FIELD: rocketry and space engineering; small descent spacecraft injected into orbit by ballistic missiles removed from combat duty.
SUBSTANCE: proposed descent spacecraft has case, control members for its orientation in space and units for coupling with launch vehicle. Plane of connection of descent spacecraft with launch vehicle coincides with transversal plane of symmetry of case of spacecraft and its diameter coincides in this plane with transversal diameter of launch vehicle. Descent spacecraft case is made in form of body obtained by rotation of oval around its larger axis and said plane of connection with launch vehicle coincides with plane of smaller axis of oval.
EFFECT: increased volume of descent spacecraft at limited transversal diameter of launch vehicle.
1 dwg, 1 tbl
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|---|---|---|---|
| DESCENT SPACECRAFT | 2002 |
|
RU2234442C2 |
| METHOD FOR CONVERSION OF COMBAT SOLID-PROPELLANT ROCKETS INTO SOLID-PROPELLANT SPACE ROCKET AND SPACE ROCKET | 1998 |
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| SELF-CONTAINED ROCKET POD | 1993 |
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| METHOD OF INJECTION OF PAYLOAD INTO NEAR-EARTH SPACE BY MEANS OF AIRCRAFT ROCKET SPACE COMPLEX AND AIRCRAFT ROCKET SPACE COMPLEX FOR REALIZATION OF THIS METHOD | 2005 |
|
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| MANNED SPACECRAFT | 2001 |
|
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| SPACE SYSTEM FOR RECYCLING LARGE-SIZE SPACE DEBRIS | 2018 |
|
RU2695155C1 |
| METHOD OF RECOVERY OF RECOVERABLE LAUNCH VEHICLES AND DEVICE FOR REALIZATION OF THIS METHOD | 2001 |
|
RU2202500C2 |
| METHOD OF ATTAINMENT OF STEADY PROGRESS AND PROTECTION OF EARTH AGAINST DANGEROUS SPACE OBJECTS AND SYSTEM FOR STEADY PROGRESS OF CIVILIZATION | 1996 |
|
RU2112718C1 |
