CN100347433C - 组合的混合火箭系统 - Google Patents
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Abstract
本发明的混合火箭系统的特征在于，所使用的氧化剂箱具有被外罩环绕的圆柱形中部，所述中部通过弹性粘合剂层粘合到所述外罩。而所述外罩的外表面以粘合方式固定到航天器的内表面。延伸的固体燃料发动机壳通过机械方式刚性固定到氧化剂箱的中后表面，该发动机壳的末端具有喉部和喷嘴。所述箱体到所述外罩的弹性粘合、以及所述外罩到所述航天器的刚性粘合形成火箭系统的唯一支撑，而且不需要用于发动机壳的单独支撑。
Description
相关中请的交叉引用
本申请要求于2003年3月28日提交的、申请号为60/458,296的美国临时专利申请的权益。
技术领域
本申请涉及一种混合火箭系统，其例如用于推进带机翼亚轨道航天器，但并不限于该应用。
背景技术
与固体燃料和液体燃料火箭相反，混合火箭发动机同时使用这两种燃料。也就是说，某种液体氧化剂例如氧化氮(N2O)被用来燃烧固体燃料。氧化剂被盛放在加压箱内，而固体燃料(例如HTPB、或端羟基聚丁二烯)则被铸在中空且通常是管形的燃烧室壳体或发动机的内壁上，其中所述燃烧室壳或发动机从氧化剂箱向后延伸，而终止于喉部和喷嘴。飞行员控制的阀门使氧化剂进入燃烧室壳体内，点火器(如火花或火焰型)启动燃烧。
发明内容
本发明涉及两个重要的改进。首先，涉及一种将火箭固定和安装到航天器机身或相关结构的简化方法；其次，涉及一种集成式发动机结构，该结构明显地限制了可能的漏泄路径，从而提高了可靠性和安全性。
本发明的混合火箭系统的特征在于，所使用的氧化剂箱具有圆柱形中部，该中部可以通过弹性粘合剂层而被粘合到航天器的内表面。延伸的固体燃料发动机壳以机械方式刚性固定到氧化剂箱的中后表面，该发动机壳的末端具有喉部和喷嘴。氧化剂箱对航天器的弹性粘合形成火箭系统的唯一支撑，而且不需要对于发动机壳的单独支撑。
附图说明
图1是安装在具有机翼的航天器(所示为横截面)内的一种混合火箭的侧视图；
图2是火箭部件的分解图；
图3是火箭的固体燃料发动机箱的前端的剖视立体图；
图4是发动机壳与氧化剂箱的连接处的局部剖视图；而
图5是氧化剂箱的局部剖视图。
具体实施方式
图1所示为一种混合火箭10，其安装在具有机翼的航天器的机身11内，该机身采用局部剖示出，机身11具有飞行员舱12。火箭10的主要部件是氧化剂箱14，其具有延长的圆柱形中部15，圆柱形中部15固定到机身的内表面17，该箱体具有后隔板(下文中描述)，圆柱形的发动机19固定到该后隔板，发动机的末端有一喷嘴20。为清楚起见，图1中省去了可缩回的起落架和航天器机翼和尾部。
图5示出了氧化剂箱14的横截面图，该氧化剂箱具有相对薄(例如0.1至0.125英寸)的内衬22，该内衬是由环氧纤维玻璃预浸复合材料制成的。内衬被涂有环氧基体的石墨增强纤维层23所过度卷绕。增强纤维/环氧层的厚度在箱体圆柱形中部15处的厚度约为四分之一英寸，且朝着相对的箱体两端逐渐变厚到大约1至1/2英寸，在此处箱体与圆柱形的前凸缘26和后凸缘27(图5)接触并密封接合。
密封固定到前凸缘26的是前隔板29，前隔板闭合箱体的前端，但提供了有阀的入口(未示出)用以加载氧化剂。类似地密封固定到后凸缘27的是向前凸出的后隔板30，后隔板闭合箱体的后端。氧化剂输送阀和点火系统(未示出)安装在箱体内的后隔板上。
箱体的圆柱形中部15被圆柱形外罩32所覆盖，在一优选方式中外罩32是由大约十一片或十一层柔韧的纤维玻璃布制成的，这些粘合在一起的片被定向为相对于箱体的纵轴成45度角。外罩的内径略大于箱体中部的外径，使得一厚(约0.1英寸)层弹性粘合剂(由PRC Desoto制造的Proseal P5890，Class B是令人满意的)能够注入，从而将外罩粘合到箱体。
这种粘合在一起的外罩和箱体在航天器机身11的配套的内圆柱表面34内形成滑动配合，让一薄(约0.02英寸)层刚性粘合剂能够注入，从而将箱体和外罩固定到机身。例如Hysol 9396之类的粘合剂是令人满意的。箱体-外罩及外罩-机身的粘合形成航天器内火箭10的唯一支撑。
图4是发动机19对氧化剂箱后凸缘27和后隔板30的刚性连接的局部剖视图。发动机壳36具有大约0.1英寸厚的硅酚醛树脂(silicon-phenolic)内衬37，及大约0.3英寸厚的碳增强纤维外套38。固体燃料39被铸到发动机壳内，留下机壳中心线周围的开放部分。压铸的头部绝缘40形成在固体燃料的前方，且具有向前凸出的前端41，该前端与隔板30后端的配合曲率一致。机壳36的前端外扩，从而贴靠到圆柱形的钢楔43，此钢楔具有三角形的截面并具有前表面44，该前表面具有O形密封圈45，贴靠到后隔板30上外延的圆柱形凸缘46。
铝制压圈50具有向前和向外倾斜的锥形内表面51，该内表面套在发动机壳的前端上并紧靠凸缘46的后表面。若干个螺纹紧固件52延伸穿过压圈50、凸缘46、及凸缘27中的配合孔直到螺母53，以将那些部件紧密地夹在一起，从而将发动机壳刚性固定到氧化剂箱。额外的O形密封圈54被置于凸缘46和向前延伸的衬圈55中，衬圈55是与后隔板一体形成的。有孔的圆柱形管56固定到衬圈55，并在氧化剂箱内向前延伸以供作防荡板。
氧化剂箱装载有加压至700磅/平方英寸的含氮氧化物，在此压强下氧化剂是液体。加压箱的向外膨胀至少部分地被弹性粘合剂厚层所吸收，该厚层将箱体外罩粘合到机身，而且这个粘合剂层也吸收和减弱了发动机振动。
除去圆柱形中部15，氧化剂箱大体近似于一个球体，所提供的压力容器的强度足以支撑由点火后的发动机所施加的负载。这个强度使得发动机能以悬臂的方式从氧化剂箱的后端延伸，而不再需要来自机身的支撑。这种单一的连接方式让发动机(通常是一次性使用的部件)能够容易地更换，并可以放置不同长度的发动机，而且减少了可能的漏泄路径的数目。另外，在发动机支撑方面没有产生任何额外的重量，因为坚固的箱体/机身的安装结构就支撑了整个火箭系统。
Claims (7)
1.一种亚轨道航天器内的混合火箭推进系统，该亚轨道航天器的机身具有大致中空的内圆柱表面，所述推进系统包括：一氧化剂箱，该箱具有中部的圆柱外表面，该表面被一外罩所覆盖，并可插到所述机身内表面内，所述外罩和箱是通过一弹性部件被固定在一起的，且所述外罩的外表面是粘合固定到所述机身内表面的；一延长的和大致圆柱形的固体燃料发动机壳，该机壳刚性固定到所述氧化剂箱的中后表面，所述机壳具有一后端，该后端形成一喉部以及一在所述机身后延伸的喷嘴；且其中所述推进系统的唯一支撑是所述弹性部件，所述机壳是以悬臂的形式设置在所述箱体之后的，并不直接固定到所述机身。
