EP0033283A2 - Vereinfachtes Selbststeuerungssystem für Flugkörper, wie z.B. Granaten und Raketen - Google Patents

Vereinfachtes Selbststeuerungssystem für Flugkörper, wie z.B. Granaten und Raketen Download PDF

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Publication number
EP0033283A2
EP0033283A2 EP81400119A EP81400119A EP0033283A2 EP 0033283 A2 EP0033283 A2 EP 0033283A2 EP 81400119 A EP81400119 A EP 81400119A EP 81400119 A EP81400119 A EP 81400119A EP 0033283 A2 EP0033283 A2 EP 0033283A2
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EP
European Patent Office
Prior art keywords
machine
target
axis
self
vector
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
EP81400119A
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English (en)
French (fr)
Other versions
EP0033283B1 (de
EP0033283A3 (en
Inventor
Richard Heidmann
Dino Noel Crapiz
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.)
Societe Europeenne de Propulsion SEP SA
Original Assignee
Societe Europeenne de Propulsion SEP SA
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 Societe Europeenne de Propulsion SEP SA filed Critical Societe Europeenne de Propulsion SEP SA
Publication of EP0033283A2 publication Critical patent/EP0033283A2/de
Publication of EP0033283A3 publication Critical patent/EP0033283A3/fr
Application granted granted Critical
Publication of EP0033283B1 publication Critical patent/EP0033283B1/de
Expired legal-status Critical Current

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Classifications

    • 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
    • F41G7/222—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
    • F41G7/2273—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

