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1. 发明申请

WO2009134510A3 ROCKET MOTOR WITH PELLET AND BULK SOLID PROPELLANTS 审中-公开
标题翻译：带电池和散装固体推进剂的电动马达
公开(公告)号：WO2009134510A3
公开(公告)日：2010-01-21
申请号：PCT/US2009033694
申请日：2009-02-10
申请人： RAYTHEON CO , CAVALLERI ROBERT , OLDEN THOMAS
发明人： CAVALLERI ROBERT , OLDEN THOMAS
IPC分类号： F02K9/08
CPC分类号： F02K9/08 , F02K9/10 , F02K9/24 , F02K9/346
摘要： There is disclosed a solid fuel rocket motor (500) which may include a case (510) and a nozzle (540) coupled to the case (510). A plurality of fuel pellets (525) may be disposed within the case (510). An igniter (550) may be disposed to ignite at least a portion of the fuel pellets (525). A pellet retainer (535) may be positioned within the case (510) to retain the plurality of fuel pellets (525) within the case (510). The pellet retainer (535) may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle (540) while preventing unburned fuel pellets from being expelled through the nozzle (540).
摘要翻译：公开了一种固体燃料火箭发动机（500），其可以包括壳体（510）和联接到壳体（510）的喷嘴（540）。多个燃料粒子（525）可以设置在壳体（510）内。可以设置点火器（550）以点燃至少一部分燃料颗粒（525）。颗粒保持器（535）可以定位在壳体（510）内以将多个燃料颗粒（525）保持在壳体（510）内。颗粒保持器（535）可以被穿孔以允许废气从点燃的燃料颗粒流到喷嘴（540），同时防止未燃燃料颗粒通过喷嘴（540）排出。

2. 发明申请

WO2009134499A3 PELLET LOADED ATTITUDE CONTROL ROCKET MOTOR 审中-公开
标题翻译： PELLET负载姿态控制摇臂电机
公开(公告)号：WO2009134499A3
公开(公告)日：2010-01-28
申请号：PCT/US2009033248
申请日：2009-02-05
申请人： RAYTHEON CO , CAVALLERI ROBERT , OLDEN THOMAS
发明人： CAVALLERI ROBERT , OLDEN THOMAS
IPC分类号： F02K9/08
CPC分类号： F02K9/08 , F02K9/10 , F02K9/18 , F02K9/36 , Y10T29/49346
摘要： There is disclosed a solid fuel rocket motor (500) which may include a case (510) and a nozzle (540) coupled to the case. A plurality of fuel pellets (525) may be disposed within the case. An igniter (550) may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer (535) may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle.
摘要翻译：公开了一种固体燃料火箭发动机（500），其可以包括壳体（510）和连接到壳体的喷嘴（540）。多个燃料颗粒（525）可以设置在壳体内。可以设置点火器（550）以点燃至少一部分燃料颗粒。颗粒保持器（535）可以定位在壳体内以将多个燃料颗粒保持在壳体内。颗粒保持器可以被穿孔以允许废气从点燃的燃料颗粒流到喷嘴，同时防止未燃烧的燃料颗粒通过喷嘴排出。

3. 发明申请

WO2009134510A2 ROCKET MOTOR WITH PELLET AND BULK SOLID PROPELLANTS 审中-公开
标题翻译：带泡沫和块状固体推进剂的ROCKET电机
公开(公告)号：WO2009134510A2
公开(公告)日：2009-11-05
申请号：PCT/US2009/033694
申请日：2009-02-10
申请人： RAYTHEON COMPANY , CAVALLERI, Robert , OLDEN, Thomas
发明人： CAVALLERI, Robert , OLDEN, Thomas
IPC分类号： F02K9/10 , F02K9/12 , F02K9/18
CPC分类号： F02K9/08 , F02K9/10 , F02K9/24 , F02K9/346
摘要： There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle.
摘要翻译：公开了一种固体燃料火箭发动机，其可以包括壳体和连接到壳体的喷嘴。多个燃料丸可以设置在壳体内。可以设置点火器以点燃至少一部分燃料颗粒。颗粒保持器可以定位在壳体内以将多个燃料颗粒保持在壳体内。颗粒保持器可以被穿孔以允许废气从点燃的燃料颗粒流到喷嘴，同时防止未燃烧的燃料颗粒通过喷嘴排出。

4. 发明申请

WO2010147910A1 MODULAR DIVERT AND ATTITUDE CONTROL SYSTEM 审中-公开
公开(公告)号：WO2010147910A1
公开(公告)日：2010-12-23
申请号：PCT/US2010/038547
申请日：2010-06-14
申请人： RAYTHEON COMPANY , OLDEN, Thomas A. , CAVALLERI, Robert J.
发明人： OLDEN, Thomas A. , CAVALLERI, Robert J.
IPC分类号： F42B15/00
CPC分类号： F42B15/01 , F02K9/18 , F02K9/26 , F05D2240/40 , F42B10/661
摘要： There is disclosed a vehicle and methods for maneuvering the vehicle. The vehicle may include a plurality of multiple-impulse rocket motors, each of which comprises a plurality of independently ignitable solid fuel propellant charges, and a processor that generates at least one command to ignite at least one solid fuel propellant charge of at least one of the plurality of multiple-impulse rocket motors.
摘要翻译：公开了用于操纵车辆的车辆和方法。车辆可以包括多个多冲程火箭发动机，每个多冲程火箭发动机包括多个独立可点燃的固体燃料推进剂装料，以及处理器，其产生至少一个命令以点燃至少一个固体燃料推进剂装料多个多冲程火箭发动机。

