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1.发明授权
公开(公告)号：US4679752A
公开(公告)日：1987-07-14
申请号：US695156
申请日：1985-01-28
摘要： Apparatus for use in gyroscopically ejecting a spacecraft supported in the open end of a spacecraft supporting cradle. The invention comprises a separable ejection restraint mechanism attached between the cradle and the spacecraft. The mechanism restrains the thrust force applied to the spacecraft for a predetermined time period in order to dissipate undetermined forces acting upon the spacecraft prior to the ejection thereof. The mechanism comprises a separable resilient portion and a releasable clamp portion coupled thereto. The resilient portion comprises a spring loaded anchor rod arrangement while the releasable clamp portion comprises a spring loaded split ball clamp arrangement. The invention also contemplates the use of a flexible carrier coupled between the spacecraft and the cradle. The invention acts as a tether connected between the cradle and spacecraft 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.
摘要翻译： 用于陀螺仪弹射支撑在航天器支架的开口端的航天器的装置。 本发明包括一个连接在支架和航天器之间的可分离的弹出约束机构。 该机构限制施加到航天器的预定时间段的推力，以便在弹射之前消散作用在航天器上的未确定的力。 该机构包括可分离的弹性部分和与其连接的可释放的夹紧部分。 弹性部分包括弹簧加载的锚杆装置，而可释放的夹紧部分包括弹簧加载的分离球形夹具装置。 本发明还考虑使用耦合在航天器和支架之间的柔性载体。 本发明用作连接在摇篮和航天器之间的系绳，其用于在货物部署之前确定货物上的决定性状态并消除不期望的与喷射有关的问题。 此外，作为唯一货物释放引发器使用的单个系绳的释放使由于结构变形能量而可能对货物施加不受控制的动量最小化。
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公开(公告)号：US5310144A
公开(公告)日：1994-05-10
申请号：US909260
申请日：1992-07-06
摘要： A method and apparatus for balancing environmental disturbance torques acting upon a satellite (10) by tilting the satellite solar panels (14,16) toward or away from the sun to change the solar pressure acting upon the satellite (10) as well as the gravity gradient torque generated by different panel (14,16) tilt angles. By balancing the disturbance torque acting upon the satellite (10), satellite disturbances are minimized so that the satellite stabilization system can be made smaller and fuel used for satellite attitude control is minimized. Torque balancing is accomplished at the beginning of the mission through a linear actuator (37) at the mounting location of each solar panel (14,16) to the satellite main body (12) and, once set, is passive and does not require continuous active satellite control.
摘要翻译： 一种通过将卫星太阳能电池板（14,16）朝向或远离太阳倾斜以改变作用在卫星（10）上的太阳能压力以及重力作用于平衡作用在卫星（10）上的环境扰动扭矩的方法和装置， 不同面板（14,16）倾斜角产生的梯度转矩。 通过平衡作用在卫星（10）上的扰动扭矩，卫星干扰被最小化，使得卫星稳定系统可以变得更小，并且用于卫星姿态控制的燃料被最小化。 通过在每个太阳能电池板（14,16）到卫星主体（12）的安装位置处的线性致动器（37）在任务开始时完成扭矩平衡，并且一旦设置为无源并且不需要连续的 主动卫星控制。
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公开(公告)号：US5112012A
公开(公告)日：1992-05-12
申请号：US427675
申请日：1989-10-26
申请人： Mark S. Yuan , Alois Wittmann
发明人： Mark S. Yuan , Alois Wittmann
CPC分类号： B64G1/285 , F16M11/046 , F16M11/125 , F16M11/18 , Y10T74/1872 , Y10T74/20207
摘要： A momentum wheel (14, 142) for compensating for the adverse effects of disturbing torques on stabilized spacecraft is mounted on a base (12, 124) on the spacecraft by three circumferentially spaced supports which include at least two linear actuators (26, 118) that tilt the wheel (14, 142) in any desired direction. One end of each actuator (26) is mounted to a base (38, 154) supporting the wheel by a spherical connection (32, 34, 36) which allows freedom of motion about multiple axes. The other end of each actuator (26) is mounted to the base (12) by either a pair of spaced hinges (22, 24, 46) and a support bracket (18) which is secured to the actuator (26) or a flexible bracket (78). The wheel base (12,124) may also be mounted on the actuators by flexible members (150) which allow tilting of the wheel.
