ARTIFICIAL ORBITAL RING COMPLEX BY YUNITSKI AND METHOD OF REALIZATION THEREOF

Abstract

The disclosure relates to the area of space science, in particular, to the area of industrialization of outer space and, directly, to the facilities for inserting and moving various objects in circumplanetary cosmic space. It is intended to solve geocosmic problems in industrial-scale volumes—to carry out research and development, special-purpose, touristic and other types of works and services in outer space and stabilize global climate. Artificial orbital ring complex by Yunitski is made in the form of a ring satellite, located in a circular orbit around a natural cosmic body in the equatorial plane, which comprises: structural frame, utilities and communications, power units, transition galleries positioned in annular housing with protective shell, gate chambers with docking units, configured to dock with space vehicles, residential and research-production units, equipped with systems of control, life support, active and passive protection against the harmful effects of space. The structural frame is longitudinally tensioned, and the ring satellite is in circular motion in orbit around the natural cosmic body with velocity V.sub.0, m/sec, defined by the ratio:

1≤V0/V.sub.1H≤1.01,

where V.sub.1H, m/sec,—first space velocity for the equatorial circular orbit of the location of the ring line connecting the centers of mass of the cross sections of the artificial orbital ring complex, at altitude of H.sub.0, m defined by the ratio:

0.02≤H.sub.0/R.sub.0≤0.5,

where R.sub.0, m,—radius of natural cosmic body in equatorial plane.

Claims

1. An artificial orbital ring complex, in the form of a ring satellite, located in a circular orbit around a natural cosmic body in an equatorial plane, comprising: a structural frame, utilities and communications, power units, transition galleries placed in annular housing with a protective shell, gate chambers with docking units configured to dock with space vehicles, residential and research-production units equipped with systems of control, life support, active and passive protection against the harmful effects of space; wherein the structural frame is longitudinally tensioned, and the ring satellite is in circular motion in orbit around the natural cosmic body with velocity V.sub.0, m/sec, defined by the ratio:
1≤V.sub.0/V.sub.1H≤1.01, where V.sub.1H, m/sec,—first space velocity for the equatorial circular orbit of the location of the ring line connecting centers of mass of cross sections of the artificial orbital ring complex, at altitude of H.sub.0, m, defined by the ratio:
0.02≤H.sub.0/R.sub.0≤0.5, where R.sub.0, m,—radius of the natural cosmic body in the equatorial plane.

2. The complex according to claim 1, wherein the center of mass of each cross section of the structural frame is aligned with the center of mass of the same cross section of the artificial orbital ring complex.

3. The complex according to claim 1, wherein the structural frame contains at least one tensioned load-bearing member encircling the natural cosmic body in the equatorial plane.

4. The complex according to claim 1, wherein the load-bearing member is formed by mating of load-bearing structure comprising longitudinally tensioned extended elements, with a body of the load-bearing member and/or with an annular housing with the protective shell.

5. The complex according to claim 1, wherein extended elements of the load-bearing structure are at least one of: wire, and/or rods, and/or twisted or untwisted ropes, and/or strands, strips, bands, tapes, tubes and other extended elements.

6. The complex according to claim 1, wherein the structural frame is electrically conductive.

7. The complex according to claim 1, wherein the structural frame is longitudinally tensioned with force F.sub.0, N, defined by the ratio:
1≤F.sub.0/F.sub.1≤1.01, where: F.sub.1, N,—axial force due to action of centrifugal force on the structure of the ring satellite.

8. The complex according to claim 1, wherein the natural cosmic body is planet Earth.

9. The complex according to claim 1, wherein the structural frame is at least one longitudinally tensioned thin-walled tube of internal diameter D.sub.0, m, defined by the ratio:
1≤D.sub.0/h.sub.0≤5, where: h.sub.0, m,—the average height of homo sapiens living on Earth.

