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公开(公告)号：US3952664A
公开(公告)日：1976-04-27
申请号：US478009
申请日：1974-06-10
申请人： Joseph A. Schmidt , W. James Stone
发明人： Joseph A. Schmidt , W. James Stone
摘要： A rocket motor assembly for a rocket motor utilized for towing a load or racting an aircrew member from an aircraft. The rocket motor is formed in two separate sections, a casing portion and a unitary nozzle igniter housing portion. The nozzle and igniter housing portion has a circumferential portion that mates with the internal surface wall of the casing portion. A seal and fastener holds the housing in place whenever the rocket motor is assembled. A shackle secured to the igniter mechanism is fastened to a tow line extending to a load to be towed.
摘要翻译： 一种用于火箭发动机的火箭发动机组件，用于牵引负载或从飞行器提取空勤人员。 火箭发动机形成为两个分开的部分，即壳体部分和单一喷嘴点火器壳体部分。 喷嘴和点火器收纳部分具有与壳体部分的内表面壁相配合的圆周部分。 当组装火箭发动机时，密封件和紧固件将壳体保持在适当位置。 固定到点火器机构的钩环被紧固到延伸到待牵引的负载的牵引线上。
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公开(公告)号：US3949676A
公开(公告)日：1976-04-13
申请号：US478008
申请日：1974-06-10
申请人： Joseph A. Schmidt , W. James Stone
发明人： Joseph A. Schmidt , W. James Stone
CPC分类号： F42C19/12
摘要： An igniter mechanism for a rocket motor utilized for towing a load or extting an air crew member from a disabled aircraft. The mechanism operates whenever a sufficient force is exerted on the tow line to shear a pin allowing closure of the switch. Electrical energy coupled to the switch is conducted to a squib which ignites a charge to cause ignition of the rocket motor propellant. The electrical switch mechanism can only be actuated by a predetermined pulling force on the tow line thereby causing the electrical contacts to be brought positively together.
摘要翻译： 用于火箭发动机的点火器机构，用于牵引负载或从残疾飞机上提取机组人员。 只要在牵引线上施加足够的力来剪切允许开关闭合的销，该机构就起作用。 耦合到开关的电能被引导到点火器，其点燃电荷以引起火箭发动机推进剂的点燃。 电开关机构只能通过在牵引线上的预定的拉力来致动，从而使电触头被积极地结合在一起。
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公开(公告)号：US4017040A
公开(公告)日：1977-04-12
申请号：US648557
申请日：1976-01-12
CPC分类号： F42B10/663 , B64D25/10
摘要： A steerable rocket motor for towing a load or extracting an aircrew memberrom a disabled aircraft, regardless of aircarft attitude or altitude. The rocket motor is formed from a hollow cylindrical thin walled casing containing a high burn rate propellant and having a plurality of rocket nozzles at one end. The rocket nozzles are positioned around the circumference of the rocket body and are angled to thrust outward and toward the load or aircrew member being towed. A thrust control proportions thrust among the plurality of nozzles for controlling the pitch and yaw of the rocket. Position and rate sensing apparatus informs the thrust control regarding rocket attitude to enable the rocket to steer a predefined desirable flight trafectory. One or more lines are attached to the rocket and are adapted to be fastened to the load or aircrew member being towed.
摘要翻译： 一种可操纵的火箭发动机，用于从残疾飞机上牵引负载或提取机组人员，无论驾驶姿态或高度如何。 火箭发动机由包含高燃烧速率推进剂的中空圆柱形薄壁壳体形成，并且在一端具有多个火箭喷嘴。 火箭喷嘴围绕火箭体的圆周定位并且被成角度以向外推动并且朝向被牵引的负载或空勤人员构件。 用于控制火箭的俯仰和偏转的多个喷嘴中的推力控制比例推力。 位置和速率感测装置通知推力控制关于火箭姿态，以使得火箭能够引导预定的期望的飞行行为。 一根或多根线连接到火箭上，并适于被紧固到被牵引的负载或空勤人员。
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公开(公告)号：US3949682A
公开(公告)日：1976-04-13
申请号：US478011
申请日：1974-06-10
IPC分类号： B64D25/08
CPC分类号： B64D25/08 , Y10T428/2962 , Y10T428/31663 , Y10T428/31739
摘要： An improved tow line and attachment apparatus for use with a rocket motor ilized in carrying a line, towing a load or extracting an aircrew member from a disabled aircraft. The tow or pendant line is attached to the rear end of a rocket motor adjacent its nozzles and sustains the load to be carried during powered flight. Flame and heat exiting from the nozzles during powered flight from the burning propellant can impinge a pendant line attached adjacent the nozzles. To prevent weakening or destruction of this portion of the tow line a silicone rubber envelope is fabricated around the line.
摘要翻译： 用于与携带线路一起使用的火箭发动机的改进的牵引线和附接装置，牵引负载或从残疾飞机上提取机组人员。 拖曳线或吊坠线在其喷嘴附近附接到火箭发动机的后端，并维持在动力飞行期间承载的负载。 在从燃烧的推进剂的动力飞行期间从喷嘴出来的火焰和热量可以撞击附近的喷嘴附近的吊坠线。 为了防止纤维束的这一部分的削弱或破坏，在该线周围制造硅橡胶包层。
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公开(公告)号：US4303212A
公开(公告)日：1981-12-01
申请号：US33590
申请日：1979-04-26
IPC分类号： B64D25/10
CPC分类号： B64D25/10
摘要： An aircraft ejection seat which seeks the upward vertical direction to ene safe ejection from inverted aircraft at low altitude. An attitude control processor processes signals from three-axis attitude sensors and controls servo valves which regulate the flow of hydraulic fluid to hydraulic actuators connected to a spherical rocket motor mounted on a two axis gimbal system.
