| 摘要 |
<p>Apparatus for use in gyroscopically ejecting a spacecraft (23) supported in the open end of a spacecraft supporting cradle (21). The invention comprises a separable ejection restraint mechanism (30) attached between the cradle (21) and the spacecraft (23). The mechanism (30) restrains the thrust force applied to the spacecraft (23) for a predetermined time period in order to dissipate undetermined forces acting upon the spacecraft (23) prior to the ejection thereof. The mechanism (30) comprises a separable resilient portion (40) and a releasable clamp portion (50) coupled thereto. The resilient portion (40) comprises a spring loaded anchor rod arrangement (42, 43, 44) while the releasable clamp portion (50) comprises a spring loaded split ball clamp arrangement (51, 52). The invention also contemplates the use of a flexible carrier coupled between the spacecraft (23) and the cradle (21). The invention acts as a tether connected between the cradle (21) and spacecraft (23) which acts to establish a determinant state of force on the cargo and eliminate unwanted ejection-related problems prior to cargo deployment. In addition, the release of a single tether employed as the sole cargo release initiator minimizes the possible imparting of uncontrolled momentum to the cargo due to structural deformation energy.</p> |
