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公开(公告)号：US4579302A
公开(公告)日：1986-04-01
申请号：US587764
申请日：1984-03-09
申请人： William C. Schneider , Reginald B. Berka , Herbert C. Kavanaugh , Kornel Nagy , Richard C. Parish , John A. Schliesing , Paul D. Smith , Frederick J. Stebbins , Clarence J. Wesselski
发明人： William C. Schneider , Reginald B. Berka , Herbert C. Kavanaugh , Kornel Nagy , Richard C. Parish , John A. Schliesing , Paul D. Smith , Frederick J. Stebbins , Clarence J. Wesselski
CPC分类号： B64G9/00 , Y10S136/292
摘要： A triangular space station deployable in orbit. The framework is comprised of three trusses, formed of a pair of generally planar faces comprised of foldable struts which expand and lock into rigid structural engagement forming a repetition of equilateral triangles and non-folding diagonal struts interconnecting the two faces. The struts are joined together by node fittings. The framework can be packaged into a size and configuration which can be transported by a space shuttle orbiter in a single orbital flight and when deployed, provides large work/construction area and ample planar surface area for solar panels and thermal radiators. A plurality of modules are secured to the framework and then joined by tunnels to comprise an interconnected modular array disposed along the free edges of the framework. Thruster units for space station orientation and altitude maintenance are provided. The triangular space station provides a structurally stable unit having sufficiently high structural integrity and natural frequency for facilitating docking, satellite servicing and launch operations.
摘要翻译： 可在轨道上部署的三角形空间站。 该框架由三个桁架构成，由一对大体上平坦的面构成，该平面由可折叠的支柱膨胀并锁定成刚性结构接合，形成重复的等边三角形和互相连接两个面的非折叠对角支柱。 支柱通过节点配件连接在一起。 框架可以包装成一个尺寸和配置，可以在单轨道飞行中由航天飞机轨道运输，并且部署时，为太阳能电池板和散热器提供大的工作/建筑面积和宽的平面表面积。 多个模块被固定到框架上，然后由隧道连接以包括沿框架的自由边缘设置的互连的模块化阵列。 提供了用于空间站定向和高度维护的推进装置。 三角空间站提供了具有足够高的结构完整性和固有频率的结构稳定的单元，以便于对接，卫星维修和发射操作。
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公开(公告)号：US5441221A
公开(公告)日：1995-08-15
申请号：US161038
申请日：1993-12-03
申请人： Donald C. Wade , Horacio M. De La Fuente , Reginald B. Berka , Steven L. Rickman , Edgar O. Castro , Kornel Nagy , Clarence J. Wesselski , Timothy E. Pelischek , John A. Schliesing
发明人： Donald C. Wade , Horacio M. De La Fuente , Reginald B. Berka , Steven L. Rickman , Edgar O. Castro , Kornel Nagy , Clarence J. Wesselski , Timothy E. Pelischek , John A. Schliesing
摘要： Methods and apparatus are provided for a single heavy-lift launch to place a complete, operational space station on-orbit. A payload including the space station takes the place of a Shuttle Orbiter using the launch vehicle of the Shuttle Orbiter. The payload includes a forward shroud, a core module, a propulsion module, and a transition module between the core module and the propulsion module. The essential subsystems are pre-integrated and verified on Earth. The core module provides means for attaching international modules with minimum impact to the overall design. The space station includes six control moment gyros for selectably operating in either LVLH (local-vertical local-horizontal) or SI (solar inertial) flight modes.
摘要翻译： 为单个重型起重机提供了方法和装置，以便在轨上放置一个完整的，可操作的空间站。 包括空间站的有效载荷代替了Shuttle Orbiter，使用Shuttle Orbiter的运载火箭。 该有效载荷包括前护罩，芯模块，推进模块以及在核心模块和推进模块之间的过渡模块。 基本子系统是在地球上预先集成和验证的。 核心模块提供了连接国际模块的方法，对整体设计的影响最小。 空间站包括六个控制力矩陀螺仪，用于可选择地在LVLH（局部垂直局部水平）或SI（太阳能惯性）飞行模式下操作。
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公开(公告)号：US4860975A
公开(公告)日：1989-08-29
申请号：US292131
申请日：1988-12-30
IPC分类号： B64G1/64
摘要： A docking mechanism for the docking of a space vehicle 11 to a space station 12 comprising a flexible tunnel frame structure which is deployable from the space station. The tunnel structure comprises a plurality of series connected frame sections 21, one end section of which is attached to the space station and the other end attached to a docking module 15 of a configuration adapted for docking in the payload bay of the space vehicle 11. The docking module is provided with trunnions 41, 42 adapted for latching engagement with latches 17 installed in the vehicle payload bay and with hatch means 44 connectable to a hatch of the crew cabin of the space vehicle. Each frame section 21 comprises a pair of spaced ring members 31a, 31b interconnected by actuator-attenuator devices 33 which are individually controllable by an automatic control means to impart relative movement of one ring member to the other in six degrees of freedom of motion. The control means includes computer logic responsive to sensor signals of range and attitude information, capture latch condition, structural loads, and actuator stroke for generating commands to the on-board flight control system and the individual actuator-attenuators to deploy the tunnel to effect a coupling with the space vehicle or to adjust the relative attitude of the space vehicle and space station after coupling. A tubular fluid-impervious liner, preferably fabric 51, is disposed through the frame sections 21 of a size sufficient to accommodate the passage of personnel and cargo.
