EP1600728A1 - Engin volant pour l'observation du sol - Google Patents
Engin volant pour l'observation du sol Download PDFInfo
- 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
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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
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- 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
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- 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
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- 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)
- Jib Cranes (AREA)
- Investigating, Analyzing Materials By Fluorescence Or Luminescence (AREA)
- Analysing Materials By The Use Of Radiation (AREA)
- Earth Drilling (AREA)
Abstract
Description
- en ce qu'il comporte :
- un propulseur de sustentation et de déplacement, du type à charge propulsive combustible, associé à des premières tuyères d'échappement, dirigées vers l'arrière dudit corps allongé et réparties latéralement autour de celui-ci, engendrant des forces de manoeuvre latérales dont les lignes d'action passent par le centre de gravité dudit engin volant, lesdites forces étant aptes à assurer la sustentation et les déplacements dudit engin volant dans une position d'observation pour laquelle celui-ci est au moins approximativement vertical avec l'extrémité arrière dudit engin volant dirigée vers le bas ;
- un propulseur d'attitude, du type à charge propulsive combustible, associé à des deuxièmes tuyères d'échappement, dirigées du côté arrière dudit corps allongé et réparties latéralement autour de celui-ci, engendrant des forces de manoeuvre latérales aptes à maintenir ledit engin volant dans ladite position d'observation au moins approximativement verticale ; et
- des moyens de prise de vues, disposés à l'arrière dudit corps allongé et aptes à observer ledit sol lorsque ledit engin volant est dans ladite position d'observation au moins approximativement verticale ; et
- en ce que ledit propulseur de sustentation et de déplacement et ledit propulseur d'attitude sont disposés de part et d'autre dudit centre de gravité de l'engin volant et en ce que, lors de la combustion des charges propulsives respectives de ces deux derniers propulseurs, la position dudit centre de gravité reste au moins approximativement fixe.
- un propulseur de sustentation et de déplacement 3, du type à charge propulsive combustible, comportant des tuyères d'échappement 4 pour les gaz de combustion, par exemple au nombre de 4, équiréparties latéralement autour dudit corps allongé 2 et dirigées vers l'arrière 2R de celui-ci. Les axes des tuyères 4 passent par le centre de gravité CG dudit engin volant 1, de sorte que le propulseur 3 engendre des forces de manoeuvre latérales dont les lignes d'action passent également par ledit centre de gravité. Ces forces de manoeuvre sont commandables, de façon connue, par exemple par des déviateurs de jet mobiles, pouvant prendre au moins deux positions, de préférence trois, aptes à obturer au moins partiellement ou à dégager complètement lesdites tuyères 4. Ainsi, comme cela est connu pour certains missiles, ledit engin volant 1 est pilotable "en force" par le propulseur 3 ; et
- un propulseur d'attitude 5, également du type à charge propulsive combustible, comportant des tuyères d'échappement 6 pour les gaz de combustion, distantes du centre de gravité CG et étant par exemple également au nombre de 4, équiréparties latéralement autour dudit corps allongé 2 et dirigées vers l'arrière 2R de celui-ci. Le propulseur d'attitude 5 engendre donc des forces de manoeuvre latérales commandables, de façon connue, par exemple par des déviateurs de jets mobiles, également à au moins deux positions, de préférence trois, aptes à obturer au moins partiellement ou à dégager complètement lesdites tuyères 6. Les tuyères 6 étant distantes du centre de gravité CG, le propulseur d'attitutde 5 exerce un pilotage "en couple" sur l'engin volant 1.
