EP0482970A1 - 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
EP0482970A1
EP0482970A1 EP91402521A EP91402521A EP0482970A1 EP 0482970 A1 EP0482970 A1 EP 0482970A1 EP 91402521 A EP91402521 A EP 91402521A EP 91402521 A EP91402521 A EP 91402521A EP 0482970 A1 EP0482970 A1 EP 0482970A1
Authority
EP
European Patent Office
Prior art keywords
projectile
roll
projectile according
tail
angle
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
EP91402521A
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English (en)
French (fr)
Other versions
EP0482970B1 (de
Inventor
Jean Deffayet
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
Original Assignee
Thomson Brandt Armements SA
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Filing date
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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Publication of EP0482970B1 publication Critical patent/EP0482970B1/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
    • 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 method and a device for laterally bending the trajectory of the projectile relative to the direction of fire.
  • 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, to be credible, evolves within limits of which the aircraft is capable. This implies, among other things, that the rocket is launched along the trajectory of the aircraft, and that after launch, its relative speed with respect to it remains low, in practice of the order of 20 m / s. Under these conditions, the gap between the rocket and the plane does not grow quickly, 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 another method for printing a projectile laterally deflected trajectory in a controlled manner after firing, as well as means for its implementation, which have the advantage of being simple, and therefore inexpensive, and to be easily applicable to the launching of a decoy rocket.
  • the method according to the invention is characterized in that it consists in providing that the projectile is provided with a lift wing, and that when launched from a vehicle in flight, said wing lift of the projectile is inclined transversely, so that the load factor has a horizontal component causing a lateral displacement of the projectile.
  • the airfoil is then calculated so that for the cruising speed of the projectile, the vertical component of the load factor cancels gravity.
  • the projectile shown 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 deployable wing system, 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 propulsion section 3 comprises two separate 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 for 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 may 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 thruster 8.9 then no longer having any reason for being.
  • Means are provided to ensure the positioning of the rocket on the ramp in a determined position of rotation about its longitudinal axis, and also to maintain 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 made in the inner wall of the tube.
  • the rotational position of the rocket on the launching ramp defines a determined angle ⁇ 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 aircraft 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 which 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, 0z) for a transverse tilt angle ⁇ equal to 45 °.
  • the projections f y 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.
  • Va (airplane speed) 300 m / s
  • ⁇ 17.5 °
  • the value of the transverse angle of inclination ⁇ can be chosen within a range limited below by the need to obtain a sufficient lateral deviation, and above 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 propellant cruise 10, 11, and a part 3b in the form of a cylindrical block mounted to rotate freely, by means of bearings 12, around the part 3a.
  • Part 3b comprises the take-off thruster 8.9, as well as means for installing 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 and 9 illustrate means by which signals are produced when these deviations reach a determined value d ⁇ in one or the other 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 separated by the value d ⁇ 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 d ⁇ 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 cannons 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 ⁇ of transverse inclination of the lift wing are obviously much greater than for the case of a decoy rocket. .

Landscapes

  • 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)
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 true EP0482970A1 (de) 1992-04-29
EP0482970B1 EP0482970B1 (de) 1995-05-03

Family

ID=9400755

Family Applications (1)

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

Country Status (3)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6682054B2 (en) * 2000-02-24 2004-01-27 Frederic Jean-Pierre Demole Acceleration system

Citations (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
GB2226624A (en) * 1987-12-12 1990-07-04 Thorn Emi Electronics Ltd Projectile.

Patent Citations (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
GB2226624A (en) * 1987-12-12 1990-07-04 Thorn Emi Electronics Ltd Projectile.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6682054B2 (en) * 2000-02-24 2004-01-27 Frederic Jean-Pierre Demole Acceleration system

Also Published As

Publication number Publication date
EP0482970B1 (de) 1995-05-03
FR2667390B1 (fr) 1995-01-27
DE69109443T2 (de) 1995-09-14
FR2667390A1 (fr) 1992-04-03
DE69109443D1 (de) 1995-06-08

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