring an ozone hole during lifting of the general planetary vehicle onto the circular orbit of the altitude H, m, to improve weather and to stabilize climate on Planet Earth as a result of its spraying in the planetary atmosphere.
Description
BRIEF DESCRIPTION OF DRAWINGS
[0061] The essence of the present invention is clarified with use of drawings,
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[0082] Item numbers on drawings:
1—planet 1;
2—section line of planet surface received by plane parallel to plane of the equator;
3—plane parallel to plane of the equator;
4—plane of the equator;
4.1—the equator of planet;
5—general planetary vehicle (GPV);
6—launch overpass;
6.1—pillars—supports;
6.2—superstructures;
6.3—network passages;
6.4—floating support;
6.5—counterweight;
6.6—tension cable;
7—linear bearing structure of GPV, encircling the planet;
8—pressure hull of GPV;
9—vacuum channel of linear bearing structure of GPV;
9.1—first vacuum channel;
9.2—second vacuum channel;
10—endless linear flywheel, encircling the planet;
10.1—first endless linear flywheel;
10.2—second endless linear flywheel;
10.3—closed multilayer endless flywheel belt;
11—system of magnetic and/or electromagnetic suspension of endless linear flywheel;
11.1—system of magnetic and/or electromagnetic suspension of first endless linear flywheel;
11.2—system of magnetic and/or electromagnetic suspension of second endless linear flywheel;
12—system of linear electromagnetic drive of endless linear flywheel;
12.1—system of linear electromagnetic drive of first endless linear flywheel;
12.2—system of linear electromagnetic drive of second endless linear flywheel;
13—planned circular orbit;
14—payload of GPV;
15—transportation compartments of GPV;
15.1—built-in transportation compartments;
15.2—detachable (mounted) transportation compartments;
16—linear power supply source;
17—control system;
18—energy communications system;
19—locks for fixing of linear bearing structure;
20—liquid of planetary ocean;
21—planetary ocean bed;
21.1—anchoring block on planetary ocean bed;
21.2—anchoring block on hard surface of planet;
22—pontoon means;
23—gaseous environment of planetary atmosphere;
24—balloon;
25—linear ballast system, covering the planet;
26—ballast;
27—unit of pressure hull of GPV;
28—telescopic connection of units of pressure hull of GPV;
29—bellow;
30—orbital circular (ringing around planet) complex.
h, m—altitude of launch overpass;
H, m—altitude of planned circular orbit;
L.sub.0, m—length of linear bearing structure;
R, m—radius of planet in plane of arranging launch overpass;
V.sub.eh, m/sec—first cosmic velocity at altitude h, m;
V.sub.1H, m/sec—first cosmic velocity at altitude H, m
h.sub.v, m—launch depth of GPV at launch in liquid of planetary ocean;
R.sub.v, m—radius of planet in plane of arranging GPV in liquid of planetary ocean;
V.sub.vh, m/sec—first cosmic velocity at launch depth h.sub.v, m;
ρ.sub.1v, kg/m.sup.3—launch density of GPV at launch depth h.sub.v, m;
ρ.sub.2, kg/m.sup.3—density of liquid of planetary ocean at launch depth h.sub.v, m;
h.sub.l, m—launch altitude of GPV at launch in gaseous environment of planetary atmosphere;
R.sub.l, m—radius of planet in plane of arranging GPV in gaseous environment of planetary atmosphere;
V.sub.lh, m/sec—first cosmic velocity at launch altitude h.sub.l, m;
ρ.sub.1l, kg/m.sup.3—launch density of GPV at launch altitude h.sub.l, m;
ρ.sub.3, kg/m.sup.3—density of gaseous environment of planetary atmosphere at launch altitude h.sub.l, m;
V.sub.0, m/sec—acceleration rate of one of linear flywheels;
P, N,—centrifugal force;
N, N—force of longitudinal stretching of GPV;
r.sub.p,—reference radius of orbit of one of linear flywheels;
R.sub.e, m,—radius of the equator of planet 1;
φ, rps,—angular velocity of one of linear flywheels;
{dot over (r)}.sub.p, m/sec,—radial velocity of GPV;
φ, °,—turning angle of orbit of one of linear flywheels;
δ, °,—center angle;
F.sub.1, N, and F.sub.2, N,—elastic forces, acting on ends of a member corresponding to arc with center angle δ, °, of linear bearing structure of GPV;
F, N,—equivalent elastic force in element corresponding to arc with center angle δ, °, of linear bearing structure of GPV;
G, N,—planetary gravity force;
Q, N,—drag force of gaseous environment of planetary atmosphere;
X and Y—x-axis and y-axis, respectively.
DETAILED DESCRIPTION
[0083] The essence of the claimed invention is further presented in a closer detail as follows.
[0084] The claimed general planetary geospatial transportation complex by Yunitski (see
10.sup.−7≤h/R≤10.sup.−4, (1)
where R, m,—radius of planet 1 in plane 3 of arranging launch overpass 6.
[0085] Alternatively, specific launch overpass 6 can be constructed according to any existing technologies of building overpasses, for example, manufactured according to SkyWay technology, which is based on use, as bearing structure, of continuous prestressed track structure, positioned along the equator 4.1. Altitude of launch overpass 6 depending on relief varies from several meters to several hundred meters and may include (see
[0086] Optimal altitude h, m, of launch overpass 6 is the value determined by the ratio (1). Under these conditions, the costs of manufacturing, maintenance and operation of general planetary vehicle 5 are minimized.
[0087] Decrease in altitude h, m, of launch overpass 6 below the lower boundary of value h/R=10.sup.−7, defined by the ratio (1), i.e. at h/R<10.sup.−7, does not allow to meet requirements on reduction of costs for construction of launch overpass 6 while adhering to the design assignment of general planetary vehicle 5, whereas increase of its altitude h, m, above the upper boundary of value h/R=10.sup.−4, defined by the ratio (1), i.e. at h/R>10.sup.−4, does not allow to reach maximum altitude of positioning launch overpass 5 above surface of planet 1 (see
[0088] Hereby, general planetary vehicle 5 (see
[0089] By linear flywheel 10, is meant a seizing planet 1 giant annular closed rim in the form of open torus rotatably mounted around the joint with planet 1 center of mass. Linear flywheel 10 may be realized in various technical embodiments, for instance, as closed multilayer endless belt 10.3, which represents a kind of rotor of linear electromagnetic motor with linear electromagnetic drive (see
[0090] Both linear flywheels 10.1 and 10.2 are contactlessly positioned in relation to walls of the relevant vacuum channel 9.1 or 9.2, and equipped with the systems of magnetic and/or electromagnetic suspension 11, respectively 11.1 and 11.2, and linear electromagnetic drives 12, accordingly, 12.1 and 12.2. Hereby, systems of magnetic and/or electromagnetic suspension 11 and linear electromagnetic drives 12 are configured to accelerate linear flywheels 10 up to velocity V.sub.0, m/sec, determined by the ratio:
1.1≤V.sub.0/V.sub.eh≤5, (2)
where V.sub.eh, m/sec,—first cosmic velocity at altitude h, m.
[0091] Acceleration of at least one of linear flywheels 10 up to velocity V.sub.0, m/sec, determined from ratio (2), makes it possible to achieve, at minimum required energy consumption, balancing of attraction force from planet towards general planetary vehicle 5 and its subsequent launch into space with lifting to planned circular orbit 13 of altitude H, m, and reaching of first cosmic (circumferential around planet 1) velocity V.sub.1H, m/sec, by pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5 at planned circular orbit 13 of altitude H, m.
[0092] Thus, the optimum velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 to provide accumulation of kinetic energy and the launch amount (angular momentum) of motion sufficient to launch general planetary vehicle 5 and ensure it enters space into planned circular orbit 13 with payload 14 (see
[0093] Reduction in velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 below the lower boundary V.sub.0/V.sub.eh=1.1, determined by the ratio (2), i.e. at V.sub.0/V.sub.eh<1.1, does not allow to meet the requirements of stable and reliable operation of general planetary vehicle 5 at launch, in dense atmosphere, as well as limits the altitude of cosmic orbit on which general planetary vehicle 5 can be inserted, as well as the circumferential (orbital) velocity of linear bearing structure 7, and, correspondingly, mass of payload 14—passengers and cargoes—inserted into planned circular orbit 13 (see
[0094] Increase in velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 above the upper boundary of value V.sub.0/V.sub.eh=5, determined by the ratio (2), that is, at V.sub.0/V.sub.eh>5, leads to unjustified increase in energy costs required to ensure the operability of general planetary vehicle 5 in accordance with the design assignment. This is due to excess kinetic energy of flywheels 10 at launch, which can lead to the destruction of linear structure 7 due to its excessive elongation (increase in the diameter of ring encircling planet 1) in the process of entering a critically high orbit, that is, due to excessive increase in altitude of cosmic orbit onto which general planetary vehicle 5 and, accordingly, the payload 14 can be inserted.
[0095] Linear bearing structure 7 is equipped with transportation compartments 15, both built-in—15.1, and detachable (mounted)—15.2 (see
1.01≤L.sub.H/L.sub.0≤1.25, (3)
where L.sub.H, m,—length of linear bearing structure 7 on planned circular orbit 13 of altitude H, m.
