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1. 发明授权

US4573648A Ram air combustion steering system for a guided missile 失效
标题翻译：导弹的Ram空气燃烧转向系统
公开(公告)号：US4573648A
公开(公告)日：1986-03-04
申请号：US491953
申请日：1983-01-20
申请人： Richard C. Morenus , Alson C. Frazer
发明人： Richard C. Morenus , Alson C. Frazer
IPC分类号： F02K7/18 , F02K9/00 , F02K9/80 , F02K9/95 , F41G7/00 , F42B20060101 , F42B10/66 , H04K1/02
CPC分类号： F42B10/663
摘要： An open-ended diffusion chamber and an adjacent combustion chamber located in the nose of a projectile to receive ram air that ignites a solid fuel material within the combustion chamber. A pair of oppositely disposed lateral steering ports are provided aft of the combustion chamber and are interconnected therewith via a diverting valve that is controllable to selectively divert the escaping combustion gases from the combustion chamber to one or both of the steering ports to thereby change or maintain the trajectory course of the projectile after firing.
摘要翻译： PCT No.PCT / US83 / 00086 Sec。 371日期1983年1月20日 102（e）日期1983年1月20日PCT提交1983年1月20日PCT公布。出版物WO84 / 02975 日期1984年8月2日。开放式扩散室和位于射弹鼻部的相邻燃烧室，以接收在燃烧室内点燃固体燃料的冲压空气。一对相对设置的侧向转向端口设置在燃烧室的后部，并且经由转向阀与其互连，该转向阀可控制以选择性地将排出的燃烧气体从燃烧室转移到一个或两个转向端口，从而改变或维持射弹射击后的轨迹过程。

2. 发明授权

US4807529A Hot gas control system 失效
标题翻译：热气控制系统
公开(公告)号：US4807529A
公开(公告)日：1989-02-28
申请号：US118375
申请日：1987-11-06
申请人： Alson C. Frazer
发明人： Alson C. Frazer
IPC分类号： B01J7/00 , C06D5/00 , C06B45/00
CPC分类号： C06D5/00 , B01J7/00
摘要： A hot gas control system includes a pressure vessel defining a chamber in which is disposed a body of solid propellant material that has a leading portion and a trailing portion. A first layer of the body of solid propellant material extends between the leading portion and an intermediate region of the body of solid propellant material, and a second layer extends between the intermediate region and the trailing portion of the body of solid propellant material. The first layer is composed of a first propellant composition that produces a relatively clean gas, and the second layer is composed of a second propellant composition that produces a relatively less clean gas. The body of solid propellant is arranged to burn within the chamber from the leading portion toward the trailing portion and thereby produce a quantity of gas that passes through an outlet port to a ducting path, the first layer having a thickness sufficient to produce enough relatively clean gas to preheat the ducting structure and thereby inhibit contaminant accumulation due to the withdrawal of heat from the less clean gas.
摘要翻译：热气体控制系统包括限定腔室的压力容器，其中设置有具有前部和后部的固体推进剂材料体。固体推进剂材料体的第一层在固体推进剂材料体的引导部分和中间区域之间延伸，第二层在固体推进剂材料体的中间区域和尾部之间延伸。第一层由产生相对清洁气体的第一推进剂组合物组成，第二层由产生相对较少清洁气体的第二推进剂组合物组成。固体推进剂的主体被布置成在腔室内从引导部分向后部燃烧，从而产生一定量的气体，其通过出口到管道路径，第一层具有足以产生足够相对干净的厚度气体以预热管道结构，从而由于从较不清洁的气体中排出热而抑制污染物积聚。

3. 发明授权

US5115742A Integrated and mechanically aided warhead arming device 失效
标题翻译：集成和机械辅助弹头布防装置
公开(公告)号：US5115742A
公开(公告)日：1992-05-26
申请号：US719426
申请日：1991-06-24
申请人： Alson C. Frazer
发明人： Alson C. Frazer
IPC分类号： F42C15/295 , F42C15/40
CPC分类号： F42C15/295 , F42C15/40
摘要： An integrated and mechanically aided warhead afterbody arming device for siles using mechanical rotation of the missile to arm the warhead is disclosed. A self-contained electrical generation system provides electrical power for the proper arming of the warhead. Mechanical rotation energy is used to generate electrical power for warhead arming. Revolution counters and mechanical detents are used to prevent premature arming.
摘要翻译：公开了一种使用导弹机械旋转以弹起弹头的导弹的集成和机械辅助弹头后身体装备装置。一个独立的发电系统提供电力来适当地布置弹头。机械旋转能量用于产生用于弹头布防的电力。革命柜台和机械制动器用于防止过早的布防。

