ES2154487T3 - Sistema y metodo de control de alabes del chorro para misiles. - Google Patents

Sistema y metodo de control de alabes del chorro para misiles.

Info

Publication number
ES2154487T3
ES2154487T3 ES98202177T ES98202177T ES2154487T3 ES 2154487 T3 ES2154487 T3 ES 2154487T3 ES 98202177 T ES98202177 T ES 98202177T ES 98202177 T ES98202177 T ES 98202177T ES 2154487 T3 ES2154487 T3 ES 2154487T3
Authority
ES
Spain
Prior art keywords
control
missile
jet
fins
alabes
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
ES98202177T
Other languages
English (en)
Inventor
William M Hatalsky
Andrew B Facciano
Stephen D Haight
Sean A Johnson
Aszetta D Jordan
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Co
Original Assignee
Raytheon Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Raytheon Co filed Critical Raytheon Co
Application granted granted Critical
Publication of ES2154487T3 publication Critical patent/ES2154487T3/es
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/805—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control servo-mechanisms or control devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/90—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using deflectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/978—Closures for nozzles; Nozzles comprising ejectable or discardable elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/62—Steering by movement of flight surfaces
    • F42B10/64—Steering by movement of flight surfaces of fins
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/60—Steering arrangements
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/665—Steering by varying intensity or direction of thrust characterised by using a nozzle provided with at least a deflector mounted within the nozzle

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

SE PRESENTA UN SISTEMA Y UN PROCEDIMIENTO DE CONTROL DE LAS ALETAS DE CHORRO DE UN MISIL. ESTE SISTEMA ES COMPACTO, ROBUSTO Y LIGERO, Y VA UNIDO, DE FORMA DESMONTABLE AL EXTREMO POSTERIOR DE UN MISIL. EL SISTEMA PERMITE UN CONTROL MUY RAPIDO DE CABECEO Y BALANCEO DURANTE EL LANZAMIENTO. A CONTINUACION, EL SISTEMA SE SEPARA DEL MISIL, PARA NO CARGARLO DURANTE SU VUELO HACIA EL BLANCO. LAS ALETAS DEL SISTEMA SE DIVIDEN EN CUADRANTES, CADA UNO DE LOS CUALES TIENE SU PROPIO SOPORTE DE MONTAJE Y CONJUNTO DE TREN DE ENGRANAJES. CADA ALETA ESTA CONECTADA TAMBIEN MEDIANTE UN ACOPLAMIENTO SEPARABLE AL SISTEMA DE CONTROL DE DIRECCION DEL MISIL, DE FORMA QUE EL ACCIONAMIENTO DEL SISTEMA DE CONTROL DE DIRECCION ACTIVA SIMULTANEAMENTE EL SISTEMA DE CONTROL DE LAS ALETAS DE CHORRO.
ES98202177T 1995-05-26 1996-05-15 Sistema y metodo de control de alabes del chorro para misiles. Expired - Lifetime ES2154487T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US08/452,211 US5806791A (en) 1995-05-26 1995-05-26 Missile jet vane control system and method

Publications (1)

Publication Number Publication Date
ES2154487T3 true ES2154487T3 (es) 2001-04-01

Family

ID=23795545

Family Applications (1)

Application Number Title Priority Date Filing Date
ES98202177T Expired - Lifetime ES2154487T3 (es) 1995-05-26 1996-05-15 Sistema y metodo de control de alabes del chorro para misiles.

Country Status (9)

Country Link
US (1) US5806791A (es)
EP (2) EP0744591A3 (es)
AU (1) AU686050B2 (es)
CA (1) CA2176048C (es)
DE (1) DE69611940T2 (es)
ES (1) ES2154487T3 (es)
IL (1) IL118251A (es)
NO (1) NO309668B1 (es)
TR (1) TR961035A2 (es)