[0096] The range of elastic extension of linear bearing structure 7 without loss of continuity indicated in the ratio (3) is due to the range of change in length L.sub.0, m of linear bearing structure 7 in launch state and length L.sub.H, m, of this linear bearing structure 7 on planned circular orbit 13 of altitude H,
[0097] Embodiment of linear bearing structure 7 and, accordingly, of general planetary vehicle 5 with possibility of their elastic extension without loss of continuity with values of ratio (3) L.sub.H/L.sub.0<1.01, does not allow to put linear bearing structure 7 to planned circular orbit 13 of assigned altitude H,
[0098] In its turn, linear flywheels 10, respectively, 10.1 and 10.2, have corresponding masses m.sub.1 and m.sub.2, kg, defined from the ratio:
0.1≤m.sub.1/m.sub.2≤10; (4)
[0099] Embodiment of linear flywheels 10.1 and 10.2 with corresponding masses m.sub.1m.sub.2, kg, specified in the ratio (4), is conditioned by the modes of realization of processes of launch into space and return landing on planet 1 of general planetary vehicle 5 with use of launch kinetic energy accumulated therein and launch amount (angular momentum) of motion.
[0100] Optimal for carrying out launch of general planetary vehicle 5 into space on planned circular orbit 13 of assigned altitude H, m, and ensuring all stages of its motion, including launch, lifting, hovering on planned circular orbit 13 with the planned circumferential (orbital) velocity V.sub.1H, m/sec, and return to planet 1, appears to be embodiment of linear flywheels 10.1 and 10.2 with corresponding masses m.sub.1 and m.sub.2, kg, indicated in the ratio (4).
[0101] Embodiment of linear flywheels 10.1 and 10.2 with masses m.sub.1 and m.sub.2, kg, ratio of which is less than 0.1 or more than 10, leads either to reduction in efficiency of general-planet vehicle 5 as a whole, or to significant and impractical increase of velocity (rotation) of at least one of linear flywheels at the moment of launch of general planetary vehicle 5 from planet 1, which causes considerable complication and increase of cost of realization of the entire project on transportation complex. In addition, this will lead to additional losses of significant portion of energy when it is switched from one flywheel, which is slowed, with its drive is operating in generator mode, to another flywheel, which at this time accelerates in counter-direction.
[0102] Systems 11 of magnetic and/or electromagnetic suspension and drives 12 of linear flywheels 10 along their entire length L.sub.0 are connected to linear power supply source 16, embodied, for example, in the form of linear (running along linear bearing structure 7) power supply system, capable of including a variety of possible combinations of generating power systems available on planet 1, through control system 17 and power communication system 18 (see
[0103] General planetary vehicle 5 is also equipped with fixing locks 19 for fastening linear bearing structure 7 to the launch overpass 6 along the entire length L.sub.0, m, which automatically operate and release linear bearing structure 7 at the moment of its launch from planet 1 and fix the position of linear bearing structure 7 of general planetary vehicle 5 in the initial position when it returns to planet 1 (see
[0104] The above mentioned result is also achieved by the fact that the claimed general planetary geospatial transportation complex by Yunitski (see
10.sup.−7≤h.sub.v/R.sub.v≤10.sup.−4, (5)
where R.sub.v, m,—radius of planet 1 in plane 3 of arranging general planetary vehicle 5 in liquid 20 of ocean of planet 1.
[0105] Location of general planetary vehicle 5 in liquid 20 of ocean of planet 1 at launch depth h.sub.v, m, indicated in the ratio (5) is due to optimization of technology for construction and maintenance of general planetary vehicle 5 at its launch from liquid 20 of ocean.
[0106] Optimal value of launch depth hv, m, of immersion of general planetary vehicle 5 into liquid 20 of planet 1 ocean is the value determined by the ratio (5). Under these conditions, the manufacturing, maintenance and operation costs of general planetary vehicle 5 are minimized and buoyancy of liquid 20 is maximized.
[0107] Decrease in launch depth h.sub.v, m, of submerging general planetary vehicle 5, below the lower boundary of the ratio (5) h.sub.v/R.sub.v=10.sup.−7, that is, when it will have value lower than 10.sup.−7, does not allow to eliminate possible negative impact on operation of general planetary vehicle 5 as a result of possible atmospheric wind, seismicity, and other natural factors that may cause, inter alia, roughness of liquid 20 on the ocean surface, and increase of its value above the upper boundary, determined by the ratio (5), of the ratio (5) h.sub.v/R.sub.v=10.sup.−4, i.e. when it will have value above 10.sup.−4, does not allow to effectively perform, at such substantial depth, high-tech maintenance of general planetary vehicle 5 and meet the requirement to reduce the cost of its operation.
[0108] At the same time, similar to the first variant of the claimed invention, it is characteristic that general planetary vehicle 5 is, in this case, represents a linear bearing structure 7 of length L.sub.0, m, encircling the planet 1, comprising pressure hull 8 with at least two vacuum channels 9, respectively, 9.1 and 9.2, also encircling planet 1, with endless linear flywheels 10 fastened therein. Hereby, first linear flywheel 10.1 is arranged in first vacuum channel 9.1 and second linear flywheel 10.2 is arranged in second vacuum channel 9.2.
[0109] By linear flywheel 10, as in the first embodiment of the invention, is meant a seizing planet 1 giant annular closed rim in the form of open torus rotatably mounted around the joint with planet 1 center of mass.
[0110] Both linear flywheels 10.1 and 10.2 are contactlessly positioned in relation to walls of the relevant vacuum channel 9.1 or 9.2, and equipped with the systems of magnetic and/or electromagnetic suspension 11, respectively 11.1 and 11.2, and linear electromagnetic drives 12, accordingly, 12.1 and 12.2, of first and second linear flywheels 10.1 and 10.2, respectively (see
1.1≤V.sub.0/V.sub.vh≤5, (6)
where V.sub.vh, m/sec,—first cosmic velocity at launch depth h.sub.v, m.
[0111] Acceleration of at least one of linear flywheels 10 up to velocity V.sub.0, m/sec, determined from ratio (6), makes it possible to achieve balancing of attraction force from planet 1 towards general planetary vehicle 5 and its launch into space at minimum required energy consumption.
[0112] Thus, the optimum velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 to provide accumulation of kinetic energy and the launch amount (angular momentum) of motion sufficient to launch general planetary vehicle 5 and ensure it enters space into planned circular orbit 13 from thickness of liquid 20 of ocean of planet 1, is a value determined by the ratio (6). Under the specified limits, energy costs necessary to ensure the operability of general planetary vehicle 5 are minimized.
[0113] Reduction in velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 below the lower boundary V.sub.0/V.sub.vh=1.1, determined by the ratio (6), i.e. at V.sub.0/V.sub.vh<1.1, does not allow to meet the requirements of stable and reliable operation of general planetary vehicle 5 at launch, in thickness of liquid 20, in dense atmosphere, as well as limits the altitude of cosmic orbit on which general planetary vehicle 5 can be inserted, as well as the circumferential (orbital) velocity V.sub.1H, m/sec, of linear bearing structure 7.
[0114] Increase in velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 above the upper boundary V.sub.0/V.sub.vh=5, determined by the ratio (6), i.e. at V.sub.0/V.sub.vh>5, leads to unjustified hike in energy costs required to ensure the operability of general planetary vehicle 5 according to the design assignment and excessively increases altitude H, m, of planned circular orbit 13.
[0115] Linear bearing structure 7, similar to the first embodiment of the invention, is also provided (see
1.01≤L.sub.H/L.sub.0≤1.25;
[0116] Substantiation of the range of elastic extension of linear bearing structure 7 without loss of continuity indicated in the ratio (3) is similar to the justification of this range given as such for the first embodiment and due to the range of change of length L.sub.0, m, of linear bearing structure 7 in launch state at launch depth h.sub.v, m, and length L.sub.H, m, of this linear bearing structure 7 on planned circular orbit 13 of altitude H,
[0117] In turn, linear flywheels 10, respectively, 10.1 and 10.2, by analogy with justification of the choice of value of their masses m.sub.1 and m.sub.2, kg, specified in the first variant of embodiment of general planetary vehicle 5, have the corresponding masses m.sub.1 and m.sub.2, kg, defined by the ratio (4):
0.1≤m.sub.1/m.sub.2≤10;
[0118] Embodiment of linear flywheels 10.1 and 10.2 with masses m.sub.1 and m.sub.2, kg, ratio of which is less than 0.1 or more than 10, leads either to reduction of efficiency of general planetary vehicle 5, or to significant and impractical increase of velocity (rotation) of at least one of linear flywheels at the moment of launch of general planetary vehicle 5 from planet 1, which leads to considerable complication and increase of cost of realization of the entire project on transportation complex.
[0119] Hereby, general planetary vehicle 5, according to the second variant of the claimed invention, is embodied with launch density ρ.sub.1v, kg/m.sup.3, defined by the ratio:
0.5≤ρ.sub.2/ρ.sub.1v≤2, (7)
where ρ.sub.2, kg/m.sup.3,—density of liquid 20 of ocean of planet 1 at launch depth h.sub.v, m.
[0120] In this case, launch density ρ.sub.1v, kg/m.sup.3, of general planetary vehicle 5 should be understood to mean the mass of the structure in unit volume of general planetary vehicle 5 in its prelaunch state at launch depth h.sub.v, m, in liquid 20 of ocean of planet 1.
[0121] Embodiment of general planetary vehicle 5 with launch density ρ.sub.1v, kg/m.sup.3, indicated in the ratio (7), is due to optimization of technology for construction and maintenance of general planetary vehicle 5 while ensuring its location in liquid 20 at assigned launch depth h.sub.v, m, in global ocean.
