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21. 发明授权

US5010730A Gas-fed hybrid propulsion system 失效
标题翻译：燃气混合推进系统
公开(公告)号：US5010730A
公开(公告)日：1991-04-30
申请号：US434526
申请日：1989-11-07
申请人： William H. Knuth , John H. Beveridge
发明人： William H. Knuth , John H. Beveridge
IPC分类号： F02K9/72
CPC分类号： F02K9/72
摘要： Self-contained hybrid propulsion systems have long been recognized as a class of propulsion systems that combine a liquid propellant and a solid propellant into a single system. The propellants are stored separately and the liquid propellant is delivered to the motor casing that holds the solid propellant. The present invention contemplates gasifying the liquid propellant prior to introduction into the motor casing in order to enhance system performance. The solid propellant grain is ignited and partially burned generating heat to evaporate the remaining solid propellant grain at a controlled rate. The resulting mixture is then passed to a secondary combustion region where it is mixed with additional gasified liquid propellant to complete the combustion. An integrated turbopump assembly including a pump portion, a preburner portion and a turbine portion is provided to pressurize and gasify the liquid propellant.
摘要翻译：长期以来，独立混合动力推进系统被公认为将液体推进剂和固体推进剂组合成单一系统的一类推进系统。推进剂分开储存，液体推进剂被运送到保持固体推进剂的马达外壳上。本发明考虑在引入电动机壳体之前使液体推进剂气化，以增强系统性能。固体推进剂颗粒被点燃并部分燃烧产生热量以以受控的速率蒸发剩余的固体推进剂颗粒。然后将所得混合物通入二次燃烧区域，在其中与另外气化的液体推进剂混合以完成燃烧。提供包括泵部分，预燃器部分和涡轮部分的集成涡轮泵组件以对液体推进剂进行加压和气化。

22. 发明授权

US4644745A Fixed geometry rocket thrust chamber with variable expansion ratio 失效
标题翻译：固定几何火箭推力室具有可变膨胀比
公开(公告)号：US4644745A
公开(公告)日：1987-02-24
申请号：US762030
申请日：1985-08-02
申请人： William R. Wagner
发明人： William R. Wagner
IPC分类号： F02K9/56 , F02K9/62 , F02K9/00 , F02K9/42 , F02K9/72
CPC分类号： F02K9/56 , F02K9/62
摘要： The present invention provides a rocket thrust chamber (30) comprising a combustor (32) with a fixed divergent profile, a nozzle (36) for further expanding the output of the divergent combustor and a high-velocity, throttleable injector (34) for injecting propellants at such an initial velocity and initially rapid, axial burning rate that the injected propellants achieve sonic flow conditions at preselected locations within the divergent combustor according to throttle setting. In operation, the throttle setting fixes the location of the sonic flow line within the divergent combustor, and the ratio of the nozzle exit area with respect to the effective area of the divergent combustor at the sonic location area fixes the expansion ratio for that throttle setting. At launch, the engine delivers a high propellant flow rate and a moderate expansion ratio, while in space, it delivers a low propellant flow rate and a far greater expansion ratio.
摘要翻译：本发明提供了一种包括具有固定发散轮廓的燃烧器（32）的火箭推进室（30），用于进一步扩展发散燃烧室的输出的喷嘴（36）和用于喷射的高速可节流喷射器（34）推进剂以这样的初始速度和初始快速的轴向燃烧速率，喷射的推进剂根据节气门设置在发散燃烧器内的预选位置处实现声波流动状态。在操作中，节气门设定固定了发散燃烧器内的声流线的位置，并且喷嘴出口面积相对于发声燃烧器在声音位置区域的有效面积的比率固定了该节气门设定的膨胀比。在发射时，发动机提供高推进剂流量和适度的膨胀比，而在空间中，它提供低推进剂流量和更大的膨胀比。

23. 发明授权

US4384454A Thrust nozzle for rocket engine with ablating lining 失效
标题翻译：具有烧蚀内衬的火箭发动机推力喷嘴
公开(公告)号：US4384454A
公开(公告)日：1983-05-24
申请号：US210624
申请日：1980-11-26
申请人： Ernst Engl
发明人： Ernst Engl
IPC分类号： F02K9/97 , F02K9/72
CPC分类号： F02K9/978 , F02K9/974 , Y10S60/909
摘要： A thrust nozzle for a reaction engine having a combustion chamber with a sustained flight discharge nozzle defined therein for the passage of thrust gases and a sustained flight thrust arrangement connected to the combustion chamber for supplying thrust gases through the combustion chamber, the thrust nozzle comprising a starting nozzle formed on an interior wall of the combustion chamber radially inwardly of the sustained flight discharge nozzle made of a plurality of layers of ablatable material which are ablated by the passing thrust gases to discharge vaporized or fragmentary parts of the layers of ablatable material.
摘要翻译：一种用于反应发动机的推力喷嘴，其具有燃烧室，其具有限定在其中的推进气体通过的持续的排放喷嘴，以及连接到燃烧室的持续的飞行推力装置，用于通过燃烧室供应推力气体，该推力喷嘴包括起始喷嘴形成在燃烧室的内壁上，径向向内由可再生材料层组成的持续排放喷嘴的内侧，该多层可消融材料被通过的推力气体排出，以排出可消融材料层的蒸发或零碎部分。

