US3522667A - Firing training simulators for remotely - controlled guided missiles - Google Patents

Firing training simulators for remotely - controlled guided missiles Download PDF

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Publication number
US3522667A
US3522667A US692354A US3522667DA US3522667A US 3522667 A US3522667 A US 3522667A US 692354 A US692354 A US 692354A US 3522667D A US3522667D A US 3522667DA US 3522667 A US3522667 A US 3522667A
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missile
firing
simulator
target
radiation
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US692354A
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Pierre De Guillenchmidt
Paul Gabriet
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/006—Guided missiles training or simulation devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/26—Teaching or practice apparatus for gun-aiming or gun-laying
    • F41G3/2616—Teaching or practice apparatus for gun-aiming or gun-laying using a light emitting device
    • F41G3/2622—Teaching or practice apparatus for gun-aiming or gun-laying using a light emitting device for simulating the firing of a gun or the trajectory of a projectile
    • F41G3/2644—Displaying the trajectory or the impact point of a simulated projectile in the gunner's sight

Definitions

  • FIG. 3 FIRING TRAINING SIMULATORS FOR REMOTELY-CONTROLLED GUIDED MISSILES Filed Dec. 21. 1967 FIG. 3
  • the combination with a simulator reproducing optically the apparent displacements of a guided missile through a landscape from a firing point towards a target.
  • the simulator comprises a sight and a semi-transparent mirror through which a firer may observe the landscape and the target.
  • a projecting system includes a source of light and is capable of superimposing on the landscape by reflection on said semi-transparent mirror a luminous virtual image representing @the guided missile.
  • Means are provided for convertintg the measured deviations to correction signals, and means for transmitting the correction signals to the virtual image in line of sight,
  • This invention relates to firing training simulators for remotely'controlled guided missiles and more particularly firing trainers for missiles guided by remotely-controlled guiding on the target.
  • Missiles remotely guided by aligning on the target are at present in most cases guided by a manual control means.
  • the control is made automatict The operator is no longer required to programme the guidance orders for the missile but still while concentrating on aiming at the target, has to watch events which may occur during firing in order to be able to intervene immediately.
  • the training and instruction of operators requires, as in the case of manually-guided missiles, the firing of a number of simulated shots in order to avoid the undue consumption of practice missiles.
  • the operator When firing under manual control, the operator must combine suitable directional and elevational orders for ensuring and maintaining the alignment of the missile on the target.
  • Simulator equipment for firing with manual guidance control comprises an optical system presenting the firer with a view of a light spot simulating the tracer on an actual mission (or any other representation thereof).
  • the fixed or moving target with possibly a landscape background is represented by a reproduction, a mock-up, or a light projection, presented to the view of the pilot with a superposed image of the spot to be guided.
  • a simulator also comprises electronic devices, in particular, for computing the motion (flight) data of the simulated missile, the servocontrols evaluating these data for the purpose of operating the optical guidance system of the missile image, programming the firing sequence, simulating the trajectory of the missile, and events during firing.
  • Such simulators are often equipped with a second optical outlet to be used by an observerhuman or robotsighting the same view as the firer, and controlling or recording the progress of the shoot.
  • the spot-emitting device When a simulator is installed in a mobile firing point the spot-emitting device should be stabilised with reference to the ground coordinates by means counteracting the real motions of the missile image caused by angular displacements of the optical part of the appliance during simulated firing,
  • a gyroscopic stabilising device is described in the French patent specification No. 1,489,865.
  • the firer aims at sighting device at the selected target, whether stationary or moving, and maintains the sighting line and the ideal firing axis passing through the target in line.
  • the sighting device is hinged on its support with two degrees of freedom, allowing the tracking of a moving target.
  • the sighting device is a usually magnifying optical system, having a grid or graticule defining the optical line of sight.
  • the line of sight may alternatively be defined by dilferent means such as the detection of electromagnetic radiations of any wavelength (e.g. ultraviolet rays, radio waves, visible light or infrared radiation) emitted by or reflected from the target, detection by radar, laser or maser beams, detection of the magnetic field of the target, or, finally, the detection of acoustic or ultrasonic waves.
  • electromagnetic radiations of any wavelength (e.g. ultraviolet rays, radio waves, visible light or infrared radiation) emitted by or reflected from the target, detection by radar, laser or maser beams, detection of the magnetic field of the target, or, finally, the detection of acoustic or ultrasonic waves.
  • the means of determining the line of sight are'combined with a viewing device furnishing the firer with the requisite reference points for bringing a reference axis of the sighting arrangement into coincidence with the ideal line of fire.
  • the missile is remotely-controlled by guidance signals generated by a servo-system which data are fed from an RDF.
  • the latter tracks the angular position of the missile, or, more particularly, the angular displacements between the firers line of sight and the position of the missile.
  • the guidance orders are computed in such manner that their action on the trajectory of the missile is to cancel the detected deflection. During the firing period, the missile is thus practically held, up to the instant of impact, on the line of sight, ending at the target.
  • the RDF instrument receives by known, optical or electronic means, the radiations emanating from the missile. These variations (deflections) may be emitted by a missile-linked device such as an emitter, a. tracking unit, an infrared source, or by reflection from the missile, such as radiations from. a radar, laser or maser source. In the general case, the firer controls the missile position with reference to the target visually, either directly or by means of an optical system.