5. 发明申请

WO2010019299A2 INTEGRAL THRUST VECTOR AND ROLL CONTROL SYSTEM 审中-公开
标题翻译：整体推力矢量和滚子控制系统
公开(公告)号：WO2010019299A2
公开(公告)日：2010-02-18
申请号：PCT/US2009/044439
申请日：2009-05-19
申请人： RAYTHEON COMPANY , KINSEY, Lloyd , CAVALLERI, Robert
发明人： KINSEY, Lloyd , CAVALLERI, Robert
IPC分类号： F42B10/66
CPC分类号： F42B10/665 , F02K9/90 , F02K9/978 , F05D2240/40 , F05D2250/411 , F05D2250/42
摘要： An apparatus for vectoring the thrust of a motor that produces thrust along a longitudinal axis by expelling combustion gases through a nozzle may include a plurality of linearly-positionable non-rotatable thrust deflectors. The thrust deflectors may be disposed at around a perimeter of the nozzle. Each thrust deflector may be independently extended to simultaneously generate both a force transverse to the longitudinal axis and a torque about the longitudinal axis.
摘要翻译：通过排出燃烧气体通过喷嘴而沿着纵向轴线产生推力的马达的推力矢量的装置可以包括多个可线性定位的不可旋转的推力偏转器。推力偏转器可以设置在喷嘴周边的周围。每个推力偏转器可以独立地延伸以同时产生横向于纵向轴线的力和围绕纵向轴线的扭矩。

6. 发明申请

WO2009134499A2 PELLET LOADED ATTITUDE CONTROL ROCKET MOTOR 审中-公开
标题翻译： PELLET负载姿态控制摇臂电机
公开(公告)号：WO2009134499A2
公开(公告)日：2009-11-05
申请号：PCT/US2009/033248
申请日：2009-02-05
申请人： RAYTHEON COMPANY , CAVALLERI, Robert , OLDEN, Thomas
发明人： CAVALLERI, Robert , OLDEN, Thomas
IPC分类号： F02K9/10 , F02K9/18 , F02K9/24 , F02K9/36
CPC分类号： F02K9/08 , F02K9/10 , F02K9/18 , F02K9/36 , Y10T29/49346
摘要： There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle.
摘要翻译：公开了一种固体燃料火箭发动机，其可以包括壳体和连接到壳体的喷嘴。多个燃料丸可以设置在壳体内。可以设置点火器以点燃至少一部分燃料颗粒。颗粒保持器可以定位在壳体内以将多个燃料颗粒保持在壳体内。颗粒保持器可以被穿孔以允许废气从点燃的燃料颗粒流到喷嘴，同时防止未燃烧的燃料颗粒通过喷嘴排出。

7. 发明专利

CA1306228C LOW FRICTIONAL LOSS ROTARY VANE GAS COMPRESSOR HAVING SUPERIOR LUBRICATION CHARACTERISTICS 未知
公开(公告)号：CA1306228C
公开(公告)日：1992-08-11
申请号：CA482593
申请日：1985-05-28
申请人： CAVALLERI ROBERT J , CLARK WILLIAM E
发明人： CAVALLERI ROBERT J , CLARK WILLIAM E
IPC分类号： F04C29/02
摘要： A low frictional loss, rotary vane gas compressor utilizing a housing having a generally elliptical cavity therein, and a rotor disposed in the cavity, with the axis of rotation of the rotor being offset from the central axis of the cavity. The housing has an inlet passage and a discharge passage, each in contact with the cavity, with the rotor having a plurality of radial slots in equally spaced relation about its periphery. A slidable vane is disposed in each of these slots, with the outer tip of each vane being in close proximity to an inner stator wall that defines the outer boundary of the cavity. The vanes serve to define a plurality of chambers in the cavity, which chambers undergo significant volume changes as they move about the cavity during rotation of the rotor, the vanes thus cooperating with the inner stator wall to compress gas entering the inlet passage, such that as it leaves through the discharge passage, it is at a higher pressure. Means provide a film of lubricant on the inner stator wall, with the outer tips of the vanes each possessing a compound contour that interacts with the film of lubricant to effect a good seal with the inner stator wall, while minimizing friction.

