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1. 发明申请

WO2013001267A1 A BOMB FOR DEPLOYMENT FROM AN AIR VEHICLE 审中-公开
标题翻译：用于从空中车辆部署的物料清单
公开(公告)号：WO2013001267A1
公开(公告)日：2013-01-03
申请号：PCT/GB2012/000552
申请日：2012-06-28
申请人： MBDA UK LIMITED , IRVINE, Rodney, Andrew
发明人： IRVINE, Rodney, Andrew
IPC分类号： F02K9/18 , F02K9/22 , F42B15/10
CPC分类号： F02K9/10 , F02K9/12 , F02K9/18 , F02K9/22 , F02K9/95 , F42B10/38 , F42B15/10
摘要： A bomb for deployment from an air vehicle includes a rocket motor (1) for propelling the bomb. The rocket motor includes propellant (5) which at least partially defines a void (11) downstream of an initial burning surface. As the propellant (5) is burned the void 11 will be exposed, increasing the surface area of the burning surface (9) of the propellant (5) to increase the thrust of the rocket motor.
摘要翻译：用于从空中飞行器部署的炸弹包括用于推进炸弹的火箭发动机（1）。火箭发动机包括推进剂（5），其至少部分地限定初始燃烧表面下游的空隙（11）。随着推进剂（5）燃烧，空气11将被暴露，增加推进剂（5）的燃烧表面（9）的表面积以增加火箭发动机的推力。

2. 发明申请

WO01014705A1 IGNITERS FOR GAS GENERATORS 审中-公开
标题翻译：气体发生器IGNITERS
公开(公告)号：WO01014705A1
公开(公告)日：2001-03-01
申请号：PCT/GB2000/003086
申请日：2000-08-15
IPC分类号： F02K9/08 , F02K9/18 , F02K9/22 , F02K9/95
CPC分类号： F02K9/08 , F02K9/18 , F02K9/22 , F02K9/95
摘要： An igniter for igniting the propellant of a rocket motor or gas generator, especially of the radial cigarette burn type, having at least one sheet of vapour deposited pyrotechnic material (18) locatable adjacent to the surface of the propellant to be ignited, and a means (26) for igniting the vapour deposited pyrotechnic material, e.g. by direct electrical or laser ignition.
摘要翻译：用于点燃火箭发动机或气体发生器的推进剂的点火器，特别是径向卷烟燃烧型的推进剂，其具有至少一层蒸气沉积的烟火材料（18），邻近待点燃的推进剂的表面定位;以及装置（26），用于点燃蒸汽沉积的烟火材料，例如通过直接电或激光点火。

3. 发明申请

WO01038711A1 END-BURNING ROCKET MOTOR 审中-公开
标题翻译：终点滚动电机
公开(公告)号：WO01038711A1
公开(公告)日：2001-05-31
申请号：PCT/US2000/016971
申请日：2000-06-20
IPC分类号： C06B33/00 , C06B45/12 , F02K9/08 , F02K9/22 , F02K9/34
CPC分类号： C06B33/00 , C06B45/12 , F02K9/08 , F02K9/22 , F02K9/34
摘要： A solid propellant rocket motor which utilizes a propellant casing enclosing one or more propellant segments in an end-burning configuration wherein each propellant segment comprises a substantially homogeneous mixture of fuel particles distributed throughout a matrix of solid oxidizer. Such propellant segments provide sufficiently high burn rates to provide the desired thrust profiles for a variety of applications. Such a solid propellant rocket motor in the end-burning configuration permits larger payloads due to the weight savings realized by the reduced binder and propellant casing requirements, with less complicated manufacturing procedures than conventional CP rocket motor configurations. In addition, the end-burning configuration permits easier segmentation of the propellant grain to tailor the thrust profile during the burn, with the added flexibility of dynamically chosen thrusts, triggered by either guidance circuitry or human intervention.
摘要翻译：一种固体推进剂火箭发动机，其使用封闭一个或多个推进剂段的推进剂壳体，其末端燃烧构型，其中每个推进剂段包括分布在整个固体氧化剂基质中的燃料颗粒的基本上均匀的混合物。这种推进剂段提供足够高的燃烧速率以为各种应用提供期望的推力轮廓。这种固体推进剂火箭发动机在最终燃烧结构中允许更大的有效载荷，这是由于减少的粘合剂和推进剂壳体要求所实现的重量节省，与常规CP火箭发动机构造相比，制造程序不太复杂。此外，最终燃烧配置允许在燃烧期间更容易地分割推进剂颗粒以调整推力轮廓，并且由引导电路或人为干预触发的动态选择的推力的增加的灵活性。

