发明名称 |
D-wing deployable solar array |
摘要 |
<p>The power to weight ratio obtained with a spacecraft's solar array (3) is enhanced by a factor of at least two to five through use of support structure for individual solar panels or solar arrays (31a-17a) containing a curved outwardly bowed surface as deployed that packs essentially flat for storage. Defining a D-shaped wing (15a) in cross-section as deployed, the support structure (4 & 6) for a string of solar cells (10, Fig. 3) provides greater inertia and thereby greater rigidity than prior designs. One member (4) to the support structure is relatively flexible. One-hundred and eighty degree strain energy hinges (19) carried by the other support member (6) outwardly bows that flexible to define a curved sector when the support structure is released from the stowed condition in which the support structure is held relatively thin and flat. <IMAGE></p> |
申请公布号 |
EP1043228(A2) |
申请公布日期 |
2000.10.11 |
申请号 |
EP20000107487 |
申请日期 |
2000.04.06 |
申请人 |
TRW INC. |
发明人 |
DAILEY, DEAN R.;ELLIOTT, LEE E. |
分类号 |
B64G1/22;B64G1/44;(IPC1-7):B64G1/44;H01L31/045 |
主分类号 |
B64G1/22 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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