公开(公告)号：US5407092A

公开(公告)日：1995-04-18

申请号：US118105

申请日：1993-09-08

Applicant: John A. Hardgrove ,  Pamela S. Adney ,  Scott J. Rotenberger

Inventor： John A. Hardgrove ,  Pamela S. Adney ,  Scott J. Rotenberger

IPC: F02K9/50 ,  F02K9/60 ,  B65D8/08

CPC classification number: F02K9/50 ,  F02K9/605 ,  F05D2300/12 ,  F05D2300/603

Abstract: A liquid propellant tank of the rolling bonded diaphragm type used for missile propulsion systems contains a flexible piston that is formed together with the outer tank diaphragm in a unitary one piece assembly.

Abstract translation: 用于导弹推进系统的滚动粘合隔膜类型的液体推进剂罐包含柔性活塞，该活塞与外罐隔膜一体形成一体式组件。

公开(公告)号：US5802842A

公开(公告)日：1998-09-08

申请号：US688628

申请日：1996-07-29

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

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

IPC: F02K9/64 ,  F02K9/97 ,  F02K1/00

CPC classification number: B23P15/008 ,  F02K9/974 ,  Y10T29/49346

Abstract: 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).

Abstract translation: 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。

公开(公告)号：US06591603B2

公开(公告)日：2003-07-15

申请号：US09802002

申请日：2001-03-08

Applicant: Gordon A. Dressler ,  Thomas J. Mueller ,  Scott J. Rotenberger

Inventor： Gordon A. Dressler ,  Thomas J. Mueller ,  Scott J. Rotenberger

IPC: B64C1502

CPC classification number: F02K9/52 ,  F02K9/972

Abstract: The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A propellant injector (20) is in fluid communication between a propellant line and an inside periphery of the combustion chamber injector end (14). A nozzle throat (18) is formed at the nozzle end (14) of the combustion chamber (12). A nozzle exit cone (22) extends outwardly from the nozzle throat (18). A plug support (30) is coupled between a nozzle plug (28) and the propellant injector (20). The nozzle plug (28) aerodynamically self-compensates for changes in ambient backpressure at the nozzle exit cone (22) such that the nozzle thrust coefficient is maximized for any ambient backpressure.

Abstract translation: 本发明提供了一种火箭发动机（10），其对于改变环境背压的喷嘴推力系数进行自补偿。 火箭发动机（10）包括具有喷射器端（14）和喷嘴端（16）的燃烧室（12）。 推进剂喷射器（20）在推进剂管线和燃烧室喷射器端部（14）的内周边之间流体连通。 在燃烧室（12）的喷嘴端（14）处形成喷嘴喉（18）。 喷嘴出口锥体（22）从喷嘴喉部（18）向外延伸。 插头支撑件（30）联接在喷嘴塞（28）和推进剂喷射器（20）之间。 喷嘴塞（28）在空气动力学上自我补偿喷嘴出口锥体（22）处的环境背压的变化，使得喷嘴推力系数对于任何环境背压最大化。

公开(公告)号：US6134781A

公开(公告)日：2000-10-24

申请号：US916379

申请日：1997-08-22

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

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

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

CPC classification number: B23P15/008 ,  F02K9/974 ,  Y10T29/49346

Abstract: 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).

Abstract translation: 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。