4. 发明申请

WO01038710A1 NOZZLELESS ROCKET MOTOR 审中-公开
标题翻译：无喷嘴电机
公开(公告)号：WO01038710A1
公开(公告)日：2001-05-31
申请号：PCT/US2000/017033
申请日：2000-06-20
IPC分类号： F02K9/00 , F02K9/08 , F02K9/12 , F02K9/22 , F02K9/34
CPC分类号： F02K9/12 , F02K9/00 , F02K9/08 , F02K9/22 , F02K9/34
摘要： A solid rocket motor for accelerating a payload comprises a motor casing and a solid propellant matrix, utilizing a high burn-rate fuel. The use of a high burn rate fuel allows the rocket motor to operate in an end-burning fashion without the use of a constricting aperture to increase the back-pressure upon the burn-front of the fuel matrix. The exhaust gas produced from combustion of the propellant matrix exits directly to the ambient environment through a simple aperture without the use of an expansion nozzle. By eliminating the mass of the nozzle and allowing the use of lighter, less structurally robust motor casings, the needed acceleration of the vehicle can be achieved while using less propellant and a lighter launch vehicle.
摘要翻译：用于加速有效载荷的固体火箭发动机包括使用高燃耗燃料的马达壳体和固体推进剂基质。使用高燃耗燃料允许火箭发动机以终端燃烧的方式运行，而不使用收缩孔来增加燃料基体的燃烧前沿上的背压。由推进剂基质的燃烧产生的废气通过简单的孔直接流到周围环境，而不使用膨胀喷嘴。通过消除喷嘴的质量并允许使用更轻，结构更坚固的电机壳体，可以在使用较少的推进剂和较轻的运载火箭的情况下实现车辆所需的加速。

5. 发明申请

WO01038170A1 SINGLE-STAGE-TO-ORBIT ROCKET 审中-公开
标题翻译：单级到ORBIT ROCKET
公开(公告)号：WO01038170A1
公开(公告)日：2001-05-31
申请号：PCT/US2000/005126
申请日：2000-02-29
IPC分类号： B64G1/00 , B64G1/14 , B64G1/40 , F02K9/22 , F02K9/26 , F02K9/28
CPC分类号： B64G1/002 , B64G1/14 , B64G1/403 , F02K9/22 , F02K9/26 , F02K9/28
摘要： A solid fueled rocket motor capable of accelerating a vehicle into Earth orbit using only a single stage of engines using a high burn-rate propellant matrix. The propellant matrix is designed so as to be burned from one end to the other, rather than from the center outwards. By operating in this end-burning configuration, the motor is capable of being configured to produce varying levels of thrust throughout the operation of the motor. This will allow the use of the same engine for all phases of the launch to orbit.
摘要翻译：一种固体燃料火箭发动机，其能够仅使用高燃烧率推进剂基质的单级发动机将车辆加速到地球轨道。推进剂基体设计成从一端燃烧而不是从中心向外燃烧。通过在该端部燃烧构造中操作，电动机能够被配置成在电动机的整个运行过程中产生不同程度的推力。这将允许在发射轨道的所有阶段使用相同的引擎。

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