  • a missile-linked device such as an emitter, a. tracking unit, an infrared source, or by reflection from the missile, such as radiations from. a radar, laser or maser source.
  • the firer controls the missile position with reference to the target visually, either directly or by means of an optical system.
  • the weapon. system i.e. the combination of sighting gear, radiation receivers, detectors, electronic firing control equipment or equipment for trajectory correction, whether manual or automatic, responding to signals from the detector, the missile remote controls and the auxiliaries, thus forms a complete servo-system with a feedback loop, controlling the positions of the missile on the line of sight.
  • the firer (gunner) must precisely align the sighting telescope on the target and follows the progress of'the operation. He must further be alert for incidents which may occur during firing. Atmospheric conditions, the tracking of a highly-mobile tagret, the maneuvering of the vehicle carrying the firing point, combat environment, enemy counter-action or other fortuitous events are capable of causing trouble, often transiently, during the course of firing.
  • the missile may move out of detection range, or even out of the field of view, visual observation may become impeded, or even impossible, in particular through fog, the detection and guidance signals of the missile may be blurred, or the missile, the sighting and/or detection means may become uncontrollable
  • the firer may be able to cope with a critical situation by taking immediate action, some of the appliances even allowing of overriding by manual control.
  • the object of the present invention is an improvement in simulators for manual guidance control allowing them to be used also for automatic control.
  • the present invention is a simulator for firing training with missiles guided by alignment on the target by automatic remote control comprising at least one optical sighting device presenting the tire with view of the image of a light. spot. simulating the tracer element of a missile superposed on. a target background, the said optical de vice being coupled with means for detecting the position or location of the said spot with reference to the line of sight of the said optical system and means for emitting the said spot and simulating its receding motion in accord ance with a preset programme controllable by signals originated in an automatic guidance device responding to data received. and transmitted by the said detecting means.
  • the optical system of such a simulator may include an optical outlet for the gunner with a further such output for observing and controlling the firing by the gunner.
  • the detector system may be incorporated. with the optical system, using the same input.
  • the spot emitter can be gyroscopically stabilised when mounted on a movable (travelling) base,
  • the guidance system may be controlled by a signal transducer linked with a remotecontrol system for missiles of a weapon system with a real (unsimulated) launcher of such missiles.
  • A. radiation source linked with the spot emitter one be used to simulate the detector emission after firing.
  • the spot emitter can be assimilated with the radiation source for the detector.
  • the invention likewise proposes in the capacity of novel industrial products apparatus for controlling weapon systems on real missile launchers, consisting of a simulator in accordance with the present invention comprising adapting means for elements or element assemblies of the guidance systems of such weapon systems.
  • a simulator according to this invention may be arranged to use, either the complete weapon system, or, for reasons of economy, a simplified or only partially simulated weapon system. It may comprise particular known devices already used in simulators for firing training with manual control of the missiles guided by aligning on the target such as means for visualising the simulated or real target and background environment or landscape, simulation of the missile, guidance of the simulated missile, and the different means used for such simulation, i.e. computers, servo-mechanisms for guiding the simulated missile, programming for simulating the missile course and firing events, fire control and stabilisation.
  • a simulator according to this invention must comprise a device simulating the radiation beam from a missile in actual firing, in order to allow the RDF unit to supply the data on the position of the missile.
  • a radiation source emitting radiation of the same kind as that to be detected in actual firing in the form of a beam, such beam being then guided by a servo system 10- cating it positionally in space.
  • Such a radiation source simulator may for particular purposes be linked or combined, at least partially, with the simulator device presenting the firer with the simulated view of a guided missile.
  • an equivalent system is used by which the motions of the simulated missile are detected in the simulator and sup ply the data for locating the missile.
  • a servo-control system for guidance control of the simulated missile evaluates the guidance orders transmitted from the weapon system to the missile in actual firing; in order to evaluate the guidance signals for the control system, to obtain from the simulated missile the same response as from a real missile.
  • the conditions of real. firing are thus simulated, both for the gunner and the automatic guidance system.
  • Con trol with a closed feedback loop, as used in real systems, is obtained in a simulator using the complete weapon system.
  • the optical head and spot emitter may be light and compact so as to be interchangeably connectable with the sighting and tracking means of the weapon system,
  • FIG. l is a diagrammatic view of the sighting and dc 5 tection arrangements of a simulator in accordance with the invention.
  • FIG, 2 is a similar view to FIG, 1 of a variant form of embodiment:
  • FIG, 3 is the diagram of a simulator according to the invention fitted with another variant of the sighting and detecting (tracking) means,
  • the spot projected by a light-source L is reflected in a semi-transparent mirror MS and passes through the telescope V to reach the gunner"s eye 0, while the target background or landscape P is observed directly through the semi-transparent mirror MS.
  • the sources L and R are, of course, guided to follow the motions of the simulated missile,