8. 发明专利

CA2016172A1 SELF-MACHINING SEAL RING LEAKAGE PREVENTION ASSEMBLY FOR ROTARY VANE DEVICE 未知
公开(公告)号：CA2016172A1
公开(公告)日：1991-11-07
申请号：CA2016172
申请日：1990-05-07
申请人： CAVALLERI ROBERT J
发明人： CAVALLERI ROBERT J
IPC分类号： F04C18/00 , F04C27/00
摘要： A low internal leakage, rotary vane gas compressor utilizing a housing having a generally elliptical cavity, whose outer boundary is defined by an inner stator wall. A shaft mounted rotor is disposed offset from the central axis of the cavity, with an end plate secured on each end of the housing. Each end plate has a centrally mounted hole for rotatably supporting the respective side of the rotor shaft. The housing has inlet and discharge passages, each in contact with the cavity. The rotor has a plurality of radial slots in equally spaced relation about its periphery, in each of which slots a slidable vane of minimal weight is disposed. Each vane is approximately the width of the rotor, and the outer tip of each vane is in close proximity to the inner stator wall. These vanes define a plurality of chambers which undergo significant volume changes during rotation of the rotor. The vanes thus cooperate with the inner stator wall and the end plates to compress gas entering the inlet passage, such that the gas thereafter leaving through the discharge passage is at a higher pressure. Advantageously, a seal ring of particularly hard, tough steel is mounted in each end plate, and biased into contact with the respective side of the rotor to effect an essentially zero gap therewith. Each seal ring has a tapered cross section, such that the initial footprint area is small, but with rotor wear, the small contact area desirably becomes a surface contact.

9. 发明申请

WO2010019299A3 INTEGRAL THRUST VECTOR AND ROLL CONTROL SYSTEM 审中-公开
标题翻译：整体推力矢量和滚子控制系统
公开(公告)号：WO2010019299A3
公开(公告)日：2010-04-29
申请号：PCT/US2009044439
申请日：2009-05-19
申请人： RAYTHEON CO , KINSEY LLOYD , CAVALLERI ROBERT
发明人： KINSEY LLOYD , CAVALLERI ROBERT
IPC分类号： F42B10/66
CPC分类号： F42B10/665 , F02K9/90 , F02K9/978 , F05D2240/40 , F05D2250/411 , F05D2250/42
摘要： An apparatus for vectoring the thrust of a motor that produces thrust along a longitudinal axis by expelling combustion gases through a nozzle (310) may include a plurality of linearly-positionable non-rotatable thrust deflectors (322, 325, 326, 328). The thrust deflectors (322, 325, 326, 328) may be disposed at around a perimeter of the nozzle (310). Each thrust deflector (322, 325, 326, 328) may be independently extended to simultaneously generate both a force (Fl, F2, F3, F4) transverse to the longitudinal axis (305) and a torque (Tl, T2, T3, T4 ) about the longitudinal axis (305).
摘要翻译：通过排出燃烧气体通过喷嘴（310）排出沿纵向轴线产生推力的马达的推力的装置可以包括多个可线性定位的不可旋转的推力偏转器（322,325,326,328）。推力偏转器（322,325,326,328）可以设置在喷嘴（310）的周边的周围。每个推进偏转器（322,325,326,328）可以独立地延伸以同时产生横向于纵向轴线（305）的力（F1，F2，F3，F4）和扭矩（T1，T2，T3，T4 ）围绕纵向轴线（305）。

10. 发明申请

WO2009151796A3 SOLID-FUEL PELLET THRUST AND CONTROL ACTUATION SYSTEM TO MANEUVER A FLIGHT VEHICLE 审中-公开
公开(公告)号：WO2009151796A3
公开(公告)日：2009-12-17
申请号：PCT/US2009/041240
申请日：2009-04-21
申请人： RAYTHEON COMPANY , OLDEN, Thomas, A. , CAVALLERI, Robert, J. , KINSEY, Lloyd, E.
发明人： OLDEN, Thomas, A. , CAVALLERI, Robert, J. , KINSEY, Lloyd, E.
IPC分类号： F42B10/64 , F42B10/66
摘要： A solid-fuel pellet thrust and control actuation system (PT-CAS) provides command authority for maneuvering flight vehicles (10) over subsonic and supersonic speeds and within the atmosphere and exo-atmosphere. The PT-CAS includes a chamber (26) of solid-fuel pellets (28) that are ignited to expel gas through a throat (30). The expelled gas (34) is directed at supersonic vehicle speeds in atmosphere to a cavity (19) between an aero control surface (12) and the airframe (13) to pressurize the cavity (19) and deploy the surface (12) or at subsonic speeds in atmosphere or any speed in exo-atmosphere allowed to flow out a through-hole (14) in the surface where the throat (30) and through-hole provide a virtual converging/diverging nozzle (72) to produce a supersonic divert thrust. A pellet and control actuation system (P-CAS) without the through-hole (14) provides command authority at supersonic speeds in atmosphere. A restrictor mechanism (42) controls the bleed of pressurized gas from the cavity (19) to the external environment to achieve a deployment time objective for either the PT-CAS or P-CAS.

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