EP0316216B1 - Einrichtung zur Kreiselstabilisierung eines Geschoss-Steuerorgans - Google Patents

Einrichtung zur Kreiselstabilisierung eines Geschoss-Steuerorgans Download PDF

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Publication number
EP0316216B1
EP0316216B1 EP88402754A EP88402754A EP0316216B1 EP 0316216 B1 EP0316216 B1 EP 0316216B1 EP 88402754 A EP88402754 A EP 88402754A EP 88402754 A EP88402754 A EP 88402754A EP 0316216 B1 EP0316216 B1 EP 0316216B1
Authority
EP
European Patent Office
Prior art keywords
section
axis
projectile
missile
control member
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 - Lifetime
Application number
EP88402754A
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English (en)
French (fr)
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EP0316216A1 (de
Inventor
Didier Creusot
Jean-Pierre Roux
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.)
Thomson Brandt Armements SA
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Thomson Brandt Armements SA
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Publication date
Application filed by Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0316216A1 publication Critical patent/EP0316216A1/de
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Publication of EP0316216B1 publication Critical patent/EP0316216B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • 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

Definitions

  • the present invention relates to a gyroscopic stabilization device used to maintain an axial reference for a member for operating a projectile, intended to modify the trajectory of the latter. It relates more particularly to such a device mounted in a rocket.
  • a rocket launch from an airplane or a helicopter, takes place at a great distance from the objective.
  • the aircraft uses an initial point as a reference point and, therefore, its position relative to the objective is well determined.
  • This firing mode is practiced with smooth bombs. It allows the plane to carry out a resource in front of the objective, where it is sheltered from enemy defenses.
  • a classic rocket arrives at the ground at a very small angle of incidence relative to the horizontal. Under these conditions, the sensitivity regarding the point of impact is very poor. Therefore, the shot is imprecise.
  • the solution to improve the accuracy of the firing consists in bending the end of trajectory of the rocket, so that it arrives towards the objective with a significant angle of incidence.
  • a lateral force is therefore applied to the rocket, said force being obtained by means of an operating member.
  • the latter can be a lateral impeller or an aerodynamic control surface.
  • One solution would be to use a gyroscope providing information to a servo which, in response, would position the operating member in the right plan.
  • the rocket should then take away the entire servo mechanism, as well as a source of energy to power it.
  • a device of this kind is described in patent FR-A-2,418,922. It is characterized in that the gyroscope has a double servo loop intended to maintain the proper axis of rotation of the gyroscope in a reference plane and an armature of the rotating part in a horizontal plane.
  • Such a device is complex and expensive and is preferably reserved for more sophisticated machines, the trajectories of which must be longer and the destinations even more precise.
  • the vertical reference is a sensor 11 consisting of a block of dense material connected by wire at the two ends of a diameter of a part of the projectile, free in roll relative to the rest of the projectile.
  • the roll position of the projectile is identified with respect to the position of the free section in roll by electromagnetic magnetic, photosensitive, radio-sensitive optical sensors, etc.
  • the function of the free roll section is to ensure, in coordination with the counterweight 11, the vertical reference, the function of the sensors is to know with respect to this vertical the angular roll position of the rest of the projectile.
  • An object of the present invention is to provide a device of the gyroscopic type for keeping said operating member in the right plane, which is simple and specially adapted to devices, such as rockets, whose path and, therefore, duration of the latter, are relatively short.
  • the gyroscopic stability is used directly, that is to say that there is a rigid mechanical connection between the gyroscope and the operating member.
  • Said device is formed by a free section in rotation about itself relative to the projectile, an internal frame coupled along one of its median axes to said section, and free in rotation around said axis, which is radial relative to the section, and, mounted in said frame, a router whose axis of rotation perpendicularly meets the axis of rotation of said frame, said projectile actuating member being carried by said section thus allowing it to remain in a fixed angular position relative to a fixed mark at ground.
  • the section and the internal frame constitute a Cardan joint.
  • the router being rotated at high speed, from the start of the trajectory, its angular moment stabilizes it in its initial position.
  • the section is linked to the router, around the axis of symmetry, or roll axis, of the projectile, by the axis of said internal frame. The section is therefore also stabilized in roll in its initial position and it is located in a fixed angular position relative to a fixed reference on the ground.
  • any overall movement of the projectile about its axis of symmetry shows friction couples at the connections between the section and the front and rear parts.
  • said connections are bearings to reduce the friction torques as much as possible.
  • the section of the projectile retains its roll position throughout the trajectory and the preservation of an axial reference makes it possible, at the end of the trajectory, to make the operating member act in a predetermined direction.
  • said member will act in the vertical plane of the trajectory and, consequently, it will be in the plane defined by the roll axis of the projectile and the axis of rotation of said internal frame.