24. 发明授权

US4132165A Fuel supply system for a missile or the like 失效
标题翻译：用于导弹等的燃料供应系统
公开(公告)号：US4132165A
公开(公告)日：1979-01-02
申请号：US730806
申请日：1976-10-08
申请人： Plato J. Leeson
发明人： Plato J. Leeson
IPC分类号： F02K9/50 , F02K9/72 , F42B13/00
CPC分类号： F02K9/72 , F02K9/50
摘要： A missile is initially propelled through space by the burning of solid fuel in a combustor. The heat produced by the combustion of such fuel is used to vaporize a liquid, the pressurized vapor being used to pump liquid fuel to the combustor after the solid fuel has been depleted.
摘要翻译：导弹最初是通过在燃烧器中燃烧固体燃料而被推进空间的。这种燃料的燃烧所产生的热量用于蒸发液体，加压蒸汽用于在固体燃料已经耗尽之后将液体燃料泵送到燃烧器。

25. 发明授权

US4000613A Dual mode fluid management system 失效
标题翻译：双模流体管理系统
公开(公告)号：US4000613A
公开(公告)日：1977-01-04
申请号：US550103
申请日：1975-02-13
申请人： Akiharu Fukumoto , Phil D. La Force
发明人： Akiharu Fukumoto , Phil D. La Force
IPC分类号： F02K9/58 , F02K9/72 , F02K9/06 , B05B7/12
CPC分类号： F02K9/58 , F02K9/72
摘要： A dual orifice injector assembly for use in a hybrid rocket motor having aoost and sustain mode and capable of controlling liquid flow rate for the two different modes of operation comprising an inlet manifold to distribute the fluid through a sustain injector and boost injector, actuating means for axially moving the sustain injector into a position to close off the boost injector for the sustain mode of operation and a flow deflector to cause the fluid to be dispersed in a fan like pattern at an angle 180.degree. to the axis of the manifold housing.
摘要翻译：一种用于具有升压和维持模式并能够控制两种不同操作模式的混合火箭发动机的双孔喷射器组件，包括入口歧管以将流体分配通过维持喷射器和增压喷射器，致动装置用于将维持喷射器轴向移动到关闭用于维持操作模式的升压喷射器的位置和导流板，以使流体以与歧管壳体的轴线成180°的角度分散在类似风扇的风扇中。

26. 发明授权

US3807170A Fuel injection subsystem for supersonic combustion 失效
标题翻译：燃油喷射系统用于超级燃烧
公开(公告)号：US3807170A
公开(公告)日：1974-04-30
申请号：US62466967
申请日：1967-03-16
申请人： US ARMY
发明人： KESTING L
IPC分类号： F02K7/18 , F02K9/72 , F02K3/00
CPC分类号： F02K7/18 , F02K9/72
摘要： A fuel injection subsystem for a missile having an engine provided with a predetermined fixed geometry for subsonic and supersonic operation. The subsystem utilizes both solid and liquid fuels to provide a multiplicity of engine operating conditions. According to the operating requirements, a central control station provided for gases from the solid fuel to: (a) be ducted to various points in the combustor; (b) pressurize the liquid fuel tanks, and; (c) function as a pilot light for the liquid propellant. The liquid fuels are: (a) throttled for variable flow; (b) secondarily injected to redirect hot gases from the solid fuel, and; (c) used as a regenerative coolant.
摘要翻译：一种用于具有用于亚音速和超音速操作的具有预定固定几何形状的发动机的用于导弹的燃料喷射子系统。该子系统利用固体和液体燃料提供多种发动机运行条件。根据操作要求，中央控制站提供来自固体燃料的气体到：（a）被导管到燃烧器中的各个点; （b）对液体燃料箱加压; （c）作为液体推进剂的指示灯。液体燃料为：（a）为可变流量节流; （b）二次注入以重新定向来自固体燃料的热气体; （c）用作再生冷却剂。

27. 发明授权

US3782112A Hybrid generator 失效
标题翻译：混合发电机
公开(公告)号：US3782112A
公开(公告)日：1974-01-01
申请号：US3782112D
申请日：1972-02-24
申请人： US NAVY
发明人： MUZZY R
IPC分类号： F02K9/72 , F02K9/06
CPC分类号： F02K9/72
摘要： An improved hybrid injector to gasify and aerate a liquid oxidizer. A solid propellant gas generator is enclosed in an annular manifold surrounding the passageway leading from a source of liquid oxidizer to the main combustion chamber. Openings through the manifold communicate the gas generator with the liquid oxidizer passageway to thereby gasify and aerate the liquid oxidizer passing into the main combustion chamber.
摘要翻译：一种改进的混合注射器，用于气化和充气液体氧化剂。固体推进剂气体发生器封闭在围绕从液体氧化剂源引导到主燃烧室的通道的环形歧管中。通过歧管的开口将气体发生器与液体氧化剂通道连通，从而使通入主燃烧室的液体氧化剂气化和充气。

