EP2876405B1 - Missile guidé et procédé de guidage d'un missile guidé - Google Patents

Missile guidé et procédé de guidage d'un missile guidé Download PDF

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Publication number
EP2876405B1
EP2876405B1 EP14003885.2A EP14003885A EP2876405B1 EP 2876405 B1 EP2876405 B1 EP 2876405B1 EP 14003885 A EP14003885 A EP 14003885A EP 2876405 B1 EP2876405 B1 EP 2876405B1
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EP
European Patent Office
Prior art keywords
drive
guided missile
missile
thrust
longitudinal axis
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.)
Active
Application number
EP14003885.2A
Other languages
German (de)
English (en)
Other versions
EP2876405A1 (fr
Inventor
Ludwig Netter
Harald Wasner
Thomas Gallhauser
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.)
MBDA Deutschland GmbH
Original Assignee
MBDA Deutschland GmbH
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Publication date
Application filed by MBDA Deutschland GmbH filed Critical MBDA Deutschland GmbH
Priority to PL14003885T priority Critical patent/PL2876405T3/pl
Publication of EP2876405A1 publication Critical patent/EP2876405A1/fr
Application granted granted Critical
Publication of EP2876405B1 publication Critical patent/EP2876405B1/fr
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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
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/661—Steering by varying intensity or direction of thrust using several transversally acting rocket motors, each motor containing an individual propellant charge, e.g. solid charge
    • 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
    • F42B10/66—Steering by varying intensity or direction of thrust
    • F42B10/663—Steering by varying intensity or direction of thrust using a plurality of transversally acting auxiliary nozzles, which are opened or closed by valves

Definitions

  • the longitudinal axis can be aligned to a velocity vector of the missile such that the first thrust of the first drive generates a predefined transverse acceleration perpendicular to the velocity vector. Since a direction of the first thrust deviates from the direction of a current speed of the guided missile by the orientation of the guided missile, the first thrust can be dismantled into a longitudinal thrust component and into a transverse thrust component.
  • the method is carried out with the following additional steps: First, an angle of attack between the longitudinal axis and the velocity vector is determined, which is necessary for the first thrust of the first drive to generate the specified lateral acceleration. This is possible in particular by trigonometric calculation, since the first thrust of the first drive and the lateral acceleration are known. Subsequently, the second drive is at least partially activated, so that the missile occupies the specific angle of attack. This is done in particular by a suitable control of the second drive.
  • the guided missile is additionally configured in such a way that it has an aerodynamic control unit. Therefore, it is the missile in particular possible to switch between aerodynamic steering and steering by interaction of the first drive and the second drive.

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)

Claims (8)