Definitions

  • the present invention relates to a simplified self-guiding system for a shell or rocket type vehicle that is not actively stabilized in attitude.
  • Ground-to-ground artillery systems or air-to-ground armaments based on shells or rockets more and more often use self-propelled missiles fitted with military heads which can include multiple under-charges.
  • These devices that constitute these heads intended to reach a determined target can be divided into several categories.
  • the so-called directed effect machines that is to say whose action is e xer - ced at a distance, without guidance, towards a target as soon as this has been detected, have the advantage of making the economy of a guidance system but are limited in range and efficiency due to the limitations of the precision of the action at a distance.
  • Radio-controlled devices can be very precise, but are relatively complex and expensive.
  • self-directing terminal guiding machines using for example a proportional guiding law, can be precise but require active means for stabilizing the attitude of the machine and means for mounting the detection device on a gyroscopic system in order to have a free and inertial antenna capable of keeping the target in view.
  • Such systems can thus combine sufficient efficiency, both in terms of target search and probability of hit, only at the cost of transforming the munitions to which they are applied into sophisticated and expensive missiles.
  • the present invention aims precisely to produce a simplified guidance material which makes it possible to eliminate the inaccuracies and limitations in range of the directed effect systems while providing a simplification of the design of conventional self-directing systems, in particular by avoiding the use of gyroscopic equipment and the need to actively stabilize a craft in attitude.
  • the present invention also aims to extend the search field of the target, that is to say the range of action of detection systems. and to decrease the acquisition time of the data relating to the target and consequently to increase the duration of the guidance phase, therefore the maneuverability.
  • a simplified self-guiding system for a shell or rocket type vehicle that is not actively stabilized in roll, comprising means for detecting a target associated with the device; an accelerometric device mounted directly on the structure of the vehicle and including at least one accelerometer with a radial sensitive axis relative to the vehicle to detect the lateral acceleration of the vehicle; and means for developing a piloting force Fp applied to the machine by means of actuators acting on control surfaces, characterized in that it also comprises passive means ensuring the maintenance of the movement in roll of the craft; means associated with the accelerometric device for discriminating the lateral acceleration of the machine Y ext due to external forces and the centrifugal acceleration i c due to roll; means for determining useful quantities linked to the vector V representing the relative speed of the machine with respect to the air in a frame linked to the machine from information provided by the accelerometric device and the associated discrimination means ; in that the means for detecting a target are mounted directly on the structure of the machine; in that it further comprises means for determining useful quantities
  • all the detection means can be mounted on the structure of the machine and there is no need to have gyroscopic equipment.
  • the craft does not have to be stabilized in roll either since the accelerometric device makes it possible to permanently determine the relative position in roll of the craft with respect to the direction of the target and to the direction of the speed vector. On the contrary, it is sufficient to have means of maintaining the roll produced, for example, by stabilizing the tail.
  • the discrimination means associated with the accelerometric device comprise a circuit for determining the average value of the signal supplied by said accelerometer and a circuit for measuring the peak-to-peak amplitude of said signal supplied by said accelerometer to respectively supply a signal representative of the centrifugal acceleration ⁇ c of the machine and a signal representative of the lateral acceleration of the machine ⁇ ext due to external forces.
  • the accelerometric device comprises at least two accelerometers with a sensitive radial axis arranged at 180 ° from one another in a plane perpendicular cular to the axis of the machine.
  • the accelerometric device comprises at least two accelerometers with a sensitive radial axis arranged at 90 ° from one another in a plane perpendicular to the axis of the machine.
  • the discrimination means associated with the accelerometric device can comprise a circuit for summing the signals supplied by said accelerometers and a circuit for subtracting the signals supplied by said accelerometers to respectively produce a signal representative of the centrifugal acceleration of the vehicle ⁇ c and a signal representative of the lateral acceleration of the vehicle due to external forces ⁇ ext .
  • the means for determining useful quantities linked to the vector - V comprise square root extractor means for determining the roll speed ⁇ of the machine from the centrifugal acceleration ⁇ c provided by the means of discrimination, circuits for detecting the extremes of lateral acceleration ⁇ ext provided by the discrimination means, means for integrating the roll speed ⁇ controlled by the circuits for detecting extremes to provide a signal representative of the roll angle j between the projection of the vector V on a plane perpendicular to the axis of the machine and a reference axis of said plane linked to the machine, means for providing a signal for approximation of the lift force F ⁇ actuators from the steering angle provided by a steering indicator, means for determining the component Fe cos j of of the approximate lift force F ⁇ in the plane of incidence, from the signals supplied by the means of approximation of the lift force F ⁇ of the actuators and said integration means, means for developing the overall force F linked to the acceleration ⁇ ext , means for subtracting the component F ⁇ cos
  • the target detection means can comprise an optical system associated with at least one strip comprising a plurality of infrared detectors, aligned and making a predetermined angle e relative to the axis of the machine and the determination means.
  • useful quantities linked to the vector representative of the gear-target direction comprise at least one circuit for determining the angle ⁇ between said vector and the axis of the machine, from the identification of the excited detectors, and means for integrating the roll speed w supplied by square root extractor means, from the centrifugal acceleration ⁇ c , to provide a signal representative of a relative roll angle between a detection plane defined by the vector and the axis of the machine and an axial reference plane linked to the machine.
  • the target detection means comprise an electronic scanning system of the target search field.
