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公开(公告)号：US4364530A
公开(公告)日：1982-12-21
申请号：US184823
申请日：1980-09-08
CPC分类号： F42B15/36 , F42B10/665
摘要： A modular, apogee-control package is disclosed which can be added to exisg missiles, and which will limit the apogee of the missile trajectory by implementation of thrust vector control (TVC). The package comprises a boost guidance unit, a solid rocket propellant motor, and jet vane TVC.
摘要翻译： 公开了一种模块化的远地点控制组件，可以将其添加到现有的导弹中，并通过实施推力矢量控制（TVC）来限制导弹轨迹的远地点。 该包装包括增压引导单元，固体火箭推进剂马达和喷气叶片TVC。
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2.依法登记的发明Vapor deposition of a thin polymer film on solid propellant rocket grain surface 失效固体推进剂火箭颗粒表面上的薄聚合物膜的蒸汽沉积
公开(公告)号：USH1824H
公开(公告)日：1999-12-07
申请号：US912969
申请日：1997-08-01
CPC分类号： B05D1/60 , C06B21/0083 , C06B45/12
摘要： A thin film of ignition inhibitor is applied uniformly to a rocket propelt grain which may be large and have a complex shape. The film is applied by condensation and polymerization of a vaporized monomer to which the grain is subjected. The monomer is prepared by thermally cracking the dimer of paraxylylene or a halogenated paraxylylene derivative.
摘要翻译： 点火抑制剂的薄膜均匀地施加到可能很大并且具有复杂形状的火箭推进剂颗粒上。 该薄膜通过使谷物所经受的气化单体的冷凝和聚合而被施加。 单体通过热裂解对二甲苯或二卤代对二甲苯衍生物的二聚体来制备。
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公开(公告)号：USH384H
公开(公告)日：1987-12-01
申请号：US55810
申请日：1987-05-28
IPC分类号： F02K9/90
CPC分类号： F02K9/90
摘要： A thrust vector control apparatus for selective deployment of a vane withinn exhaust stream has the vane mounted on the periphery of an exhaust nozzle for pivotable movement between a retracted position without the stream and an inserted position within the stream. A pivotally mounted link assembly is used with an actuator to urge the vane into the stream. The link assembly becomes locked in place upon the full insertion of the vane. This locked position precludes unintended pivotal motion of the vane; however, rotational motion of the vane is still possible due to the pivotal connection of the link. A second actuator rotates the vane in the stream, thereby controlling the direction of the stream.
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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：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：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：US5379699A
公开(公告)日：1995-01-10
申请号：US104954
申请日：1993-08-02
CPC分类号： F02K9/95 , C06C9/00 , F42C19/0803 , F42C19/0819
摘要： An igniter for solid fuel rockets in which hot gases from an initiator arehanneled to drive a piston against a reservoir of combustion modifying fluid, like ethylene glycol, so as to spray the fluid onto the propellant grain just before ignition. After the piston moves, the hot gases escape the igniter as to ignite the propellant directly or through an intermediate main ignition charge.
摘要翻译： 用于固体燃料火箭的点火器，其中来自起动器的热气体被引导以将活塞驱动抵靠诸如乙二醇的燃烧改性流体的储存器，以便在点火之前将流体喷射到推进剂颗粒上。 在活塞移动之后，热气体逸出点火器，直接点燃推进剂或通过中间的主要点火装置点燃。
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公开(公告)号：USH710H
公开(公告)日：1989-11-07
申请号：US700981
申请日：1984-11-02
CPC分类号： G01S5/0247 , G01S3/14
摘要： A horizon reference system has a plurality of microwave radiation sensors which are selectively connected by a controller to a superheterodyne receiver. The output signals of the receiver are processed in conjunction with antenna selection data to provide roll angle with reference to the horizon and roll angle rate data about any particular axis of the platform on which the sensors are mounted.
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