4. 发明授权

US4607810A Passive constraint for aerodynamic surfaces 失效
标题翻译：空气动力学表面的被动约束
公开(公告)号：US4607810A
公开(公告)日：1986-08-26
申请号：US689351
申请日：1985-01-07
申请人： Alson C. Frazer
发明人： Alson C. Frazer
IPC分类号： F42B10/16 , F42B13/32
CPC分类号： F42B10/16
摘要： In a guided projectile such as a missile, it is often necessary to negate the lift force imparted by the wings (5) during early low velocity stages of flight. Thus, wings (5) can be flattened against the airframe (2) of the missile (1) by a passive constraint, e.g., a shrink tubing (35) which disintegrates due to aerodynamic heating at a higher velocity stage of the flight, allowing each wing (5) to deploy into a position generally orthogonal to the airframe (2). The deployment force can be provided by torsionally and compressionally preloaded springs (19).
摘要翻译：在诸如导弹的引导弹药中，通常需要在早期的低速飞行阶段期间否定由翼（5）施加的升力。因此，翼（5）可以通过被动约束（例如，由于在飞行的更高速度阶段的空气动力学加热而分解的收缩管（35））而平坦地抵靠导弹（1）的机身（2），允许每个翼（5）部署到大致垂直于机身（2）的位置。部署力可以通过扭转和压缩的预加载弹簧（19）来提供。

5. 发明授权

US4523728A Passive auto-erecting alignment wings for long rod penetrator 失效
标题翻译：被动自动竖立对准翼长杆穿透器
公开(公告)号：US4523728A
公开(公告)日：1985-06-18
申请号：US472891
申请日：1983-03-07
申请人： Alson C. Frazer
发明人： Alson C. Frazer
IPC分类号： F42B10/16 , F42B11/06 , F42B13/32
CPC分类号： F42B10/16
摘要： In a guided moving warhead (1) which can be a missile or a projectile containing a long rod penetrator (3), alignment wings (5) keep the rod (3) in alignment with the warhead's velocity vector, thus maximizing its destructive potential. Two pairs of wings (5) are coupled to the rod (3) by means of a two-axis gimbal (7). One pair of wings (5) pivots along one axis of the gimbal (7) while another pair pivots about a second orthogonal axis. Aerodynamic forces cause the wings (5) to align with the relative wind, and as a result, the rod (3) aligns with the warhead's velocity vector as desired. Orthogonal components of crossflow acting upon the wings (5) can be compensated out by means of gearing the shafts (11, 15) which connect the wings (5) with the gimbal (7). In the case where warhead (1) is a missile, it is often necessary to negate the lift force imparted by the wings (5) during early low velocity stages of flight. Thus, wings (5) can be flattened against the airframe (2) of the missile (1) by a passive constraint, e.g., a shrink tubing (35) which disintegrates due to aerodynamic heating at a higher velocity stage of the flight, allowing each wing (5) to deploy into a position generally orthogonal to the airframe (2). The deployment force can be provided by torsionally and compressionally preloaded springs (19).
摘要翻译：在可以是导弹或包含长杆穿透器（3）的射弹的导向移动弹头（1）中，对准翼（5）保持杆（3）与弹头的速度矢量对准，从而最大化其破坏性潜力。两对翼（5）通过双轴万向节（7）联接到杆（3）上。一对翼（5）沿着万向节（7）的一个轴线枢转，而另一对翼绕第二正交轴线枢转。空气动力使翼（5）与相对风对准，结果，杆（3）根据需要与弹头的速度矢量对准。作用在翼（5）上的横流的正交分量可以通过齿轮将翼（5）与万向节（7）连接的轴（11,15）进行补偿。在弹头（1）是导弹的情况下，通常需要在早期的低速飞行阶段期间否定由翼（5）施加的升力。因此，翼（5）可以通过被动约束（例如，由于在飞行的更高速度阶段的空气动力学加热而分解的收缩管（35））而平坦地抵靠导弹（1）的机身（2），允许每个翼（5）部署到大致垂直于机身（2）的位置。部署力可以通过扭转和压缩的预加载弹簧（19）来提供。

6. 发明授权

US4027834A Missile nozzle configuration 失效
标题翻译：导弹喷嘴配置
公开(公告)号：US4027834A
公开(公告)日：1977-06-07
申请号：US359222
申请日：1964-04-13
申请人： Louis F. Heilig , Alson C. Frazer
发明人： Louis F. Heilig , Alson C. Frazer
IPC分类号： F02K9/97 , F41G7/30 , F42B15/00 , F41G7/00
CPC分类号： F02K9/97 , F41G7/30 , F42B15/00
摘要： 1. In a guiding and propulsion system for a missile, the combination which comprises:Communication means mounted in a central portion of the missile toward the aft end thereof and effective to receive and emit radiant energy along a rearward line of view substantially axial of the missile, to guide the missile, andNozzle means mounted on said aft end to propel the missile by generally rearward discharge of fluid, said nozzle means being canted outward from said central portion to keep said line of view free from said fluid.
摘要翻译： 1.在导弹和导弹系统中，组合包括：

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