  • a target sensor may also be provided.
  • the curve T represents the trajectory of a rocket provided with a device according to the invention, launched from an airplane or a helicopter.
  • the length of the trajectory is relatively short, 5000 m in this case.
  • the time interval between launch and impact is therefore very short.
  • the aircraft fires at a very low altitude, of the order of 100 m, and the trajectory of the projectile is very tense and very little inclined relative to the horizontal since it peaks at around 400 m, at a distance of 4200 m from the starting point. It is therefore essential, as explained above, to bend the end of the trajectory towards the ground to have good accuracy.
  • the rocket shown in Figures 2 and 3 has a rear part 1, a section 2 and a front part or head 3, of revolution about a longitudinal axis or roll axis X-X.
  • the tail of the rear part 1 comprises a tail unit 4 composed, for example of four fins.
  • the rear part 1 contains the propellant, the actual charge of the projectile being able to be placed in front of or behind the section.
  • the section 2 is an element of the device of the invention. Its front and rear ends are respectively connected to the head 3 and to the part 1, by means of bearings 5 and 6 which appear clearly in FIG. 3. Thus, the section 2 is free to rotate around the axis of roll XX with respect to the rear part 1 and to the head 3 of the projectile.
  • Section 2 has been fixed in this way to reduce the influence of aerodynamic forces on the projectile.
  • the aerodynamic forces being exerted for the most part on the front part of the projectile the positioning of the section 2 on the front part of the projectile could disturb the implementation of the device according to the invention, but this embodiment can be envisaged.
  • the uprights 8 and the crosspieces 9 are flanges which give it a certain depth.
  • the external faces of the crosspieces 9 carry in their center axes 10 aligned on the longitudinal median axis ZZ of the frame 7.
  • the axes 10 are engaged in bearings 11 integral with the section 2. Between the axes 10 and the bearings 11, are provided bearings 12 to reduce friction torques as much as possible.
  • the Z-Z axis meets the X-X roll axis perpendicularly.
  • the internal frame 7 and the section 2 form a gimbal assembly with one freedom around the roll axis X-X and the other freedom around the axis Z-Z.
  • a gyrostat or router 13 In the frame 7, is mounted a gyrostat or router 13.
  • the router 13 is formed of an outer ring with rectangular section 14, connected to a cylindrical hub 15 by an intermediate ring 16 of small thickness.
  • In the hub 15, passes an axis 17 carried in bearings which are located in the middle of the uprights 8 of the frame 7.
  • the hub 15 is mounted on the axis 17 by means of bearings 18.
  • the axis 17 is aligned along YY, Figure 3, YY being perpendicular to ZZ and passing through the meeting point of ZZ and XX.
  • this means is for example a turbine 19 which couples to a motor means of the carrier aircraft for print a rotational movement with the router 13 in the direction, figure 3.
  • the section 2 carries an operating member 20.
  • the member 20 may be an impeller or an aerodynamic control surface. It lies in the plane defined by the roll axis X-X and the axis Z-Z. In the same plane, the section 2 may also include a target sensor, not shown. A conventional proximometric sensor will generally be chosen.
  • the rocket is carried by an airplane or a helicopter with the router 13 directed along the longitudinal axis X-X of the projectile. It is held in this position by the turbine 19 coupled to the engine means of the aircraft. Therefore, the Y-Y axis is perpendicular to the X-X axis. The Z-Z axis is in the vertical plane passing through the X-X axis.
  • the aircraft makes a resource towards the objective.
  • the router 13 is rotated at high speed. Its axis of rotation is therefore perpendicular to the vertical plane of the trajectory which the rocket will follow.
  • the router 13 is stabilized in this position and, consequently, the section 2 is also stabilized, the operating member being in the vertical plane of the trajectory. Any subsequent rolling movement of the front part 1 and of the head 3 then causes friction couples to appear at the bearings 5 and 6. These couples are translated into a precession of the internal frame 7 around the axis Z-Z.
  • the drift in precession of the internal frame 7 does not become large enough to affect the operation of the device and, at the end of the trajectory, the operating member is still correctly positioned.
  • the operating member When it enters service, it therefore acts in the right plane and bends the trajectory towards the ground, towards the objective.
  • the rocket therefore arrives on the ground at a high angle of incidence and with all its kinetic energy. Its penetration capacities are important and allow its use against hard goals. On the other hand, the high angle of incidence makes it possible to increase the efficiency of the military charge, the shine of which is then horizontal. We benefit from the same advantage by equipping proximity rockets exploding the charge at altitude.
  • a vertical reference makes it possible to fix a sensor and a load focused downwards.
  • the sensor identifies its presence and triggers a charge thus attacking the target from above.
  • the primary advantage is to attack the targets according to their attitude of maximum vulnerability.
  • the advantage of the device of the invention is to get rid of the servos used to orient the load downward, in the plane of the vertical.
  • This gyro-stabilized section method according to the invention is adaptable to infantry rockets, aeronautical rockets and missiles in general.
  • the focused charge can be a hollow charge, a wafer charge or the like.
  • Such ammunition will be particularly effective against targets like tanks, armored vehicles and, in general, point targets weakly protected on top.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Claims (7)

