EP0077273B1 - Système de conduite de tir pour une arme à tir tendu montée sur un aéronef à voilure tournante - Google Patents

Système de conduite de tir pour une arme à tir tendu montée sur un aéronef à voilure tournante Download PDF

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Publication number
EP0077273B1
EP0077273B1 EP82401872A EP82401872A EP0077273B1 EP 0077273 B1 EP0077273 B1 EP 0077273B1 EP 82401872 A EP82401872 A EP 82401872A EP 82401872 A EP82401872 A EP 82401872A EP 0077273 B1 EP0077273 B1 EP 0077273B1
Authority
EP
European Patent Office
Prior art keywords
target
aircraft
pilot
weapon
helicopter
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
Application number
EP82401872A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0077273A1 (fr
Inventor
Alain Michel Brunello
Guy Gabriel Catani
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.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
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Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0077273A1 publication Critical patent/EP0077273A1/fr
Application granted granted Critical
Publication of EP0077273B1 publication Critical patent/EP0077273B1/fr
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G5/00—Elevating or traversing control systems for guns
    • F41G5/14—Elevating or traversing control systems for guns for vehicle-borne guns
    • F41G5/18—Tracking systems for guns on aircraft

Definitions

  • the present invention relates to a fire control system for a straight-fire weapon, in particular a cannon, mounted on a rotary wing aircraft, such as a helicopter.
  • patent US Pat. No. 2,724,998 describes a fire control system for a tensioned weapon mounted on an airplane, capable of being actuated by the pilot himself, and comprising an electromechanical calculation device, said weapon being rotatably mounted around two transverse axes, by means of motor means controlled by said calculating device, of the type comprising a sighting system on which a target and a reticle are likely to appear simultaneously, said reticle being able to be moved over said sighting system by a pilot command, as well as means for determining the coordinates of the position of said reticle with respect to an axis system linked to the aircraft and transmitting them to said electromechanical calculation device at least when on said system of aiming said reticle is brought into superposition on said target.
  • the subject of the present invention is a fire control system for a tight-shot weapon mounted on a rotary wing aircraft capable of being actuated by the pilot himself and allowing total decoupling between the aiming carried out by the pilot and the corrections shooting.
  • the firing control system for a tensioned weapon mounted on a rotary wing aircraft capable of being actuated by the pilot himself, and comprising a calculation device, said weapon being rotatably mounted around two transverse axes by means of motor means controlled by said calculating device, of the type comprising a sighting system on which a target and a marker may appear simultaneously, said marker being able to be moved on said tracking system aiming by a pilot command, as well as means for determining the coordinates of the position of said reference point with respect to an axis system linked to the aircraft and transmitting them to said calculation device at least when on said aiming system said reference point is superimposed on said target, is characterized in that said calculation device is an electronic calculator and in that said aiming system is of the semi-transparent mirror type allowing nt appear by transparency the target and forming the image of a light symbol generated by an electro-optical device, said image constituting the reference, while said electro-optical device forms said means for determining the coordinates of
  • the pilot after having detected a target can orient the axis of his aircraft towards it, thanks to the flight controls, until the alignment is roughly achieved and the target appears in the field of the mirror. of sight. Then, continuing to drive to maintain and if possible perfect this alignment, by means of a control member, it makes the reference mark coincide with the target on the aiming system.
  • the system according to the invention comprises means for indicating to the calculator the distance separating the aircraft from the target.
  • These means can be display means controlled by the pilot or be constituted by a telemetric system.
  • the calculator receives the coordinates of the sighting frame, that is to say those of the target, when the coincidence is obtained by the pilot. It also receives information concerning the distance separating the aircraft from the target. Furthermore, the calculator receives gyrometers, gyroscopes and / or on-board anemometric sensors, information concerning the attitude and the variations in attitude of the aircraft, as well as its relative speed with respect to the ambient air. All of this data is used to predict the movement of the target and determine the orientation to give to the weapon.
  • the calculator is programmed to take into account the movement of the target. If accelerations are involved, it is necessary to measure the distance between the target and the aircraft, not just to estimate it.
  • the calculator assumes, in its calculations, that the target follows a rectilinear trajectory at constant speed during the flight time of the projectile fired by the weapon or a trajectory at constant acceleration and determines the position to give to the line of sight of the weapon in a reference linked to the helicopter so that the trajectories of the target and the projectile intersect at the same instant.