  • the sources L and R are combined but while the light beam L reaches the gunner's eye by reflection in the mirror MS, the radiation beams pass through that mirror and are reflected in the normal mirror to fall on the detector D,
  • the detector or track ing device D and the sighting device V have the same optical input.
  • the gunners eye 0 views the landscape (terrain) P directly through the semi-transparent mirror MS, by reflection in the mirror M 8 and reflection in thesemitransparent mirror M
  • the gunner simultaneously views the superposed image of the (light) spot coming from the source LR after reflection in a first optical reflecting device M stabilised by a gyroscopic element S, further reflection in the mirror M controlled by a guidance system P, another reflection in the semi-transparent mirrors M 3 and M 8
  • the radiations emitted by the source R are likewise reflected in M M and MS but pass through the semi'transparent mirror M 5 and reach the sensing elements of the detector D,
  • These sensing elements transmit their data to an automatic guidance device PA in a weapon system for firing real missiles.
  • the signals emitted by this automatic guidance device PA are transmitted to the spot-guidance system PB by a signal transducer TO,
  • the operation of firing by the gunner is controlled by a monitoring device the scanner whereof C scans the same images of the landscape and the light spot as are viewed by the gunner 0 directly through the semi-reflecting mirror M 8 and by reflection in the mirror M,
  • the missile is equipped at the rear with a luminous tracer, the light emitted by which is utilised by the optical part of the weapon system and the infra-red radiation by the detector of the radio direction finder,
  • the optical device of the weapon system consists of a monocular telescope which the gunner aims at the target, the optical axis being accurately set by appropriate crosshairs.
  • the RDF detector is incorporated in the telescope in such a manner as directly to detect the deviation of the missile position from the optical axis,
  • the radiation emitted by the missile enters the ap paratus described above in the form of a single beam, through a common intake.
  • a selector device inside the apparatus projects the beam in such a manner that the light rays enter the telescope while the infrared radiation passes to the detector of the radio direction finder.
  • the data supplied by the detector are evaluated by a servo-controlled electronic device which computes the guidance signals to be transmitted to the missile, in such a manner that this action on the trajectory of the latter tends to correct the detected deviation.
  • a remote control system transmits the results to the missile for the purpose of initiating the appropriate action of the control means,
  • the missile is practically servo-controlled to maintain its course, up to the instant of impact, along the optical axis of the (sighting) telescope,
  • the said scanning head comprises a radiation source of small dimensions, emitting visible light and infrared radiation, located in the focus of a concave mirror or a convergent lens, ilt further incorporates an arrangement of gyroscopically stabilised mirrors reflecting the collimated beam emitted by the source, in a direction linked with the terrestrial axis (ground coordinates).
  • the weapon comprises an arrangement of two mirrors in the form of an apidiascope, successively reflecting the beam into the common entry of the weapon system,
  • One of the mirrors has two angular degrees of freedom, and guides the beam, for which purpose it is actuated by a servo-mechanism controlled by an electronic device
  • the other, semi-reflecting mirror displays the (target) landscape in its transparent part and projects the target image into the telescope objective lens, It also reflects into the common entry of the light rays and the infrared radiation for which provision is made in the weapon system, a collimatd beam simulating the radiation emitted by the missile,
  • the optical device in the scanning head of the simulator by the nature of its radiation source, the quality of the glasses (lenses) through which the beam is projected, and the reflecting power of the mirrors, en-
  • the weapon system incorporating a servo-controlled electronic device computing the guidance signals from the data supplied by the detection system, is also used for simulation.
  • the guidance signals are transmitted, not to the missile itself, but to the computer device in the simulator device which computes from the signals received, the signals producing the corresponding response of the missile in actual firing and the characteristics of motion of the missile, the signals for the servo-mechanisms acting on the guidance mirror to deflect the collimated radiation beam in the same manner as an actual missile,
  • the two images are identically superposed on the images viewed by the gunner, Firing control can consequently be exercised either by a instructor, directly or with the help of an optical system, or by a robot recorder, the one and the other 'both making use of the second optical outlet, 1
  • the use of the weapon system in simulation is optional, It can be partly or wholly replaced by simpler means which can allow equivalent results to be obtained with simulated firing,
  • the facility with which the complete weapon system can be used in conjunction. with a simulator according to the present invention allows complete check and testing determined by the computer of the simulator, in ac cordance with the guidance signals received,
  • simulator in accordance with the present invention can be incorporated in a simulation apparatus for training on a complete mission or task, including, for instance, observation, warning, detection of the objective, spotting the target and firing the missile,
  • Such a simulator can equally be applied to an automatic guidance system, suitably by means of an electromagnetic field directed from the firing point to direct the missile by alignment on the target,
  • a simulator reproducing optically the apparent displacements of a guided missile through a landscape from a firing point toward a target
  • said simulator comprising a sight and a semi-transparent mirror through which a, firer may observe said landscape and said target, a projecting system including a source of light and capable of superimposing on said landscape by reflection on said semi-transparent mirror a luminous virtual image representing the guided missile, and manually operable control means connected to a movable member of the projecting system to impart to said virtual image, from an initial position corresponding to said firing point,