Claims (15)
- Engin volant pour l'observation du sol, comportant un corps allongé (2),
caractérisé :en ce qu'il comporte :un propulseur de sustentation et de déplacement (3), du type à charge propulsive combustible, associé à des premières tuyères d'échappement (4), dirigées vers l'arrière (2R) dudit corps allongé et réparties latéralement autour de celui-ci, engendrant des forces de manoeuvre latérales dont les lignes d'action passent par le centre de gravité (CG) dudit engin volant, lesdites forces étant aptes à assurer la sustentation et les déplacements dudit engin volant dans une position d'observation pour laquelle celui-ci est au moins approximativement vertical avec l'extrémité arrière dudit engin volant dirigée vers le bas ;un propulseur d'attitude (5), du type à charge propulsive combustible, associé à des deuxièmes tuyères d'échappement (6), dirigées vers l'arrière (2R) dudit corps allongé et réparties latéralement autour de celui-ci, engendrant des forces de manoeuvre latérales aptes à maintenir ledit engin volant dans ladite position d'observation au moins approximativement verticale ; etdes moyens de prise de vues (14), disposés à l'arrière (2R) dudit corps allongé et aptes à observer ledit sol lorsque ledit engin volant est dans ladite position d'observation au moins approximativement verticale ; eten ce que ledit propulseur de sustentation et de déplacement (3) et ledit propulseur d'attitude (5) sont disposés de part et d'autre dudit centre de gravité (CG) de l'engin volant et en ce que, lors de la combustion des charges propulsives respectives de ces deux derniers propulseurs, la position dudit centre de gravité reste au moins approximativement fixe. - Engin volant selon la revendication 1,
caractérisé en ce que ledit propulseur de sustentation et de déplacement (3) présente une masse plus importante que ledit propulseur d'attitude (5) et est plus proche du centre de gravité (CG) de l'engin volant que ce dernier. - Engin volant selon l'une des revendications 1 ou 2,
caractérisé en ce que ledit propulseur d'attitude (5) est disposé à l'arrière dudit corps allongé, alors que ledit propulseur de sustentation et de déplacement est disposé juste en avant du centre de gravité (CG) dudit engin volant. - Engin volant selon l'une des revendications 1 à 3,
caractérisé en ce que l'orientation en roulis dudit engin volant est contrôlée par le propulseur de sustentation et de déplacement (3). - Engin volant selon l'une des revendications 1 à 4,
caractérisé en ce qu'il est lancé par un poste de lancement et de commande (18) comportant un système de propulsion ou d'éjection qui lui est propre et qui n'est pas porté par ledit engin volant. - Engin volant selon la revendication 5,
caractérisé en ce qu'il comporte des moyens de liaison (16) avec ledit poste de lancement et de commande (18). - Engin volant selon la revendication 6,
caractérisé en ce que lesdits moyens de liaison (16) comportent au moins une fibre optique. - Engin volant selon l'une des revendications 1 à 7,
caractérisé en ce qu'il comporte des moyens de prise de vues supplémentaires (17) disposés à l'avant dudit corps allongé. - Engin volant selon l'une quelconque des revendications 1 à 8,
caractérisé en ce qu'il porte une charge militaire et en ce qu'il comporte des moyens de propulsion et des moyens de guidage lui permettant d'attaquer, par la partie arrière (2R) dudit corps allongé, une cible (21) détectée pour lesdits moyens de prise de vues (14) disposés à l'arrière dudit corps allongé. - Engin volant selon la revendication 9,
caractérisé en ce que lesdits moyens de propulsion et lesdits moyens de guidage (11, 13) dudit engin en direction de ladite cible (21) sont indépendants dudit propulseur de sustentation et de déplacement (3) et dudit propulseur d'attitude (5). - Engin volant selon la revendication 10,
caractérisé en ce que lesdits moyens de propulsion et lesdits moyens de guidage dudit engin en direction de ladite cible sont constitués par un propulseur supplémentaire (11, 13) disposé à l'avant (2A) dudit corps allongé. - Engin volant selon la revendication 11,
caractérisé en ce que ledit propulseur supplémentaire (11, 13) est disposé derrière une coiffe largable (12). - Engin volant selon la revendication 9,