2.如权利要求1所述的推进系统，其中所述箱具有用环氧纤维玻璃复合材料制成的内衬，所述内衬被一具有石墨增强纤维和环氧基体的外层所过度卷绕。
3.如权利要求2所述的推进系统，其中所述外罩是纤维玻璃。
4.如权利要求3所述的推进系统，其中所述弹性部件是将所述外罩粘合到所述箱的弹性粘合剂层。
5.如权利要求4所述的推进系统，其中所述弹性粘合剂的厚度是大约0.1英寸。
6.如权利要求2所述的推进系统，其中所述箱的内衬和外层是围绕和固定到前凸缘和后凸缘的，各所述凸缘又分别固定到前隔板和后隔板，所述隔板密封所述箱。
7.如权利要求6所述的推进系统，其中所述发动机壳通过可拆卸的紧固件刚性固定到所述后隔板，而能够更换燃烧发动机壳。
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US45829603P | 2003-03-28 | 2003-03-28 | |
| US60/458,296 | 2003-03-28 |
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| CN1768200A CN1768200A (zh) | 2006-05-03 |
| CN100347433C true CN100347433C (zh) | 2007-11-07 |
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| US (1) | US7540145B2 (zh) |
| EP (1) | EP1608863B1 (zh) |
| JP (1) | JP4456080B2 (zh) |
| KR (1) | KR100730607B1 (zh) |
| CN (1) | CN100347433C (zh) |
| CA (1) | CA2519936C (zh) |
| RU (1) | RU2333869C2 (zh) |
| WO (1) | WO2004085252A2 (zh) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US7614347B2 (en) * | 2005-10-13 | 2009-11-10 | Ohnstad Thomas S | Solid-fuel-combustion fire-insulation interface with adjacent container-wall |
| US20080264372A1 (en) * | 2007-03-19 | 2008-10-30 | Sisk David B | Two-stage ignition system |
| FR2929339B1 (fr) | 2008-03-27 | 2012-10-05 | Snpe Materiaux Energetiques | Procede et dispositifs de propulsion pyrotechnique avec modulation de poussee, engin spatial comprenant un tel dispositif |
| US8727264B1 (en) | 2013-06-11 | 2014-05-20 | Elbert L. Rutan | Dynamic tow maneuver orbital launch technique |
| US8960590B2 (en) | 2013-07-18 | 2015-02-24 | Elbert L. Rutan | Pressure-equalizing cradle for booster rocket mounting |
| FR3011902B1 (fr) * | 2013-10-16 | 2015-11-27 | Herakles | Procede de liaison d'une jupette a une enveloppe d'un corps de propulseur |
| CN104309560A (zh) * | 2014-10-25 | 2015-01-28 | 贺州学院 | 一种车用固体推进剂火箭防护系统 |
| CN104309559A (zh) * | 2014-10-25 | 2015-01-28 | 陈恒兰 | 一种车用固液混合推进剂火箭防护系统 |
| US10823115B2 (en) | 2016-02-16 | 2020-11-03 | Raytheon Company | Hybrid rocket motor with integral oxidizer tank |
| US10023505B2 (en) | 2016-03-01 | 2018-07-17 | Raytheon Company | Method of producing solid propellant element |
| US10259756B2 (en) | 2016-03-01 | 2019-04-16 | Raytheon Company | Solid propellant with integral electrodes, and method |
| CN106050475A (zh) * | 2016-08-03 | 2016-10-26 | 杨斯涵 | 一种液固耦合式火箭发动机 |
| RU173608U1 (ru) * | 2016-09-05 | 2017-09-01 | Публичное акционерное общество Научно-производственное объединение "Искра" | Корпус ракетного двигателя на твердом топливе |
| US10662898B2 (en) | 2016-09-08 | 2020-05-26 | Raytheon Company | Integrated thruster |
| US11028802B2 (en) | 2016-11-14 | 2021-06-08 | Northrop Grumman Systems Corporation | Liquid rocket engine assemblies and related methods |