[0122] Optimum launch density ρ.sub.1v, kg/m.sup.3, for the second embodiment of general planetary vehicle 5 is the value determined by the ratio (7). Under these conditions, the costs of manufacturing, maintenance and operation of general planetary vehicle are minimized 5.
[0123] Reduction in launch density ρ.sub.1v, kg/m.sup.3, of general planetary vehicle 5 beyond the upper boundary of the ratio (7) ρ.sub.2/ρ.sub.1v=2, that is at ρ.sub.2/ρ.sub.1v>2, does not allow efficient use for prelaunch maintenance of general planetary vehicle 5 at assigned launch depth h.sub.v, m, due to its excessive buoyancy (floatation miss), thereby increasing the likely negative impact thereon from possible roughness on the ocean surface, whereas increasing launch density ρ.sub.1v, kg/m.sup.3, below the lower boundary of the ratio (7) ρ.sub.2/ρ.sub.1v=0.5, that is at ρ.sub.2/ρ.sub.1v<0.5, does not allow to meet requirements on reduction of costs for maintenance of general planetary vehicle 5 at a considerable depth in the ocean of planet 1 because of its insufficient (negative) buoyancy.
[0124] In this embodiment, drives 12 of linear flywheels 10 are also connected to power supply source 16 through control system 17 and power communication system 18 (see
[0125] Besides, similar to the first variant of the claimed invention, general planetary geospatial transportation complex by Yunitski, as per its second embodiment, is also equipped with fixing locks 19 (see
[0126] According to the second variant of the claimed invention, it is expedient that launch density ρ.sub.1v, kg/m.sup.3, of general planetary vehicle 5 was secured with pontoon means 22 connected with fixing locks 19 of linear bearing structure 7 installed all over its length L.sub.0, m, and which are fastened in liquid 20 of ocean and/or at its bed 21 by anchors 21.1 (see
[0127] The use of pontoon means 22 to compensate launch density ρ.sub.1v, kg/m.sup.3, of general planetary vehicle 5 up to design limits indicated in the ratio (7) makes it possible to simplify its design and increase its technological effectiveness and efficiency (see
[0128] The above result is also achieved thanks to the fact that the proposed general planetary geospatial transportation complex of Yunitski includes general planetary vehicle 5, covering planet 1 along the line 2 of surface section of planet 1 by the plane 3 parallel to the plane 4 of the equator 4.1, fixed, according to the third variant of the invention (see
10.sup.−7≤h.sub.l/R.sub.l≤10.sup.−2, (8)
where R.sub.l, m,—radius of planet 1 in plane 3 of arranging general planetary vehicle 5 in gaseous environment 23 of atmosphere of planet 1.
[0129] Positioning of general planetary vehicle 5 in gaseous environment 23 of atmosphere of planet 1 at launch altitude h.sub.l, m indicated in the ratio (8), is due to optimization of technology of construction and maintenance of general planetary vehicle 5 at its “atmospheric” launch.
[0130] Optimal value of launch altitude h.sub.l, m, of lifting general planetary vehicle 5 above surface of planet 1 is the value determined by the ratio (8). Under these conditions, the costs of manufacturing, maintenance and operation of general planetary vehicle 5 are minimized.
[0131] Decrease in value of launch altitude h.sub.l, m, of location of general planetary vehicle 5 above the surface of planet 1 below the lower boundary of the ratio (8) h.sub.l/R.sub.l=10.sup.−7, that is, at h.sub.l/R.sub.l<10.sup.−7, does not allow to reduce negative impact on operation of general planetary vehicle 5 due to inhomogeneity of surface relief of planet 1 along the launch location of linear bearing structure 7 throughout its length, and increase of its value above the upper boundary of the ratio h.sub.l/R.sub.l=10.sup.−2, i.e. at h.sub.l/R.sub.l>10.sup.−2, determined by the ratio (8), does not allow to effectively reduce the costs of pre-launch preparation, maintenance and loading of general planetary vehicle 5 at high altitude in more rarefied atmosphere layers of planet 1.
[0132] At the same time, according to third variant of the invention, for general planetary geospatial transportation complex by Yunitski, however, similar to both its first and second variants, it is characteristic that general planetary vehicle 5 is, in this case, represents a linear bearing structure 7 of length L.sub.0, m, encircling the planet 1, comprising pressure hull 8 with at least two vacuum channels 9, respectively, 9.1 and 9.2, also encircling planet 1, with endless linear flywheels 10 placed therein. Hereby, first linear flywheel 10.1 is arranged in first vacuum channel 9.1 and second linear flywheel 10.2 is arranged in second vacuum channel 9.2.
[0133] By linear flywheel 10, as in the first two embodiments of the invention, is meant a seizing planet 1 giant annular closed rim in the form of open torus rotatably mounted around the center of mass of planet 1.
[0134] Both linear flywheels 10.1 and 10.2 are contactlessly positioned in relation to walls of the relevant vacuum channel 9.1 or 9.2, and equipped with the systems of magnetic and/or electromagnetic suspension 11, respectively 11.1 and 11.2, and linear electromagnetic drives 12, accordingly, 12.1 and 12.2, of first and second linear flywheels 10.1 and 10.2, respectively (see
1.1≤V.sub.0/V.sub.lh≤5, (9)
where V.sub.lh, m/sec,—first cosmic velocity at launch altitude h.sub.l, m.
[0135] Acceleration of at least one of linear flywheels 10 up to velocity V.sub.0, m/sec, determined from ratio (9), makes it possible to achieve balancing of attraction force from planet towards general planetary vehicle 5 and its launch into space at minimum required energy consumption.
[0136] Thus, the optimum velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 to provide accumulation of kinetic energy and the amount (angular momentum) of motion sufficient to launch general planetary vehicle 5 and ensure it enters space into planned circular orbit 13 from gaseous environment 23 of atmosphere of planet 1, is a value determined by the ratio (9). Under the specified limits, energy costs necessary to ensure the operability of general planetary vehicle 5 are minimized.
[0137] Reduction in velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 below the lower boundary V.sub.0/V.sub.vh=1.1, determined by the ratio (9), does not allow to meet the requirements of stable and reliable operation of general planetary vehicle 5 at launch, in dense atmosphere, and also limits the altitude of cosmic orbit on which general planetary vehicle 5 can be inserted, as well as the circumferential (orbital) velocity V.sub.1H, m/sec, of linear bearing structure 7.
[0138] Increase in velocity V.sub.0, m/sec, of acceleration of at least one of linear flywheels 10 above the upper boundary V.sub.0/V.sub.vh=5, determined by the ratio (9), leads to unjustified hike in energy costs required to ensure the operability of general planetary vehicle 5 according to the design assignment and excessively increases altitude H, m, of planned circular orbit 13.
[0139] According to the third embodiment of the present invention, linear bearing structure 7, similar to the first two embodiments of the invention, is provided with transportation compartments 15 (see
1.01≤L.sub.H/L.sub.0≤1.25;
[0140] Substantiation of the range of elastic extension of linear bearing structure 7 without loss of continuity indicated in the ratio (3) is similar to the justification of this range given as such for the first two embodiments of the installation and due to the range of change of length L.sub.0, m, of linear bearing structure 7 in launch state (see
[0141] In turn, linear flywheels 10, respectively, 10.1 and 10.2, by analogy with justification of the choice of value of their masses m.sub.1 and m.sub.2, kg, specified in the first two variants of embodiment of general planetary vehicle 5, have the corresponding masses m.sub.1 and m.sub.2, kg, defined by the ratio (4):
0.1≤m.sub.1/m.sub.2≤10;
[0142] Embodiment of linear flywheels 10.1 and 10.2 with masses m.sub.1 and m.sub.2, kg, ratio of which is less than 0.1 or more than 10, leads either to reduction of efficiency of general planetary vehicle 5, or to significant and impractical increase of velocity (rotation) of at least one of linear flywheels at the moment of launch of general planetary vehicle 5 from planet 1, which leads to considerable complication and increase of cost of realization of the entire project on transportation complex.
[0143] Hereby, general planetary vehicle 5 is embodied with launch density ρ.sub.1l, kg/m.sup.3, determined by the ratio:
0.1≤ρ.sub.3/ρ.sub.1l≤2, (10)
where ρ.sub.3, kg/m.sup.3,—density of gaseous environment 23 of atmosphere of planet 1 at launch altitude h.sub.l
[0144] Implementation of general planetary vehicle 5 with launch density ρ.sub.1l, kg/m.sup.3, indicated in the ratio (10), determined by optimization of technology for construction and maintenance of general planetary vehicle 5 while ensuring its location in gaseous environment 23 of atmosphere of planet 1 at assigned launch altitude h.sub.l, m.
[0145] The optimum launch density ρ.sub.1l, kg/m.sup.3, for the third embodiment of general planetary vehicle 5, is value determined by the ratio (10). Under these conditions, the costs of manufacturing, maintenance and operation of general planetary vehicle 5 are minimized.