1. Drallstabilisierungseinrichtung für ein Raketen-Lenkorgan zur Beibehaltung einer festen Winkelstellung relativ zu einer festen Bezugsmarke am Boden, bestehend aus einem Teilstück (2) der Rakete, das sich relativ zur Rakete frei um sich selbst dreht, einem inneren Rahmen (7), der mit dem Teilstück (2) entlang einer seiner Mittelachsen (Z-Z) gekoppelt ist und sich um diese Achse frei drehen kann, und einem im Rahmen (7) montierten Kreisel (13), dessen Drehachse (Y-Y) senkrecht zur Drehachse (Z-Z) des Rahmens (7) verläuft, wobei das Lenkorgan (20) von dem Teilstück (2) getragen wird, so daß es in seiner festen Winkelposition verharren kann.
2. Einrichtung nach Anspruch 1, dadurch gekennzeichnet, daß das Teilstück (2) mit seinen beiden Seiten an den vorderen (3) bzw. hinteren Abschnitt (1) der Rakete gekoppelt ist.
3. Einrichtung nach Anspruch 2, dadurch gekennzeichnet, daß die Verbindungen zwischen dem Teilstück (2) und den vorderen und hinteren Abschnitten (1, 3) aus Roll-Lagern (5, 6) bestehen.
4. Einrichtung nach Anspruch 1, 2 oder 3, dadurch gekennzeichnet, daß das Lenkorgan (20) ein Impulsgeber ist.
5. Einrichtung nach Anspruch 1,m 2 oder 3, dadurch gekennzeichnet, daß das Lenkorgan (20) ein aerodynamisches Ruder ist.
6. Einrichtung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß sich das Lenkorgan (20) in der durch die Rollachse (X-X) der Rakete und die Drehachse (Z-Z) des inneren Rahmens (7) definierten Ebene befindet.
7. Einrichtung nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß das Teilstück (2) einen Sensor zur Erfassung eines Zielobjekts aufweist.
EP88402754A 1987-11-06 1988-11-03 Einrichtung zur Kreiselstabilisierung eines Geschoss-Steuerorgans Expired - Lifetime EP0316216B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8715419 1987-11-06
FR8715419A FR2622966B1 (fr) 1987-11-06 1987-11-06 Dispositif de stabilisation gyroscopique pour un organe de manoeuvre de projectile

