WO1994010527A1 - Procede de guidage d'un missile et son dispositif de mise en ×uvre - Google Patents

Procede de guidage d'un missile et son dispositif de mise en ×uvre Download PDF

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Publication number
WO1994010527A1
WO1994010527A1 PCT/RU1993/000187 RU9300187W WO9410527A1 WO 1994010527 A1 WO1994010527 A1 WO 1994010527A1 RU 9300187 W RU9300187 W RU 9300187W WO 9410527 A1 WO9410527 A1 WO 9410527A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas
ρaκeτy
ρulya
force
control
Prior art date
Application number
PCT/RU1993/000187
Other languages
English (en)
Russian (ru)
Inventor
Ivan Ivanovich Arkhangelsky
Sergei Pavlovich Belyavsky
Evgeny Georgievich Bolotov
Petr Dmitrievich Grushin
Yury Gavrilovich Kaloshin
Vladimir Yakovlevich Mizrokhi
Viktor Pavlovich Mikheev
Vladimir Grigorievich Svetlov
Grigory Andreevich Stanevsky
Original Assignee
Arkhangelsky Ivan I
Belyavsky Sergei P
Bolotov Evgeny G
Grushin Petr D
Yury Gavrilovich Kaloshin
Vladimir Yakovlevich Mizrokhi
Viktor Pavlovich Mikheev
Vladimir Grigorievich Svetlov
Grigory Andreevich Stanevsky
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
Application filed by Arkhangelsky Ivan I, Belyavsky Sergei P, Bolotov Evgeny G, Grushin Petr D, Yury Gavrilovich Kaloshin, Vladimir Yakovlevich Mizrokhi, Viktor Pavlovich Mikheev, Vladimir Grigorievich Svetlov, Grigory Andreevich Stanevsky filed Critical Arkhangelsky Ivan I
Publication of WO1994010527A1 publication Critical patent/WO1994010527A1/fr

Links

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
    • F42B10/64—Steering by movement of flight surfaces of fins
    • 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 control system is known to be, for example, self-propelled, with the result of a healthy, non-existent, healthy
  • a disadvantage of the indicated method is the absence of an effective control of the pitch to the vessel, and thereby the generation of the waste gas is consumed.
  • E ⁇ ⁇ g ⁇ anichenie not ⁇ zv ⁇ lyae ⁇ is ⁇ lz ⁇ va ⁇ s ⁇ s ⁇ b for u ⁇ avleni mal ⁇ gaba ⁇ i ⁇ nymi ⁇ a ⁇ e ⁇ ami, ⁇ s ⁇ benns ⁇ i ve ⁇ i ⁇ aln ⁇ m s ⁇ a ⁇ e, ⁇ gda for ⁇ bes ⁇ echeniya ne ⁇ b ⁇ dim ⁇ g ⁇ for ⁇ e ⁇ e ⁇ va ⁇ a tsel ⁇ mal ⁇ gs v ⁇ emeni ⁇ ea ⁇ tsii and ⁇ adiusa ⁇ azv ⁇ a ⁇ ebuyu ⁇ sya b ⁇ lshie u ⁇ avlya- guides ⁇ ea ⁇ ivnye force.
  • the regulation of reactive and aerodynamic forces at a value and a sign is carried out by a single through the movement of vehicles.
  • the total magnitude of the control force changes at the angle of the angle of inclination of the ruler, reaching the maximum value of the angle of inclination of it at an angle of ⁇ 10 °.
  • the gas source may be either in the form of a gas accumulator of pressure, or in the form of a gas generator of liquid with a high momentum or a high momentum - 4 -
  • the proposed method for fixing a launcher is illustrated by the fact that there is a rapid merging of a project 5 on the target after a 1-3 page.
  • the process of deletion of the rocket terminates after information is disclosed to zero in the sale of the rocket by the pitch, the smoke and the crankshaft after the engine is running.
  • ⁇ n ⁇ s ⁇ - de ⁇ zhi ⁇ bl ⁇ u ⁇ avleniya is ⁇ chni ⁇ gas I, in zy ⁇ lnenny Vila ⁇ ze ⁇ d ⁇ livn ⁇ gs gaz ⁇ gene ⁇ a ⁇ a in ⁇ u- ce 2 ⁇ a ⁇ e ⁇ y with gaz ⁇ v ⁇ l ⁇ m 3 za ⁇ anchivayuschimsya ⁇ dvizhn ⁇ y ge ⁇ me ⁇ i- zi ⁇ uyuschey v ⁇ ul ⁇ y 4 ⁇ as ⁇ l ⁇ zhennym ⁇ ⁇ a ⁇ zhe in ⁇ use ⁇ a ⁇ e ⁇ y 2 ae ⁇ dinamiches ⁇ y ⁇ ul 5 ⁇ syu 6 ⁇ ulevym ⁇ iv ⁇ d ⁇ m 7 ⁇ snaschen- ny ⁇ gaz ⁇ s ⁇ uyn ⁇ m ⁇ as ⁇ edeli ⁇ elem, imeyushih two ⁇ len ⁇ b ⁇ az
  • the gas outlet (Fig. 9) is of the _ 6 - missiles and are separated by a transitive ⁇ (fig. 6, 7, b).
  • the shell of the rocket has a protective erosion-proof casing II (6. 6. 6. 7. b).
  • the gas starts to be sold in a predominant way in one of the gas lines (as shown in Fig. 7 - the gas inlet is exhausted and the resultant is an exhausted product). and, on the other hand, that aerodynamic class is for. 25
  • the effective force achieves a maximum when combining all of the primary and secondary rotations with an angle of ull to the side of the cooler ⁇ 10 °.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)