[0146] Increase in launch density ρ.sub.1l, kg/m.sup.3, of general planetary vehicle 5, beyond the lower boundary of the ratio (10) ρ.sub.3/ρ.sub.1l=0.1, that is at ρ.sub.3/ρ.sub.1l<0.1, does not allow to effectively use technical parameters of general planetary vehicle 5 for its maintenance in prelaunch state at assigned launch altitude of h.sub.l, m, in gaseous environment 23 of atmosphere of planet 1 because of complication in processes of maintenance of general planetary vehicle 5 at considerable altitude (in upper, more rarefied atmosphere layers), and decrease of launch density, ρ.sub.1l, kg/m.sup.3, beyond the upper boundary of the ratio (10) ρ.sub.3/ρ.sub.1l=2, that is, at ρ.sub.3/ρ.sub.1l>2, determined by the ratio (10), does not allow to reduce negative impact which is rendered on operation of general planetary vehicle 5 by inhomogeneity of surface relief of planet 1 along launch location of linear bearing structure 7 throughout thereof.
[0147] Furthermore, in the third embodiment, similar to the first above described two embodiments, drives 12 of linear flywheels 10 are also connected to power supply source 16 through control system 17 and power communication system 18 (see
[0148] Similar to the first two variants of the invention, general planetary geospatial transportation complex by Yunitski according to third variant, also equipped by fixing locks 19 (see
[0149] According to the third embodiment (variant) of the invention, it is advantageous that launch density, ρ.sub.1v, kg/m.sup.3, of general planetary vehicle 5 was secured, for example, with balloons 24, connected to fixing locks 19 of linear bearing structure 7 and fixed, for example, in gaseous environment 23 of atmosphere of planet 1, and/or in liquid 20 of ocean, and/or on hard surface of planet 1, respectively, on balloons 24, floating supports 6.4 and/or anchors 21.1, and/or anchors 21.2 along its entire length L.sub.0, m, of linear bearing structure 7 and performing pre-launch positioning of general planetary vehicle 5 in gaseous environment 23 of atmosphere of planet 1 at launch altitude h.sub.l
[0150] Using balloons 24 to compensate launch density ρ.sub.1l, kg/m.sup.3, of general planetary vehicle 5 to design limitations, specified in the ratio (10) will simplify its design and increase its technological efficiency and efficiency (see
[0151] For general planetary geospatial transportation complex by Yunitski according to any of the three variants of the present invention, it is distinguishable that transportation compartments 15 may be placed both inside pressure hull 8 of linear bearing structure 7, or fastened outside thereupon, correspondingly, those are built-in transportation compartments 15.1 and detachable transportation compartments 15.2 (see
[0152] Using outside detachable transportation compartments 15.2 will allow to increase efficiency and lower costs of their maintenance on stages of loading and unloading of general planetary vehicle 5.
[0153] It is advantageous to embody general planetary geospatial transportation complex by Yunitski in such a way that general planetary vehicle 5 is provided with a linear ballast system 25 covering the planet 1 and uniformly loaded along its entire length with liquid and/or gaseous ballast 26 (see
[0154] As structure of linear ballast system 25, a portion of interconnected along the entire length L.sub.0, m, transportation compartments 15 of linear bearing structure 7 of general planetary vehicle 5, can be used.
[0155] Equipping of general planetary vehicle 5 with linear ballast system 25, covering the planet 1 and uniformly loaded along its entire length with liquid and/or gaseous ballast 26, provides balancing of the whole structure and excludes its vibrations at operation during motion of general planetary vehicle 5 from launch moment to rise to planned circular orbit 13 of altitude H, m.
[0156] General planetary geospatial transportation complex by Yunitski according to any of the three variants may be embodied in such way, that linear bearing structure 7 of general planetary vehicle 5 is made elastically of elastically deformable material with modulus of elasticity E, Pa, within the following range:
10.sup.8≤E≤5×10.sup.11 (11).
[0157] The range of the modulus of elasticity E, Pa is selected on the basis of strength conditions stipulated by design assignment and the possibility of providing elastic deformation of pressure hull 8 of linear bearing structure 7 without loss of continuity within the range of change of length L.sub.0, m, of linear bearing structure 7 from launch state up to its length L.sub.H, m, on planned circular orbit 13 of altitude H,
[0158] Embodiment of linear bearing structure 7 and, accordingly, of general planetary vehicle 5 as a whole, from materials with values of modulus of elasticity E, Pa, less than 10.sup.8 does not allow to ensure their required strength and rigidity.
[0159] Embodiment of linear bearing structure 7 and, accordingly, of general planetary vehicle 5 as a whole with possibility of their elastic extension without loss of continuity, from materials with values of modulus of elasticity E, Pa, more than 5×10.sup.11, leads to significant increase of costs for elastic deformation of structural members of general planetary vehicle 5 and reduction of operation efficiency thereof.
[0160] Further, according to any of the three variants of the invention, general planetary geospatial transportation complex by Yunitski can be realized in such a way that pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5 is embodied in the form of units 27 joined to each other by telescopic connections 28 (see
[0161] Embodiment of pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5 in the form of units 27 integrated with each other along the length of telescopic connections 28 allows to reduce power consumption required to provide elastic deformation in longitudinal direction of structural members of general planetary vehicle 5 and expand the range of materials used for manufacture thereof.
[0162] Alternatively, general planetary geospatial transportation complex by Yunitski according to any of the three variants can be realized in such a way that pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5 is embodied in the form of units 27 interconnected with each other by bellows 29 (see
[0163] The use of bellows 29 as structural members for interconnecting units 27 of general planetary vehicle 5 also leads to reduction in power consumption, required to ensure linear elastic deformation of structure of pressure hull 8 of general planetary vehicle 5 during its lifting to planned circular orbit 13 of altitude H, m, and increases reliability and durability of the structure as a whole while simplifying it.
[0164] In accordance with the initial technical requirements of specific design solution, the achievement of the required value of elasticity of elastically deformable linear bearing structure 7 of general planetary vehicle 5 can be embodied both with combination of the specified structural and technological solutions, and by other known and tested in the art techniques.
[0165] The above mentioned result is also achieved by the method of inserting payload from surface of planet 1 into circular orbit of altitude H, m, according to which:
[0166] First, the presence of general planetary geospatial transportation complex by Yunitski is guaranteed, including seizing the planet 1 along the line 2 of cross-section of surface of planet 1 by plane 3 parallel to the plane of the equator 4, general planetary vehicle 5 embodied according to any claims 1, 2 and 3;
[0167] General planetary vehicle 5, as noted above, is a self-supporting aircraft made in the form of a torus with cross section of up to a few meters, encircling the planet 1 in a plane 3 parallel to the plane of the equator 4. It can exit into space, overcoming the attraction of planet 1, using only the internal forces of the system, without any energetic, mechanical, chemical and other types of environmentally harmful interaction with the environment, that is, it will be extremely environmentally friendly.
[0168] Only tensile cord having infinitesimal cross sizes in relation to length (a ratio about 1:10.000.000), can be a steady self-bearing structure, hence, general planetary vehicle 5 in the longitudinal direction will be always stretched by force N, N (see
[0169] The optimal version of operation of general planetary vehicle 5, which has entered planned circular orbit 13 of altitude H, m, is the state of equilibrium, therefore, all members of its structure as a whole should be in the state of weightlessness. For this purpose, in optimal versions of operation, each linear member of general planetary vehicle 5 must have first cosmic velocity V.sub.1H, m/sec, on planned circular orbit 13 at altitude H, m.
[0170] When general planetary vehicle 5 is lifted into space (see
[0171] Prior to launch of general planetary vehicle 5, linear flywheels 10.1 and/or 10.2 should have sufficient initial kinetic energy and launch amount (kinetic momentum) of motion to provide (see
[0178] Accordingly, the kinetic energy K, J, of at least one of linear flywheels 10 required to lift general planetary vehicle 5 to planned circular orbit 13 of altitude H, m is determined by the dependence:
κ=½(r.sub.p.sup.2φ.sup.2+m.sub.0{dot over (r)}.sub.p.sup.2), (12)
where , kg,—weight of at least one of linear flywheels 10;
r.sub.p, m,—current orbit radius of at least one of linear flywheels 10;
φ, rps,—angular velocity of at least one of linear flywheels 10;
m.sub.0, kg,—mass of general planetary vehicle 5;
{dot over (r)}.sub.p, m/sec,—radial velocity of general planetary vehicle 5;
and it must be greater than the attractive force to the center of planet 1, the elastic force acting on the members of linear bearing structure 7 during lifting of general planetary vehicle 5 and the resistance force of gaseous environment 23 of atmosphere of planet 1 (see
G=m.sub.0gR.sub.e.sup.2/r.sub.p.sup.2 (13)
F=2πcl(r.sub.p/R.sub.e−1) (14)
Q=k.sub.fρ.sub.0{dot over (r)}.sub.p.sup.2 exp(−α.sub.n(r.sub.p/R.sub.e−1)) (15)
[0179] where, respectively, G, H,—attractive force of planet 1 (e.g., Earth);
[0180] g, m/sec.sup.2,—gravitational acceleration at the equator;
[0181] R.sub.e, m,—radius of the equator of the planet 1;
[0182] F, N,—elastic total force in a member of linear bearing structure 7 of general planetary vehicle 5;
[0183] c, N/m,—total rigidity of linear bearing structure 7 of general planetary vehicle 5;
[0184] l, m,—length of linear bearing structure 7 of general planetary vehicle 5 at the current orbit radius;
[0185] Q, N,—drag force of gaseous environment 23 of planetary 1 atmosphere;
[0186] k.sub.f—factor depending on shape of shell of general planetary vehicle 5;
[0187] ρ.sub.o, kg/m.sup.3,—density of gaseous environment 23 of atmosphere of planet 1 on its surface;
[0188] α.sub.n—exponent degree index, which determines decreasing density of atmosphere with height.