10. A method of using an artificial orbital ring comprising a structural frame, the method comprising transporting electric power as a power line; docking gate chambers with space vehicles; the orbital ring comprising residential and research-production units equipped with systems of control, life support, active and passive protection against the harmful effects of space; longitudinally tensioning the structural frame; and causing the ring satellite to orbit in a circular motion around a natural cosmic body with velocity V.sub.0, m/sec, defined by the ratio:
1≤V.sub.0/V.sub.1H≤1.01, where V.sub.1H, m/sec,—first space velocity for an equatorial circular orbit of a location of a ring line connecting centers of mass of cross sections of the artificial orbital ring complex, at altitude of H.sub.0, m, defined by the ratio:
0.02≤H.sub.0/R.sub.0≤0.5, where R.sub.0, m,—radius of the natural cosmic body in an equatorial plane.

11. A method of realization of an artificial orbital ring satellite complex comprising delivery at a first space velocity of parts of structural frame with a load-bearing member onto a circular orbit of a natural cosmic body, utilities, communications, power, residential and research-production units, transition galleries, their arrangement and assembly in and/or on the annular housing with a protective shell, encircling the natural cosmic body, testing and verifying performance of all operational parameters of the ring satellite complex, the method further comprising: (a) positioning the ring satellite complex in an equatorial plane of a circular orbit of the natural cosmic body, wherein the ring satellite complex is made with a length of a ring L.sub.0m, defined by the ratio
1.01≤L.sub.0/L.sub.1≤1.5, where: L.sub.1, m,—length of an equator of the natural cosmic body; and (b) during installation, longitudinal tensioning an extended load-bearing structure of the load-bearing member of the structural frame, by increasing rotation velocity of the ring satellite complex in the circular orbit to a velocity of V.sub.0, m/sec, defined by the ratio:
1≤V.sub.0/V.sub.1H≤1.01, where V.sub.1H, m/sec—first space velocity for the equatorial circular orbit of a location of a ring line connecting centers of mass of cross sections of the artificial orbital ring complex, at an altitude of H.sub.0, m, defined by the ratio:
0.02≤H.sub.0/R.sub.0≤0.5, where R.sub.0, m,—radius of the natural cosmic body in the equatorial plane.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The essence of the invention will be explained in detail by the accompanying drawings (FIGS. 1-11) showing the following:

[0031] FIG. 1—layout image of the artificial orbital ring complex by Yunitski—view from space from the pole side (embodiment);

[0032] FIG. 2—layout image of the plane of location of the orbit of the artificial orbital ring complex by Yunitski—general view from space from the side of the equator (embodiment);

[0033] FIG. 3—layout image of the artificial orbital ring complex by Yunitski on the specified circular orbit around the natural cosmic body—view from space from the pole side (embodiment);

[0034] FIG. 4—layout image, on the specified circular orbit around the natural cosmic body, of the artificial orbital ring complex by Yunitski in toroidal form—general view with sections (embodiment);

[0035] FIG. 5—layout image of the general view of the artificial orbital ring complex by Yunitski on the specified circular orbit—general view with cross section (embodiment);

[0036] FIG. 6—layout image of embodiment of the artificial orbital ring complex by Yunitski with high-speed transport system in the form of the string track structure—general view with cross section;

[0037] FIG. 7—layout image of embodiment of docking of the artificial orbital ring complex by Yunitski with space vehicle—general view;

[0038] FIG. 8—layout image of the general view of the artificial orbital ring complex by Yunitski, consisting of three frames with annular housings combined in a single belt—general view (embodiment);

[0039] FIG. 9—layout image of cross section of the layers of passive protection of protective shell of annular housing;

[0040] FIG. 10—layout image of distribution of forces acting on the elements of the structure of the artificial orbital ring complex by Yunitski; and

[0041] FIG. 11—layout image of the elements of the annular housing, connected with each other by bellows—longitudinal section (embodiment).

