公开(公告)号：US5572865A

公开(公告)日：1996-11-12

申请号：US299782

申请日：1994-09-01

申请人： Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

发明人： Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

IPC分类号： B64G1/40 ,  B64G1/00 ,  B64G1/24 ,  B64G1/26 ,  F02K9/42 ,  F02K9/44 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68

CPC分类号： F02K9/42 ,  B64G1/401 ,  B64G1/402 ,  B64G1/406 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  B64G1/007 ,  B64G1/242 ,  B64G1/26

摘要： In the preferred embodiment of the invention, a cooled bipropellant thruster 70 for controlling the on-orbit position and orientation of a spacecraft is provided. The cooled bipropellant thruster 70 uses a liquid fuel and liquid oxidizer. The liquid fuel is decomposed in a first chamber 72 with a catalytic bed of decomposition material 74 and produces at least one reaction gas, which flows to the second reaction chamber 90. The second reaction chamber 90 is heated by the reaction gas, but is cooled by liquid oxidizer flowing through cooling passages 92, 94, 98, and 102, which brings the oxidizer into a heat exchange relationship with the second reaction chamber 90. During the heat exchange relationship, heat is transferred from the second reaction chamber 90 to the oxidizer and the oxidizer transforms into a gas. The gaseous oxidizer is fed into a second reaction chamber 90 to secondarily react with the reaction gas.

公开(公告)号：US5417049A

公开(公告)日：1995-05-23

申请号：US748990

申请日：1991-08-21

申请人： Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

发明人： Robert L. Sackheim ,  Dale L. Hook ,  Gary W. Joseph

IPC分类号： B64G1/40 ,  B64G1/00 ,  B64G1/24 ,  B64G1/26 ,  F02K9/42 ,  F02K9/44 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  F02K9/28

CPC分类号： F02K9/42 ,  B64G1/401 ,  B64G1/402 ,  B64G1/406 ,  F02K9/50 ,  F02K9/52 ,  F02K9/54 ,  F02K9/58 ,  F02K9/64 ,  F02K9/68 ,  B64G1/007 ,  B64G1/242 ,  B64G1/26

摘要： In the preferred embodiment of the invention, a cooled bipropellant thruster 70 for controlling the on-orbit position and orientation of a spacecraft is provided. The cooled bipropellant thruster 70 uses a liquid fuel and liquid oxidizer. The liquid fuel is decomposed in a first chamber 72 with a catalytic bed of decomposition material 74 and produces at least one reaction gas, which flows to the second reaction chamber 90. The second reaction chamber 90 is heated by the reaction gas, but is cooled by liquid oxidizer flowing through cooling passages 92, 94, 98, and 102, which brings the oxidizer into a heat exchange relationship with the second reaction chamber 90. During the heat exchange relationship, heat is transferred from the second reaction chamber 90 to the oxidizer and the oxidizer transforms into a gas. The gaseous oxidizer is fed into a second reaction chamber 90 to secondarily react with the reaction gas.

摘要翻译： 在本发明的优选实施例中，提供了用于控制航天器的在轨位置和取向的冷却双组元推进器推进器70。 冷却的双组元推进剂推进器70使用液体燃料和液体氧化剂。 液体燃料在分解材料74的催化床的第一室72中分解，并产生至少一个流到第二反应室90的反应气体。第二反应室90被反应气体加热，但被冷却 通过液体氧化剂流过冷却通道92,94,98和102，其使氧化剂与第二反应室90成热交换关系。在热交换关系期间，热量从第二反应室90转移到氧化剂 氧化剂转化为气体。 将气态氧化剂进料到第二反应室90中以与反应气体二次反应。