[0189] Second, general planetary vehicle 5 is held along its entire length L.sub.0, m, on launch overpass 6 of altitude h, m, and/or in liquid 20 of ocean at launch depth h.sub.v, m, and/or in gaseous environment 23 of planetary 1 atmosphere at launch altitude h.sub.l, m, by means of fixing locks 19 of linear bearing structure 7 in the corresponding initial launch position (see
[0190] At the same time, depending on the design solution, various design versions of both locks 19 themselves and combinations of their anchoring schemes on planet 1, known in modern art, are possible.
[0191] Third—payload 14 of total mass m.sub.3, kg, including ballast 26, is placed uniformly along the entire length L.sub.0, m, of linear bearing structure 7 in transportation compartments 15;
[0192] Ballast 26 performs several important functions for operation of general planetary vehicle 5.
[0193] It provides for: [0194] balancing of linear bearing structure 7 during launch and lifting of general planetary vehicle 5 from planet [0195] reduction of power consumption due to reduction of total mass m.sub.3, kg, of payload 14 inserted into space onto planned circular orbit 13 of altitude H,
[0197] Fourth, at least one linear flywheel 10 is accelerated in the co-rotational direction regarding the planet 1 to velocity V.sub.0, m/sec, exceeding first cosmic velocity V.sub.eh, m/sec, at altitude h, m, of launch overpass 6, and/or V.sub.vh, m/sec,—first cosmic velocity in liquid of ocean at launch depth h.sub.v, m, and/or V.sub.lh, m/sec,—first cosmic velocity in gaseous environment of planetary atmosphere at launch altitude h.sub.l, m, by at least 10%.
[0198] At least one of linear flywheels 10 is accelerated along the corresponding vacuum channel 9, wherein that linear flywheel 10 does not experience motion resistance and is rotated around the planet 1 with an axis of rotation passing through the center of mass of planet 1. As velocity increases, at least one of linear flywheels 10 accumulates the required amount of kinetic energy K, J, the pulse (angular momentum) which is necessary for general planetary vehicle 5 to reach planned circular orbit 13 at a given orbital velocity V.sub.1H, m/sec.
[0199] Hereby, since acceleration path of linear flywheels 10 is infinite, therefore, the charging time of general planetary vehicle 5 is not limited to the necessary energy even under the condition of low power of linear electromagnetic drive 12. Efficiency of linear electromagnetic drives 12 of general planetary vehicle 5 is not less than 95%, that is, it will be about one hundred times higher than that of rocket (missile) (taking into account pre-launch and launch costs and energy losses, including for obtaining rocket fuel), energy efficiency of modern rocket carriers is less than 1%. Therefore, with the same drive capacity as heavy launch vehicle (about 100 million kilowatts), it will be possible to take into space not just tens of tons, but millions of tons of payload 14 per flight.
[0200] Various structural and operational characteristics of general planetary vehicle 5 with different combinations of weights of linear flywheels 10 are possible (with equal masses, or when one linear flywheel 10 is heavier and the other is lighter), with different launch acceleration modes of linear flywheels 10 (both linear flywheels 10 are accelerated on planet 1 either in one direction, or one flywheel in one direction, the other flywheel in the other direction), etc.
[0201] Fifth, general planetary vehicle 5 is launched by detaching along its entire length L.sub.0, m, of fixing locks 19 of linear bearing structure 7.
[0202] When at least one of linear flywheels 10, encircling the planet 1, reaches first cosmic velocity V.sub.eh, m/sec, in vacuum channel 9, for example, when starting from launch overpass 6 of altitude h, m, it will become weightless. As velocity of this linear flywheel 10 increases, the centrifugal force acting vertically (that is, from the center of planet 1 along its radius) will exceed its weight, that is, it will try to break it off from planet 1. When centrifugal forces from the accelerated linear flywheel 10 exceed the specific gravity of general planetary vehicle 5 (for example, equal to 1000 kgf/m), the entire system will become conditionally weightless (the weight of general planetary vehicle 5 will become zero, that is, it will stop pressing on launch overpass 6. If such linear flywheel 10 is accelerated to even higher velocity, there will be excessive lifting force sufficient to lift entire general planetary vehicle 5 together with payload 14 to planned circular orbit 13.
[0203] By simultaneously solving the equations (12), (13), (14) and (15), an expression is obtained for determining the acceleration from the centrifugal force of inertia of at least one of linear flywheels 10 when the above-mentioned forces are applied to general planetary vehicle 5 (see
a=/m.sub.0rφ.sup.2−gR.sub.e.sup.2/r.sub.p.sup.2−2πcl/m.sub.0(r.sub.p/R.sub.e−1)−k.sub.fρ.sub.0/m.sub.0{dot over (r)}.sub.p.sup.2 exp(−α.sub.n(r/R.sub.e−1)) (16)
[0204] Which suggests the condition for beginning of radial movement upwards general planetary vehicle 5, defined by the expression:
V.sub.0>V.sub.1h√(1+m.sub.0/), (17)
where, depending on initial start (launch) position, V.sub.1h, m/sec, respectively—V.sub.eh, m/sec, or V.sub.vh, m/sec, or V.sub.lh, m/sec.
[0205] Thus, as can be seen from the expressions (16) and (17), the following data are necessary to calculate the implementation of the start (launch) process, for example from the Earth, of general planetary vehicle 5 and its insertion into planned circular orbit 13 of altitude H, m:
[0206] 1) Initial constant parameters for launch of general planetary vehicle 5 from the surface of Earth in the equator region, are as follows: [0207] radius R.sub.e, m, of Earth in plane of the equator; [0208] gravitational acceleration g, m/sec.sup.2, at the equator; [0209] initial density ρ.sub.0, kg/m.sup.3, of gaseous environment 23 of the Earth's atmosphere at which piezometric height H.sub.a, m, of the averaged atmosphere with constant temperature corresponds to the value 6665, and the exponent degree index α.sub.n in Halley formula, which determines the decrease in the density of the atmosphere the higher it gets, corresponds to the value of 995,736.
[0210] 2) Parameters determining the position of planned circular orbit; value of corresponding launch velocity of at least the first linear flywheel 10.1, its length, weight and mechanical properties; specific mass of linear meter of general planetary vehicle 5; aerodynamic characteristics of the outer shell of general planetary vehicle 5.
[0211] 3) Parameters determining the position of the elastic and friction expansion sections of at least the first linear flywheel 10.1; iteration step on each section; radial velocity reduction factors at the end of friction sections.
[0212] Sixth, payload 14 of total mass m.sub.3, kg, is lifted by means of linear bearing structure 7 of general planetary vehicle 5 to planned circular orbit 13 of altitude H, m, under action of centrifugal forces of at least one of linear flywheels 10;
[0213] Seventh, linear bearing structure 7 of general planetary vehicle 5 is guaranteed to attain circumferential velocity around planet 1 in co-rotational direction re planet 1, equal to first cosmic velocity V.sub.1H, m/sec, on planned circular orbit of altitude H, M, above planet surface, by decelerating the first linear flywheel 10.1 and transmitting, respectively, according to law of conservation of angular momentum in closed system, the motion pulse from linear flywheel 10 of linear bearing structure 7 of general planetary vehicle 5, whereas energy generated during deceleration of the first linear flywheel 10.1—for acceleration in counter-direction of the second linear flywheel 10.2;
[0214] Eighth, linear electromagnetic drives 12 of both linear flywheels 10 are turned off in planned circular orbit 13 of altitude H, m, above surface of planet 1, and general planetary vehicle 5 is unloaded, for example, into orbital circular (seizing the planet) complex 30 (see
[0215] At this stage, alternatively, launch of classic interplanar rocket-type satellite (not shown in the figures), fixed on the outer part of pressure hull 8 of linear bearing structure 7 similar to transportation compartments 15.2, can be carried out from general planetary vehicle 5 inserted on planned circular orbit 13 of altitude H, m, above the surface of planet 1.
[0216] Ninth, general planetary vehicle 5 is returned to the initial launch position by lowering the altitude of linear bearing structure 7 of general planetary vehicle 5 from planned circular orbit 13 of altitude H, m, above the surface of planet 1 to h, m, or h.sub.v, m, or h.sub.l, m, respectively, on launch overpass 6, in liquid 20 of ocean or in gaseous environment 23 of planetary 1 atmosphere, by decelerating one of linear flywheels 10 and accelerating the other linear flywheel 10 in opposite direction until linear bearing structure 7 has a zero circumferential velocity relative to planet 1.
[0217] Tenth—upon return of general planetary vehicle 5 into initial launch position by means of fixing locks 19 (see
[0218] Modes of smooth acceleration and/or deceleration of linear flywheels 10 are secured thanks to action of adjustable linear force N.sub.0, N/m, thereon, coming from all uniformly distributed over the entire length L.sub.0, m, of linear bearing structure 7 of general planetary vehicle 5 of subsystems of the system of linear electromagnetic drives 12, as well as by maintaining the standard operation of subsystems of the system of magnetic and/or electromagnetic suspension 11, respectively, together with the system of linear electromagnetic drives 12. Operation of linear electromagnetic drives 12, in turn, is controlled and coordinated by control system 17 connected with them by means of communication system 18 equipped with feedback and technical parameters monitoring subsystems (see
[0219] Control of motion of linear flywheels 10 and coordination of value of linear force N.sub.1, N/m, acting on each individual section thereof, are performed so that all members of linear bearing structure 7 of general planetary vehicle 5 move uniformly, excluding occurrence of longitudinal vibrations and other possible disturbances in motion of members of its structure.
