EP1600728A1 - Flugkörper zur Geländeaufklärung - Google Patents

Flugkörper zur Geländeaufklärung Download PDF

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Publication number
EP1600728A1
EP1600728A1 EP05291021A EP05291021A EP1600728A1 EP 1600728 A1 EP1600728 A1 EP 1600728A1 EP 05291021 A EP05291021 A EP 05291021A EP 05291021 A EP05291021 A EP 05291021A EP 1600728 A1 EP1600728 A1 EP 1600728A1
Authority
EP
European Patent Office
Prior art keywords
flying machine
propellant
machine according
flying
displacement
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.)
Granted
Application number
EP05291021A
Other languages
English (en)
French (fr)
Other versions
EP1600728B1 (de
Inventor
Bernard Teneze
Michel Blin
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.)
MBDA France SAS
Original Assignee
MBDA France SAS
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 MBDA France SAS filed Critical MBDA France SAS
Publication of EP1600728A1 publication Critical patent/EP1600728A1/de
Application granted granted Critical
Publication of EP1600728B1 publication Critical patent/EP1600728B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/365—Projectiles transmitting information to a remote location using optical or electronic means
    • 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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • 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

Definitions

  • the present invention relates to a flying machine for observation ground, which can be used for the attack of terrestrial targets, in particular masked by an obstacle.
  • the present invention aims to overcome these disadvantages.
  • the lift and displacement, on the one hand, and attitude, on the other hand are ordered by two separate thrusters dedicated solely to their respective function, which allows a great precision in the follow-up of the trajectory of the flying machine and in the vertical presentation of it in relation to the ground, making it less vulnerable to terrestrial anti-aircraft defenses an enemy and allows him to observe, carefully and slowly, any suspicious of the ground, for example hidden behind an obstacle.
  • said lift and displacement propellant has a larger mass than said attitude propellant and is closer to the center of gravity of the flying machine than the latter.
  • Said attitude thruster may be disposed at the rear of said elongated body, while said levitation and displacement propellant is disposed just in front of the center of gravity of the said flying machine.
  • the flying machine according to the invention is launched, so known for some attack missiles, by a launching station and control comprising a propulsion or ejection system which is clean and not worn by said flying machine. So, we can remove of said flying machine according to the invention the rear thruster generally charged with launching and having, in place of the said stern thruster, the said means of shooting.
  • said flying machine After its launch, said flying machine can fly autonomously, for example to achieve a pre-established flight plan.
  • the machine steering wheel according to the present invention may comprise means link with said launch and control station. So, he can possibly receive information from said station or have it carried out calculations by the latter, which lighten said flying machine.
  • said connecting means comprise, in known manner, the less an optical fiber, unwindable from said flying machine. Thus, information circulating between the spacecraft and the said post may not be blurred.
  • the flying machine according to the invention may comprise means of additional shots arranged at the front of the elongated body.
  • the flying machine complies the present invention carries a military load and includes propulsion means and guide means enabling it to attack, preferably without turning over, that is to say by its rear part, a target detected by said rear-view means.
  • the attack of said target can be commanded, either from the launch station and command to which the images of the target are transmitted by said means of connection, either automatically by a recognition device target carried by said flying machine.
  • Said propulsion means and said guide means of said gear towards the detected target may be independent of the said thrust propeller and displacement and said attitude thruster.
  • said propulsion means and said guide means said craft towards the target may be constituted by a additional thruster disposed forward of said elongated body.
  • additional propellant may be of the propellant fuel type, possibly provided with a steerable nozzle. It is better that said additional thruster is deposited behind a releasable cap said flying machine.
  • said propulsion means and said means for guiding said machine towards the target detected are respectively formed by said levitation and displacement propellant and by said attitude thrusters, associated respectively with thirds and with fourth nozzles, directed forward of said elongated body and distributed laterally around it.
  • Said first and second nozzles may be orientable and form said third and fourth nozzles when facing forward of said elongate body.
