EP2876405B1 - Missile guidé et procédé de guidage d'un missile guidé - Google Patents
Missile guidé et procédé de guidage d'un missile guidé Download PDFInfo
- 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
- Authority
- 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
Links
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- 230000001133 acceleration Effects 0.000 claims description 35
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- 230000008859 change Effects 0.000 description 2
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- 230000006378 damage Effects 0.000 description 1
- 230000009849 deactivation Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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- 238000009434 installation Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
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- 230000001105 regulatory effect Effects 0.000 description 1
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Images
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)
- 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.
- 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) .
- 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.
- 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.
- 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).
- 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.
- 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.
- 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.
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)
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)
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 |
-
2014
- 2014-03-24 DE DE102014004251.0A patent/DE102014004251A1/de active Pending
- 2014-11-19 EP EP14003885.2A patent/EP2876405B1/fr active Active
- 2014-11-19 PL PL14003885T patent/PL2876405T3/pl unknown
- 2014-11-19 ES ES14003885.2T patent/ES2665370T3/es active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
DE102014004251A1 (de) | 2015-06-25 |
EP2876405A1 (fr) | 2015-05-27 |
PL2876405T3 (pl) | 2018-07-31 |
ES2665370T3 (es) | 2018-04-25 |
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