[0220] For this purpose, during operation of general planetary vehicle 5, throughout its linear flywheels 10, linear force N.sub.1, N/m, their acceleration and/or deceleration are adjusted relative to the nominal value of that linear force N.sub.0, N/m, within the boundaries, determined from the ratio:
0.9≤N.sub.1/N.sub.0≤1.1 (12)
[0221] Range of ratio of linear force N.sub.1, N/m, of acceleration and/or deceleration of linear flywheels 10 to nominal value of that linear force N.sub.0, N/m, is selected on the basis of conditions of operation reliability of general planetary vehicle 5, stipulated by the design assignment, and possibility of achieving of the required velocity, including launch velocity, of linear flywheels 10 without possible disturbances in motion of members of general planetary vehicle 5.
[0222] In case the ratio (12) is equal to 1, the whole structure and all systems of general planetary vehicle 5 will have increased parameters for reliability and stability of their operation, however, at the same time, the cost of achieving this result will significantly increase.
[0223] In cases, when values of the ratio (12) are less than 0.9 or more than 1.1, the tasks of prevention of longitudinal vibrations and elimination of possibility of occurrence of other disturbances during free motion of extended linear members of general planetary vehicle 5 will become complicated to tackle, which is unacceptable, as it can lead to a penalized reliability and deteriorated stability of functioning thereof.
[0224] To carry out all transportation and insert into calculated orbit, for example, in the conditions of planet Earth, at altitude of 400 km, the payload 14 (passengers and cargoes), at least one of linear flywheels 10 of general planetary vehicle 5,—which has operational weight, e.g., 40 million tons (and, accordingly, specific weight—approximately 1000 kg/m),—should accumulate kinetic energy in the amount of 1.25×10.sup.18 J (around 3.5×10.sup.11 kW×h). Taking into account energy losses and expenditures when entering circular orbit 13 (in particular, due to efficiency of linear electromagnetic drives 12 in order of 95%), the initial energy reserves should be at least by 10% more, that is, will be around 1.4×10.sup.18 J (3.9×10.sup.11 kW×h). Then, when connecting the power of general planetary vehicle 5, which is equal to less than 2% of the capacity of the world's power plants, to the external power system (Earth grid) of 100 million kW (or 2.5 kW per meter of length of linear bearing structure 7 of general planetary vehicle 5), initial charging time of the general planetary geospatial transportation complex—acceleration of at least one of linear flywheels 10 up to calculated velocity of V.sub.0, m/sec—will take 420 hours (17.5 days).
[0225] After calculated velocity V.sub.0, m/sec, is reached by at least one of linear flywheels 10, general planetary vehicle 5 of total mass of 40 million tons, of which 20 million tons are for linear flywheels 10, is ready for launch. But it is kept from lifting along its entire length L.sub.0, m, by means of fixing locks 19 of linear bearing structure 7 of general planetary vehicle 5, for example, to launch overpass 6.
[0226] After payload 14 has been placed on general planetary vehicle 5, it is released by locks 19 along the entire length L.sub.0, m, of linear bearing structure 7, and general planetary vehicle 5 is no longer kept by anything on planet 1.
[0227] Since flywheels are accelerated to velocities that allow the centrifugal forces to exceed the weight of each linear meter of general planetary vehicle 5, each of its linear meters begins to move from the center of rotation of linear flywheels 10, that is, to rise vertically upwards in plane of the equator passing through the center of mass of the Earth. At the same time, the ring (circle) of general planetary vehicle 5 will increase in diameter symmetrically in all directions relative to the center, and its body—elongate, stretch, without any displacement of the center of mass of this giant ring, which, according to law of conservation, will always coincide, in this case, with the center of mass of the planet Earth.
[0228] The acceleration of climbing into space depends on excessive centrifugal forces. For example, if lifting force acting on each linear meter of general planetary vehicle 5 is bigger than the weight of each linear meter thereof by 5%, general planetary vehicle 5 will start to climb up with a comfortable acceleration of 0.5 m/sec.sup.2, or equal to 5% of gravitational acceleration. When moving with this acceleration, general planetary vehicle 5 will rise (expand in plane of the Earth's equator) to altitude of 100 km in 5 minutes 16 seconds and will have a vertical lift velocity at this altitude of 570 km/h.
[0229] During lifting for every 100 km above the Earth, the hull of general planetary vehicle 5 should extend by 1.57%. Accordingly, the diameter of pressure hull 8 of general planetary vehicle 5 will also increase by 1.57%, which is easily achievable by structural and technological solutions such as telescopic connections 28 along the length of the rigid units 27 of linear bearing structure 7 of general planetary vehicle 5, or by uniting them with each other by means of bellows 29 (spring tabs) and other proven techniques known from the art.
[0230] After leaving the dense atmosphere of the Earth (at altitudes of more than 10 km), the braking (generator) mode is activated on linear electromagnetic drive 12.1 of the first linear flywheel 10.1, accelerated at the surface of the Earth to cosmic velocity V.sub.0, m/sec, in co-rotational direction of planet 1. The generated power is transmitted by means of control system 17 and communication system 18 to acceleration of the second linear flywheel 10.2 in the counter-direction in relation to the first linear flywheel 10.1. As a result, general planetary vehicle 5 receives a double pulse and begins to rotate towards the rotation of the Earth. If the acceleration of rotation is the same comfortable 0.5 m/sec.sup.2, general planetary vehicle 5, and the entire payload 14 located therein (or thereon), will gain an estimated orbital, i.e. circular, velocity, for example, of 7671 m/sec (for an altitude of 400 km) after 4 hours.
[0231] The climbing and orbital velocity modes are selected so that general planetary vehicle 5 at a given altitude has an appropriate orbital velocity and is in equilibrium and its vertical (radial) velocity is zero. For this purpose, a special ballast system 25 is used in the process of entering space, if necessary. As part of payload 14, in amount of 0.1-10%, liquid and/or gaseous ballast 26 is used, uniformly arranged along the whole length L.sub.0, m, of linear bearing structure 7.
[0232] In order to lift general planetary vehicle 5, it is necessary to have either initial excess of kinetic energy (linear flywheels 10 are accelerated on Earth, before launch, to a higher velocity) or, during lifting, it is required to reduce weight of general planetary vehicle 5 by dropping ballast 26. Most preferred is combination of these techniques.
[0233] With ballast 26 reserve of less than 0.1% of mass of payload 14, a significant increase in the velocity of rotation of linear flywheels 10 at launch is required in order to improve stabilization of general planetary vehicle 5 when it is lifted into space (to use the gyroscopic effect), resulting in unduly high energy costs and additional structural difficulties.
[0234] With ballast 26 reserve exceeding 10% of payload 14′ mass, the share of payload 14 placed by linear bearing structure 7 of general planetary vehicle 5 into circular orbit 13 of altitude H, m, above the surface of planet 1, is significantly reduced, which leads to penalized efficiency of operation of the whole complex.
[0235] The total consumption of ballast 26 during lifting will be about 10-100 kilograms per linear meter of general planetary vehicle 5 (for the above cited input data).
[0236] Hereby, as ballast 26, ecologically friendly to Planet Earth substances and materials are used: water and/or compressed, and/or liquid air and/or oxygen, and/or nitrogen.
[0237] If such ballast 26 is sprayed in a predetermined amount in the ozone layer of planet 1 and above (altitudes from 10 to 60 km), it will be possible to regulate the oxygen and ozone content in the upper atmosphere and to “heal” the ozone holes, as well as ecologically safely manage the weather and climate on planet Earth.
[0238] It is also an object of the claimed invention to use ballast 26 when lifting general planetary vehicle 5 into planned circular orbit 13 of altitude H, m to restore the ozone layer, improve weather and stabilize the climate on Earth by spraying the it in the atmosphere of planet 1, which is also a new essential feature corresponding to the inventive step.
[0239] Similar to the described example, launch of general planetary vehicle 5 placed in liquid 20 of the ocean of planet 1 at launch depth of h.sub.v, m, and/or in gaseous environment 23 of planetary 1 atmosphere at launch altitude of h.sub.l, m (see
[0240] After reaching planned circular orbit 13 and stabilizing general planetary vehicle 5 along the entire length L.sub.0, m, of linear bearing structure 7 (no local vibrations) relative to the ideal orbit), the payload 14 is unloaded, for example, into the orbital circular (seizing the planet) complex 30 (see
[0241] The load-carrying capacity of the described variant of general planetary vehicle 5 is 250 kg/m under Earth conditions, or 10 million tons of payload 14.
[0242] The cost of geospatial transportation by general planetary vehicle 5 along the routes Earth-Orbit and Orbit-Earth consists of three main components:
[0243] 1) Energy costs of operation of all systems of general planetary vehicle 5, first of all —linear electromagnetic drives 12 and systems of magnetic and/or electromagnetic suspension 11 of linear flywheels 10, which consumes more than 95% of energy consumed by the whole general planetary geospatial transportation complex;
[0244] 2) Depreciation charges;
[0245] 3) Overhead costs for maintenance of the general planetary geospatial transportation complex.
[0246] Initial energy supply required to lift general planetary vehicle 5 with total mass of m.sub.0, kg, e.g. 40 million tons, into space, and return to Earth without payload 14, of total mass of m.sub.3, kg, e.g. 10 million tons left in orbit (for example, in orbital circular complex 30—see
420 000 000 000 kW×hour×0.05 USD/kW×hour=21 000 000 000 USD, or:
E.sub.0=2 100 USD/t.
