公开(公告)号：US4290570A

公开(公告)日：1981-09-22

申请号：US50256

申请日：1979-06-20

申请人： John V. Smolik ,  Ronald V. Swanson ,  Charles P. Rubin ,  James C. Blaschke ,  Roger J. Wagner

发明人： John V. Smolik ,  Ronald V. Swanson ,  Charles P. Rubin ,  James C. Blaschke ,  Roger J. Wagner

IPC分类号： B64G1/14 ,  B64G1/22

CPC分类号： B64G1/22 ,  B64G1/14

摘要： A spacecraft specifically adapted for launch from the space shuttle by means of a cradle having locking and ejection mechanisms mounted therein. The cradle fastens into the payload bay of the space shuttle and returns therewith for reuse in subsequent launches. The spacecraft mounts at three points to the cradle, and the cradle mounts at three points to the shuttle such that a plane through the attachment points passes through the roll axis of the spacecraft at approximately the center of mass thereof. The cradle utilizes the truss structure of the spacecraft to produce the required stiffness by providing a structural tie between the two ends and the bottom of the cradle. At launch, the spacecraft is ejected with both linear and angular momentum, the spin providing gyroscopic stability. The locking mechanisms in the cradle can be remotely controlled to relock the spacecraft to the cradle in the event of an unsuccessful deployment attempt. The spacecraft includes a safety circuit employing acceleration sensing switches which sense spin-up of the spacecraft and prevent premature ignition of the perigee boost motor. The spacecraft has imbedded within its envelope a solid-propellant perigee boost motor surrounded by a liquid-propellant apogee motor. By employing apogee and perigee propulsion stages internal to the spacecraft, the storage length in the space shuttle is minimized, and the geometry and mass characteristics of the spacecraft make for a stable spinning vehicle during both the perigee and apogee boost phases.

摘要翻译： 专用于通过其中安装有锁定和弹出机构的支架从航天飞机发射的航天器。 托架紧固到航天飞机的有效载荷舱中，并随之返回，以便在随后的发射中重新使用。 航天器在三点安装在支架上，支架在三点上安装在梭子上，使得穿过连接点的平面大致在其中心附近穿过航天器的滚轴。 摇篮利用航天器的桁架结构，通过在支架的两端和底部之间提供结构连接来产生所需的刚度。 在发射时，航天器以线性和角动量喷射，旋转提供陀螺稳定性。 在不成功的部署尝试的情况下，托架中的锁定机构可以被远程控制以将航天器重新锁定到支架上。 航天器包括一个采用加速度传感开关的安全电路，该开关感测到航天器的旋转并防止近地点升压马达的过早点火。 航天器在其信封内嵌入了由液体推进剂远地度电机包围的固体推进剂近地点升压电机。 通过在航天器内部采用远地点和近地点推进阶段，航天飞机的存储长度最小化，并且在近地点和远地点升压阶段期间，航天器的几何形状和质量特性为稳定的纺纱车辆。