摘要翻译： 用于将空间车辆11对接到空间站12的对接机构，其包括可从空间站展开的柔性隧道框架结构。 隧道结构包括多个串联连接的框架部分21，其一端部附接到空间站，另一端连接到适于对接在空间车辆11的有效载荷舱室中的构造的对接模块15。 对接模块设置有耳轴41,42，其适于与安装在车辆有效载荷舱中的闩锁17锁定接合，并且具有可连接到空间车辆的船员舱舱口的舱口装置44。 每个框架部分21包括通过致动器 - 衰减装置33互连的一对隔开的环件31a，31b，它们可由一个自动控制装置单独控制，以在六个运动自由度中使一个环件相对运动。 控制装置包括响应于范围和姿态信息的传感器信号的计算机逻辑，捕获锁定状态，结构负载和致动器行程，用于向车载飞行控制系统和各个致动器衰减器生成命令以部署隧道以实现 与空中飞行器联动，或者在联动后调整航天器和空间站的相对姿态。 优选地，织物51的管状的不透液体的衬套穿过框架部分21设置成足以容纳人员和货物的通过。
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公开(公告)号：US4858857A
公开(公告)日：1989-08-22
申请号：US292123
申请日：1988-12-30
IPC分类号： B64G1/64
CPC分类号： B64G1/646
摘要： A system for docking a space vehicle 11 to a space station 12 where a connecting tunnel for in-flight transfer of personnel is required. Cooperable coupling mechanisms 51, 52 include docking rings 56, 61 on the space vehicle 11 and space station 12, respectively. The space station is provided with a tunnel structure 15, a retraction mechanism 30, and a docking ring 56 attached thereto. The vehicle coupling mechanism 52 is designed to capture the station coupling mechanism 51, arrest relative spacecraft motions while limiting loads to acceptable levels, and then realign the spacecraft for final docking and tunnel interconnection. The docking ring 61 of the space vehicle coupling mechanism is supported by linear attenuator actuator devices 63 each of which is controlled by a control system (FIG. 10) which receives loading information signals and attenuator stroke information signals from each device 63 and supplies output signals for controlling its linear actuation to attenuate impact loading or to realign the spacecraft for final docking and tunnel interconnection. Retraction mechanism 30 is used to draw the spacecraft together after initial contact and coupling. Tunnel trunnions 21, 22, 23, 25 cooperative with latches 67 on the space vehicle 11 constitute the primary structural tie between the spacecraft in final docked configuration.
摘要翻译： 用于将空间车辆11对接到空间站12的系统，其中需要用于飞行中人员转移的连接隧道。 可协作的联接机构51,52分别包括空间车辆11和空间站12上的对接环56,61。 空间站设置有隧道结构15，收回机构30和附接到其上的对接环56。 车辆联接机构52被设计成捕获站联接机构51，阻止相对的航天器运动，同时将负载限制到可接受的水平，然后重新对准航天器进行最终对接和隧道互连。 空间车辆联接机构的对接环61由线性衰减器致动器装置63支撑，线性衰减器致动装置63由控制系统（图10）控制，控制系统从每个装置63接收负载信息信号和衰减器行程信息信号，并提供输出信号 用于控制其线性致动以衰减冲击载荷或重新对准航天器进行最终对接和隧道互连。 退回机构30用于在初始接触和耦合之后将飞船拼接在一起。 与空间车辆11上的闩锁67协作的隧道耳轴21,22,23,25构成最终对接配置中的航天器之间的主要结构。
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