EP0482970B1 - Einrichtung zur Verleihung einer Flugbahnabweichung an einen aus einem Fluggerät abgeschossenen Flugkörper - Google Patents

Einrichtung zur Verleihung einer Flugbahnabweichung an einen aus einem Fluggerät abgeschossenen Flugkörper Download PDF

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Publication number
EP0482970B1
EP0482970B1 EP19910402521 EP91402521A EP0482970B1 EP 0482970 B1 EP0482970 B1 EP 0482970B1 EP 19910402521 EP19910402521 EP 19910402521 EP 91402521 A EP91402521 A EP 91402521A EP 0482970 B1 EP0482970 B1 EP 0482970B1
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EP
European Patent Office
Prior art keywords
projectile
roll
projectile according
angle
rocket
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
EP19910402521
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English (en)
French (fr)
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EP0482970A1 (de
Inventor
Jean Deffayet
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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 EP0482970A1 publication Critical patent/EP0482970A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/10—Missiles having a trajectory only in the air
    • F42B15/105—Air torpedoes, e.g. projectiles with or without propulsion, provided with supporting air foil surfaces

Definitions

  • the present invention relates to the launching of a projectile from an aerial vehicle, in the direction of its trajectory. It relates more particularly to a device for laterally bending the trajectory of the projectile relative to the direction of the shot.
  • the invention applies in particular to the launching of a self-propelled projectile, such as a decoy rocket, from an airplane.
  • a self-propelled projectile such as a decoy rocket
  • the mission of such a rocket is to protect, by means of an on-board decoy, an airplane flying at very low altitude during the final attack phase of an objective defended by solair systems.
  • the confrontation with means of detection and processing of information capable of distinguishing between different signatures requires that the rocket, in order to be credible, evolves within limits of which the airplane is capable. This implies, among other things, that the rocket is launched along the path of the aircraft, and that after launch, its relative speed relative to it remains low, in practice of the order of 20 m / s. Under these conditions, the gap between the rocket and the aircraft does not grow rapidly, and if the latter follows a straight path as is generally the case, this gap remains insufficient to avoid the risk of interception by incoming missiles. front.
  • the subject of the invention is a device for imparting a laterally deflected trajectory to a projectile in a controlled manner after firing, and comprising means which have the advantage of being simple, and therefore inexpensive, and of being easily applicable to launching a decoy rocket.
  • a device according to the invention is defined in claim 1.
  • the preamble corresponds to a known state of the art.
  • the airfoil is then calculated in such a way that for the cruising speed of the projectile, the vertical component of the load factor cancels gravity.
  • the projectile represented in the drawings is a decoy rocket intended to be launched from an airplane, substantially in the direction of its speed vector when it is in horizontal flight.
  • the rocket comprises a front section 1 containing the lure (which can be of any type, for example electromagnetic, pyrotechnic or thermal), an intermediate section 2 at the level of which is the wing structure made up of two wings 4, and a rear section or propulsive part 3.
  • a tail fin is installed formed by a plurality of fins 5.
  • the fins 5, as well as the wings 4 forming the lift wing are deployable, which makes it possible to have all the elements of the rocket included in its caliber and to reduce the aerodynamic constraints in flight before launching.
  • Figs. 2 and 3 schematically represent a simple system of deployable lift wing, which ensures an opening conjugation of the two wings 4. These are articulated so as to be able to be fully retracted inside the section 2, in the position shown in dashed lines in FIG. 3, and they comprise pinions 6 meshed with the two sides forming a rack of a flat rod 7. The longitudinal displacement of the rod 7 necessary for the combined opening of the wings 4 is ensured, for example, by spring means and lock released when launching the rocket.
  • the section propulsion system 3 comprises two distinct parts: either a take-off stage with the load 8 and the peripheral nozzles 9, which stage must provide the acceleration necessary for launching, and a second cruising stage with the load 10 and the central nozzle 11, which has the function of maintaining the rocket at a predetermined speed substantially constant, after launch.
  • the rocket takes place on a plane launching ramp, directed forward and oriented so as to be parallel to the speed vector when the plane is in horizontal flight.
  • the ramp can be a rail, or else a tube when the lift wing and the tail of the rocket are deployable, and included in its caliber in the folded position.
  • the tube may be a cannon, the take-off propellant 8.9 then no longer having any reason to be.
  • Means are provided for ensuring the positioning of the rocket on the ramp in a determined position of rotation about its longitudinal axis, and also for maintaining this position throughout the ramp at the time of launch.
  • these means comprise, for example, a finger secured to the rocket, which can be engaged in a guide groove formed in the inner wall of the tube.
  • the rotational position of the rocket on the launching ramp defines a determined angle a of transverse inclination of its lift wing (wings of the aircraft in horizontal position).
  • said lift wing is calculated so that under these conditions of transverse inclination, and for a speed V slightly higher than the recommended speed of the airplane at the time of the firing, the load factor resulting from the lift and of the thrust component of the cruise thruster is oriented perpendicular to the axis of the rocket and has a vertical component that cancels gravity.
  • the thrust generated by the cruising thruster 10, 11 is approximately equal to the drag of the rocket, so that this speed V is kept constant, or slightly increasing.
  • Fig. 5 represents the load factor f on a graph (Oy, Oz) for a transverse tilt angle a equal to 45 °.
  • the projections fy and f z are then equal to g, which implies for f the value g ⁇ 2.
  • This trajectory is represented on the graph (Ox, Oy) of FIG. 7, C being the center of the trajectory, the origin 0 representing the position of the airplane at the time of launch and Ox the direction of its trajectory.
  • the value of the transverse angle of inclination a can be chosen within a range limited inferiorly by the need to obtain a sufficient lateral deviation, and superiorly by the credibility of evolution of the rocket and by the excessive increase in the factor of charge f.
  • the value of 45 ° in addition to its geometric simplicity, represents an interesting compromise.
  • the criterion is the risk that the rocket hits the ground too early because, in practice, this type of projectile is launched at very low altitude, of the order of 30 m.
  • Fig. 4 illustrates such an arrangement, in which the propulsion section 3 comprises a part 3a joined to the intermediate section 2 and housing the cruising thruster 10, 11, and a part 3b in the form of a cylindrical block mounted free to rotate, by through bearings 12, around part 3a.
  • Part 3b comprises the take-off thruster 8.9, as well as means for implanting the tail unit, that is to say in the example shown of the legs 13 on which the fins 5 are articulated.
  • the tail unit is mounted on bearings around section 3.
  • FIGS. 8 to 11 An example of a simple and therefore inexpensive embodiment of such means is shown in FIGS. 8 to 11.
  • a flywheel 14 is mounted to rotate freely around the axis of the rocket, so as not to be driven by the roll deviations of the latter.
  • the friction may be considered negligible insofar as the stresses are alternative. In practice, this tendency is favored, to the detriment of stresses repeating in the same direction, by providing a free tail in rotation as described above.
  • Figs. 8 and 9 illustrate means by which signals are produced when these deviations reach a determined value of in either direction.
  • these means consist of a through channel 15, located in a radial plane r, at a distance d from the axis.
  • two sets each include a light source 16 on one side of the steering wheel 14, and a photoelectric cell 17 on the other side.
  • these two assemblies are also located at a distance d from the axis, and are angularly spaced from the value da with respect to the longitudinal plane of symmetry of the lift wing formed by the wings 4.
  • means are necessary for bring the radial plane r of the flywheel 14 to coincide with this plane of symmetry, between the two assemblies, FIG. 9.
  • the steering wheel 14 is retained in this position by a lock released at launch.
  • the angular spacing da of the assemblies with respect to said plane of symmetry corresponds to the maximum roll angle deviation that is tolerated.
  • the corresponding photoelectric cell receives light from its light source and produces a signal that can be used to control a roll correction device, two embodiments of which are shown by way of example in FIGS. 10 and 11.
  • a reserve of pressurized gas 18 is connected by conduits 19 to peripheral nozzles 20. They are preferably associated in pairs, each of which is capable of producing counter-roll pulses in one direction, following the selective and time-controlled opening of solenoid valves 21.
  • the device of FIG. 11 is made up of small guns 22, also associated in pairs, preferably. By launching projectiles, these guns produce recoil forces which can be used as counter-roll pulses.
  • the field of use of the invention is not limited to the launching of decoy rockets which has just been described.
  • the ranges of possible values for the speed V and the angle a of transverse inclination of the lift wing are obviously much greater than for the case of a decoy rocket. .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Claims (12)