摘要翻译： 一个飞机弹射座椅，寻求向上的垂直方向，以便在低空下从倒立的飞机安全弹出。 姿态控制处理器处理来自三轴姿态传感器的信号并且控制伺服阀，其将液压流体的流量调节到连接到安装在双轴万向节系统上的球形火箭发动机的液压致动器。
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公开(公告)号：US4004764A
公开(公告)日：1977-01-25
申请号：US469739
申请日：1974-05-13
IPC分类号： B64D17/72
CPC分类号： B64D17/725
摘要： A drogue parachute deployment system for an ejection seat comprises a dro parachute mounted in a bag on the seat, a rocket motor, and a tow line attached between the parachute and the rocket motor. Upon firing of the rocket motor, the bag is caused to rip and the parachute is deployed.
摘要翻译： 用于喷射座椅的锥形降落伞部署系统包括安装在座椅上的袋中的锥形降落伞，火箭发动机和连接在降落伞和火箭发动机之间的拖绳。 在火箭发动机点火时，袋子被撕裂并且降落伞被展开。
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公开(公告)号：US4395001A
公开(公告)日：1983-07-26
申请号：US890099
申请日：1978-03-27
IPC分类号： B64D25/10
CPC分类号： B64D25/10
摘要： A line cutter or discharge valve responsive to aircraft attitude is posited on an aircraft ejection seat to interrupt the gas initiated sustainer rocket system. During inverted ejections, the cutter or valve will either sever or discharge pressure from a tube which leads from the firing squib to the sustainer rocket. Preventing sustainer rocket ignition enhances inverted ejection survivability by reducing crew member velocity toward the ground, thereby lengthening the time available for parachute deployment.
摘要翻译： 响应于飞机姿态的线切割器或排出阀定位在飞行器喷射座上以中断气体启动的维持器火箭系统。 在反向喷射过程中，切割器或阀门将会从管道中切断或排出压力，导管从点火点火器引导到持续火箭。 防止持续火箭点火通过降低乘员对地面的速度提高反向弹射生存能力，从而延长降落伞部署时间。
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公开(公告)号：US4236687A
公开(公告)日：1980-12-02
申请号：US42170
申请日：1979-05-24
申请人： W. James Stone , Lovic P. Thomas
发明人： W. James Stone , Lovic P. Thomas
IPC分类号： B64D25/10
CPC分类号： B64D25/10
摘要： An aircraft ejection seat having pitch, roll, and yaw control. Two gimbal rocket motors are attached to an aircraft ejection seat. A servo control circuit rotates the rocket motors in response to command signals.
摘要翻译： 具有俯仰，俯仰和偏航控制的飞行器弹射座椅。 两个巨型火箭发动机连接到飞机喷射座。 伺服控制电路根据指令信号使火箭发动机旋转。
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公开(公告)号：US3979089A
公开(公告)日：1976-09-07
申请号：US615867
申请日：1975-09-22
IPC分类号： B64D25/10
CPC分类号： B64D25/10
摘要： A rocket powered escape vehicle is equipped with an electrostatic attitudeensing system which commands a rocket motor mounted in gimbals on the bottom of the vehicle to provide a vertically upward seeking escape from an aircraft independent of aircraft attitude.
摘要翻译： 火箭动力逃生车配备有静电姿态感测系统，其命令安装在车辆底部的万向面中的火箭发动机，以提供独立于飞行器姿态的飞行器的垂直向上寻求逃生。
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公开(公告)号：US4216928A
公开(公告)日：1980-08-12
申请号：US892054
申请日：1978-03-31
IPC分类号： B64D25/10
CPC分类号： B64D25/10
摘要： An attitude reference system which uses microwave radiometry to sense the orientation of a vehicle. A fundamental fact of microwave radiometry is that more natural energy emanates from the earth than from the sky. The difference in energy, which is directly proportional to temperature, can be used to estimate attitudinal position. Microwave antennas mounted on an escape vehicle, such as an aircraft ejection seat, receive energy from different directions in a base plane and from a direction perpendicular to the base plane. Vehicle orientation relative to the earth is discerned by comparing the sensed radiometric temperature received from each antenna direction, and seat guidance equipment is programmed to steer the seat in a predefined direction based upon the radiometrically sensed orientation.
摘要翻译： 使用微波辐射测量来感测车辆方向的姿态参考系统。 微波辐射测量的一个基本事实是，从地球发出的天然能量比天空更多。 与温度成正比的能量差异可用于估计态度位置。 安装在诸如飞机弹出座椅的逃生车辆上的微波天线从基座平面中和从垂直于基础平面的方向上的不同方向接收能量。 通过比较从每个天线方向接收到的感测辐射温度来识别相对于地球的车辆定向，并且座椅引导设备被编程为基于放射线检测的取向在预定方向上转向座椅。
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