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US5631830A (en) 1995-02-03 1997-05-20 Loral Vought Systems Corporation Dual-control scheme for improved missle maneuverability
DE19632893C2 (de) * 1996-08-16 2001-02-08 Industrieanlagen Betr Sgmbh Ia Verfahren zur Herstellung von Flugkörperkomponenten aus faserverstärkter Keramik
DE19640540C1 (de) * 1996-10-01 1998-04-02 Daimler Benz Aerospace Ag Ruderstellsystem für einen Lenkflugkörper
US6308911B1 (en) 1998-10-30 2001-10-30 Lockheed Martin Corp. Method and apparatus for rapidly turning a vehicle in a fluid medium
US6668542B2 (en) 1999-10-27 2003-12-30 Allison Advanced Development Company Pulse detonation bypass engine propulsion pod
RU2154593C1 (ru) * 1999-12-08 2000-08-20 Лабзин Василий Васильевич Блок рулевых приводов
WO2001054981A2 (en) 2000-01-12 2001-08-02 Allison Advanced Development Company Propulsion module
US6450443B1 (en) 2000-08-17 2002-09-17 The United States Of America As Represented By The Secretary Of The Navy High torque 2.75-inch rocket nozzle
RU2177601C1 (ru) * 2000-08-21 2001-12-27 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Управляемый артиллерийский снаряд
US6548794B2 (en) 2001-03-13 2003-04-15 Raytheon Company Dissolvable thrust vector control vane
DE10210433C1 (de) * 2002-03-09 2003-08-14 Dornier Gmbh Fluggerät zur IR-Flugzieldarstellung
US6726147B1 (en) * 2003-05-15 2004-04-27 Moog Inc. Multi-function actuator, and method of operating same
NO318772B1 (no) * 2003-09-24 2005-05-02 Nammo Raufoss As Rakettmotor med styrevinger i motorens dyse
RU2265553C1 (ru) * 2004-03-29 2005-12-10 Московский авиационный институт (государственный технический университет) Исполнительный механизм рулевого привода
DE102004037487A1 (de) * 2004-07-27 2006-03-23 Deutsches Zentrum für Luft- und Raumfahrt e.V. Strahlruder und Verfahren zur Herstellung eines Strahlruders
US7026540B1 (en) * 2005-04-04 2006-04-11 The United States Of America As Represented By The Secretary Of The Navy Tailcone assembly for a submarine countermeasure
US7509903B2 (en) 2005-04-08 2009-03-31 Raytheon Company Separable structure material
FR2891618B1 (fr) * 2005-10-05 2010-06-11 Giat Ind Sa Dispositif d'entrainement de gouvernes de projectile.
EP1934547B1 (en) * 2005-10-13 2012-12-12 Raytheon Company Exhaust assembly for mass ejection drive system
US7800032B1 (en) * 2006-11-30 2010-09-21 Raytheon Company Detachable aerodynamic missile stabilizing system
US7755012B2 (en) * 2007-01-10 2010-07-13 Hr Textron, Inc. Eccentric drive control actuation system
US9341453B2 (en) * 2007-07-10 2016-05-17 Omnitek Partners, Llc Mechanical stepper motors for guided munitions and industrial machinery
US8193754B2 (en) * 2007-07-10 2012-06-05 Omnitek Partners Llc Mechanical stepper motors
US8117847B2 (en) 2008-03-07 2012-02-21 Raytheon Company Hybrid missile propulsion system with reconfigurable multinozzle grid
EP2297544B1 (en) * 2008-05-21 2017-06-21 Raytheon Company Integral thrust vector and roll control system
USD599854S1 (en) * 2008-06-09 2009-09-08 Lockheed Martin Corporation Writing instrument
KR101730664B1 (ko) 2009-02-02 2017-04-26 에어로바이론먼트, 인크. 멀티모드 무인 항공기
DE102009013150B4 (de) 2009-03-06 2011-05-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. Bauteil zum Einsatz in Heißgasströmungen
DK3133019T3 (en) 2009-09-09 2019-02-18 Aerovironment Inc NOISE DEVICE FOR A DRONE PROTECTION PIPE
JP5886201B2 (ja) 2009-09-09 2016-03-16 エアロバイロメント, インコーポレイテッドAerovironment, Inc. エレボン制御システム
US8436285B2 (en) * 2010-07-26 2013-05-07 Raytheon Company Projectile that includes a fin adjustment mechanism with changing backlash
KR101244490B1 (ko) * 2010-10-27 2013-03-18 최용준 제트베인 분리식 발사체의 방향 조종 장치
CN104089546B (zh) * 2014-04-29 2015-09-30 北京理工大学 弹体的可变气动布局结构
KR101603154B1 (ko) 2014-08-26 2016-03-14 국방과학연구소 제트베인 분리가 가능한 통합형 구동장치
JP6361404B2 (ja) * 2014-09-17 2018-07-25 三菱重工業株式会社 推力偏向装置、および、推力偏向装置を備える飛しょう体
FR3041744B1 (fr) * 2015-09-29 2018-08-17 Nexter Munitions Projectile d'artillerie ayant une phase pilotee.
US10222189B2 (en) * 2016-07-22 2019-03-05 Raytheon Company Stage separation mechanism and method
CN107416213B (zh) * 2017-05-16 2020-03-24 上海航天控制技术研究所 一种带燃气舵的飞行器尾端防火结构
US10112691B1 (en) * 2017-06-12 2018-10-30 The Boeing Company Releasable forward section of an underwater vehicle
CN108915901B (zh) * 2018-07-26 2021-04-20 西安航天动力技术研究所 一种柔性喷管固定体与扩张段防错位结构及方法
CN112129179B (zh) * 2019-06-24 2024-09-03 北京恒星箭翔科技有限公司 一种40mm火箭筒发射的激光驾束制导导弹
RU2740978C1 (ru) * 2020-02-10 2021-01-22 Акционерное общество Московский научно-производственный комплекс "Авионика" имени О.В. Успенского (АО МНПК "Авионика") Блок рулевых приводов ракеты или снаряда
CN111946461A (zh) * 2020-07-27 2020-11-17 山东鑫聚龙动力科技集团有限公司 一种航天发动机用翼轴及其制造工艺
IL277997B2 (en) * 2020-10-01 2024-08-01 Rafael Advanced Defense Systems Ltd Aileron control operating system
US11733011B2 (en) * 2020-11-24 2023-08-22 Raytheon Company Steering system with power take-off from actuators
US11879416B1 (en) 2022-09-09 2024-01-23 Raytheon Company Method for reducing jet tab exposure during thrust vectoring
TWM657368U (zh) * 2023-11-20 2024-07-01 台灣飛行器股份有限公司 無人飛行裝置
KR20250086854A (ko) 2023-12-06 2025-06-16 현대자동차주식회사 보조 추진부를 갖춘 비행체 및 보조 추진부의 제어방법
US12540587B1 (en) 2024-08-15 2026-02-03 Pratt & Whitney Canada Corp. Gas turbine engine nozzle with variable area