Abstract

Un procédé de guidage d'un missile utilise une combinaison de pousée de réaction et de commande aérodynamique. Une fois le missile lancé par le lanceur et avant l'allumage du moteur de croisière, les écarts entre l'assiette voulue et l'assiette réelle du missile en termes d'inclinaison longitudinale, de direction et d'inclinaison latérale sont déterminés, et tout écart rencontré est éliminé par la production d'une poussée de commande orientée dans le même sens que la force aérodynamique, à l'aide de la pleine puissance du jet de pousée s'écoulant perpendiculairement à la face latérale de la surface de commande, et dont l'ampleur et la direction sont régulées par réglage de l'angle de la surface de commande. Le moteur de croisière est allumé une fois tout écart éliminé. Le dispositif de mise en ÷uvre de ce procédé comprend: une unité de commande, une source (1) de gaz séparé doté de conduits (3) d'alimentation en gaz, des surfaces (5) de commande aérodynamique présentant des organes de commande (7) et doté de répartiteurs de flux de gaz munis de tuyères (9), ces dernières étant montées dans le corps de la surface de commande (5); deux des tuyères (9) sont perpendiculaires à la face latérale de la surface de commande (5), et les parties tuyères sont à 180° les unes par rapport aux autres et reliées par l'intermédiaire des manchons angulaires (8) des répartiteurs de flux de gaz aux ouvertures d'admission divisées par un diaphragme, et situées sur la face terminale inférieure de la surface de commande (5) adjacente au corps (2) du missile. Les axes de l'ouverture de sortie du conduit (3) d'alimentation en gaz ainsi que les tuyères d'admission du répartiteur du flux de gaz sont décalés par rapport à l'axe de rotation (6) de la surface de commande.
PCT/RU1993/000187 1992-10-23 1993-08-06 Procede de guidage d'un missile et son dispositif de mise en ×uvre WO1994010527A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU92001916/23 1992-10-23
RU92191623 1992-10-23

Publications (1)

Publication Number Publication Date
WO1994010527A1 true WO1994010527A1 (fr) 1994-05-11

Family

ID=20135207

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU1993/000187 WO1994010527A1 (fr) 1992-10-23 1993-08-06 Procede de guidage d'un missile et son dispositif de mise en ×uvre

Country Status (1)

Country Link
WO (1) WO1994010527A1 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3041015A (en) * 1957-03-08 1962-06-26 Snecma Aircraft controls
US3286956A (en) * 1965-07-19 1966-11-22 Douglas Aircraft Co Inc Missile control system
US3637167A (en) * 1969-11-05 1972-01-25 Mc Donnell Douglas Corp Missile steering system
US4044970A (en) * 1975-08-08 1977-08-30 General Dynamics Corporation Integrated thrust vector aerodynamic control surface
DE3227336A1 (de) * 1982-07-22 1984-02-02 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Steuereinrichtung fuer flugkoerper
EP0244971A2 (fr) * 1986-05-09 1987-11-11 LUCAS INDUSTRIES public limited company Dispositif de pilotage pour missile
US4913379A (en) * 1988-02-23 1990-04-03 Japan as represented by Director General, Technical Research and Development Institute, Japan Defence Agency Rocket flight direction control system
FR2659733A1 (fr) * 1990-03-14 1991-09-20 Aerospatiale Systeme pour le pilotage d'un missile au moyen de tuyeres laterales.
FR2659734A1 (fr) * 1990-03-14 1991-09-20 Aerospatiale Systeme pour le pilotage d'un missile au moyen de jets gazeux lateraux.

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3041015A (en) * 1957-03-08 1962-06-26 Snecma Aircraft controls
US3286956A (en) * 1965-07-19 1966-11-22 Douglas Aircraft Co Inc Missile control system
US3637167A (en) * 1969-11-05 1972-01-25 Mc Donnell Douglas Corp Missile steering system
US4044970A (en) * 1975-08-08 1977-08-30 General Dynamics Corporation Integrated thrust vector aerodynamic control surface
DE3227336A1 (de) * 1982-07-22 1984-02-02 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Steuereinrichtung fuer flugkoerper
EP0244971A2 (fr) * 1986-05-09 1987-11-11 LUCAS INDUSTRIES public limited company Dispositif de pilotage pour missile
US4913379A (en) * 1988-02-23 1990-04-03 Japan as represented by Director General, Technical Research and Development Institute, Japan Defence Agency Rocket flight direction control system
FR2659733A1 (fr) * 1990-03-14 1991-09-20 Aerospatiale Systeme pour le pilotage d'un missile au moyen de tuyeres laterales.
FR2659734A1 (fr) * 1990-03-14 1991-09-20 Aerospatiale Systeme pour le pilotage d'un missile au moyen de jets gazeux lateraux.

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