Publications (2)

Publication Number Publication Date
EP0316216A1 EP0316216A1 (de) 1989-05-17
EP0316216B1 true EP0316216B1 (de) 1992-04-15

Family

ID=9356566

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88402754A Expired - Lifetime EP0316216B1 (de) 1987-11-06 1988-11-03 Einrichtung zur Kreiselstabilisierung eines Geschoss-Steuerorgans

Country Status (4)

Country Link
US (1) US4923142A (de)
EP (1) EP0316216B1 (de)
DE (1) DE3870159D1 (de)
FR (1) FR2622966B1 (de)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0358376B1 (de) * 1988-09-07 1995-02-22 Texas Instruments Incorporated Integrierte Prüfschaltung
DE4325218C2 (de) * 1993-07-28 1998-10-22 Diehl Stiftung & Co Artillerie-Rakete und Verfahren zur Leistungssteigerung einer Artillerie-Rakete
US6162123A (en) * 1997-11-25 2000-12-19 Woolston; Thomas G. Interactive electronic sword game
EP2304383A4 (de) 2008-07-09 2014-01-01 Bae Sys Land & Armaments Lp Isoliertes kugellager
SE541615C2 (sv) 2017-04-28 2019-11-12 Bae Systems Bofors Ab Projektil med valbar anfallsvinkel
CN108681329A (zh) * 2018-05-10 2018-10-19 哈尔滨工业大学 基于可控舵面的火箭及其姿态自主矫正控制方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60253912A (ja) * 1984-05-31 1985-12-14 Fujitsu Ltd ジヤイロスコ−プ

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2963243A (en) * 1959-03-04 1960-12-06 Heinrich C Rothe Space vehicle guidance mechanism and method
US3937144A (en) * 1972-07-03 1976-02-10 The United States Of America As Represented By The Secretary Of The Navy Internal stabilizing device for air and water missiles
DE2518593C3 (de) * 1975-04-26 1979-12-06 Diehl Gmbh & Co, 8500 Nuernberg Mörsergeschoß
US4389028A (en) * 1976-01-14 1983-06-21 The United States Of America As Represented By The Secretary Of The Navy Flat trajectory projectile
US4374577A (en) * 1976-01-14 1983-02-22 The United States Of America As Represented By The Secretary Of The Navy Adapter assembly for flat trajectory flight
CA1087883A (en) * 1978-03-02 1980-10-21 Michael J. Lanni Dual suspension gyroscopic device
FR2425049A1 (fr) * 1978-03-09 1979-11-30 Serat Perfectionnements apportes aux armes sol-sol agissant en survolant l'objectif
US4431150A (en) * 1982-04-23 1984-02-14 General Dynamics, Pomona Division Gyroscopically steerable bullet
JPS60253913A (ja) * 1984-05-31 1985-12-14 Fujitsu Ltd ジヤイロスコ−プ

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60253912A (ja) * 1984-05-31 1985-12-14 Fujitsu Ltd ジヤイロスコ−プ

Also Published As

Publication number Publication date
EP0316216A1 (de) 1989-05-17
FR2622966A1 (fr) 1989-05-12
FR2622966B1 (fr) 1993-05-07
US4923142A (en) 1990-05-08
DE3870159D1 (de) 1992-05-21

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