公开(公告)号：US5833176A

公开(公告)日：1998-11-10

申请号：US748920

申请日：1996-11-14

申请人： Charles P. Rubin ,  John A Fabbri ,  George N. Young

发明人： Charles P. Rubin ,  John A Fabbri ,  George N. Young

IPC分类号： B64G1/22 ,  B64G1/44

CPC分类号： B64G1/443 ,  B64G1/222

摘要： A constrained solar array (24) for a satellite (20) and method for making the same are disclosed. The solar array (24) includes a superstructure (30) with solar cells (80) mounted thereon to provide power to a main satellite body (22) and instruments mounted thereon. A flexible tensile member (40) extends relative to the superstructure (30) and is placed under tension to place the solar array (24) in a constrained condition which reduces thermal transients in and increases the bending frequency of the solar array (24). Preferably, a pair of support arms (34,36) are cantilevered from the superstructure (30). The flexible tensile member (40) pulls upon the support arms (34,36) to apply bending moments to the superstructure (30) to maintain the solar array (24) in a distorted shape. The method includes heating one surface of the solar array (24) to thermally deform or bow the solar array (24) and then constraining the bowed solar array using a flexible tensile member (40) to prevent the solar array (24) from returning to its original configuration when the heat is removed from the solar array (24) during an eclipse.

摘要翻译： 公开了一种用于卫星（20）的约束太阳能阵列（24）及其制造方法。 太阳能阵列（24）包括其上安装有太阳能电池（80）的上部结构（30），以向主卫星体（22）和安装在其上的仪器提供电力。 柔性拉伸构件（40）相对于上部结构（30）延伸并且被放置在张力下，以将太阳能阵列（24）置于约束条件下，其降低太阳能阵列（24）的热瞬变并增加太阳能阵列（24）的弯曲频率。 优选地，一对支撑臂（34,36）从上部结构（30）悬臂。 柔性拉伸构件（40）拉动支撑臂（34,36）以向上层结构（30）施加弯矩，以将太阳能阵列（24）维持在变形状态。 该方法包括加热太阳能阵列（24）的一个表面以使太阳能阵列（24）热变形或弯曲，然后使用柔性拉伸构件（40）约束弓形太阳能阵列，以防止太阳能阵列（24）返回 其在日食期间当从太阳能阵列（24）去除热量时的其原始构造。

公开(公告)号：US4796033A

公开(公告)日：1989-01-03

申请号：US063347

申请日：1987-06-18

申请人： Charles P. Rubin ,  Thomas A. Bockrath

发明人： Charles P. Rubin ,  Thomas A. Bockrath

IPC分类号： H01Q15/14 ,  H01Q15/16

CPC分类号： H01Q15/168

摘要： A non-furlable paraboloidal radio frequency reflector (10) is formed of a mesh-like flexible reflective surface (18) supported by a central hub (12) and a peripheral rim (14). The hub and rim are interconnected by flexible spoke-like structural cables (16, 24) acting in tension to establish the desired spatial relationship. Reflector surface-positioning cables (20, 26) are secured at their ends to the hub, rim or structural cables and are further secured to the reflector surface at points of intersection (22) therewith intermediate their ends to thereby establish an approximation of the desired curved shape of the reflector surface.

摘要翻译： 非可膨胀抛物面射频反射器（10）由由中心毂（12）和外围边缘（14）支撑的网状柔性反射表面（18）形成。 轮毂和轮辋通过柔性的轮辐状结构电缆（16,24）相互连接起来，以起到张力作用以建立所需的空间关系。 反射器表面定位电缆（20,26）的端部固定到轮毂，轮辋或结构电缆上，并且在它们的端部之间的相交点（22）处进一步固定到反射器表面，从而建立所需的 反射面的弯曲形状。

公开(公告)号：US4303214A

公开(公告)日：1981-12-01

申请号：US910321

申请日：1978-05-30

申请人： Alois Wittmann ,  Charles P. Rubin

发明人： Alois Wittmann ,  Charles P. Rubin

IPC分类号： B64G1/14 ,  B64G1/22

CPC分类号： B64G1/14

摘要： A spacecraft specifically adapted for launch from a reusable launch vehicle such as 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可重复使用的运载火箭（例如航天飞机）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，托架在三点安装在梭子上，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。

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。

公开(公告)号：US4324374A

公开(公告)日：1982-04-13

申请号：US140555

申请日：1980-04-15

申请人： Alois Wittmann ,  Charles P. Rubin

发明人： Alois Wittmann ,  Charles P. Rubin

IPC分类号： B64G1/14 ,  B64G1/64

CPC分类号： B64G1/14 ,  B64G1/641

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 permature 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，托架在三点安装在梭子上，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，该开关检测到航天器的上升并防止近地点升压马达的高频点火。 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。