[0247] Therefore, on trips with the preferred one-way direction of the cargo traffic from planet 1 to planned circular orbit 13, it will be necessary to compensate in each trip only for the energy costs of the payload 14 delivered to space, the total mass m.sub.3, kg, of which (loading factor) makes 25% of gross mass of general planetary vehicle 5. Thus, during this period of operation of general planetary vehicle 5 (in the first year), the delivery of one ton of cargo to planned circular orbit 13 of the Earth will require energy costs as follows: E.sub.1=2 100 USD/t×0.25=525 USD/t.
[0248] Hereby, once accelerated, linear flywheels 10 can rotate inside vacuum channels 9 for years, as the magnetic cushion of the magnetic and/or electromagnetic suspension system 11, like the vacuum of vacuum channels 9, will not create resistance when they travel at space velocities.
[0249] At equal Earth-Orbit and Orbit-Earth cargo traffic volumes, which will have been established approximately at the 10.sup.th year of operation of general planetary vehicle 5, additional energy will be necessary only for compensation of energy dissipation in linear electromagnetic drives 12 of linear flywheels 10. The total energy loss within general planetary vehicle 5 is less than 10%, so the cost of shipping a ton of cargo to orbit in this case (and, accordingly, to descend a ton of cargo to the surface of planet) will be: E.sub.2=2 100 USD/T×0.1=210 USD/t.
[0250] Once the orbital space industry is fully operational, and commercial exploitation of asteroids and the Moon as sources of raw materials has started, the need to deliver raw materials from Earth to planned circular orbit 13 will be significantly reduced. At the same time, the return cargo traffic from planned circular orbit 13 to the planet will significantly exceed the direct (one-way), as the main part of industrial production for earth-based citizens will be delivered from space. Even if in future the space-based industrial products of much higher quality (than that of the existing) will be produced by order less per capita than the current production on the planet, the annual volume of transportation on the route Orbit-Earth will reach 500 million tons after 10 years of operation of general planetary vehicle 5, which would require 50 launches into planned circular orbit 13 (approximately one launch per week). Hereby, general planetary vehicle 5 will insert less payload 14 into planned circular orbit 13 (it will make an outbound trip loaded of about 20% only), mainly because it will primarily shuttle into space to take the products manufactured there to deliver them to our planet to consumers—by then about 10 billion earthlings. This will make it possible to convert the potential and kinetic energy of space cargo delivered to Earth into electricity and annually provide the Earth's energy system with the equivalent of energy of 1 billion tons of oil. At that stage and the subsequent stages, energy costs will have negative value, and general planetary vehicle 5 will operate in the mode of a power plant making profit amounted to: 500,000,000 tons/year×8000 kW×hour/t×0.05 USD/kW×hour=200 billion. USD/year, or, net, 400 USD for each excess ton of cargo delivered from planned circular orbit 13 to Earth.
[0251] At the same time, part of the energy will be spent on the own needs of general planetary vehicle 5 (around half), so each ton of excess cargo delivered to the planet from space will yield a net energy profit of: E.sub.3=200 USD/t.
[0252] The capital costs for development (design and construction) of general planetary vehicle 5 can be estimated similarly to contemporary, high-potential electric vehicles, in which the majority of the cost comes from electrical equipment. In terms of complexity of equipment and composition of components, general planetary vehicle 5 is also approximately equivalent to electric vehicle (even less sophisticated) and will cost about the same amount, in terms of the cost of one ton of construction—not more than 25,000 USD/ton. Since mass of the loaded general planetary vehicle 5 (without payload 14) will be, in the described embodiment, 30 million tons, its estimated cost will be: 30 000 000 t×25 000 USD/t=750 billion USD.
[0253] A large hadron collider of 26.5 km, built on the border between Switzerland and France and located underground in a special tunnel of large diameter, is certainly a more technically complex product, in which the velocity of acceleration of elementary particles reaches light velocity (not 10-15 km/s, as for linear flywheels of general planetary vehicle), cost more than 6 billion USD—which also confirms justification of above stated estimated value of general planetary vehicle 5.
[0254] General planetary vehicle 5 is designed for 10,000 space launches and return landings. During that time, it will carry 100 billion tons of cargo. At the same time, depreciation charges per 1 ton of cargo from capital investments in general planetary vehicle 5 will be:
C.sub.OTC=750 000 000 000 USD/100 000 000 000 t=7.5 USD/t.
[0255] The length of the equatorial complex of launch overpass 6 of general planetary vehicle 5 will be 40,076 km, of which about 20% will be for land sections and 80% for sea sections.
[0256] Launch overpass 6 of general planetary vehicle 5, located along the equator 4.1, will represent transport and infrastructure communicator. Power transmission lines and communication lines will also be integrated into launch overpass 6 (not shown).
[0257] The cost of the support and communication part based on launch overpass 6 located along the equator 4.1 can be estimated at 1.320 billion USD, provided that, on average, it will cost 25 million USD/km on land sections and 35 million USD/km—on sea sections.
[0258] Accordingly, depreciation charges per 1 ton of cargo from capital investments in transport and communication part at the equatorial basing of launch overpass 6 will amount to:
C.sub.CT=1 320 000 000 000 USD/100 000 000 000 .sub.T=13.2 USD/t.
[0259] Whereby total depreciation charges will be:
=C.sub.omc+C.sub.cm=7.5 USD/t+13.2 USD/t=20.7 USD/t.
TABLE-US-00001 TABLE 1 Net cost of geospatial traffic per years of operation of general planetary vehicle (GPV) (for one of possible valiants of embodiment) Year (starting from Annual traffic, beginning of million tons Cost components on geospatial transportation Net cost of operation To To planet of ton of cargo, USD/t traffic, of GPV) orbit Earth Power Payroll Depreciation Miscellaneous USD/t 1 100 10 525 90.9 20.7 63.4 700 2 200 50 450 40.0 20.7 39.3 550 3 300 100 300 25.0 20.7 24.3 370 4 400 150 200 18.2 20.7 21.1 260 5 500 200 150 14.3 20.7 15.0 200 6 500 250 100 13.3 20.7 11.0 145 7 400 300 50 14.3 20.7 10.0 95 8 300 350 0 15.4 20.7 8.9 45 9 200 400 −100 16.7 20.7 7.6 −55 10 100 500 −200 16.7 20.7 7.6 −155 11 100 500 −200 16.7 20.7 7.6 −155 12 100 500 −200 16.7 20.7 7.6 −155 13 100 500 −200 16.7 20.7 7.6 −155 14 100 500 −200 16.7 20.7 7.6 −155 15 100 500 −200 16.7 20.7 7.6 −155 16 100 500 −200 16.7 20.7 7.6 −155 17 100 500 −200 16.7 20.7 7.6 −155 18 100 500 −200 16.7 20.7 7.6 −155 19 100 500 −200 16.7 20.7 7.6 −155 20 100 500 −200 16.7 20.7 7.6 −155 Total 4 000 7 310
[0260] Analysis of data presented in Table 1 allows to draw the following conclusions:
[0261] 1) The highest net cost of geospatial cargo traffic—700 USD/t—in the first year of operation, is driven by the need to initially accelerate linear flywheels 10 with substantial energy consumption required therefor, as well as—relatively low volume of annual traffic.
[0262] 2) Over the years, as the volume of traffic increases, both direct and return, their cost decreases significantly.
[0263] 3) On the 9.sup.th year of operation, when return cargo traffic (planned circular orbit 13 to planet 1) will substantially exceed direct cargo traffic (planet 1 to planned circular orbit 13), the net cost of traffic will become negative. This means that general planetary geospatial transportation complex will become profitable not only as a transport, but also as a giant power plant with a length of more than 40 thousand kilometers.
INDUSTRIAL APPLICABILITY
[0264] Development of general planetary geospatial transportation complex in conditions of planet Earth includes the following basic directions (stages):
[0265] 1) Engineering research and design development of equatorial launch overpass 6 with transportation-communication part of general planetary geospatial transportation complex;
[0266] 2) Preparation and realization (construction) of the equatorial launch overpass 6, with corresponding communication system (not shown on figures).
[0267] 3) Manufacture and installation of general planetary vehicle 5 (length 40 076 km, total mass, without payload—30 million tons), commissioning. The entire totality of works related to realization of general planetary geospatial transportation complex is planned to have been completed during 20 years—by 2038.
[0268] The cost of realization general planetary geospatial transportation complex and related works, until 2037 inclusive, is shown in Table 2. It should be noted that the maximum of future annual costs, i.e. 260 billion USD for the period 2032-2037, for example, is about 2 times less than the current US military budget. It also proves that the program of creating general planetary geospatial transportation complex can be implemented, based on their budgets for these years, by countries such as the USA, China, Russia, India and even Brazil, all on their own.