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公开(公告)号：US4000350A
公开(公告)日：1976-12-28
申请号：US559274
申请日：1975-03-17
申请人： Alois Wittmann
发明人： Alois Wittmann
CPC分类号： H01M10/0413 , H01M10/345
摘要： A battery comprising a battery vessel, battery plates having a central aperture, electrolye impregnated separator, a battery plate holder and a battery plate retainer. The battery plate holder comprises a base retainer and a central tube protruding from the base retainer. The battery plates are placed onto the battery plate holder by inserting the central tube through the apertures in the battery plates. The battery plate retainer holds the plates onto the battery plate holder and the complete assembly comprising the battery plates, the holder and cover is mounted with the battery vessel by coupling the base plate of the holder to the interior of the vessel.
摘要翻译： 一种电池，包括电池容器，具有中心孔的电池板，电解浸渍分离器，电池板保持器和电池板保持器。 电池板支架包括基座保持器和从基座保持器突出的中心管。 通过将中心管插入电池板的孔中，将电池板放置在电池板支架上。 电池板保持器将板保持在电池板保持器上，并且包括电池板，保持器和盖的完整组件通过将保持器的基板联接到容器的内部而与电池容器一起安装。
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公开(公告)号：US4715565A
公开(公告)日：1987-12-29
申请号：US866812
申请日：1986-05-27
申请人： Alois Wittmann
发明人： Alois Wittmann
IPC分类号： B64G1/64
CPC分类号： B64G1/641
摘要： An improved clamping connection assembly for separable parts of spacecraft is provided and includes a tension belt for securing a plurality of retainers against camming surfaces on flange members on separable spacecraft component parts. The other peripheral edges of the flange members have detents to respectively receive a single shear pin mounted on each of the retainers. The shear pins receive any shear and torsional forces and transmits them between the structural parts of the spacecraft components without creating additional forces on the tension belt.
摘要翻译： 提供了一种用于航天器可分离部件的改进的夹紧连接组件，并且包括用于将多个保持器抵靠在可分离的航天器部件上的凸缘部件上的凸轮表面固定的张力皮带。 凸缘构件的其它周缘具有棘爪以分别容纳安装在每个保持器上的单个剪切销。 剪切销承受任何剪切力和扭转力，并将它们在航天器部件的结构部件之间传递，而不会在张力带上产生额外的力。
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公开(公告)号：US4214406A
公开(公告)日：1980-07-29
申请号：US973492
申请日：1978-12-26
申请人： Alois Wittmann , Ronald J. McGrath
发明人： Alois Wittmann , Ronald J. McGrath
摘要： There is herein described a support structure for antennas, optical systems and the like which are generally subject to non uniform dimensional changes due to temperature variations and gradients in the support structure material, the invention overcoming such dimensional changes by combining the use of a material having a low coefficient of thermal expansion and the use of a heat pipe as an integral part of the aforementioned structural member for isothermalization, to reduce the distortion resulting from residual non-zero coefficient of thermal expansion.