| KR102011484B1 (ko) | 2017-09-26 | 2019-08-19 | 플로우플러스 주식회사 | 로켓장치용 산화제공급유닛과 산화제공급유닛의 파열부재 |
| KR102011482B1 (ko) | 2017-09-26 | 2019-08-19 | 플로우플러스 주식회사 | 파열식 로켓장치 |
| CN111114834B (zh) * | 2019-12-17 | 2021-05-04 | 西安航天动力研究所 | 一种轻质侧壁悬挂垂向传力机架及一级发动机 |
| CN112610359B (zh) * | 2020-12-28 | 2022-02-22 | 中国航天空气动力技术研究院 | 一种内埋安装的固体火箭发动机固定装置 |
| CN114718763B (zh) * | 2022-05-17 | 2022-10-14 | 星河动力(北京)空间科技有限公司 | 液体运载火箭及其推进剂贮箱 |
| CN115596573B (zh) * | 2022-11-25 | 2023-04-14 | 精易兴航(北京)科技创新有限公司 | 一种精简结构的球形底火箭贮箱 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3354647A (en) * | 1965-10-22 | 1967-11-28 | Thiokol Chemical Corp | Method for initiating or quenching the combustion in a solid propellant rocket motor |
| CN87103346A (zh) * | 1986-05-07 | 1987-11-25 | 三菱重工业株式会社 | 液体燃料火箭发动机 |
| US5893266A (en) * | 1994-10-21 | 1999-04-13 | Environmental Aeroscience Corp. | Hybrid rocket system and integrated motor for use therein |
| CN1343282A (zh) * | 1999-03-10 | 2002-04-03 | 威廉国际有限责任公司 | 火箭发动机 |
Family Cites Families (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3068641A (en) * | 1955-04-18 | 1962-12-18 | Homer M Fox | Hybrid method of rocket propulsion |
| US3097766A (en) * | 1959-09-17 | 1963-07-16 | Curtiss Wright Corp | Pre-filled propellant tank for rockets |
| US3178885A (en) * | 1961-06-12 | 1965-04-20 | Lockheed Aircraft Corp | Hybrid rocket engine |
| US3568448A (en) * | 1969-04-01 | 1971-03-09 | Thiokol Chemical Corp | Ignition system for igniting a gas generator by the use of combustion gases from a solid propellant rocket motor having selective zoning capabilities |
| US3969812A (en) * | 1974-04-19 | 1976-07-20 | Martin Marietta Corporation | Method of manufacturing an overwrapped pressure vessel |
| US4504530A (en) * | 1982-03-17 | 1985-03-12 | Structural Fibers, Inc. | Lined pressure vessels |
| FR2549146B1 (fr) * | 1983-07-11 | 1987-12-24 | Europ Propulsion | Ensemble propulsif pour missile statoreacteur a propulseur d'acceleration integre |
| US4561568A (en) * | 1984-03-02 | 1985-12-31 | The United States Of America As Represented By The Secretary Of The Army | Liquid fuel expulsion system |
| US4577542A (en) * | 1984-03-07 | 1986-03-25 | The United States Of America As Represented By The Secretary Of The Air Force | Dome restraint assembly for rocket motors |
| US5070691A (en) * | 1988-08-03 | 1991-12-10 | Thiokol Corporation | Solid propellant canister loaded multiple pulsed or staged rocket |
| US5119627A (en) * | 1989-11-03 | 1992-06-09 | American Rocket Company | Embedded pressurization system for hybrid rocket motor |
| US5101623A (en) * | 1990-02-06 | 1992-04-07 | Rockwell International Corporation | Rocket motor containing improved oxidizer injector |
| US5613358A (en) * | 1990-09-26 | 1997-03-25 | Thiokol Corporation | Reduced cost membrane seal assembly for pulsed rocket motor |
