EP0952424A1 - Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses - Google Patents

Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses Download PDF

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Publication number
EP0952424A1
EP0952424A1 EP98401013A EP98401013A EP0952424A1 EP 0952424 A1 EP0952424 A1 EP 0952424A1 EP 98401013 A EP98401013 A EP 98401013A EP 98401013 A EP98401013 A EP 98401013A EP 0952424 A1 EP0952424 A1 EP 0952424A1
Authority
EP
European Patent Office
Prior art keywords
warhead
flat
trajectory
fin
rotation
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
EP98401013A
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English (en)
French (fr)
Other versions
EP0952424B1 (de
Inventor
Pascal Tarayre
Jean-Pierre Frehaut
Jean-Paul Labroche
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.)
TDA Armements SAS
Original Assignee
TDA Armements SAS
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
Priority to FR9704276A priority Critical patent/FR2761769B1/fr
Application filed by TDA Armements SAS filed Critical TDA Armements SAS
Priority to EP98401013A priority patent/EP0952424B1/de
Priority to DE1998610265 priority patent/DE69810265T2/de
Publication of EP0952424A1 publication Critical patent/EP0952424A1/de
Application granted granted Critical
Publication of EP0952424B1 publication Critical patent/EP0952424B1/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
    • F42B10/62—Steering by movement of flight surfaces

Definitions

  • the present invention relates to a micro-control device for the correction of trajectory of ammunition stabilized by rotation.
  • the deviations between the point of impact of a shell and its target are usually defined in terms of precision and accuracy errors measured in the longitudinal and transverse directions of movement of the shell.
  • the precision error corresponds to random dispersions inherent in weapon systems. This error which cannot be compensated by the aiming of the weapon intervenes mainly on the range deviations.
  • the accuracy error corresponds to identical deviations during a short time interval, it is due to atmospheric disturbances and pointing errors. This error, which can be corrected by a change in the aiming of the weapon, is characterized by both lateral and range deviations. However, a correction by simple deflection of the weapon is generally not sufficient to compensate for the effects of disturbances encountered by the shell.
  • the deployable skirt system allows to control the trajectory of the shell by increasing the drag, by opening the petals at an opportune moment of the trajectory.
  • the major drawback of this system lies in the fact that it only makes it possible to carry out a correction on the range error, the lateral deviations due to the winds and pointing errors are not corrected.
  • the duck-based system has the advantage over the previous one of correcting the range and lateral deviations by creating a force in a fixed plane by fins deflected at the front of the shell and which are decoupled in rotation.
  • the object of the invention is to overcome the aforementioned drawbacks.
  • the subject of the invention is a micro-control device for correcting the trajectory of ammunition stabilized by rotation of the type comprising a proximity rocket having a warhead movable in rotation relative to the body of the ammunition, characterized in that it includes a retractable flat on the surface of the proximity rocket to create an aerodynamic transverse force normal to the flat plane when the flat is uncovered and a deployable fin articulated on the warhead to allow a fixed stabilization of the warhead relative to fixed space markers.
  • the invention has the advantage that it makes it possible to improve both the precision and the accuracy of the shots by controlling both the drag and the lift of the shell by modifying the obliquity of balance. It also has the advantage of being able to be applied to statically unstable shells, that is to say devoid of tail, which makes them compatible with the systems for loading shells into existing guns.
  • the example of rocket architecture according to the invention which is represented in FIG. 3 comprises a warhead 1 of frustoconical shape movable in rotation about its axis of symmetry XX 'at the end 2 of an axis 3 whose another threaded end 4 is engaged at the conical front of a shell 5.
  • the rotation of the warhead 1 on the axis 3 is ensured by a rolling bearing 6.
  • the warhead 1 contains a satellite positioning system 7 still known by the abbreviation Anglo-Saxon GPS for ⁇ global positioning system ⁇ possibly associated with a vertical or horizontal indicator 8 composed for example by an inertial unit, and with a guidance system 9 with calculator for calculating and correct trajectory errors.
  • the shell of the warhead 1 is made of a material transparent to electromagnetic waves.
  • the angular position of the rocket relative to the landmarks is controlled by a fin 10 articulated along a generator of the truncated cone of the warhead deflected outside the warhead under the action a motor 11 controlled from the guidance system 9.
  • the computer is arranged not in the guidance system 9 but in the ground station and the data necessary for the correction calculation are transmitted by radio between the elements 7, 8 and 9 of the warhead 1 and the calculator.
  • the fin 10 When firing the shell, the fin 10 is wound on the surface of the fuselage and is deployed during the flight when a trajectory correction is to be made.
  • a flat 12 parallel to the axis of symmetry XX ' is formed in the fuselage opposite the fin 10.
  • the flat 12 is covered by an ejectable cover 13. It allows when the cover 13 is ejected to create a force lateral F able to modify the obliquity of the shell.
  • the cover 13 is unlocked during flight by a pyrotechnic cutter 14.
  • An electric current generator in the form of a alternator constituted by a stator 15 fixed to the warhead 1 and a rotor 16 fixed to the end of the axis 3 makes it possible to supply electricity to all of the electrical and electronic circuits of the warhead 1.
  • the operating principle of the system consists in starting from a target whose position known a priori is transmitted by radio to the guidance system, to detect via the satellite navigation system 7 or the inertial unit 8 trajectory errors sufficiently early to have time to integrate forces of small amplitudes.
  • the computer of the guidance system 9 or of the ground station gives the instant of triggering of the correction system and the correction plan.
  • the duration of the correction represents the parameter which modulates the amplitude of the correction.
  • the cover 13 is separated by centrifugal effect from the warhead 1 at the instant of the calculated triggering. It then gives way to the flat 12 which generates, by asymmetry of the resulting air flow, a lateral force F, as shown in FIG.
  • a pyrotechnic device unlocks the fin 10 before the cover 13 is ejected.
  • the fin then unfolds from the skin of the rocket by centrifugal effect around an axis of rotation 17, and is locked in the deployed position in a fixed position on this axis by means of a ball locking device for example, not shown.
  • the fin 10 thus deployed stops the rotation of the warhead 1 and makes it possible to determine the orientation to be given to the flat 12 relative to the landmarks in order to correct the trajectory.
  • the orientation of the flat 12 in one direction is controlled by the action of the fin 10 in the deployed position, which is rotated by the motor 11 around an axis 18 normal to the surface of the fuselage of the warhead 1 .
  • the efficiency of the fin 10 which thus acts like a control surface makes it possible to define the capacity of correction of the shell on its trajectory. This capacity is also directly linked to the action of the flat 12 which causes an asymmetry in the air flow in the vicinity of the shell.
  • the flow in the vicinity of the proximity rocket presents the characteristics of FIG. 5 with a shock wave indexed 2 which is generated by the plane 19 which interfaces the rocket with the body of the shell at the level of the flat part 12.
  • the compression downstream of this shock creates a bearing force and a torque reducing the distance or static margin separating the center of thrust F from the aerodynamic forces of the center of gravity as shown in Figure 9.
  • the improvement in the range accuracy is obtained by the increase in the drag induced by the two shock waves generated by the flat (shock wave 2) and the fin 10 (shock wave 3) in FIG. 5.
  • the range is increased if the lateral force F thus created is vertical and directed upwards.