摘要翻译： 这里描述了由于支撑结构材料中的温度变化和梯度而通常受到不均匀的尺寸变化的天线，光学系统等的支撑结构，本发明克服了这种尺寸变化，结合使用具有 热膨胀系数低，并且使用热管作为上述用于等温化的结构件的组成部分，以减少由残余的非零热膨胀系数引起的变形。
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公开(公告)号：US06347719B1
公开(公告)日：2002-02-19
申请号：US09615671
申请日：2000-07-14
申请人： Harold Rosen , Alois Wittmann , Scott Pano
发明人： Harold Rosen , Alois Wittmann , Scott Pano
IPC分类号： B65D2500
摘要： A light weight fuel tank for a hydrogen powered airplane used as a platform for communication repeaters for communication services. An outer spherical shell member of a sandwich configuration surrounds an inner thin walled spherical shell member in which the liquid hydrogen is contained. A radial gap between the shell members is evacuated to a high vacuum. The facing surfaces of the shell members are coated with a low emissivity material. Electrical heaters are provided to control the evaporation rate of the hydrogen to match the fuel usage and to prevent icing during ascent and descent of the airplane.
摘要翻译： 用作氢动力飞机的轻型燃料箱，用作通信中继器用于通信服务的平台。 三明治构造的外球形壳构件包围内部薄壁球形壳构件，其中容纳液态氢。 壳件之间的径向间隙被抽真空至高真空。 外壳构件的面对表面涂覆有低辐射率材料。 提供电加热器以控制氢气的蒸发速率以匹配燃料使用并防止飞机上升和下降期间结冰。
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8.发明授权Apparatus and method for transporting a spacecraft and a fluid propellant from the earth to a substantially low gravity environment above the earth 失效将航天器和液体推进剂从地球运送到地球上方的基本上低重力环境的装置和方法
公开(公告)号：US4699339A
公开(公告)日：1987-10-13
申请号：US707278
申请日：1985-03-01
申请人： Harold A. Rosen , Alois Wittmann
发明人： Harold A. Rosen , Alois Wittmann
CPC分类号： B64G1/14
摘要： An apparatus for transporting a spacecraft and fluid propellant from the earth to a substantially low gravity environment above the earth with substantially reduced loading of the spacecraft due to forces upon the fluid propellant during the transport, the apparatus including a vehicle for carrying the spacecraft and the fluid propellant from the earth to a substantially low gravity environment above the earth; a plurality of external tanks disposed within the vehicle, external to the spacecraft, for containing the fluid propellant as the vehicle carries the spacecraft and the fluid propellant from the earth to the substantially low gravity environment above the earth; a plurality of spacecraft tanks disposed within the spacecraft for receiving the fluid propellant and for containing the fluid propellant; and means for transferring the fluid propellant from the external tanks the spacecraft tanks in the substantially low gravity environment above the earth.
摘要翻译： 一种用于将航天器和流体推进剂从地球运输到地球上的基本上低重力环境的装置，由于在运输期间由于力在流体推进剂上而大大减少了航天器的载荷，该装置包括用于承载航天器和 流体推进剂从地球到地球上方的极低重力环境; 设置在车辆外部的多个外部容器，位于航天器的外部，用于当车辆将地球上的飞船和流体推进剂从地球运送到地球上的基本上低重力环境时，用于容纳流体推进剂; 设置在航天器内的用于接收流体推进剂并用于容纳流体推进剂的多个航天器舱; 以及用于在地球上方的基本上低重力环境中将液体推进剂从外部罐传送到航天器坦克的装置。
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公开(公告)号：US4359201A
公开(公告)日：1982-11-16
申请号：US125807
申请日：1980-02-28
申请人： Graham S. Thomson , Alois Wittmann
发明人： Graham S. Thomson , Alois Wittmann
摘要： A payload such as a spacecraft is deployed from launch vehicle with linear and angular velocity, using a structural arrangement for applying a tangential, single point ejection force to the spacecraft, in which, the single point ejection force and the spacecraft/launch vehicle reaction points enclose the spacecraft center of mass and center of percussion.
摘要翻译： 使用用于向航天器施加切向单点弹射力的结构布置，使用诸如航天器的载荷从运载火车部署，具有线性和角速度，其中单点弹射力和航天器/运载火箭反应点 包围航天器的中心和撞击中心。
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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
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。
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