28. 发明授权

US3595022A Thermodynamic reaction drive 失效
标题翻译：热力学反应驱动
公开(公告)号：US3595022A
公开(公告)日：1971-07-27
申请号：US3595022D
申请日：1969-04-09
申请人： LICENTIA GMBH
发明人： RADEBOLD REINHART , LANG HERMANN
IPC分类号： F02K7/18 , F02K9/44 , F02K9/72 , F02K9/02 , F02K7/10
CPC分类号： F02K9/72 , F02K7/18 , F02K9/44
摘要： A thermodynamic reaction drive or rocket engine which employs liquefiable solid propellant. An alkali metal, which is used as the propellant, is stored in the fuel tank of the rocket engine in the solid state and then, whenever engine operation is desired, liquefied by heating to the necessary temperature. The liquid propellant is fed from the fuel tank through a De Laval nozzle into the mixing or combustion chamber where it is combined with an oxidizer. The propellant, which can be forced through the nozzle primarily by means of its own vapor pressure, is changed over at the nozzle into a two-phase flow. The oxidizer, which is simultaneously introduced into the mixing chamber at a higher pressure than the pressure in the chamber, effects the combustion of the propellant so that the internal energy of the products of combustion may be converted to kinetic energy in an appropriate thrust nozzle.

29. 发明授权

US3555824A Gas generator construction and a method of operating a combustion chamber 失效
标题翻译：气体发生器结构和操作燃烧室的方法
公开(公告)号：US3555824A
公开(公告)日：1971-01-19
申请号：US3555824D
申请日：1968-11-22
申请人： MESSERSCHMITT BOELKOW BLOHM
发明人： BUSE WILHELM G , WEIGELT HEINRICH
IPC分类号： F02K9/62 , F02K9/72 , F02K9/04
CPC分类号： F02K9/62 , F02K9/72
摘要： A ROCKET COMBUSTION ENGINE OR GAS GENERATOR COMPRISES A CYLINDRICAL HOUSING WHICH TERMINATES IN A THRUST NOZZLE AT ONE END FOR THE DISCHARGE OF GENERATED GASES AND WHICH INCLUDES AN OPPOSITE CLOSED END FOR DIRECTING A PROPELLANT COMPONENT, NAMELY, A LIQUID OXYGEN OR AN OXYGEN CARRIER INTO THE COMBUSTION CHAMBER. THE COMBUSTION CHAMBER IS LINED WITH A SOLID FUEL WHICH IS ADVANTAGEOUSLY DESIGNED AS A CENTRAL BURNER OR A COMBINATION CENTRAL AND END BURNER. THE SOLID FUEL DEFINES A CENTRAL PASSAGE FOR THE FLOW OF COMBUSTION GASES OR GENERATED GASES WHICH ARE ADVANTAGEOUSLY CONFINED FOR PASSAGE THROUGH A CENTRAL OPENING OF A PLATE ADJACENT THE DISCHARGE THRUST GAS NOZZLE. THE OXYGEN IS INTRODUCED IN A MANNER SUCH THAT IT WHIRLS ALONG THE INTERIOR WALL OF THE COMBUSTION CHAMBER, AND FOR THIS PURPOSE IT MAY BE INTRODUCED BY A TURBULENCE NOZZLE MEMBER OR BY INTRODIRECTION IN A TANGENTIAL MANNER INTO A PRECHAMBER WHICH LEADS INTO THE CLOSED END OF THE COMBUSTION CHAMBER. A SOLID FUEL IS DESIGNED AS A CYLINDER WHICH ABUTS AGAINST THE CLOSED END WALL AND WHICH RESTS ON A RING PLATE LOCATED ADJACENT THE NOZZLE OR OPPOSTE END. THE END ADJACENT THE NOZZLE MAY ADVANTAGEOUSLY BE FORMED IN A CURVED MANNER SO THAT THE OXYGEN MAY FLOW IN A WHIRLING STREAM IN A SMOOTH MANNER AGAINST THE END WALL THEREOF. COMBUSTION TAKES PLACE HYPERGOLICALLY OR IF THE PROPELLANT COMPONENTS ARE NOT OF A TYPE TO REACT HYPERGOLICALLY THEN AN ADDITIONAL MIXTURE TO PROMOTE HYPERGOLIC REACTION AND IGNITION WITH THE OXYGEN IS INTRODUCED.

30. 发明授权

US3529420A Adjustment device for the flow of a liquid propellant into a hypergolic reaction system 失效
标题翻译：液体推进剂流入高压反应系统的调节装置
公开(公告)号：US3529420A
公开(公告)日：1970-09-22
申请号：US3529420D
申请日：1968-12-19
申请人： NORD AVIAT SOC NATIONALE DE CO
发明人： GUYOT PIERRE
IPC分类号： F02K9/58 , F02K9/72 , F02K9/94 , F02K9/02 , F16K31/12
CPC分类号： F02K9/94 , F02K9/58 , F02K9/72

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