DETAILED DESCRIPTION

Positions in the Figures

[0042] 1—ring satellite; [0043] 2—natural cosmic body; [0044] 3—plane of location of the ring satellite (plane of the equator of the natural cosmic body); [0045] 4—equator of the natural cosmic body; [0046] 5—circular orbit; [0047] 6—center of mass of the natural cosmic body; [0048] 7—structural frame; [0049] 8—utilities; [0050] 9—communications; [0051] 10—power units; [0052] 11—transition galleries; [0053] 12—annular housing; [0054] 13—protective shell; [0055] 14—gate chambers; [0056] 15—docking units; [0057] 15.1—docking units on the external and/or lateral sides of the load-bearing body; [0058] 15.2—docking units on the internal side of the load-bearing body (for space vehicle); [0059] 16—space vehicle (embodiment); [0060] 17—passive protection system; [0061] 17.1—anti-meteorite layer; [0062] 17.2—anti-radiation layer; [0063] 17.3—heat insulation layer; [0064] 18—space; [0065] 19—residential units; [0066] 20—research-production units; [0067] 21—clusters of annular housing; [0068] 22—bellows; [0069] 23—load-bearing member; [0070] 23.1—extended element of load-bearing member; [0071] 23.2—body of load-bearing member; [0072] 24—high-speed transport system (embodiment); [0073] 25—thin-walled tube of high-speed transport system (embodiment). [0074] M—the line of centers of mass of the structural frame; [0075] M.sub.1—the line of centers of mass of the cross sections of the artificial orbital ring complex; [0076] D.sub.0, m,—internal diameter of thin-walled tube; [0077] h.sub.0, m,—the average height of homo sapiens living on Earth (not shown in Figures); [0078] V.sub.0, m/sec,—circular velocity of the ring satellite in the orbit of the natural cosmic body; [0079] V.sub.1H, m/sec,—first space velocity for the equatorial circular orbit of the location of the ring line connecting the centers of mass of the cross sections of the artificial orbital ring complex; [0080] R.sub.0, m,—radius of natural cosmic body; [0081] R.sub.1, m,—radius of circular orbit of ring satellite; [0082] H.sub.0, m,—altitude of circular orbit of the location of the ring line connecting the centers of mass of the cross sections of the artificial orbital ring complex; [0083] L.sub.1, m,—length of ring satellite in equatorial plane of circular orbit of natural cosmic body; [0084] L.sub.0, m,—length of equator of natural cosmic body; [0085] F.sub.0, N,—axial tensile force of structural frame; [0086] F.sub.1, N,—centrifugal force on structure of ring satellite; and [0087] F.sub.T, N,—gravity force acting on ring satellite in any of its points.

[0088] The essence of the invention lies in more detail in the following. The claimed artificial orbital ring complex by Yunitski comprises ring satellite 1, encircling a natural cosmic body 2 in its equatorial 4 plane 3 (see FIGS. 1-3). Hereby, the ring satellite 1 is located in a circular orbit 5 of the natural cosmic body 2, matching with equatorial 4 plane 3 of this natural cosmic body 2.

[0089] To the ring satellite 1, a habitable space complex is referred to, encircling the natural cosmic body 2 and configured toroidal-shaped to rotate around the center of mass 6 of the natural cosmic body 2 (see FIGS. 3 and 4). Additionally, the ring satellite 1 is made self-stabilizing by centrifugal forces F.sub.1, N, axial tensile forces F.sub.0, N, and gravity forces F.sub.T, N, of any part of the said ring satellite 1 (see FIG. 1). The ring satellite 1 contains interconnected structural frame 7, utilities 8 and communications 9, power units 10 and transition galleries 11, positioned into annular housing 12 with protective shell 13 (see FIGS. 5 and 6).

[0090] Hereby, the annular housing 12 of the ring satellite 1 is equipped by integrated therein gate chambers 14 with docking units 15 (15.1 and 15.2), configured to dock with any of the known space vehicles 16, for instance, the general planetary vehicle by Yunitski (see, for instance, FIG. 7). Furthermore, the annular housing 12 of the ring satellite 1 is equipped with positioned therein and combined there in between the systems of control and life support (not shown in Figures), as well as the systems of active (not shown in Figures) and passive 17 protection against the harmful effects of space 18, and—residential 19 and research-production 20 units (see FIGS. 7-9).

[0091] The arrangement of utilities 8, communications 9, transition galleries 11, gate chambers 14 with docking units 15, as well as the united systems of control, life support, active and passive 17 protection against the harmful effects of space, residential 19, research-production 20 and power 10 units, may have any design and functioning algorithm characteristic to the similar systems used in modern operating space stations to ensure the solution of the relevant orbital problems (see FIGS. 5-7 and 9). Alternatively, as passive space protection systems 17, the protective shell 13 of the annular housing 12 may be embodied as a multilayer one and comprise, for instance, anti-meteorite 17.1, anti-radiation 17.2, and heat insulation 17.3 layers, including earth biogeocenosis with a fertile soil layer (see FIG. 9).