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)
  • Radar Systems Or Details Thereof (AREA)
EP98401013A 1997-04-08 1998-04-24 Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses Expired - Lifetime EP0952424B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR9704276A FR2761769B1 (fr) 1997-04-08 1997-04-08 Dispositif de microgouverne pour la correction de trajectoire de munition stabilisee par rotation
EP98401013A EP0952424B1 (de) 1997-04-08 1998-04-24 Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses
DE1998610265 DE69810265T2 (de) 1998-04-24 1998-04-24 Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9704276A FR2761769B1 (fr) 1997-04-08 1997-04-08 Dispositif de microgouverne pour la correction de trajectoire de munition stabilisee par rotation
EP98401013A EP0952424B1 (de) 1997-04-08 1998-04-24 Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses

Publications (2)

Publication Number Publication Date
EP0952424A1 true EP0952424A1 (de) 1999-10-27
EP0952424B1 EP0952424B1 (de) 2002-12-18

Family

ID=26151621

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98401013A Expired - Lifetime EP0952424B1 (de) 1997-04-08 1998-04-24 Mikroleitwerkeinrichtung zur Veränderung der Flugrichtung eines rotationsstabilisierten Geschosses

Country Status (2)

Country Link
EP (1) EP0952424B1 (de)
FR (1) FR2761769B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010078221A (ja) * 2008-09-25 2010-04-08 Technical Research & Development Institute Ministry Of Defence 飛しょう体

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE511986C2 (sv) * 1995-10-06 2000-01-10 Bofors Ab Sätt att korrigera projektilbanan för rotationsstabiliserande projektiler

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3262655A (en) * 1963-12-26 1966-07-26 Jr Warren Gillespie Alleviation of divergence during rocket launch
DE3612175C1 (de) * 1986-04-11 1987-10-08 Messerschmitt Boelkow Blohm Schnellfliegender Flugkoerper
DE3815290C1 (de) * 1988-05-05 1989-08-17 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
US5322243A (en) * 1992-06-25 1994-06-21 Northrop Corporation Separately banking maneuvering aerodynamic control surfaces, system and method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3262655A (en) * 1963-12-26 1966-07-26 Jr Warren Gillespie Alleviation of divergence during rocket launch
DE3612175C1 (de) * 1986-04-11 1987-10-08 Messerschmitt Boelkow Blohm Schnellfliegender Flugkoerper
DE3815290C1 (de) * 1988-05-05 1989-08-17 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
US5322243A (en) * 1992-06-25 1994-06-21 Northrop Corporation Separately banking maneuvering aerodynamic control surfaces, system and method

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
A.R. KRIEBEL: "Missile nose slat", NAVY TECHNICAL DISCLOSURE BULLETIN, NAVY CAT. NO. 4164, NAVY CASE NO. 64310, vol. 5, no. 12, December 1980 (1980-12-01), pages 33 - 35, XP002053491 *
O. BURGDORF ET AL.: "Articulated nose missile configuration", NAVY TECHNICAL DISCLOSURE BULLETIN, NAVY CAT. NO. 4182, NAVY CASE NO. 64326, vol. 5, no. 8, August 1980 (1980-08-01), pages 19 - 23, XP002053492 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010078221A (ja) * 2008-09-25 2010-04-08 Technical Research & Development Institute Ministry Of Defence 飛しょう体

Also Published As

Publication number Publication date
FR2761769B1 (fr) 1999-07-02
EP0952424B1 (de) 2002-12-18
FR2761769A1 (fr) 1998-10-09

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