ATE40467T1 - Verfahren zur endphasenlenkung und dieses verfahren verwendender lenkflugkoerper. - Google Patents

Verfahren zur endphasenlenkung und dieses verfahren verwendender lenkflugkoerper.

Info

Publication number
ATE40467T1
ATE40467T1 AT82402180T AT82402180T ATE40467T1 AT E40467 T1 ATE40467 T1 AT E40467T1 AT 82402180 T AT82402180 T AT 82402180T AT 82402180 T AT82402180 T AT 82402180T AT E40467 T1 ATE40467 T1 AT E40467T1
Authority
AT
Austria
Prior art keywords
missile
section
phase guidance
fins
trajectory
Prior art date
Application number
AT82402180T
Other languages
English (en)
Inventor
Pierre Metz
Original Assignee
Thomson Brandt Armements
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 Thomson Brandt Armements filed Critical Thomson Brandt Armements
Application granted granted Critical
Publication of ATE40467T1 publication Critical patent/ATE40467T1/de

Links

Classifications

    • 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
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/222—Homing guidance systems for spin-stabilized missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2233—Multimissile systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/006—Proximity fuzes; Fuzes for remote detonation for non-guided, spinning, braked or gravity-driven weapons, e.g. parachute-braked sub-munitions
AT82402180T 1981-12-09 1982-11-30 Verfahren zur endphasenlenkung und dieses verfahren verwendender lenkflugkoerper. ATE40467T1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8123025A FR2517818A1 (fr) 1981-12-09 1981-12-09 Methode de guidage terminal et missile guide operant selon cette methode
EP82402180A EP0081421B1 (de) 1981-12-09 1982-11-30 Verfahren zur Endphasenlenkung und dieses Verfahren verwendender Lenkflugkörper

Publications (1)

Publication Number Publication Date
ATE40467T1 true ATE40467T1 (de) 1989-02-15

Family

ID=9264837

Family Applications (1)

Application Number Title Priority Date Filing Date
AT82402180T ATE40467T1 (de) 1981-12-09 1982-11-30 Verfahren zur endphasenlenkung und dieses verfahren verwendender lenkflugkoerper.

Country Status (8)

Country Link
US (1) US4568040A (de)
EP (1) EP0081421B1 (de)
JP (1) JPS58127100A (de)
AT (1) ATE40467T1 (de)
CA (1) CA1209232A (de)
DE (1) DE3279397D1 (de)
FR (1) FR2517818A1 (de)
IL (1) IL67424A (de)

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RU2533660C2 (ru) * 2012-09-27 2014-11-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Самарский государственный технический университет" Способ и устройство автономной радиолокационной самокоррекции промаха при встрече малоразмерного летательного аппарата с объектом на заключительном участке траектории полета
CN103307938B (zh) * 2013-04-23 2015-06-03 北京电子工程总体研究所 一种旋转弹气动参数获取方法
RU2590760C2 (ru) * 2014-07-29 2016-07-10 Николай Евгеньевич Староверов Ракета и способ её работы
CN105043171B (zh) * 2015-06-30 2017-08-29 北京航天长征飞行器研究所 一种带倾角约束的火箭弹纵向导引方法
RU2644962C2 (ru) * 2016-07-07 2018-02-15 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Способ поражения цели сверхзвуковой крылатой ракетой и сверхзвуковая крылатая ракета для его осуществления
SE541615C2 (sv) * 2017-04-28 2019-11-12 Bae Systems Bofors Ab Projektil med valbar anfallsvinkel
RU2701671C1 (ru) * 2018-04-09 2019-09-30 Анатолий Борисович Атнашев Способ наведения ракеты
CN109737812B (zh) * 2018-12-27 2021-10-15 北京航天飞腾装备技术有限责任公司 空对地制导武器侧向攻击方法和装置
RU2718560C1 (ru) * 2019-07-16 2020-04-08 Акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" Способ обнаружения и поражения воздушной цели ракетным комплексом
US11280591B2 (en) * 2019-09-03 2022-03-22 Harkind Dynamics, LLC Intelligent munition
CN114812293B (zh) * 2021-01-27 2023-03-24 北京理工大学 一种末端减速机动控制方法
CN114034215B (zh) * 2021-11-23 2023-02-28 航天科工火箭技术有限公司 一种火箭的导引方法和装置

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Also Published As

Publication number Publication date
CA1209232A (en) 1986-08-05
EP0081421B1 (de) 1989-01-25
FR2517818A1 (fr) 1983-06-10
FR2517818B1 (de) 1985-02-22
JPH0449040B2 (de) 1992-08-10
JPS58127100A (ja) 1983-07-28
DE3279397D1 (en) 1989-03-02
US4568040A (en) 1986-02-04
EP0081421A1 (de) 1983-06-15
IL67424A (en) 1989-03-31

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Legal Events

Date Code Title Description
UEP Publication of translation of european patent specification
REN Ceased due to non-payment of the annual fee