[0092] The combined systems of control, energy and life support of the proposed complex are interconnected. Hereby, all said systems of the ring satellite 1 are distributed along the entire length of the annular housing 12 and ensure the functions of each of the systems in any separate section of the artificial orbital ring complex. Additionally, depending on the design option, the annular housing 12 can be made of clusters 21 combined by bellows 22 (see FIGS. 3, 7, 8 and 11). The embodiment of the annular housing 12 with the clusters 21 reduces the power consumption, required to provide elastic deformation in the longitudinal direction of the structural frame 7 of the annular housing 12 during the positioning of the ring satellite 1 in the circular orbit 5 of the natural cosmic body 2 and expand the range of materials, used for the manufacture thereof, as well as increase the effectiveness of passive protection 17, against the harmful influence of space 18, of individual zones of the artificial orbital ring complex.

[0093] An essential circumstance of the proposed artificial orbital ring complex is that its structure contains at least one continuous member, which is its structural frame 7 encircling the natural cosmic body 2 in the plane 3 of its equator 4. Hereby, the structural frame 7 contains at least one extended load-bearing member 23 (see FIGS. 5 and 6). Hereby, in any variants of practical realization of the structure of the ring satellite 1, its structural frame 7 in operational condition is tensioned in longitudinal direction of the annular housing 12. Thus, the dynamic stiffness and required strength of the ring satellite 1, which, while in orbit, rotates around the planet at a velocity exceeding the first space one, and therefore is in a prestressed state under the influence of centrifugal forces.

[0094] The tensile force for longitudinal tensioning of the structural frame 7 is ensured by a controlled additional increase in velocity during circular motion of the structural frame 7 and the annular housing 12 of the ring satellite 1 in circular orbit 5 around the natural cosmic body 2 in order to achieve a value of the specified velocity V.sub.0 when positioned in a circular orbit 5. Such additional increase in velocity during circular motion, as well as the circular motion itself, can be provided by any of the known methods, for example, by using jet engines of the ring satellite 1 (not shown in Figures), or by general planetary vehicle by Yunitski, which enters the orbit also in the equatorial plane. Positioning of the ring satellite 1 in the circular orbit 5 of the natural cosmic body 2 is performed in such a way that the center of mass M of each cross section of the structural frame 7 is aligned with the center of mass M.sub.1 of the same cross section of the artificial orbital ring complex, while these centers of mass are located in the same plane with the center of mass 6 of the natural cosmic body 2 (see FIG. 4). Moreover, the load-bearing structure of the structural frame 7 must pass along the line of the centers of mass (or the lines of the centers of inertia) of the structural elements of the ring satellite 1 in order to exclude its unfavorable dynamics (longitudinal and transverse vibrations) from the operation of the transport complex (especially during its acceleration and deceleration). This ensures the integrity of the structure of the artificial orbital ring complex and will prevent its dynamic destruction.

[0095] Equipping the artificial orbital ring complex with any of the known high-speed transport systems 24, such as one based on the string track structure, is a preferred embodiment. In this case, its structure should provide at least one transport artery, for example, in the form of a thin-walled tube 25 with a corresponding internal diameter D.sub.0. This will allow to carry out rapid commuting (communication) of specialists and required cargo flows along the entire annular housing 12 of the ring satellite 1 already in the circular orbit 5 (see FIGS. 6, 9).

[0096] Depending on the design option, the load-bearing member 23 may be formed by mating the load-bearing structure consisting of longitudinally tensioned extended elements 23.1 with the body 23.2 of the load-bearing member 23, and/or with the annular housing 12 with the protective shell 13, and/or with longitudinally tensioned, at least one, thin-walled tube 25 with the specified internal diameter D.sub.0. This will improve the efficiency of the use of the various structural elements of the ring satellite 1. As extended elements 23.1 of the load-bearing member 23, depending on the specific design option, one and/or several bundles can be used, for example, made of wire and/or rods, and/or twisted—untwisted ropes, cables, bands, strips, cords, strands, tubes or other extended elements made of any high-strength materials (not shown in the Figures).