  • the movement of the symbol is controlled in bearing by means of a two-axis gyroscope which is left free in elevation.
  • the movement of the symbol is controlled by means of a two-axis gyroscope so that, in the absence of control on the part of the pilot, the gyroscope is slaved to keep a fixed direction relative to the helicopter.
  • the system according to the invention is intended to conduct the firing of a gun 1 mounted on a helicopter (not shown) with a longitudinal axis L-L '.
  • the barrel 1 for example integral with a turret (not shown), can rotate around a bearing axis ZZ 'and an elevation axis YY' under the action of motors or jacks 2 and 3, respectively .
  • This system comprises a clear sight 4, of the semi-transparent mirror type, through which the pilot whose only eye 5 is represented in FIG. 1, can see a target 6, for example an enemy helicopter.
  • the center of the viewfinder 4 passes for example by the axis LL 'of the helicopter provided with the system according to the invention or occupies a fixed position determined relative to it and the plane of said viewfinder is inclined at 45 ° relative to said axis L-L '.
  • an electro-optical device 7, on which a symbol 8 appears Under the viewfinder 4 is provided an electro-optical device 7, on which a symbol 8 appears, the arrangement being such that the pilot can see simultaneously on the viewfinder 4 the target 6 and the image 8 'of the symbol 8.
  • the position of the symbol 8 on the screen 7 (and therefore that of the image 8 'on the viewfinder 4) can be adjusted according to two perpendicular axes yy' and zz 'one of which is for example in the vertical plane passing through l 'axis L-L', by action on a control button 9, available to the pilot and for example mounted on the handle 10 of cyclic control.
  • Two reference axes for example engraved on the viewfinder 4 and carrying respectively the marks y 1 -y ' 1 and z l - z' , allow the pilot to align with the axis LL 'when it makes optically coincide the image of the axes yy 'and zz' on the viewfinder 4 with said reference axes.
  • a control button 11 for displaying the value at which said pilot estimates the distance separating him from the target 6, when the system does not include any rangefinder performing this measurement automatically.
  • the system according to the invention finally comprises a microcomputer 13 in connection with the electro-optical device 7, the distance display device 12, the on-board gyrometers 14, the gyroscopes. on board 15 and an anemometric sensor 16, from which it receives information, as well as with motors 2 and 3, to which it addresses orders.
  • the fire control system makes it possible, on the one hand, to facilitate the aiming of the target 6 by the pilot, and on the other hand to decouple the shooting corrections from the aiming.
  • the pilot When it has detected a target 6, the pilot orients the axis L-L 'of its aircraft, using its flight controls, until the target 6 is in the field of its clear sight 4.
  • this direction of sight coincides with the longitudinal axis of the helicopter.
  • the pilot by means of the control button 9 placed on its cyclic stick 10 will make the image 8' of the symbol 8 and the target 6 coincide.
  • the pilot's job is then to pursue the target 6 with the symbol 8 throughout the aiming phase of the weapon and the shooting, so as to constantly maintain the coordinates C b , E b of the target respectively equal to the coordinates C a , E has image 8 '(see FIG. 2).
  • the control button 9 is a button with “two axes (site and deposit) making it possible to move the image of the symbol on the viewfinder. If the pilot exerts a force on the control button 9, the symbol 8 moves in the corresponding direction. In the absence of action on the button 9, the image of the symbol 8 keeps a fixed position on the clear viewfinder 4 and therefore indicates a fixed direction in a frame linked to the helicopter.
  • the pilot has two means for refining and continuing the aiming, namely his flight controls and the control button 9. He uses this last button, in particular in the case where the aiming at the flight controls would bring him towards areas of dangerous theft.
  • the calculator processes this information and deduces the score to be given to cannon 1 so that the shell reaches the target 6.
  • a simple assumption taken into account in the calculator 13 program to calculate the score for weapon 1 is that target 6 moves in a straight line and at uniform speed during the time of the shell's journey. If the helicopter is equipped with a rangefinder, a hypothesis on the acceleration of the target can be taken into account.
  • the instructions from the calculator 13 give the site sc and the gc deposit to be given to the gun and are sent to the rotation servos 2 and 3 of the latter.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP82401872A 1981-10-14 1982-10-12 Système de conduite de tir pour une arme à tir tendu montée sur un aéronef à voilure tournante Expired EP0077273B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8119344 1981-10-14
FR8119344A FR2514487A1 (fr) 1981-10-14 1981-10-14 Systeme de conduite de tir pour une arme de tir tendu montee sur un aeronef a voilure tournante

Publications (2)

Publication Number Publication Date
EP0077273A1 EP0077273A1 (fr) 1983-04-20
EP0077273B1 true EP0077273B1 (fr) 1986-12-30

Family

ID=9263043

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82401872A Expired EP0077273B1 (fr) 1981-10-14 1982-10-12 Système de conduite de tir pour une arme à tir tendu montée sur un aéronef à voilure tournante

Country Status (5)