1. Projektil mit einer Längsachse vom Typ mit einem Tragwerk (4), einem Schwanzleitwerk (5) und einem Flugtriebwerk (10, 11), welches Projektil dazu bestimmt ist, von einer Luftträgerrakete abgeworfen zu werden, wobei der Einsatz des Projektils eine Flugphase, in der es von der Trägerrakete getragen wird, eine Abschußphase und eine autonome Flugphase ab dem Abwurf umfaßt, dadurch gekennzeichnet, daß sie folgendes enthält:
- Mittel zum Halten des Projektils in einer um einen Winkel a gegenüber der Horizontalen geneigten Rollstellung im Verlauf der Tragphase und derAbschußphase, wobei diese Mittel dazu bestimmt sind, zu diesem Zweck mit entsprechenden Mitteln der Trägerrakete zusammenzuwirken; und
- Mittel zum Halten des Projektils in einer gegenüber der Horizontalen geneigten Rollstellung im Verlauf der autonomen Flugphase.
2. Projektil nach Anspruch 1, dadurch gekennzeichnet, daß die Mittel zum Halten des Projektils in einer geneigten Rollstellung im Verlauf der autonomen Flugphase Mittel zum Erfassen einervorbestimmten Abweichung da zwischen dem tatsächlichen Wert des Neigungswinkels des Tragwerks und dem vorgesehenen Wert a und Mittel für eine Korrektur dieser Abweichung enthalten, die von den Erfassungsmitteln gesteuert werden.
3. Projektil nach Anspruch 2, dadurch gekennzeichnet, daß die Mittel zum Erfassen einer Abweichung durch ein Schwungrad (14) gebildet sind, das zwei Seiten besitzt und als Achse die Achse des Projektils aufweist, wobei das Schwungrad ein in einer Radialebene r in einem Abstand d von der Achse angeordnetes Durchgangsloch (15) enthält; durch
- zwei fest mit dem Projektil verbundene Lichtquellen (16), die eine erste Seite des Schwungrades beleuchten und in einem Abstand d von der Achse des Projektils sowie in Radialebenen angeordnet sind, die zwischen sich einen Winkel bilden, der gleich dem doppelten des vorbestimmten Werts d ist;
- zwei Photozellen (17), die zu den Lichtquellen bezüglich des Schwungrades symmetrisch vorgesehen sind; und
- zurückziehbare Mittel zum Halten des Schwungrades in einer Stellung, in der die Radialebene r des Durchgangsloches (15) einen Winkel d mit jeder der durch die Photozellen (17) und die Lichtquellen (16) hindurchgehenden Radialebenen bildet.
4. Projektil nach Anspruch 2, dadurch gekennzeichnet, daß die Rollkorrekturmittel durch einen Druckgasvorrat (18) gebildet sind, der durch Leitungen (19) mit Umfangsdüsen (20) verbunden ist, wobei das Öffnen und das Schließen des Vorrats durch wenigstens ein Elektroventil (21) gesteuert ist.
5. Projektil nach Anspruch 2, dadurch gekennzeichnet, daß die Rollkorrekturmittel durch kleine Kanonen (22) gebildet sind, die imstande sind, im Fall eines Zündens Rückstoßkräfte zu erzeugen, die als Gegenrollimpuls nutzbar sind.
6. Projektil nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß es überdies ein Starttriebwerk (8, 9) enthält.
7. Projektil nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß das Schwanzleitwerk (5) frei um seine Längsachse drehbar angebracht ist.
8. Projektil nach Anspruch 6, dadurch gekennzeichnet, daß das Schwanzleitwerk (5) und das Starttriebwerk (8, 9) eine Einheit bilden, die frei um die Längsachse des Projektils drehbar angebracht ist.
9. Projektil nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, daß das Tragwerk (4) und das Schwanzleitwerk (5) ausfahrbar sind.
10. Projektil nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, daß das Flugtriebwerk dazu bestimmt ist, das Projektil bei einer vorbestimmten Geschwindigkeit V zu halten, und daß bei dieser Geschwindigkeit V die Komponente (fz) des dem um den Rollwinkel geneigten Projektil auferlegten Lastvielfachen das Gewicht des Projektils aufhebt.
11. Projektil nach einem der Ansprüche 1 bis 10, dadurch gekennzeichnet, daß es elektromagnetische oder Infrarot-Ablenkmittel enthält.
12. Projektil nach Anspruch 11, dadurch gekennzeichnet, daß es aus drei Abschnitten aufgebaut ist, einem die Ablenkmittel enthaltenden Vorderabschnitt (1), einem das Tragwerk (4) enthaltenden mittleren Abschnitt (2) und einem den Antriebsteil und das Schwanzleitwerk enthaltenden hinteren Abschnitt (3).
EP19910402521 1990-09-28 1991-09-23 Einrichtung zur Verleihung einer Flugbahnabweichung an einen aus einem Fluggerät abgeschossenen Flugkörper Expired - Lifetime EP0482970B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9011990 1990-09-28
FR9011990A FR2667390B1 (fr) 1990-09-28 1990-09-28 Procede et dispositif pour imprimer une trajectoire inflechie lateralement a un projectile lance a partir d'un engin aerien.