[0097] Hereby, the structural frame 7 may be electrically conductive in the longitudinal direction, which will expand its functionality. Accordingly, the described embodiment of the structural frame 7 in the form of a longitudinally conductive element makes it possible to consider, as an additional object of the invention, the use of the structural frame 7 for an additional purpose—as a power line for transmitting electric power along the orbital ring complex.

[0098] Alternatively, the proposed artificial orbital ring complex by Yunitski may comprise several (two or more) interconnected annular housings 12. Such annular housings 12 may be arranged in parallel planes 3 and combined into a single annular belt which center of mass coincides with the center of mass 6 of the natural cosmic body 2 (see FIG. 8).

[0099] Maintaining the stability of the positioning of the ring satellite 1 in a specified circular orbit 5 is ensured by centrifugal forces and, therefore, depends on the rotation velocity thereof. The optimal mode of operation of the artificial orbital ring complex by Yunitski located in the circular orbit 5 around said natural cosmic body 2 is the equilibrium state (see FIG. 10). For this, in optimal embodiments of operation, each element of the ring satellite 1 must have the velocity of V.sub.0 slightly higher than the first cosmic velocity for the circular orbit 5 of the ring satellite 1.

[0100] Maintaining equilibrium and stabilizing positioning of the ring satellite 1 in the specified circular orbit 5 is achieved by its rotation around the natural cosmic body 2 with the velocity V.sub.0, defined by the ratio:

1≤V.sub.0/V.sub.1H≤1.01,  (1)

[0101] where V.sub.1H,—first space velocity for the equatorial circular orbit of the location of the ring line connecting the centers of mass of the cross sections M.sub.1 of the artificial orbital ring complex.

[0102] The achievement in the circular orbit 5 by the ring satellite 1 of the specified velocity V.sub.0, satisfying the ratio (1), ensures the stability of its positioning and minimization of energy costs to realize such stabilization. A decrease in the velocity V.sub.0 beyond the lower limit of the ratio (1), that is, at V.sub.0/V.sub.1<1, will not allow, without special measures, to keep the ring satellite 1 from falling on the natural cosmic body 2, and an increase in its value beyond the upper limit of ratio (1), that is, at V.sub.0/V.sub.1>1.01, will not allow to realize the requirements of safety and preservation of the structural integrity of the artificial orbital ring complex due to the critical increase in internal tensile strain in the structural frame 7 and destruction thereof.

[0103] Hereby, the ring satellite 1 is positioned at altitude H.sub.0, m, defined by the ratio:

0.02H.sub.0/R.sub.0≤0.5,  (2)

[0104] where R.sub.0—radius of the natural cosmic body in the equatorial plane.

[0105] A decrease in the altitude H.sub.0 beyond the lower limit of the ratio (2), that is, at H.sub.0/R.sub.0<0.02, will lead to intensive deceleration of the ring satellite 1 in the upper atmosphere of the natural cosmic body 2, for example, the planet Earth, and the need for additional run-up thereof around the natural cosmic body 2, for example, using jet engines. An increase in values of the altitude H.sub.0 beyond the upper limit of the ratio (2), that is, at H.sub.0/R.sub.0>5, will lead to an excessively high altitude for the placement of the ring satellite 1 above the natural cosmic body 2 and a penalized efficiency of geospatial transportation between the natural cosmic body 2 and the ring satellite 1, wherein, for example, the industry of civilization living on the planet Earth can be located.

[0106] Additionally, the structural frame 7 of the ring satellite 1 in the operational state is formed longitudinally tensioned by force F.sub.0 defined by the ratio:

1≤F.sub.0/F.sub.1≤1.01,  (3)

[0107] where: F.sub.1,—centrifugal force acting on the structure of the ring satellite 1.

[0108] The range of pretension force F.sub.0 of the load-bearing structural frame 7 is selected based on the strength requirements provided by the design assignment and the feasibility of providing elastic deformation of the annular housing 12 of the ring satellite 1 under the action of centrifugal forces. The achievement of the value of the ratio (3) less than the specified limit value equal to 1, corresponds to the case when the load-bearing member 23 is not tensioned and the ring satellite 1 becomes unstable, since longitudinal compression will appear therein, which will lead to its falling on the natural cosmic body 2. If the upper limit of the ratio (3), equaling to 1.01, is exceeded, it becomes necessary to create axial tensile forces in the structure of the ring satellite 1, not due to the centrifugal forces, but, for example, with use of powerful jet engines, which is unacceptable during the long-term operation of the satellite. Additionally, the object of the present invention is to realize the artificial orbital ring complex in relation to the conditions of the planet Earth.