  • the means for developing the piloting force Fp are produced so as to control the speed on the direction of the target from the determined useful quantities providing values of the direction of the speed V, and of the direction of the target u c , from the indications provided by the accelerometric device and the target detection means and relative recorded information to the speed module and to the aerodynamic parameters making it possible to restore the incidence from the lift.
  • the invention applies more particularly to a shell or rocket type device, such as the military head 1 shown in FIG. 1.
  • a military head generally intended to be launched by means of a self-propelled device stabilized on a predetermined trajectory is separated from the transport vector at a certain altitude above the target's search field.
  • simplified self-guiding means are incorporated in the head to allow it to reach the target with sufficient precision while avoiding the use of expensive conventional systems of the self-directing type.
  • the head 1 may include a body 11 in which is stored a load of ammunition intended to be ejected onto a target, and a warhead 12 equipped with a system for self-guiding the assembly in the direction of the target.
  • a tail unit 2 deployed at the time of the release conventionally stabilizes the movement of the craft while control surfaces 3 controlled by the piloting system make it possible to direct the craft on the target when the target detection systems 4 and d 'auto-guidance were put into service at a predetermined altitude above the target search cham I.
  • the target detection and self-guiding systems according to the invention which can be implemented implemented from a relatively high altitude, for example around 1000m above the target's search range, are capable of quickly providing correction indications allowing precise guidance and continuing to operate up to an altitude very low immediately preceding the opening of the head and the ejection of all the underloads contained in the body 11 of the machine.
  • the vehicle exhibits a rolling movement, which can be maintained aerodynamically, at speed ⁇ around its rolling axis E 1 E ' l (fig. 1 and 2).
  • the relative speed vector V of the vehicle with respect to air, applied to the center of gravity G of the vehicle makes an angle of incidence i with respect to the axis of the vehicle E 1 E ' 1 .
  • the unitary vector indicating the direction of the target 10 relative to the machine 1 makes an angle ⁇ with the roll axis E 1 E ' 1 of the machine (of unit vector ) and the plane of the detected target 1 0 defined by the roll axis E 1 E ' 1 and the vector .
  • the roll angle ⁇ between the plane of the detected target , and a reference plane E 1 E ' 1 , E 3 E'3 linked to the structure of the machine is indicated in Fig.l.
  • the principle of guiding the machine 1 relative to the target 10 is illustrated by the vector diagram in FIG. 3.
  • the target 10 detected has a displacement speed V c represented in a fixed reference mark of the space OXYZ.
  • the machine 1 of center of gravity G to which is linked a reference frame Gxyz such as the reference frame E 1 , E 2 , E 3 of FIG. 1 has a relative speed of displacement V making an angle of incidence i with the axis of the Gx machine (vector ).
  • the vector indicating the direction of craft 1 - target 10 makes an angle S with the axis of craft 1.
  • the driving force of craft Fp is developed so as to enslave the velocity vector V of the machine to the vector u c giving the direction of the target machine and is both located in the plane ( , ), perpendicular to the axis u of the machine and proportional to the angle ( , ).
  • the driving force Fp is applied to the vehicle by means of actuators 140 causing the steering of the control surfaces of the vehicle 150 (fig. 4).
  • the steering force is itself developed at each instant by a computer 130 from data constituted by, on the one hand, the detection plane defined by the vectors , , and the angle ⁇ and, on the other hand, the incidence plane defined by the vectors , , and the angle of incidence i.
  • the data relating to the incidence plane and to the angle of incidence i are applied to the assembly 130 from calculation means 120 taking into account the acceleration measurement information 121 provided by the accelerometric device 5 linked to the machine 1 (fig. 1) and the associated discriminating circuits 6.
  • the data relating to the detection plane and to the angle d are also applied to the assembly 130 from calculation means 110 taking into account the information roll speed 111 also derived from the accelerometric device 5, and target position and speed 112 supplied from the detection device 4.
  • the detection and measurement devices supplying the aforementioned primary information to the guidance computer 110, 120, 130 deducing the useful quantities and developing the driving force, will be described in more detail below.
  • the measurement 5 and detection 4 elements which provide the primary information essential for self-guiding the machine 1 in the direction of the target 10 are essentially characterized by great simplicity of implementation since they are mounted on the structure of the machine and does not require no inertial support or gyroscopic type device.
  • the accelerometric device 5 (FIGS. 1 and 5) comprises at least one accelerometer 51 with a sensitive radial axis, that is to say perpendicular to the axis E 1 E ′ 1 of the machine 1.11 is however possible to associate several accelerometers with sensitive radial axes in a plane perpendicular to the axis of the machine, preferably in the vicinity of its center of gravity. According to an advantageous embodiment, two accelerometers can be arranged at 180 ° (references 51.52) or 90 ° (references 51.53) from each other in fixed positions with a reference A 1 A ' 1 , A 2 A ' 2 linked to the structure of the machine.
  • Such an accelerometric device gives the primary information from which it is possible to determine the lateral acceleration ⁇ ext due to the external forces, and therefore to know the lift P then deduce the impact i.
  • the load factor F ⁇ due specifically to the actuators, the state of which is known at all times by the steering angle 0 and to know at least approximately the modulus of speed V and all of the aerodynamic parameters making it possible to restore the incidence from the lift.
  • the accelerometric device 5 intended to allow the determination of the incidence i, it is to say the orientation of the vector V, has a second function which allows the implementation of simplified target detection devices.
  • the accelerometers 51, 52 with radial sensitive axes provide indications which make it possible to extract the centrifugal acceleration ⁇ due to roll, whose value varies little with each rotation while the acceleration ⁇ ext due to the action of the lift itself produces a sinusoidal signal.
  • the roll position of the machine at all times, that is to say the relative roll angle ⁇ between the plane of the detected target containing the roll axis u and the direction of the target u c and a reference plane E 2 E ' 2 , E 3 E' 3 .
  • a target detection system 4 which provides complete information on the target's angular position relative to the axes of the reference frame linked to the machine only limited number of times per roll period while the steering force can always be applied at any time in a well-defined plane, regardless of the roll position of the craft.