Publications (2)

Publication Number Publication Date
EP0482970A1 EP0482970A1 (de) 1992-04-29
EP0482970B1 true EP0482970B1 (de) 1995-05-03

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EP19910402521 Expired - Lifetime EP0482970B1 (de) 1990-09-28 1991-09-23 Einrichtung zur Verleihung einer Flugbahnabweichung an einen aus einem Fluggerät abgeschossenen Flugkörper

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EP (1) EP0482970B1 (de)
DE (1) DE69109443T2 (de)
FR (1) FR2667390B1 (de)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0004215D0 (en) * 2000-02-24 2000-04-12 Demole Frederic J Heavy load traction system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3952970A (en) * 1974-08-28 1976-04-27 The United States Of America As Represented By The Secretary Of The Navy Means for improving rocket missile accuracy
US4389028A (en) * 1976-01-14 1983-06-21 The United States Of America As Represented By The Secretary Of The Navy Flat trajectory projectile
US4453426A (en) * 1980-08-29 1984-06-12 The United States Of America As Represented By The Secretary Of The Navy Pivotal mono wing cruise missile with wing deployment and fastener mechanism
GB2226624B (en) * 1987-12-12 1991-07-03 Thorn Emi Electronics Ltd Projectile

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DE69109443D1 (de) 1995-06-08
DE69109443T2 (de) 1995-09-14
EP0482970A1 (de) 1992-04-29
FR2667390A1 (fr) 1992-04-03
FR2667390B1 (fr) 1995-01-27

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