公开(公告)号：US6135393A

公开(公告)日：2000-10-24

申请号：US977759

申请日：1997-11-25

申请人： Robert L. Sackheim ,  James S. Bassichis ,  Dale L. Hook

发明人： Robert L. Sackheim ,  James S. Bassichis ,  Dale L. Hook

IPC分类号： B64G1/24 ,  B64G1/26 ,  B64G1/40 ,  F02K9/50 ,  F02K9/58 ,  F02K1/00

CPC分类号： F02K9/58 ,  B64G1/26 ,  B64G1/401 ,  F02K9/50

摘要： A rocket propulsion system for spacecraft achieves greater economy, reliability and efficiency rocket by incorporating monopropellant RCS thrusters (1a-1f) for attitude control and bipropellant SCAT thrusters (5a-5c) for velocity control. Both sets of thrusters are designed to use the same liquid fuel, supplied by a pressurized non-pressure regulated tank, and operate in the blow down mode. In the propulsion system such station keeping and attitude control thrusters may function in conjunction with a large thrust apogee kick engine, which may also be of the SCAT thruster construction, that uses the same propellent fuel. Hydrazine and Binitrogen tetroxide are preferred as the fuel and oxidizer, respectively. The new system offers a simple conversion of existing monopropellant systems to a high performance bipropellant dual mode system without the extreme complexity and cost attendant to a binitrogen tetroxide--hydrazine bipropellant system.

摘要翻译： 用于航天器的火箭推进系统通过结合用于速度控制的姿态控制和双组分推进器SCAT推进器（5a-5c）的单组分推进剂RCS推进器（1a-1f）来实现更高的经济性，可靠性和效率。 两组推进器均设计为使用与加压非压力调节罐一起提供的相同的液体燃料，并在吹扫模式下运行。 在推进系统中，这种车站保持和姿态控制推进器可以与使用相同推进燃料的大推力远地点踢发动机（也可以是SCAT推进器结构）结合起作用。 分别优选肼和四氧化二氮作为燃料和氧化剂。 新系统可将现有的单组分推进剂系统简单转换为高性能双组分推进剂双模式系统，而无需四氮氧化二肼 - 双酚双组分推进剂系统的极大复杂性和成本。

公开(公告)号：US06813304B2

公开(公告)日：2004-11-02

申请号：US09886765

申请日：2001-06-21

申请人： Dale L. Hook ,  Thomas J. Engler

发明人： Dale L. Hook ,  Thomas J. Engler

IPC分类号： H01S304

CPC分类号： H01S3/095 ,  H01S3/03 ,  H01S3/0407 ,  H01S3/22 ,  Y10S372/701

摘要： A DF or HF chemical laser gain generator fabricated by a platelet technique in which internal passages are more easily formed because the generator is made as a stack of thin platelets that are separately etched and then stacked together. The gain generator is water cooled through passages formed in it during the platelet fabrication process. Water cooling results in lower and more uniform operating temperatures and gas pressures, allowing the use of stronger metals which facilitate the elimination of supporting structures that can degrade laser beam quality. The fabrication method allows for the elimination of gas dynamic and thermally induced density gradients which further degrade laser beam quality.

摘要翻译： 通过血小板技术制造的DF或HF化学激光增益发生器，其中内部通道更容易形成，因为发生器被制成作为单独蚀刻并堆叠在一起的薄片的堆叠。 在血小板制造过程中，增益发生器通过其中形成的通道进行水冷。 水冷却导致更低和更均匀的操作温度和气体压力，允许使用更强的金属，这有助于消除可能降低激光束质量的支撑结构。 制造方法允许消除气体动态和热致密度梯度，这进一步降低激光束质量。

公开(公告)号：US06785315B1

公开(公告)日：2004-08-31

申请号：US09962629

申请日：2001-09-24

申请人： Dale L. Hook ,  Josef Shwartz ,  Jeffery L. Sollee ,  Ethan W. Brigham ,  Milton H. Gran

发明人： Dale L. Hook ,  Josef Shwartz ,  Jeffery L. Sollee ,  Ethan W. Brigham ,  Milton H. Gran

IPC分类号： H01S3223

CPC分类号： F41H13/0062 ,  H01S3/095

摘要： A laser weapon system using a high energy deuterium fluoride (DF) or hydrogen fluoride (HF) laser, for which all necessary reactants and other materials are carried on an easily movable vehicle. Reactant gases are stored mixed with a diluent gas, such as helium, for ease of handling and to provide nearly ideal gas behavior. Cooling water for the laser is also employed in a high pressure steam generator that uses diesel fuel and oxygen to produce heat. Apart from a fluorine generator, the system uses only four storage tanks for reactant gases.