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US692354A 1967-02-20 1967-12-21 Firing training simulators for remotely - controlled guided missiles Expired - Lifetime US3522667A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR95567A FR1525138A (fr) 1967-02-20 1967-02-20 Simulateurs pour l'entraînement au tir de missiles automatiquement téléguidés

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US3522667A true US3522667A (en) 1970-08-04

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DE (1) DE1678620C3 (de)
FR (1) FR1525138A (de)
GB (1) GB1188700A (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3701206A (en) * 1969-02-27 1972-10-31 Solartron Electronic Group Weapon training systems
US4107854A (en) * 1976-04-23 1978-08-22 Le Materiel Telephonique Training system for simulating an animated scene
US4232456A (en) * 1977-06-30 1980-11-11 Martin Marietta Corporation Weapons system simulator and method including ranging system
WO1983001832A1 (en) * 1981-11-14 1983-05-26 Walmsley, Dennis, Arthur Guided missile fire control simulators
US4395234A (en) * 1977-09-16 1983-07-26 Farrand Optical Co., Inc. Optical scanning probe with multiple outputs
US4993819A (en) * 1989-12-06 1991-02-19 Dba Systems, Inc. External gunsight eyepiece attachment
US20030152892A1 (en) * 2002-02-11 2003-08-14 United Defense, L.P. Naval virtual target range system