TABLE-US-00002 TABLE 2 Cost of realization of general planetary geospatial transportation complex and related works (for one of possible variants of embodiment) Annualized costs, billions USD Development of the R&D on the equatorial launch overpass equatorial and land-based residential overpass and and industrial infrastructure infrastructure of (buildings, structures, power Realization Total, GPV, plants, ETL, communication (construction) billions Year miscellaneous lines, miscellaneous) of GPV USD 2018 0.1 — — 0.1 2019 0.2 — — 0.2 2020 0.3 — — 0.3 2021 0.4 — — 0.4 2022 1 — — 1 2023 2 1 — 3 2024 3 2 — 5 2025 4 3 — 7 2026 5 4 2 11 2027 6 10 3 19 2028 7 50 5 62 2029 8 80 15 103 2030 9 150 50 209 2031 10 150 75 235 2032 10 150 100 260 2033 10 150 100 260 2034 10 150 100 260 2035 10 150 100 260 2036 10 150 100 260 2037 10 150 100 260 Total 116 1 350 750 2 216
[0269] Total cost of realization of general planetary geospatial transportation complex during 20 years comparable to possible global spending in 2030 (i.e. in one year) on existing traditional space programs using rocket carriers (launch vehicles).
[0270] Currently, capacity of world market of space services amounts to, according to various estimates, 300-400 billion USD a year. The commercial component reaches 75%, and the state segment is about 25%. The volume of this market grows by 4-5% annually. Based on the level of development of existing space programs, experts predict acceleration of growth of market of space products and services.
[0271] By 2030, the market for space products and services could grow to about USD 1.5 trillion. There is a number of prerequisites for such significant growth.
[0272] Due to high cost of cargo shipments from Earth to space and back (about 10 million USD/t), at this stage of technology development, the industrial production in space is physically impossible and economically impractical. However, with a transportation system capable of providing cargo turnover between the Earth surface and the orbit in the amount of about 100 million tons per year and more at a low cost of delivery of 1 ton of cargo—about 1000 USD/ton or less—many Earth technologies will be able to reach a new level.
[0273] A variant of embodiment of the proposed solution on the planet Earth, according to one version of its design with load capacity of about 100 million tons, is as follows: general planetary vehicle 5 represents a closed “wheel” (see
[0274] The launch process of general planetary vehicle 5 proceeds as follows. When electric power is supplied to the winding of linear electromagnetic drive 12 of at least one of linear flywheels 10, a traveling magnetic field is generated. In vacuum channel 9, located in pressure hull 8 of general planetary vehicle 5, there is a linear flywheel 10 having a magnetic and/or electromagnetic suspension 11 and being a kind of rotor of linear electromagnetic motor. Therein, a current is induced that will interact with the magnetic field which generated it, and linear flywheel 10, which does not experience any resistance (it is placed in vacuum), will come into motion (see
[0275] The payload 14 (loads and passengers) is placed into general planetary vehicle 5 being held on launch overpass 6, with the first linear flywheel 10.1 having specific weight of 2 tons per meter, pre-rotated to velocity of 16 km/s, and exactly the same, but quiescent, the second linear flywheel 10.2. The payload 14 is preferably placed on general planetary vehicle 5 prior to the start of linear flywheel 10. The payload 14 is placed both inside and outside pressure hull 8 of general planetary vehicle 5, but so that the load as a whole is evenly distributed along the length of the L.sub.0, m, of linear bearing structure 7. After release of the locks 19 (see
[0276] Also, upon lifting from launch overpass 6, general planetary vehicle 5 will be subjected to increased impact from the air flows, but they will not have a significant effect on its operation. Calculations show that the non-resting general planetary vehicle 5 has a unique flexural rigidity and stability which not available to static structures due to the rotational movement of linear flywheels 10. Thus, the additional load of 1,000 tons applied to the section of the general planetary vehicle 5 with a length of 1 kilometer, will bend it relative to the ideal circle by no more than 10 centimeters.
[0277] Mathematical analysis shows that the lifted general planetary vehicle 5 will be in equilibrium only if its total kinetic energy is equal to that of a body of the same mass moving at the first cosmic velocity. If the total energy is higher, the diameter of the “ring” of general planetary vehicle 5 will begin to increase, and if lower—to decrease. Then, in order to lift the general planetary vehicle 5, it is necessary to have either initial excess of kinetic energy (linear flywheels 10 are accelerated on Earth, before launch, to a higher velocity), or in the process of lifting, it is necessary to reduce the mass of the general planetary vehicle 5 by dropping ballast 26. The preferred is the combination of these techniques.
[0278] As ballast 26, ecologically friendly to Planet Earth substances and materials are used: water or pre-liquefied air, oxygen or nitrogen.
[0279] The tension of pressure hull 8 of general planetary vehicle 5, as its diameter increases, will be relatively small: its length under Earth conditions will increase by 1.57% per each 100 kilometers of lifting. Elongation of pressure hull 8 is compensated by moving its rigid units 27 relative to each other, the ends of which, for example, telescopically fit into each other and are interconnected, for example, by hydraulic cylinders (not shown on figures). Linear flywheel 10, for example, in the form of a closed multilayer endless belt, which represents a kind of rotor of linear electromagnetic motor, will be extended by elastic stretching or slight displacement of the layers of the forming belt with respect to each other (see
[0280] The lifting velocity of general planetary vehicle 5 at any section of the track can be set within wide limits, from pedestrian speed to aircraft velocity. General planetary vehicle 5 passes through atmospheric section at minimum possible radial velocities.
[0281] After leaving the dense atmosphere, the reversible mode of linear electromagnetic drive 12.1 of the first linear flywheel 10.1 is switched on to generator mode. Linear flywheel 10.1 will start to brake and linear electromagnetic drive 12.1 will generate electric current. This energy is transmitted through control system 17 and communication system 18 to linear electromagnetic drive 12.2 of the second linear flywheel 10.2, which is accelerated in counter direction to the movement of the first linear flywheel 10.1 (see
[0282] As a result, the second linear flywheel 10.2, having, for example, same mass as the first linear flywheel 10.1, previously stationary with respect to pressure hull 8 of linear bearing structure 7 of general planetary vehicle 5, starts to rotate in reverse direction relative to the first linear flywheel 10.1. This ensures the law of energy conservation, in the process of insertion of payload 14 from surface of planet 1 into planned circular orbit 13 and stability of kinetic energy of members of general planetary vehicle 5 rotating around planet 1.
[0283] Pressure hull 8 of general planetary vehicle 5 and everything inside therein, and all that is attached to it from the outside—linear electromagnetic drives 12 with linear flywheels 10, as well as detachable transportation compartments 15.2 with payload 14 and the like—subject to law of conservation of angular momentum of the system, will come into rotation. It will start rotating in the same direction as the first linear flywheel 10.1 until it reaches a circumferential velocity equal to the first cosmic velocity. Radial velocity of general planetary vehicle 5 will fall to zero. Thereafter, at altitude of, for example, 400 kilometers, the payload 14 (cargo and passengers), delivered to destination, is unloaded, for example, into orbital circular (seizing the planet) complex 30 located at altitude H, m, of planned circular orbit 13 of planet 1 (see
[0284] Landing of general planetary vehicle 5 on Earth is performed in reverse order.
[0285] In this way, general planetary vehicle 5 will be put into near space in few hours if overloads therein are assumed at the level of the modern aerobus at the moment of its take-off (acceleration around 1-2 m/sec.sup.2).
[0286] During transportation loop of general planetary vehicle 5, it will not require any outside power supply. General planetary vehicle 5 will consume the initial kinetic energy reserve, which from the first linear flywheel 10.1, during launch of general planetary vehicle 5, will be redistributed to its pressure hull 8, and upon return to the planet 1, will be redistributed again between linear flywheels 10.1 and 10.2, for example, partially transmitted to at least the second linear flywheel 10.2. To the internal energy of the system of general planetary vehicle 5, space cargo energy will be added,—payload 14, delivered from space to Earth. For example, delivering a ton of cargo from the Moon will produce the same amount of energy as a ton of oil (the lunar cargo with respect to Earth has kinetic and potential energy which are utilized by general planetary vehicle 5 and converted into electrical form).
[0287] On the way to space and back, general planetary vehicle 5 will receive such amount of cheap energy that will satisfy both its own needs and a large part of the energy needs of mankind as a whole. In addition to the described energy source—space cargo energy, there are at least three other energy sources suitable for use by the proposed general planetary geospatial transportation complex: solar energy obtained, for example, through solar panels, which can be fixed on the pressure hull 8; ionosphere currents and the Earth's rotational energy around its axis (not shown). The energy thus obtained by general planetary vehicle 5 will be either accumulated in its linear flywheels 10 or transferred to planet Earth.
[0288] It is estimated that the gross launch mass of general planetary vehicle 5 in the described example could be 400 million tons (10 tons per linear meter), payload 14 will be 100 million tons (2.5 tons per linear meter), passenger capacity—100 million people.
[0289] As shown by the examples of calculation of process of payload 14 insertion from Earth's surface to planned circular orbit 13 of altitude H, m, the method and variants of embodiment of the invention, specified in the disclosed materials, the technical and economic parameters of the general planetary geospatial transportation complex by Yunitski, are optimized and ensure the industrialization of near space in the foreseeable future with the aim of taking the environmentally dirty earth-based manufacturing industry outside the biosphere.
[0290] Similar to the described embodiment of general planetary geospatial transportation complex by Yunitski on planet Earth, it is possible to implement it, for example, on the Moon, Mars, or on another planet, as well as on gaseous atmosphere giants such as Jupiter and Saturn, and on planets that have no land, but have an ocean.
[0291] Variants of the described design of general planetary geospatial transportation complex by Yunitski, as well as the method for planet 1 surface to its circular orbit payload insertion, possess novelty and meet the criterion of “distinctive features”, at the same time allow to create an effective geospatial transportation system ensuring achievement of all the set goals.