[0109] As noted above, to ensure the redistribution of specialists and cargos delivered from the Earth along the artificial orbital ring complex, it is advantageous to implement any of the known high-speed transport systems 24, such as high-speed transport system in the form of (not necessarily hermetically sealed) thin-walled tube 25 with the corresponding internal diameter D.sub.0 (see FIG. 6). In this alternative embodiment, the structural frame 7 may be made in the form of longitudinally tensioned, at least one, thin-walled tube 25 with the internal diameter D.sub.0 defined by the ratio:

1≤D.sub.0/h.sub.0≤5,  (4)

[0110] where: h.sub.0,—the average height of homo sapiens living on Earth.

[0111] The embodiment of the structural frame 7 from the longitudinally tensioned, at least one, thin-walled tube 25 of the internal diameter D.sub.0 defined by the ratio (4) is thanks to the optimization of the technology of constructing and servicing the artificial orbital ring complex. Reduction of the internal diameter of D.sub.0, of thin-walled tube 25 beyond the lower limit of the ratio (4), that is, when this ratio is less than 1, leads to penalized comfort of transportation of specialists and significant restrictions on the transportation of goods, in particular because a person will not be able to stand vertically in the cabin of the vehicle. When the internal diameter D.sub.0, of the thin-walled tube 25 increases beyond the upper limit of the ratio (4), that is, when this ratio has a value greater than 5, the material capacity and cost of the structure significantly increase with a significant deterioration in its manufacturability. Additionally, the thin-walled tube is required to prevent foreign objects from entering the trajectory of the orbital high-speed vehicle, for example, tools (wrench, screwdriver, etc.), parts (bolt, nut, etc.), which will be abundant in orbit if, for example, the space part of the earth industry is located in ring satellite 1.

[0112] The achievement of the set goals is also ensured by a method of realization of artificial orbital ring complex, the arrangement of which corresponds to the above design of the ring satellite 1, and its positioning in circular orbit 5 of a natural cosmic body 2. Such method includes delivery at the first space velocity of parts of the structural frame 7 with load-bearing member 23 onto the circular orbit 5 of the natural cosmic body 2, utilities 8, communications 9, power 10, residential 19 and research-production 20 units, transition galleries 11, their arrangement and assembly in and/or on the annular housing 12 with protective shell 13. Hereby, the testing and verifying performance of all operational parameters are performed on the arrangement of the ring satellite 1 assembly.

[0113] An essential condition for realization of the method is that, during installation, longitudinal tensioning is formed in the extended load-bearing structure of the load-bearing member 23 of the structural frame 7, by increasing the rotation velocity of the ring satellite 1 in circular orbit 5 to the velocity of V.sub.0, m/sec, defined by the ratio:

1≤V.sub.0/V.sub.1≤1.01,

[0114] where V.sub.1H,—first space velocity for the equatorial circular orbit of the location of the ring line connecting the centers of mass of the cross sections of the artificial orbital ring complex, at altitude of H.sub.0, m, defined by the ratio:

0.02≤H.sub.0/R.sub.0≤0.5,

[0115] where R.sub.0, m,—radius of natural cosmic body in equatorial plane.

[0116] Hereby, the ring satellite 1 is made with the length of the ring L.sub.0, m, defined by the ratio:

1.01≤L.sub.0/L.sub.1≤1.5,  (5)

[0117] where: L.sub.1, m,—length of the equator of the natural cosmic body.

[0118] Reducing the length of the ring L.sub.0 of the ring satellite 1 beyond the lower limit of the ratio (5), i.e. with L.sub.0/L.sub.1<1.01, will lead to the fact that the ring satellite 1 will be placed at too low an altitude and it will be necessary to constantly adjust its orbit in order to prevent falling thereof on the natural cosmic body 2. Increasing the length of the ring L.sub.0 of the ring satellite 1 beyond the lower limit of the ratio (5), i.e. with L.sub.0/L.sub.1>1.5, will lead to the fact that the ring satellite 1 will be placed too high above the natural cosmic body 2, which will penalize the logistics of geocosmic transportation therebetween and the natural cosmic body 2. Hereby, the positioning of the ring satellite 1 in circular orbit 5 encircling the natural cosmic body 2 is carried out in its equatorial plane 3.

