FIELD: aircraft engineering.
SUBSTANCE: spacecraft comprises airframe 1 and panel of solar batteries 6 secured at frame 2 shaped to rod-type frame structure shaped to skewed pyramid. Pyramid base 3 is articulated with spacecraft airframe 1 by brackets 5. Said base in initial position is locked by pyro means 4. Pyramid vertex 7 in working position interacts with latch (pos. B) rigidly secured at spacecraft airframe 1. Frame structure 2 and its fasteners feature higher stiffness. This allows increase in frequency and decrease in amplitude of solar battery panels oscillations caused by programmed turns of spacecraft and other manoeuvres.
EFFECT: higher reliability, longer life.
4 dwg
Title | Year | Author | Number |
---|---|---|---|
SPACECRAFT | 2002 |
|
RU2231484C2 |
SOLAR CELL PANEL FOR SPACECRAFT | 2010 |
|
RU2460676C2 |
SPACECRAFT SOLAR BATTERY | 1998 |
|
RU2167793C2 |
UNIT OFFICES AND OPENING THE VALVES OF SOLAR BATTERIES OF SPACECRAFT | 2010 |
|
RU2441817C1 |
SPACECRAFT SOLAR BATTERY | 2002 |
|
RU2214949C1 |
SOLAR BATTERY MECHANICAL DEVICE STRUCTURE MANUFACTURING METHOD | 2019 |
|
RU2716513C1 |
SOLAR BATTERY OPENING TEST BENCH | 2010 |
|
RU2468969C2 |
SPACECRAFT SOLAR BATTERY | 2001 |
|
RU2221731C2 |
SOLAR BATTERY (VERSIONS) | 2004 |
|
RU2258640C1 |
BENCH FOR OPENING PANELS OF SOLAR BATTERY | 2011 |
|
RU2483991C1 |
Authors
Dates
2015-02-10—Published
2013-09-05—Filed