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US2654552A (en) * 1948-02-24 1953-10-06 Northrop Aircraft Inc Movable jet deflector to compensate for destabilizing moment in a jet aircraft
US5082202A (en) * 1975-01-06 1992-01-21 The United States Of America As Represented By The Secretary Of The Navy Droppable jet vane TVC
US4063685A (en) * 1976-07-30 1977-12-20 The United States Of America As Represented By The Secretary Of The Army Thrust vector control by circulation control over aerodynamic surfaces in a supersonic nozzle
GB2164612B (en) * 1979-09-10 1986-09-03 British Aerospace Vehicles fitted with thrust vector control systems
US4364530A (en) * 1980-09-08 1982-12-21 The United States Of America As Represented By The Secretary Of The Navy Propulsion/control modular booster
NZ198917A (en) * 1980-11-14 1985-01-31 Commw Of Australia Rocket controlled by spoiler tabs in exhaust
DE3138869C2 (de) * 1981-09-30 1984-07-12 Messerschmitt-Bölkow-Blohm GmbH, 8000 München "Lenkflugkörper"
US4561357A (en) * 1982-09-15 1985-12-31 General Dynamics Pomona Division Steering mechanism for an explosively fired projectile
US4844380A (en) * 1985-11-25 1989-07-04 Hughes Aircraft Company Detachable thrust vector mechanism for an aeronautical vehicle
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US4867393A (en) * 1988-08-17 1989-09-19 Morton Thiokol, Inc. Reduced fin span thrust vector controlled pulsed tactical missile
US5511745A (en) * 1994-12-30 1996-04-30 Thiokol Corporation Vectorable nozzle having jet vanes

Also Published As

Publication number Publication date
DE69611940T2 (de) 2001-06-13
EP0878688B1 (en) 2001-02-28
AU5224096A (en) 1996-12-05
NO962105L (no) 1996-11-27
NO962105D0 (no) 1996-05-23
CA2176048A1 (en) 1996-11-27
DE69611940D1 (de) 2001-04-05
NO309668B1 (no) 2001-03-05
AU686050B2 (en) 1998-01-29
IL118251A0 (en) 1996-09-12
US5806791A (en) 1998-09-15
EP0744591A3 (en) 1997-12-03
TR961035A2 (tr) 1996-12-21
IL118251A (en) 1998-04-05
CA2176048C (en) 2000-02-29
EP0878688A1 (en) 1998-11-18
EP0744591A2 (en) 1996-11-27

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