| US5341638A (en) * | 1992-03-09 | 1994-08-30 | Thiokol Corporation | Low cost segmented structure for pressure vessels, rocket motors, piping |
| US6016652A (en) * | 1994-10-21 | 2000-01-25 | Hy-Pat Corporation | Hybrid rocket system with disposable cartridge |
| US6125763A (en) * | 1998-08-14 | 2000-10-03 | Environmental Aeroscience Corp. | Integral solid booster and hybrid thrust sustaining system and projectile incorporating the same |
| US6499287B1 (en) * | 1999-05-25 | 2002-12-31 | Zachary R. Taylor | Integrated tankage for propulsion vehicles and the like |
| US6745983B2 (en) * | 2000-05-25 | 2004-06-08 | Zachary R. Taylor | Integrated tankage for propulsion vehicles and the like |
| CA2367197A1 (en) * | 2001-01-10 | 2002-07-10 | Cesaroni Technology Incorporated | Liquid/solid fuel hybrid propellant system for a rocket |
| US6782693B1 (en) * | 2002-01-04 | 2004-08-31 | Brian A. Floyd | Case burning rocket with drive system for combustion chamber and nozzle |
-
2004
- 2004-03-29 EP EP04749523A patent/EP1608863B1/en not_active Expired - Lifetime
- 2004-03-29 CN CNB2004800084251A patent/CN100347433C/zh not_active Expired - Fee Related
- 2004-03-29 CA CA002519936A patent/CA2519936C/en not_active Expired - Fee Related
- 2004-03-29 RU RU2005133194/11A patent/RU2333869C2/ru not_active IP Right Cessation
- 2004-03-29 JP JP2005518924A patent/JP4456080B2/ja not_active Expired - Fee Related
- 2004-03-29 US US10/516,828 patent/US7540145B2/en active Active
- 2004-03-29 KR KR1020057018360A patent/KR100730607B1/ko active IP Right Grant
- 2004-03-29 WO PCT/US2004/009694 patent/WO2004085252A2/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3354647A (en) * | 1965-10-22 | 1967-11-28 | Thiokol Chemical Corp | Method for initiating or quenching the combustion in a solid propellant rocket motor |
| CN87103346A (zh) * | 1986-05-07 | 1987-11-25 | 三菱重工业株式会社 | 液体燃料火箭发动机 |
| US5893266A (en) * | 1994-10-21 | 1999-04-13 | Environmental Aeroscience Corp. | Hybrid rocket system and integrated motor for use therein |
| CN1343282A (zh) * | 1999-03-10 | 2002-04-03 | 威廉国际有限责任公司 | 火箭发动机 |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2004085252A2 (en) | 2004-10-07 |
| EP1608863A4 (en) | 2008-04-16 |
| EP1608863B1 (en) | 2012-06-20 |
| CA2519936C (en) | 2008-11-18 |
| US7540145B2 (en) | 2009-06-02 |
| JP2006514726A (ja) | 2006-05-11 |
| RU2005133194A (ru) | 2006-02-10 |
| CN1768200A (zh) | 2006-05-03 |
| CA2519936A1 (en) | 2004-10-07 |
| US20060145018A1 (en) | 2006-07-06 |
| WO2004085252A3 (en) | 2004-12-29 |
| EP1608863A2 (en) | 2005-12-28 |
| RU2333869C2 (ru) | 2008-09-20 |
| KR20060003336A (ko) | 2006-01-10 |
| KR100730607B1 (ko) | 2007-06-20 |
| JP4456080B2 (ja) | 2010-04-28 |
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