摘要翻译： 使用高能氘氟化物（DF）或氟化氢（HF）激光的激光武器系统，其中所有必需的反应物和其它材料都携带在容易移动的车辆上。 将反应物气体与诸如氦气之类的稀释气体混合，便于处理并提供几乎理想的气体行为。 用于激光的冷却水也用于使用柴油和氧气产生热量的高压蒸汽发生器。 除氟发生器外，该系统仅使用四个储罐作为反应气体。

公开(公告)号：US6134781A

公开(公告)日：2000-10-24

申请号：US916379

申请日：1997-08-22

申请人： Dale L. Hook ,  Thomas M. Rust ,  Scott J. Rotenberger

发明人： Dale L. Hook ,  Thomas M. Rust ,  Scott J. Rotenberger

IPC分类号： F02K9/64 ,  F02K9/97 ,  B23P15/00

CPC分类号： B23P15/008 ,  F02K9/974 ,  Y10T29/49346

摘要： A thruster rocket engine throat insert (12) has a thin walled shell (54) made from a high strength, oxidation resistant material. The shell (54) having a throat (48) of reduced cross-section and a radially extending annular stiffening ring (60) located at the throat (48). A casing (56) made from a material having a thermal conductivity at least 10 times greater than that of shell (54) is molded around an outer surface (58) of shell (54) and has a generally cylindrical exterior surface (59). Shell (54) resists yielding and oxidation caused by the extreme temperatures of rocket fuel combustion products passing through the throat insert (12), while the casing (56) acts to efficiently transfer heat from the shell (54).

摘要翻译： 推进器火箭发动机喉部插入件（12）具有由高强度，抗氧化材料制成的薄壁壳（54）。 壳体（54）具有横截面减小的喉部（48）和位于喉部（48）处的径向延伸的环形加强环（60）。 由外壳（54）的外表面（58）周围模制由具有比外壳（54）的导热系数大至少10倍的热导率的材料制成的外壳（56），并且具有大致圆柱形的外表面（59）。 壳体（54）抵抗由通过喉部插入件（12）的火箭燃料燃烧产物的极端温度引起的屈服和氧化，同时壳体（56）用于有效地传递来自壳体（54）的热量。

公开(公告)号：US4048586A

公开(公告)日：1977-09-13

申请号：US648694

申请日：1976-01-12

申请人： Arvel B. Witte ,  James E. Broadwell ,  Dale L. Hook

发明人： Arvel B. Witte ,  James E. Broadwell ,  Dale L. Hook

IPC分类号： H01S3/0953 ,  H01S3/02 ,  H01S3/095 ,  H01S3/22

CPC分类号： H01S3/0953

摘要： An inert diluent such as N.sub.2, He, Ar, etc., is injected into the reactant streams emerging from the cavity nozzle of a CW, supersonic, laser to increase the cavity power and lower the cavity temperature by enhancing mixing of the reactant stream while maintaining high pressure recovery.

公开(公告)号：US5647201A

公开(公告)日：1997-07-15

申请号：US510223

申请日：1995-08-02

申请人： Dale L. Hook ,  Hermann W. Behrens ,  Kiran R. Magiawala

发明人： Dale L. Hook ,  Hermann W. Behrens ,  Kiran R. Magiawala

IPC分类号： F02K9/44 ,  F02K9/60 ,  F15D1/06 ,  F15D1/08 ,  F02K9/52

CPC分类号： F15D1/08

摘要： Disclosed is a low flow, low Reynolds number cavitating venturi. This cavitating venturi includes an inlet for receiving a liquid at an upstream pressure and an outlet for discharging the liquid received by the inlet at a downstream pressure. The liquid passes through a converging portion having a converging sidewall which extends from said inlet, through a throat portion having a throat sidewall and a diverging diffuser portion having a diverging sidewall. The cavitating venturi provides a substantially stable liquid flow rate independent of the downstream pressure up to a downstream pressure at least as high as 80% of the upstream pressure at a Reynolds number of 60,000 or less.