  • FIGS. 8 to 10 show how it is possible to determine, from the signals supplied by the accelerometric device 5, signals representative respectively of the centrifugal acceleration ⁇ c due to the roll and of the lateral acceleration ⁇ ext due to the external forces.
  • a single accelerator 51 can be used to provide a signal ⁇ 1 representative of the total lateral acceleration to which the vehicle is subjected.
  • the signal ⁇ 1 is then applied, in a discriminator circuit 6, on the one hand to a circuit 61 which provides the average value ⁇ c of the signal 9 1 (fig 10), on the other hand to a circuit 62 for measuring the peak-to-peak amplitude of the signal ⁇ 1 which makes it possible to determine at each period the value of the lateral acceleration ⁇ ext , since the signal from of circuit 62 then corresponds to 2 ⁇ ext .
  • two accelerometers 51 and 52 with radial sensitive axis, arranged at 180 ° from one another in a plane perpendicular to the axis of the machine respectively provide signals ⁇ 1 and ⁇ 2 (fig 10) which are applied to the discriminator circuit 6 which in this case comprises a summing circuit 63 and a subtracting circuit 64 which each receive the signals ⁇ 1 and Y 2 .
  • the summing circuit 63 provides an output signal 2 Yc proportional to the centrifugal acceleration due to the roll while the subtracting circuit 64 provides a signal representative of the acceleration ⁇ ext due to external forces.
  • the signals ⁇ c and Y ext delivered by the discrimination means 6 can then be used, in combination with the signals supplied by the target detection device 4, to allow the elaboration of the driving force Fp in the calculation sets 110, 120, 130.
  • the target detection assembly 4 mounted in the head 1 may include an infrared or visible imaging system, with electronic scanning of the entire search field, making it possible to have complete information on angular position with a high frequency of recurrence, or microwave detection systems or detection of targets illuminated by laser.
  • a particularly advantageous detection assembly 4 is constituted by an optical system 45 (FIG. 7) associated with one or more strips 41, 42 (FIG. 6 and 7) of detectors. infrared 40 aligned substantially radially with respect to the axis of the machine E 1 E ' 1 and integral with the structure of the machine.
  • each strip can include, for example, around thirty IR detectors of the conventional cooled type (for example in Cd Hg Te or Pb Sn Te) covering a total field ⁇ (fig 2) around the axis optical 00 ′ of the optical system 45 linked to the detection strip.
  • the system according to the invention thus makes it possible, from purely static measuring devices with respect to the machine in which they are installed, the extended, rapid and prolonged search for a target and the simplified guidance of the machine up to this target.
  • a strip 41 of detectors may for example be inclined at an angle ⁇ of between approximately 60 and 90 ° relative to the axis E l E ' 1 of the machine, and preferably of between approximately 75 and 90 °.
  • the detection and measurement system making it possible to know, on the one hand, the parameters relating to the relative speed V of the machine with respect to air, by virtue of an accelerometric measurement of which results from the measurement of the incidence i using the subset 120 and, on the other hand, the parameters relating to the vector giving the direction target machine, from the detectors, for example of the bar type using the sub-assembly 110, the driving force Fp can be calculated, in modulus and direction at each detection for example by the following formula: in which :
  • the vector is prepared by the computer 13 0 from information relating to and available on board and supplied by sub-assemblies 110, 120.
  • FIGS. 4, 11 and 12 we see an example of circuits making it possible to develop the quantities used by the computer 130 to determine the driving force.
  • the means 120 for determining the useful quantities linked to the vector V comprise (FIG. 11) a circuit 124 square root extractor to which the signal ⁇ c from the discriminator is applied 6, to provide a signal ⁇ representing the rolling speed of the machine, a circuit 123 for detecting the extremes of lateral acceleration ⁇ ext which makes it possible to give an indication of the times when the accelerometers 51 or 52 linked to the machine 1 are in the incidence plane defined by the vectors V and u, an integrator circuit 125 to which the signal ⁇ applied by the circuit 124 is applied, and whose integration starting points are controlled by the detection circuit 123 extrums, in order to output signals representing as the roll angle j between the projection of the vector V on the plane perpendicular to the axis E 1 E ' 1 of the vehicle and containing the accelerometers 51, 52, and a reference axis linked to the vehicle in said plane containing the accelerometers 51, 52.
  • the angle j thus represents the angle between
  • the circuit 120 further comprises a circuit 122 which supplies a signal representing the approximate value of the lift force F ⁇ of the actuators 140, 150 from the value of the steering angle ⁇ provided by a steering indicator, not shown .
  • a circuit 126 to which the signals from the circuit 122 and from the integrator 125 are applied then makes it possible to supply the value F ⁇ cos j of the component in the plane of incidence V, u, of the approximate lift force FG.
  • the overall force F linked to the acceleration i ext provided by the discriminator circuit 6 is determined in the circuit 127 and applied to a subtractor circuit 128 which also receives the signal from the circuit 126 in order to output a signal representing the force P due to the lift of the machine and which is equivalent to the overall force F minus the component F ⁇ cos j which takes into account the load factor which is due specifically to the actuators and which depends on both their state (angle ⁇ ) and the roll position (angle j).
  • the value of the angle of incidence i of the vector V, which is linked to the force P by a simple coefficient of proportionality can then be supplied by the circuit 129 placed at the output of the subtractor 128.
  • FIG. 12 shows the simplified diagram of means 110 for determining useful quantities linked to the vector giving the direction of the target machine.
  • a circuit 113 supplies the value of the angle ⁇ between the vectors and .
  • the integrator circuit 115 is itself controlled by a circuit 114 which detects the instants of passage of the target in the field of the detectors and triggers the integration of the roll speed ⁇ from said instants to provide an indication of the angle f.
  • various improvements or variants can be made to the detection system.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Navigation (AREA)
EP81400119A 1980-01-29 1981-01-28 Vereinfachtes Selbststeuerungssystem für Flugkörper, wie z.B. Granaten und Raketen Expired EP0033283B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8001869A FR2474686B1 (fr) 1980-01-29 1980-01-29 Systeme d'auto-guidage simplifie pour engin du type obus ou roquette
FR8001869 1980-01-29

