FIELD: space engineering. SUBSTANCE: panels 8 are so placed between satellite supports 1 and 2 that each panel is engageable by its supports 10 with satellite supports 1 and 2. As a result, the panels do not longer transmit loads acting on them to their adjacent panels. EFFECT: lower loads on panels during rocket launching, higher reliability of freeing stack panels during their deployment because of the fact that contacting supporting members of panels and satellite are freed through turning satellite supports in the directions opposite to directions of turning of the stack; enlarged operating capabilities. 2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD OF DEPLOYMENT OF MULTI-SECTIONAL STRUCTURES AND MULTI-SECTIONAL STRUCTURE USED FOR REALIZATION OF THIS METHOD | 1993 |
|
RU2123875C1 |
| METHOD AND DEVICE FOR HOLDING OBJECTS | 1993 |
|
RU2130880C1 |
| DEVICE FOR INTERLOCK AND RELEASE OF OPENING MEMBERS | 1995 |
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RU2111155C1 |
| HOLDER | 1995 |
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| TORSION BUNDLE | 1995 |
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| METHOD FOR SEPARATION OF SATELLITES AND MOVING APART IN ORBIT AT GROUP LAUNCH BY ONE ROCKET | 1994 |
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| METHOD OF ATTACHMENT OF ARTICLES BY STATICALLY DETERMINATE COUPLING SYSTEM | 1992 |
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| EQUIPMENT FOR REGISTRATION OF MOUNTED STRUCTURES OF SATELLITE | 0 |
|
SU1818282A1 |
| FLYING VEHICLE | 1999 |
|
RU2198117C2 |
| MODULE-CONSTRUCTION SPACE VEHICLE | 1995 |
|
RU2092398C1 |