摘要翻译： 公开了低流量，低雷诺数气蚀文丘里管。 该气蚀文丘里管包括用于接收上游压力的液体的入口和用于在下游压力下排出由入口接收的液体的出口。 液体通过具有会聚侧壁的会聚部分，该会聚侧壁从所述入口延伸穿过具有喉部侧壁的喉部和具有发散侧壁的发散扩散部。 气蚀文丘里管提供基本上稳定的液体流速，独立于下游压力，直到下游压力至少高达雷诺数为60,000或更小的上游压力的80％。

公开(公告)号：US4375687A

公开(公告)日：1983-03-01

申请号：US220474

申请日：1980-12-29

申请人： Dale L. Hook ,  John Waypa ,  Theodore A. Jacobs

发明人： Dale L. Hook ,  John Waypa ,  Theodore A. Jacobs

IPC分类号： H01S3/0953 ,  H01S3/02

CPC分类号： H01S3/0953 ,  Y10S372/701

摘要： A hypersonic wedge nozzle for chemical lasers that has a radially diverginglow primary nozzle with a multiplicity of hypersonic wedge type secondary injection wedges at the exit end of the primary nozzle to allow gas flow to become supersonic in the primary nozzle before entering the regions between the secondary injection wedges or the surfaces thereof. Utilization of the large diverging primary nozzle in producing supersonic flow minimizes viscous effects in producing the supersonic flow in a chemical HF or DF laser.

摘要翻译： 用于化学激光器的超音速楔形喷嘴，其具有在主喷嘴的出口端处具有多个超音速楔形二次注射楔的径向扩张的流动主喷嘴，以允许气体在进入主喷嘴之间的区域之前变成超音速 二次注射楔或其表面。 利用大的发散主喷嘴生产超音速流量可以最大限度地减少在化学HF或DF激光器中产生超音速流动的粘滞效应。

公开(公告)号：US5802842A

公开(公告)日：1998-09-08

申请号：US688628

申请日：1996-07-29

申请人： Dale L. Hook ,  Thomas M. Rust ,  Scott J. Rotenberger

发明人： Dale L. Hook ,  Thomas M. Rust ,  Scott J. Rotenberger

IPC分类号： F02K9/64 ,  F02K9/97 ,  F02K1/00

CPC分类号： B23P15/008 ,  F02K9/974 ,  Y10T29/49346

摘要： In accordance with the teachings of the present invention, there is disclosed a thruster rocket engine throat insert (12) having a thin walled shell (54) made from a high strength, oxidation resistant material. The shell (54) having a throat (48) of reduced cross-section and a radially extending annular stiffening ring (60) located at the throat (48). A casing (56) made from a material having a thermal conductivity at least 10 times greater than that of shell (54) is molded around an outer surface (58) of shell (54) and has a generally cylindrical exterior surface (59). Shell (54) resists yielding and oxidation caused by the extreme temperatures of rocket fuel combustion products passing through the throat insert (12), while the casing (56) acts to efficiently transfer heat from the shell (54).

摘要翻译： 根据本发明的教导，公开了一种推进器火箭发动机喉部插入件（12），其具有由高强度，抗氧化材料制成的薄壁壳体（54）。 壳体（54）具有横截面减小的喉部（48）和位于喉部（48）处的径向延伸的环形加强环（60）。 由外壳（54）的外表面（58）周围模制由具有比外壳（54）的导热系数大至少10倍的热导率的材料制成的外壳（56），并且具有大致圆柱形的外表面（59）。 壳体（54）抵抗由通过喉部插入件（12）的火箭燃料燃烧产物的极端温度引起的屈服和氧化，同时壳体（56）用于有效地传递来自壳体（54）的热量。