Publications (3)

Publication Number Publication Date
EP0033283A2 true EP0033283A2 (de) 1981-08-05
EP0033283A3 EP0033283A3 (en) 1981-12-02
EP0033283B1 EP0033283B1 (de) 1986-01-22

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ID=9237983

Family Applications (1)

Application Number Title Priority Date Filing Date
EP81400119A Expired EP0033283B1 (de) 1980-01-29 1981-01-28 Vereinfachtes Selbststeuerungssystem für Flugkörper, wie z.B. Granaten und Raketen

Country Status (5)

Country Link
US (1) US4397430A (de)
EP (1) EP0033283B1 (de)
JP (1) JPS5757313A (de)
DE (1) DE3173544D1 (de)
FR (1) FR2474686B1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1983001298A1 (en) * 1981-10-08 1983-04-14 Skarman, Bengt A method and an apparatus for steering an aerodynamic body having a homing device
EP0208544A1 (de) * 1985-07-10 1987-01-14 British Aerospace Public Limited Company Ballistische Flugkörper
DE3442598A1 (de) * 1983-11-25 1989-06-15 British Aerospace Leitsystem
FR2647894A1 (fr) * 1989-05-30 1990-12-07 Matra Dispositif electro-optique de reconnaissance aerienne
EP0561163A1 (de) * 1992-03-17 1993-09-22 Daimler-Benz Aerospace Aktiengesellschaft Bildaufnahmesystem
FR2695992A1 (fr) * 1992-09-21 1994-03-25 Giat Ind Sa Sous munition à effet dirigé.
FR2712685A1 (fr) * 1983-11-25 1995-05-24 British Aerospace Système de guidage pour véhicule tel qu'une arme guidée.
DE3347941B3 (de) * 1983-08-19 2007-06-06 Shorts Missile Systems Ltd., Belfast Lenkung eines Geschosses