  • said third and fourth nozzles may be stationary and powered in propellant gas by said propellant of levitation and displacement and by said attitude thruster, by means of switching power supply arranged at the respective outputs of said thruster of levitation and displacement and said attitude booster and to feed either said first and second nozzles, or said third and fourth nozzles.
  • FIGS 1 to 4 schematically show four modes of embodiment of the flying machine according to the present invention.
  • FIGS 5 and 6 schematically illustrate two examples of flight of said flying craft.
  • FIGS 1 to 4 schematically show four embodiments I to IV of the flying vehicle 1 according to the present invention.
  • the thrusters 3 and 5 are arranged on either side of the center CG gravity of the flying machine and the thruster 3 is heavier than the thruster 5 and closer to the CG center of gravity than the latter.
  • the combustion of the propellant fuel charges of these propellants is set so that, when the thrusters 3 and 5 are in operation, the position of the center of gravity CG remains at least substantially fixed.
  • the nozzles 4 and 6 are orientable, as illustrated by the arrows, and can take positions 7 and 8 respectively directed forward 2A of the elongated body 2, as shown in dotted lines.
  • the lift propellant and displacement 3 comprises, in addition to the nozzles 4, nozzles fixed 9, equidistributed laterally around said elongated body 2 and directed forward 2A of it.
  • the thruster of levitation and displacement 3 can supply combustion gases, either the nozzles 4 or the nozzles 9.
  • the attitude booster 5 comprises, in addition to the nozzles 6, fixed nozzles 10, equally distributed laterally around the body lying 2 and directed forward 2A thereof. Through means of controllable switching known, the attitude booster 5 can feed in combustion gas, either the nozzles 6 or the fixed nozzles 10.
  • the flying machine 1 comprises an additional thruster 11, for example of the type to load propellant fuel, arranged at the front 2A of the elongated body 2, by example behind a releasable cap 12 of the latter.
  • the additional thruster 11 is provided with an axial nozzle 13, preferably orientable, directed towards the front 2A of the elongate body 2.
  • the flying machine 1 comprises, at the rear 2R of the elongated body 2, a camera 14 protected by a cap 15, transparent to the radiation to which the camera 14 is sensitive.
  • all these examples of embodiments I to IV include, known way for missiles, a military charge, an electronic system flight control device (not shown) and a rewinding reserve (no shown) of an optical fiber 16.
  • the flying machine comprises an additional camera 17 the front 2A of the elongated body 2.
  • the flying machine 1 whatever its embodiment I to IV, is able to be launched by a launch and control post 18, which is provided with a propulsion system of said flying machine 1 remaining in its launch tube 19, after launch.
  • the flying machine 1 is connected auditing launch and control station 18 through the fiber optical 16 of the reelable reserve. With such an optical fiber 16, the flying machine 1 and the post 18 can exchange information, making the possibly unnecessary the presence of a calculator on board the craft flying 1.
  • the flying machine 1 After launching by the post 18, the flying machine 1 lights its thrusters 3 and 5 that propel and fly through their nozzles 4 and 6 and make him take a vertical position, with the rear 2R and so his camera 14 In the upright position, the flying machine 1 can move laterally, being stabilized in attitude and roll, so that his camera 14 observes the ground beneath it.
  • the flying machine 1 can be propelled and directed on this target 21, by the rear 2R of the elongate body 2, or by the nozzles 4 and 6 in positions 7 and 8 (embodiment examples I and IV), or by the nozzles 9 and 10 (embodiment II), or else by the thruster additional 11 and the nozzle 13 (example III).
  • a process of recognition and attack which corresponds more particularly to a shot of bell-destruction of a masked target whose existence was likely, is shown in Figure 5.
  • the flying machine 1 must search in marauding a target 21 to attack, it is advantageous that, above of empty target lands, thrusters 3 and 5 roll over the flying machine 1 in a horizontal position and propel it in this position up to a reverse position in a vertical observation position to examine an area likely to have a target 22. In this phase of horizontal flight, the additional camera 17 is particularly useful.
  • the present invention is particularly useful for successively observing terrain zones masked at the firing point by obstacles 22, 23 and likely to contain targets 21 to be destroyed.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Geophysics And Detection Of Objects (AREA)
  • Investigating, Analyzing Materials By Fluorescence Or Luminescence (AREA)
  • Analysing Materials By The Use Of Radiation (AREA)
  • Earth Drilling (AREA)
  • Jib Cranes (AREA)
EP05291021A 2004-05-27 2005-05-12 Flugkörper zur Geländeaufklärung Expired - Lifetime EP1600728B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0405719 2004-05-27
FR0405719A FR2870932B1 (fr) 2004-05-27 2004-05-27 Engin volant pour l'observation du sol