Country Link
US (1) US4528891A (enrdf_load_stackoverflow)
EP (1) EP0077273B1 (enrdf_load_stackoverflow)
JP (1) JPS5878099A (enrdf_load_stackoverflow)
DE (1) DE3274902D1 (enrdf_load_stackoverflow)
FR (1) FR2514487A1 (enrdf_load_stackoverflow)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2143948B (en) * 1983-07-23 1986-08-06 Ferranti Plc Apparatus for determining the direction of a line of sight
IL76817A (en) * 1984-11-20 1991-06-10 Hughes Aircraft Co Indicating display of target deviations
US5129309A (en) * 1990-09-17 1992-07-14 Recon/Optical, Inc. Electro-optic targeting system
US5310136A (en) * 1992-05-19 1994-05-10 United Technologies Corporation Helicopter integrated fire and flight control having constraint limiting control
US5263662A (en) * 1992-05-19 1993-11-23 United Technologies Corporation Helicopter integrated fire and flight control system having turn coordination control
US5585813A (en) * 1992-10-05 1996-12-17 Rockwell International Corporation All aspect head aiming display
US5310135A (en) * 1992-10-28 1994-05-10 United Technologies Corporation Helicopter integrated fire and flight control having coordinated area bombing control
DE19716227C2 (de) * 1997-04-18 2000-10-05 Rheinmetall W & M Gmbh Waffensystem mit einer einen Mikrocontroller enthaltenden Munitionseinheit
US5949015A (en) * 1997-05-14 1999-09-07 Kollmorgen Corporation Weapon control system having weapon stabilization
AU730249B2 (en) * 1997-07-16 2001-03-01 Kollmorgen Corporation Weapon control system having weapon stabilization
SE519151E5 (sv) 2001-11-19 2013-07-30 Bae Systems Bofors Ab Vapensikte med siktessensorer avsett för fordon, fartyg eller motsvarande
US6769347B1 (en) * 2002-11-26 2004-08-03 Recon/Optical, Inc. Dual elevation weapon station and method of use
EP2742309B8 (en) * 2011-08-09 2017-01-18 Raytheon Company Weapon posturing system and methods of use
CN112158356B (zh) * 2020-08-28 2022-01-25 成都飞机工业（集团）有限责任公司 一种应用于机载航炮地面热校靶的飞机姿态调整方法
CN114910919B (zh) * 2022-04-20 2023-05-26 亿慧云智能科技（深圳）股份有限公司 一种微光夜视仪的使用及目标定位方法和装置

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US2724998A (en) * 1943-07-20 1955-11-29 Sperry Rand Corp Positional control apparatus
US2455963A (en) * 1945-11-08 1948-12-14 Wheeler Phillp Roed Electrical gun sight control
US3383987A (en) * 1967-03-27 1968-05-21 Army Usa Multiple-scale reticle for a fire control system with means for adjusting the servosystem to a selected one of the scales
US3641261A (en) * 1969-06-04 1972-02-08 Hughes Aircraft Co Night vision system
US3828122A (en) * 1970-09-29 1974-08-06 Bendix Corp Tv area correlation tracker
DE2411790C3 (de) * 1974-03-12 1978-06-29 Precitronic Gesellschaft Fuer Feinmechanik Und Electronic Mbh, 2000 Hamburg Verfahren und Waffensystem zur Bekämpfung von Oberflächenzielen
US4020324A (en) * 1974-08-26 1977-04-26 Lear Siegler, Inc. Weapon delivery system
US4012989A (en) * 1975-04-21 1977-03-22 Summa Corporation Inertial free-sight system
US4146780A (en) * 1976-12-17 1979-03-27 Ares, Inc. Antiaircraft weapons system fire control apparatus
JPS5442899A (en) * 1977-09-09 1979-04-05 Mitsubishi Electric Corp Automatic expectation angle set device
SE441033B (sv) * 1978-11-02 1985-09-02 Barr & Stroud Ltd Eldledningsanordning for en kanon
US4312262A (en) * 1979-02-22 1982-01-26 General Electric Company Relative velocity gunsight system and method
FR2472735B1 (fr) * 1979-12-26 1985-08-16 Sagem Perfectionnements aux dispositifs de visee pour vehicules
FR2480424B1 (fr) * 1980-04-11 1987-07-10 Sfim Systeme de conduite automatique de tir air-air ou air-sol

Also Published As

Publication number Publication date
FR2514487A1 (fr) 1983-04-15
FR2514487B1 (enrdf_load_stackoverflow) 1984-12-14
US4528891A (en) 1985-07-16
DE3274902D1 (en) 1987-02-05
JPS5878099A (ja) 1983-05-11
JPH0319480B2 (enrdf_load_stackoverflow) 1991-03-15
EP0077273A1 (fr) 1983-04-20

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