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US4728057A (en) * 1985-11-22 1988-03-01 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use
GB2186760B (en) * 1986-02-14 1990-01-04 Philips Electronic Associated Information transmission system
JP2505432B2 (ja) * 1986-11-29 1996-06-12 三菱重工業株式会社 飛翔体の方位角制御方式
US4703179A (en) * 1987-04-02 1987-10-27 Ford Aerospace & Communications Corporation Sensor for hemispherical applications
FR2745785B1 (fr) 1996-03-07 1998-04-30 Aerospatiale Procede et dispositif de guidage d'un corps volant vers une cible
FR2893154B1 (fr) * 2005-11-10 2007-12-28 Tda Armements Sas Soc Par Acti Procede et dispositif de determination de la vitesse de rotation d'une droite projectile-cible et dispositif de guidage d'un projectile, notamment d'une munition
RU2468327C1 (ru) * 2011-11-15 2012-11-27 Открытое акционерное общество "Конструкторское бюро приборостроения" Способ стрельбы управляемой ракетой с лазерной полуактивной головкой самонаведения
RU2534206C1 (ru) * 2013-05-29 2014-11-27 Открытое акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Способ стрельбы управляемой ракетой
CN111750821B (zh) * 2020-07-10 2021-05-18 江苏集萃智能光电系统研究所有限公司 一种位姿参数测量方法、装置、系统和存储介质

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US3642233A (en) * 1964-06-04 1972-02-15 Telecommunications Sa System for the optical automatic and autonomous guiding of self-rotating missiles
US3706429A (en) * 1970-01-14 1972-12-19 Us Navy Missile proportional navigation system using fixed seeker
US3735944A (en) * 1971-06-25 1973-05-29 U S A Represented By Secretary Dual mode guidance and control system for a homing missile
US3905563A (en) * 1972-09-28 1975-09-16 Fuji Heavy Ind Ltd System for controlling a missile motion in the homing mode

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GB1600201A (en) * 1967-09-11 1981-10-14 British Aerospace Guidance systems
US4264907A (en) * 1968-04-17 1981-04-28 General Dynamics Corporation, Pomona Division Rolling dual mode missile

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3642233A (en) * 1964-06-04 1972-02-15 Telecommunications Sa System for the optical automatic and autonomous guiding of self-rotating missiles
US3706429A (en) * 1970-01-14 1972-12-19 Us Navy Missile proportional navigation system using fixed seeker
US3735944A (en) * 1971-06-25 1973-05-29 U S A Represented By Secretary Dual mode guidance and control system for a homing missile
US3905563A (en) * 1972-09-28 1975-09-16 Fuji Heavy Ind Ltd System for controlling a missile motion in the homing mode

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1983001298A1 (en) * 1981-10-08 1983-04-14 Skarman, Bengt A method and an apparatus for steering an aerodynamic body having a homing device
US4529151A (en) * 1981-10-08 1985-07-16 Saab-Scania Aktiebolag Method and an apparatus for steering an aerodynamic body having a homing device
DE3347941B3 (de) * 1983-08-19 2007-06-06 Shorts Missile Systems Ltd., Belfast Lenkung eines Geschosses
DE3442598A1 (de) * 1983-11-25 1989-06-15 British Aerospace Leitsystem
FR2712685A1 (fr) * 1983-11-25 1995-05-24 British Aerospace Système de guidage pour véhicule tel qu'une arme guidée.
EP0208544A1 (de) * 1985-07-10 1987-01-14 British Aerospace Public Limited Company Ballistische Flugkörper
FR2647894A1 (fr) * 1989-05-30 1990-12-07 Matra Dispositif electro-optique de reconnaissance aerienne
EP0561163A1 (de) * 1992-03-17 1993-09-22 Daimler-Benz Aerospace Aktiengesellschaft Bildaufnahmesystem
FR2695992A1 (fr) * 1992-09-21 1994-03-25 Giat Ind Sa Sous munition à effet dirigé.
EP0589746A1 (de) * 1992-09-21 1994-03-30 GIAT Industries Sub-Munition mit kontrollierter Aktivierung
US5341743A (en) * 1992-09-21 1994-08-30 Giat Industries Directed-effect munition

Also Published As

Publication number Publication date
EP0033283B1 (de) 1986-01-22
JPS5757313A (en) 1982-04-06
FR2474686A1 (fr) 1981-07-31
EP0033283A3 (en) 1981-12-02
FR2474686B1 (fr) 1986-04-04
DE3173544D1 (en) 1986-03-06
US4397430A (en) 1983-08-09

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