SYSTEM FOR SPACE PROPULSION AND SPACE LOITERING (ABOVE-STRATOSPHERE AIR LOITERING)

Abstract

To achieve a special spacecraft (flying aircraft) having propulsion efficiency that is several times (several orders of magnitude) greater than that of a solar sailcraft and the like, and requires practically no disposable (in space) and expensive rocket fuel or the like, and also to achieve a stratospheric flying aircraft capable of loitering. The present invention applies the difference in pressure (internal pressure) acting on wall surfaces (inner walls) or the like at both ends of a propulsion module body (aerial body) in space where there is no atmosphere or the like. Specifically, the present invention adopts a propulsion method as set forth in the claims.

Claims

1-17 (canceled)

18: A spacecraft propulsion system and its related equipment (incl. the following iron balls return devices etc with a slower tempo in the operation) that could generate some power repeatedly from internal pressure difference (by uniquely relevant apparatus of a non-air pressure type), by varying each impact angle between an iron ball(s) shooting with the same ball launchers (incl. electromagnetic launchers which are able to shoot just synchronously, quickly, continuously) etc and (around) each inner wall of either side of a hollow body (as a space propulsion module), especially in case of completely (perfectly) inelastic collision by electromagnet apparatuses (see FIG. 1 & 3) and the like or by unique device with a kind of automatic opening & shutting multi-cap type (see FIG. 4) etc as to the one side, just after inserting a flowable substance(s) such as the above iron balls (with large mass) and so forth (not particles in the air in particular) inside the unique hollow body in the closed <fluid> system.

19: A spacecraft propulsion system and its associated equipment (incl. the following related devices etc) that could produce some force sustainably from internal pressure difference by mainly relevant apparatus of an air pressure type, by reducing wind pressure as to the one side of the hollow body with specific air-barrier devices (see FIG. 7, 8, 9) just after inserting a flowable substance(s) such as the particles in the air in particular for continuously air circulation inside the above hollow body (as a space propulsion module) in the closed <fluid> system.

20: A space endurance flight system (staying in air above the stratosphere, in advance, utilizing chiefly the related apparatus of the above air pressure type in the claim 19) and the attached equipment including this space propulsion module'direction changing devices applied variation on the collision angle value and so on in addition to the shooting machine adopting a special technique of a magnetic projectile(s) called Coil gun and/or Rail gun and/or a sort of Mass driver: Slingatron etc as to each driving method by the shooting devices indicated with the main claim 18 and supplementary wind power rotor units (see FIG. 10) for neutrally power distribution devices.

21: A construction (and preservation) method and its relevant apparatus for unique (aero)space structure, applying propulsive forces of the space propulsion system indicated with the claim 18 & 19, etc to a counterweight (and the like) for a space elevator (for mainly the low earth orbit) and so on.

Description

BRIEF DESCRIPTION OF DRAWINGS

[0045] FIG. 1 shows mainly names of parts for a space propulsion system device of a non-air pressure type.

[0046] FIG. 2 (omitting)

[0047] FIG. 3 indicated sequences (ordering operation) for the space propulsion system (of FIG. 1)

[0048] FIG. 4 shows each unique device with an automatic opening & shutting multi-cap type for the completely inelastic collision.

[0049] FIG. 5 gives application examples practically for the spacecraft propulsion system

[0050] FIG. 6 (omitting)

[0051] FIG. 7 shows mainly names of parts for a (aero)space propulsion system apparatus of an air pressure type.

[0052] FIG. 8 authenticates effectiveness of (aero)space propulsion by the air pressure difference with the above apparatus (of FIG. 7)

[0053] FIG. 9 shows uniquely a certain condition of the air barrier system devices.

[0054] FIG. 10 indicates supplementary wind power rotor units for neutrally power distribution devices.