[0119] The realization of the artificial orbital ring complex by Yunitski according to the claimed method can be carried out in the following ways. One alternative to the creation of an artificial orbital ring complex is the sequential delivery to the circular orbit 5 of the natural cosmic body 2 of the assembly elements and components of the ring satellite 1 by conventional space vehicles (rockets) and their subsequent assembly into a single complex. The assembly of an object in space orbit from separate parts is already known (for example, the MIR space station and the international space station). The optimum embodiment of the claimed complex is to prefabricate, assemble and debug, on the natural cosmic body 2, the entire structure of the ring satellite 1 with its subsequent delivery and positioning in intended circular orbit.

[0120] For this purpose, at the assembly stage, parts of the structural frame 7 and the annular housing 12 are combined into the ring satellite 1, equipped with a protective shell 13 provided by the design solution, as well as all systems including systems of control and life support. Further testing, verification and debugging of operability of all operational parameters of the complex in assembly are carried out, and positioning of the ring satellite 1 in circular orbit 5 of natural cosmic body 2 is carried out, for example, by combined simultaneous effort of large number of space rockets uniformly distributed along perimeter of the annular housing 12 of the ring satellite 1.

[0121] The process of positioning the ring satellite 1 in the circular orbit 5 of the natural cosmic body 2 is most expedient to be carried out in the following order: [0122] on the natural cosmic body 2, the structural frame 7 of the ring satellite 1 is assembled along the equator 4, on which the annular housing 12 thereof is fixed with the protective shell 13 and all other structural elements; [0123] perform testing and verification of operability of all operational parameters of the assembled ring satellite 1; [0124] with use of the known general planetary transport system by Yunitski, the assembled and tested structure of the ring satellite 1 fastened on the said system is raised to height of H.sub.0 at the first space velocity V.sub.1H, that is, to circular orbit 5 of a natural cosmic body 2 located in its equatorial 4 plane 3; [0125] then, by means of said general planetary transport system by Yunitski, the ring satellite 1 is further rotated in the circular orbit 5 to the intended design velocity V.sub.0 exceeding the first space velocity V.sub.1H by amount defined by the ratio (1); [0126] at the specified circular orbit 5, the ring satellite 1 is undocked from the general planetary transport system.

[0127] After delivery of the ring satellite 1 to the specified circular orbit, people and cargoes are redeployed along the zones of their priority location on the artificial orbital ring complex. It is advantageous to provide such movements by means of traffic arteries embodied as any of the known high-speed transport systems 24 mounted on the annular housing 12 and made, for example, in the form of a string transport track structure based on the above-described thin-walled tube 25 of the corresponding internal diameter D.sub.0.

[0128] Installation of the orbital ring complex in orbit using a general planetary vehicle can be carried out in stages: [0129] delivery to the circular orbit 5 of only the structural frame 7 (load-bearing structure) of the ring complex weighing within the load capacity of the general planetary vehicle—up to 10 million tons per flight; [0130] delivery of the remaining elements of the ring complex and their installation on the structural frame 7 (load-bearing structure), on the circular orbit 5 under zero gravity conditions, since the ring satellite 1 will have the first space velocity; [0131] run-up of the ring complex to the velocity exceeding the first space velocity, for example, by the value of 0.000001 V.sub.1H.

[0132] Similar to the described examples of the embodiment of the artificial orbital ring complex by Yunitski in the orbit of the Earth, its implementation is possible, for example, in the orbit of Mars, or in the orbit of another planet, or in the orbits of satellites of planets, for example, the moon, or in the orbits of other massive natural cosmic bodies, for which the above implementation principle will be entirely and completely fair.

[0133] While the said technical solution describes preferred embodiments of the structure, it is clear that the invention is not limited thereto and can be accomplished using other known structural elements within the scope of the specified combination of essential features of the present invention.