FIELD: space engineering; launching small payloads (up to 1 t) by means of light launch vehicles.
SUBSTANCE: proposed descent spacecraft has body, control units for orientation in space and units for coupling with launch vehicle. Plane of coupling descent spacecraft with launch vehicle coincides with transversal plane of symmetry of spacecraft. Body of descent spacecraft consists of two identical self-contained modules with pushing-apart member between them and connecting spacer which is made in form of extensible hollow members sunken in each other in initial state; they may be fixed relative to each other. Modules are sunken in extreme members of spacer and may move inside them; they may be fixed inside them.
EFFECT: extended functional capabilities due to elongation of spacecraft in working orbit.
1 dwg, 1 tbl
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|---|---|---|---|
| METHOD OF OPERATION OF RECOVERABLE SPACECRAFT | 1994 |
|
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| METHOD AND DEVICE FOR SINGLE-AXIS GRAVITATIONAL ATTITUDE CONTROL OF AXISYMMETRICAL SPACECRAFT IN ORBIT OF EARTH SATELLITE | 1996 |
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| METHOD OF CONTROL OF HYPERSONIC FLYING VEHICLE | 2000 |
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| METHOD OF CONTROL OF HYPERSONIC FLYING VEHICLE | 2002 |
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| METHOD OF MANOEUVRING DEVIATION OF SPACECRAFT ON ORBIT FROM COLLISION WITH OTHER BODIES | 2015 |
|
RU2586920C1 |
| DESCENT SPACECRAFT | 1991 |
|
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| METHOD OF TRANSPORT SPACE SYSTEM CONTROLLING | 2015 |
|
RU2605463C2 |