Publications (2)

Publication Number Publication Date
EP1600728A1 true EP1600728A1 (de) 2005-11-30
EP1600728B1 EP1600728B1 (de) 2006-11-02

Family

ID=34942274

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05291021A Expired - Lifetime EP1600728B1 (de) 2004-05-27 2005-05-12 Flugkörper zur Geländeaufklärung

Country Status (13)

Country Link
US (1) US7763834B2 (de)
EP (1) EP1600728B1 (de)
JP (1) JP4823219B2 (de)
KR (1) KR101287920B1 (de)
CN (1) CN100467999C (de)
AT (1) ATE344434T1 (de)
DE (1) DE602005000222T2 (de)
ES (1) ES2274506T3 (de)
FR (1) FR2870932B1 (de)
IL (1) IL176804A (de)
NO (1) NO333969B1 (de)
WO (1) WO2006000662A1 (de)
ZA (1) ZA200607459B (de)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007021112B3 (de) * 2007-05-05 2008-07-31 Lfk-Lenkflugkörpersysteme Gmbh Verfahren zur Vergrößerung des Aufklärungsradius eines Kampfhubschraubers, sowie Aufklärungsflugkörper und Kampfhubschrauber zur Durchführung des Verfahrens
JP5279523B2 (ja) * 2009-01-22 2013-09-04 三菱電機株式会社 姿勢計算装置及び誘導装置及び姿勢計算装置の姿勢計算方法及び姿勢計算装置の姿勢計算プログラム
US8878110B2 (en) * 2010-12-14 2014-11-04 Raytheon Company Projectile that includes propulsion system and launch motor on opposing sides of payload and method
FR2970702B1 (fr) * 2011-01-26 2013-05-10 Astrium Sas Procede et systeme de pilotage d'un engin volant a propulseur arriere
KR101917785B1 (ko) * 2016-10-26 2019-01-29 한국항공우주연구원 관측용 무동력형 비행 유닛
CN109141144B (zh) * 2018-09-29 2024-02-09 中国空空导弹研究院 一种红外制导导弹破碎型抛离罩
CN113776386B (zh) * 2020-06-10 2023-05-09 北京机械设备研究所 舰载垂直发射载荷的近距投放方法
CN116198734A (zh) * 2022-12-30 2023-06-02 西安航天动力技术研究所 一种导引头安装在飞行方向后方的空基拦截飞行器

Citations (4)

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GB1284487A (en) * 1970-02-24 1972-08-09 Mullard Ltd Improvements in or relating to scanning and imaging systems
US3979086A (en) * 1974-11-08 1976-09-07 The United States Of America As Represented By The Secretary Of The Army Rocketed data communication system
DE3313648A1 (de) * 1983-04-15 1984-10-18 Diehl GmbH & Co, 8500 Nürnberg Verfahren zur echtzeit-gelaendeaufklaerung mittels eines sensors und einrichtung zum ausueben des verfahrens
FR2558585A1 (fr) * 1984-01-19 1985-07-26 Stauff Emile Sous-munitions largables pour projectile, notamment antichar