caractérisé en ce que lesdits moyens de propulsion et lesdits moyens de guidage dudit engin en direction de ladite cible (21) sont respectivement formés par ledit propulseur de sustentation et de déplacement (3) et par ledit propulseur d'attitude (5), associés respectivement à des troisièmes et à des quatrièmes tuyères, dirigées vers l'avant (2A) dudit corps allongé et réparties latéralement autour de celui-ci. - Engin volant selon la revendication 13,
caractérisé en ce que lesdites premières et deuxièmes tuyères (4, 6) sont orientables et forment lesdites troisièmes et quatrièmes tuyères (7, 8) lorsqu'elles sont orientées vers l'avant (2A) dudit corps allongé. - Engin volant selon la revendication 13,
caractérisé en ce que lesdites troisièmes et quatrièmes tuyères (9, 10) sont fixes et sont alimentées en gaz de combustion par ledit propulseur de sustentation et de déplacement (3) et par ledit propulseur d'attitude (5).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0405719A FR2870932B1 (fr) | 2004-05-27 | 2004-05-27 | Engin volant pour l'observation du sol |
FR0405719 | 2004-05-27 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1600728A1 true EP1600728A1 (fr) | 2005-11-30 |
EP1600728B1 EP1600728B1 (fr) | 2006-11-02 |
Family
ID=34942274
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05291021A Active EP1600728B1 (fr) | 2004-05-27 | 2005-05-12 | Engin volant pour l'observation du sol |
Country Status (13)
Country | Link |
---|---|
US (1) | US7763834B2 (fr) |
EP (1) | EP1600728B1 (fr) |
JP (1) | JP4823219B2 (fr) |
KR (1) | KR101287920B1 (fr) |
CN (1) | CN100467999C (fr) |
AT (1) | ATE344434T1 (fr) |
DE (1) | DE602005000222T2 (fr) |
ES (1) | ES2274506T3 (fr) |
FR (1) | FR2870932B1 (fr) |
IL (1) | IL176804A (fr) |
NO (1) | NO333969B1 (fr) |
WO (1) | WO2006000662A1 (fr) |
ZA (1) | ZA200607459B (fr) |
Families Citing this family (7)
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 |
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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 |
Family Cites Families (17)
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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 |
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. |
US5456425A (en) * | 1993-11-04 | 1995-10-10 | Aerojet General Corporation | Multiple pintle nozzle propulsion control system |
GB9501594D0 (en) * | 1995-01-27 | 1995-11-08 | British Aerospace | Tethered missile system |
JP3075343B2 (ja) * | 1997-06-24 | 2000-08-14 | 防衛庁技術研究本部長 | 飛しょう体 |
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 |
WO2001050135A2 (fr) * | 1999-12-30 | 2001-07-12 | Advanced Aerospace Technologies, Inc. | Amelioration de la survivabilite et de la flexibilite des missions d'avions de reconnaissance |
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2004
- 2004-05-27 FR FR0405719A patent/FR2870932B1/fr not_active Expired - Fee Related
-
2005
- 2005-05-12 US US10/586,599 patent/US7763834B2/en not_active Expired - Fee Related
- 2005-05-12 AT AT05291021T patent/ATE344434T1/de not_active IP Right Cessation
- 2005-05-12 EP EP05291021A patent/EP1600728B1/fr active Active
- 2005-05-12 CN CNB2005800171042A patent/CN100467999C/zh not_active Expired - Fee Related
- 2005-05-12 DE DE602005000222T patent/DE602005000222T2/de active Active
- 2005-05-12 KR KR1020067015989A patent/KR101287920B1/ko active IP Right Grant
- 2005-05-12 JP JP2007513993A patent/JP4823219B2/ja not_active Expired - Fee Related
- 2005-05-12 WO PCT/FR2005/001186 patent/WO2006000662A1/fr active Application Filing
- 2005-05-12 ES ES05291021T patent/ES2274506T3/es active Active
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2006
- 2006-07-12 IL IL176804A patent/IL176804A/en active IP Right Grant
- 2006-09-06 ZA ZA200607459A patent/ZA200607459B/en unknown
- 2006-12-13 NO NO20065758A patent/NO333969B1/no not_active IP Right Cessation
Patent Citations (4)
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 |
---|---|
NO333969B1 (no) | 2013-11-04 |
IL176804A0 (en) | 2006-10-31 |
EP1600728B1 (fr) | 2006-11-02 |
FR2870932A1 (fr) | 2005-12-02 |
WO2006000662A1 (fr) | 2006-01-05 |
US20080245256A1 (en) | 2008-10-09 |
KR101287920B1 (ko) | 2013-07-18 |
CN1961194A (zh) | 2007-05-09 |
IL176804A (en) | 2011-02-28 |
JP4823219B2 (ja) | 2011-11-24 |
US7763834B2 (en) | 2010-07-27 |
DE602005000222T2 (de) | 2007-09-06 |
FR2870932B1 (fr) | 2006-08-11 |
ES2274506T3 (es) | 2007-05-16 |
KR20070015371A (ko) | 2007-02-02 |
DE602005000222D1 (de) | 2006-12-14 |
ATE344434T1 (de) | 2006-11-15 |
NO20065758L (no) | 2006-12-13 |
CN100467999C (zh) | 2009-03-11 |
ZA200607459B (en) | 2007-12-27 |
JP2008500507A (ja) | 2008-01-10 |
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