  1. Missile guidé (1), présentant un axe longitudinal (2) et comprenant au moins un premier propulseur (3), au moyen duquel une première poussée (100) peut être générée le long de l'axe longitudinal (2), et un second propulseur (2), au moyen duquel une seconde poussée (200) peut être générée perpendiculairement à l'axe longitudinal (2), le missile guidé (1) étant configuré pour commander le second propulseur (4), lorsque le premier propulseur (3) est activé, de telle manière que le missile guidé (1) peut être guidé, le centre de gravité (5) du missile guidé (1) se trouvant entre le premier propulseur (3) et le second propulseur (4) et que la commande du second propulseur (4) permet d'orienter l'axe longitudinal (2) par rapport à un vecteur de vitesse (300) du missile guidé (1) de telle manière que la première poussée (100) du premier propulseur (3) génère une accélération transversale (400) prédéfinie perpendiculairement au vecteur de vitesse (300), caractérisé en ce que le premier propulseur (3) est un groupe moteur à double impulsion, une durée de fonctionnement minimale du second propulseur (4) correspondant au moins à une durée de fonctionnement maximale d'une seconde impulsion du groupe moteur à double impulsion, et en ce que le groupe moteur à double impulsion peut être activé et désactivé plusieurs fois.
  2. Missile guidé (1) selon la revendication 1, caractérisé en ce que le missile guidé (1) peut être guidé uniquement par le premier propulseur (3) et le second propulseur (4) .
  3. Missile guidé (1) selon l'une des revendications précédentes, caractérisé en ce que le second propulseur ( 4 ) présente un écart prédéfini par rapport au centre de gravité (5) du missile guidé.
  4. Missile guidé (1) selon l'une des revendications précédentes, caractérisé en ce que le second propulseur (4) comprend des tuyères de poussée, qui sont disposées de préférence de manière cartésienne.
  5. Missile guidé (1) selon l'une des revendications précédentes, caractérisé en ce qu'une durée de fonctionnement minimale du second propulseur (4) correspond au moins à une durée de fonctionnement maximale du premier propulseur (3), la durée de fonctionnement du second propulseur (4) correspondant en particulier à celle du premier propulseur (3).
  6. Missile guidé (1) selon l'une des revendications précédentes, caractérisé en ce que la durée de fonctionnement du second propulseur (4) correspond à la durée de fonctionnement de la seconde impulsion du groupe moteur à double impulsion.
  7. Procédé de commande d'un missile guidé (1) selon l'une des revendications 1 à 6, dans lequel le missile guidé présente un axe longitudinal (2) et comprend un premier propulseur (3), au moyen duquel une première poussée (100) peut être générée le long de l'axe longitudinal (2) et comprend un second propulseur (4), au moyen duquel une seconde poussée (200) peut être générée perpendiculairement à l'axe longitudinal (2), le centre de gravité (5) du missile guidé (1) se trouvant entre le premier propulseur (3) et le second propulseur (4), le premier propulseur (3) étant un groupe moteur à double impulsion, une durée de fonctionnement minimale du second propulseur (4) correspondant au moins à une durée de fonctionnement maximale d'une seconde impulsion du groupe moteur à double impulsion, et le groupe moteur à double impulsion pouvant être activé et désactivé plusieurs fois, comprenant les étapes consistant à :
    - activer le premier propulseur (3),
    - orienter le missile guidé (1) au moyen de l'activation au moins partielle du second propulseur (4), en particulier parallèlement au fonctionnement du premier propulseur (3)
    - définir une accélération transversale (400) perpendiculaire à un vecteur de vitesse (300) du missile guidé (1), que le missile guidé (1) doit adopter, et
    - orienter l'axe longitudinal (2) du missile guidé (1) par rapport au vecteur de vitesse (300) du missile guidé (1) au moyen de l'activation au moins partielle du second propulseur (4), en particulier parallèlement au fonctionnement du premier propulseur (3), de sorte que la première poussée (100) du premier propulseur génère l'accélération transversale (400) définie.
  8. Procédé selon la revendication 7, comprenant les étapes supplémentaires consistant à :
    - déterminer un angle d'incidence (10) entre l'axe longitudinal (2) et le vecteur de vitesse (300), ledit angle d'incidence étant nécessaire pour que la première poussée (100) du premier propulseur (3) génère l'accélération transversale (400) définie, et
    - activer au moins partiellement le second propulseur (4), en particulier parallèlement au fonctionnement du premier propulseur (3), de telle manière que le missile guidé (1) adopte l'angle d'incidence (10) déterminé.
EP14003885.2A 2013-11-20 2014-11-19 Missile guidé et procédé de guidage d'un missile guidé Active EP2876405B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL14003885T PL2876405T3 (pl) 2013-11-20 2014-11-19 Pocisk kierowany oraz sposób naprowadzania pocisku kierowanego

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102013019342 2013-11-20
DE102014004251.0A DE102014004251A1 (de) 2013-11-20 2014-03-24 Lenkflugkörper und Verfahren zum Lenken eines Lenkflugkörpers

Publications (2)

Publication Number Publication Date
EP2876405A1 EP2876405A1 (fr) 2015-05-27
EP2876405B1 true EP2876405B1 (fr) 2018-01-10

Family

ID=52020884

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14003885.2A Active EP2876405B1 (fr) 2013-11-20 2014-11-19 Missile guidé et procédé de guidage d'un missile guidé

Country Status (4)

Country Link
EP (1) EP2876405B1 (fr)
DE (1) DE102014004251A1 (fr)
ES (1) ES2665370T3 (fr)
PL (1) PL2876405T3 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016101560A1 (de) * 2016-01-28 2017-08-03 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Querschubeinrichtung zur aktiven Bahn- und Lagesteuerung von Flugkörpern

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2822755A (en) * 1950-12-01 1958-02-11 Mcdonnell Aircraft Corp Flight control mechanism for rockets
US3749334A (en) * 1966-04-04 1973-07-31 Us Army Attitude compensating missile system
DE2809281C2 (de) * 1978-03-03 1984-01-05 Emile Jean Versailles Stauff Steuervorrichtung für ein Geschoß mit Eigendrehung
GB8803164D0 (en) * 1988-02-11 1988-08-24 British Aerospace Reaction control system
FR2684723B1 (fr) * 1991-12-10 1995-05-19 Thomson Csf Propulseur a propergol solide a poussee modulable et missile equipe.
US5631830A (en) * 1995-02-03 1997-05-20 Loral Vought Systems Corporation Dual-control scheme for improved missle maneuverability
US5590850A (en) * 1995-06-05 1997-01-07 Hughes Missile Systems Company Blended missile autopilot
DE19645562A1 (de) * 1996-04-02 1997-10-09 Bodenseewerk Geraetetech Regelvorrichtung für nichtlineare Regelstrecken
US6308911B1 (en) * 1998-10-30 2001-10-30 Lockheed Martin Corp. Method and apparatus for rapidly turning a vehicle in a fluid medium

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
PL2876405T3 (pl) 2018-07-31
ES2665370T3 (es) 2018-04-25
DE102014004251A1 (de) 2015-06-25
EP2876405A1 (fr) 2015-05-27

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