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GB751840A (en) 1951-07-06 1956-07-04 Armstrong Whitworth Co Eng Improvements relating to self-projected missiles
US3185096A (en) * 1959-08-31 1965-05-25 Roland G Dandelin Thrust reversal unit for rocket motor
FR1288750A (fr) * 1960-12-14 1962-03-30 Snecma Plate-forme sustentée par réaction, à poussée tarée, utilisée notamment au déminage
US3233548A (en) * 1963-11-12 1966-02-08 Canrad Prec Ind Inc Dirigible aerial torpedo
US3806064A (en) * 1968-10-03 1974-04-23 A Parilla Missile configurations, controls and utilization techniques
NZ198917A (en) * 1980-11-14 1985-01-31 Commw Of Australia Rocket controlled by spoiler tabs in exhaust
USH236H (en) * 1986-07-14 1987-03-03 The United States Of America As Represented By The Secretary Of The Army Asymmetric side-exhausting nozzles
US4777861A (en) * 1987-01-16 1988-10-18 Recon/Optical, Inc. Missile aiming sight
JP2588739B2 (ja) * 1988-02-23 1997-03-12 防衛庁技術研究本部長 ロケットの飛翔方向制御装置
US4913379A (en) * 1988-02-23 1990-04-03 Japan as represented by Director General, Technical Research and Development Institute, Japan Defence Agency Rocket flight direction control system
JPH0331698A (ja) * 1989-06-28 1991-02-12 Boeing Co:The 光ファイバ誘導弾装置
DE4132233C2 (de) * 1990-11-22 2003-03-06 Rheinmetall W & M Gmbh Panzerabwehrraketensystem
FR2699610B1 (fr) * 1992-12-22 1995-02-10 Aerospatiale Dispositif d'actionnement d'un organe mécanique, notamment pour le pilotage en force d'un missile, et missile équipé dudit dispositif.
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JP3075343B2 (ja) * 1997-06-24 2000-08-14 防衛庁技術研究本部長 飛しょう体
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JP3291542B2 (ja) * 1999-07-08 2002-06-10 防衛庁技術研究本部長 並進・姿勢制御装置
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1284487A (en) * 1970-02-24 1972-08-09 Mullard Ltd Improvements in or relating to scanning and imaging systems
US3979086A (en) * 1974-11-08 1976-09-07 The United States Of America As Represented By The Secretary Of The Army Rocketed data communication system
DE3313648A1 (de) * 1983-04-15 1984-10-18 Diehl GmbH & Co, 8500 Nürnberg Verfahren zur echtzeit-gelaendeaufklaerung mittels eines sensors und einrichtung zum ausueben des verfahrens
FR2558585A1 (fr) * 1984-01-19 1985-07-26 Stauff Emile Sous-munitions largables pour projectile, notamment antichar

Also Published As

Publication number Publication date
ATE344434T1 (de) 2006-11-15
WO2006000662A1 (fr) 2006-01-05
EP1600728B1 (de) 2006-11-02
US7763834B2 (en) 2010-07-27
FR2870932A1 (fr) 2005-12-02
KR20070015371A (ko) 2007-02-02
FR2870932B1 (fr) 2006-08-11
DE602005000222D1 (de) 2006-12-14
NO333969B1 (no) 2013-11-04
CN100467999C (zh) 2009-03-11
KR101287920B1 (ko) 2013-07-18
IL176804A (en) 2011-02-28
JP2008500507A (ja) 2008-01-10
NO20065758L (no) 2006-12-13
JP4823219B2 (ja) 2011-11-24
ZA200607459B (en) 2007-12-27
IL176804A0 (en) 2006-10-31
US20080245256A1 (en) 2008-10-09
DE602005000222T2 (de) 2007-09-06
CN1961194A (zh) 2007-05-09
ES2274506T3 (es) 2007-05-16

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