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2008986B2 (de) * 1967-04-11 1978-12-14 Solartron Electronic Group Gerät zum Simulieren von Fernlenkgeschossen

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2884829A (en) * 1955-01-14 1959-05-05 Sperry Rand Corp Auxiliary optical systems for use with computing gun sights
US2930894A (en) * 1954-07-13 1960-03-29 Republic Aviat Corp Optical sighting and tracking device
US2937559A (en) * 1957-12-05 1960-05-24 Charles F Shute Arrangement for the concurrent viewing of radar and telescopic images
US3026615A (en) * 1957-11-15 1962-03-27 Giravions Dorand Guided missile simulator
US3128623A (en) * 1960-09-07 1964-04-14 Sperry Rand Corp Flight control systems
US3233847A (en) * 1961-11-06 1966-02-08 Contraves Ag System for guiding a missile toward a moving target
US3280243A (en) * 1964-04-22 1966-10-18 Giannini Scient Corp Missile tracking simulator and trainer
US3339293A (en) * 1962-09-18 1967-09-05 Bolkow Gmbh Infrared marksmanship training apparatus
US3352196A (en) * 1963-09-03 1967-11-14 Martin Marietta Corp Sighting device which superimposes the image of target with that of a missile
US3406402A (en) * 1962-11-27 1968-10-15 Nord Aviation Optical aiming device
US3446980A (en) * 1965-09-22 1969-05-27 Philco Ford Corp Stabilized sight system employing autocollimation of gyro-stabilized light beam to correct yaw and pitch orientation of coupled sight line and servo system mirrors

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2930894A (en) * 1954-07-13 1960-03-29 Republic Aviat Corp Optical sighting and tracking device
US2884829A (en) * 1955-01-14 1959-05-05 Sperry Rand Corp Auxiliary optical systems for use with computing gun sights
US3026615A (en) * 1957-11-15 1962-03-27 Giravions Dorand Guided missile simulator
US2937559A (en) * 1957-12-05 1960-05-24 Charles F Shute Arrangement for the concurrent viewing of radar and telescopic images
US3128623A (en) * 1960-09-07 1964-04-14 Sperry Rand Corp Flight control systems
US3233847A (en) * 1961-11-06 1966-02-08 Contraves Ag System for guiding a missile toward a moving target
US3339293A (en) * 1962-09-18 1967-09-05 Bolkow Gmbh Infrared marksmanship training apparatus
US3406402A (en) * 1962-11-27 1968-10-15 Nord Aviation Optical aiming device
US3352196A (en) * 1963-09-03 1967-11-14 Martin Marietta Corp Sighting device which superimposes the image of target with that of a missile
US3280243A (en) * 1964-04-22 1966-10-18 Giannini Scient Corp Missile tracking simulator and trainer
US3446980A (en) * 1965-09-22 1969-05-27 Philco Ford Corp Stabilized sight system employing autocollimation of gyro-stabilized light beam to correct yaw and pitch orientation of coupled sight line and servo system mirrors

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3701206A (en) * 1969-02-27 1972-10-31 Solartron Electronic Group Weapon training systems
US4107854A (en) * 1976-04-23 1978-08-22 Le Materiel Telephonique Training system for simulating an animated scene
US4232456A (en) * 1977-06-30 1980-11-11 Martin Marietta Corporation Weapons system simulator and method including ranging system
US4395234A (en) * 1977-09-16 1983-07-26 Farrand Optical Co., Inc. Optical scanning probe with multiple outputs
WO1983001832A1 (en) * 1981-11-14 1983-05-26 Walmsley, Dennis, Arthur Guided missile fire control simulators
US4993819A (en) * 1989-12-06 1991-02-19 Dba Systems, Inc. External gunsight eyepiece attachment
US20030152892A1 (en) * 2002-02-11 2003-08-14 United Defense, L.P. Naval virtual target range system
US6875019B2 (en) 2002-02-11 2005-04-05 United Defense, Lp Naval virtual target range system

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Publication number Publication date
FR1525138A (fr) 1968-05-17
DE1678620B2 (de) 1973-09-13
DE1678620A1 (de) 1971-12-30
DE1678620C3 (de) 1974-04-11
GB1188700A (en) 1970-04-22

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