| 摘要 |
<p>A spacecraft (1) with at least one deployable panel structure (2, 2') comprising a first panel element (20) hingedly connected to a support element (12, 12') at the spacecraft body (10) so that the first panel element (20) can be hinged out about a first hinge axis (21) from a storage position to a deployed position; a second panel element (22) hingedly connected to said support element (12,12') so that the second panel element (22) can be hinged out about a second hinge axis (23) from a storage position to a deployed position wherein the first hinge axis (21) and the second hinge axis (23) are not parallel; and a connecting mechanism (27) adapted to interconnect the first panel element (20) with the second panel element (22) when both panel elements are deployed in order to establish a connection between both panel elements (20, 22).</p> |
