EP0447283B1 - Raketensteuerungsanlage mit seitlichem Düsen - Google Patents

Raketensteuerungsanlage mit seitlichem Düsen Download PDF

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Publication number
EP0447283B1
EP0447283B1 EP91400520A EP91400520A EP0447283B1 EP 0447283 B1 EP0447283 B1 EP 0447283B1 EP 91400520 A EP91400520 A EP 91400520A EP 91400520 A EP91400520 A EP 91400520A EP 0447283 B1 EP0447283 B1 EP 0447283B1
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EP
European Patent Office
Prior art keywords
nozzles
nozzle
gas
stopper
missile
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.)
Expired - Lifetime
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EP91400520A
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English (en)
French (fr)
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EP0447283A1 (de
Inventor
Jean-Pierre Morgand
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Airbus Group SAS
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Airbus Group SAS
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Publication of EP0447283A1 publication Critical patent/EP0447283A1/de
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Publication of EP0447283B1 publication Critical patent/EP0447283B1/de
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    • 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 present invention relates to a system for piloting a missile by means of lateral gas jets and a missile comprising such a system.
  • transverse forces can pass at points on the axis of the missile different from the center of gravity. Said transverse forces then create, in a manner similar to conventional aerodynamic control surfaces, moments allowing the missile to be controlled in attitude with respect to the center of gravity.
  • each of said nozzles is associated with an individual rotary shutter, itself individually controlled by an oscillator. Thanks to this structure, each rotary shutter can have a low inertia, so that the response time of the shutter means, and therefore of the control, can be very low.
  • each nozzle is associated with a rotary shutter and said shutters are controlled in rotation by a piston sharing a jack in two chambers of different sections, said chambers each receiving a part of the gas generated by said gas generator and the position of said piston being controlled by controlling the flow rate of said gas through the chamber of larger section, the two shutters being linked to each other by a mechanical connection such that , when a shutter rotates with a tendency to close the associated nozzle, the other shutter rotates, of the same angular amplitude, with a tendency to release the associated nozzle.
  • the object of the present invention is a system of the type mentioned above having, at the same time, shutters with low inertia and a shutter control without oscillations.
  • each shutter can have a low inertia, and the positioning of each shutter is determined, without oscillations, both by the corresponding jack, and by the action of said mechanical connection.
  • Such a joint can be of any known type, for example with a ball joint or a roller rolling in a slot and said mechanical connection is preferably disposed away from the gas flows emitted by the gas generator.
  • each connecting rod is integral in rotation with the shaft of the corresponding shutter and, at its end opposite to said articulation with the other connecting rod, each connecting rod is articulated to the piston of the corresponding jack.
  • each nozzle has an oblong section, at least in the vicinity of its neck cooperating with a shutter.
  • each obturator can be constituted by a shaft secured to a projecting radial pallet, the longitudinal end face of which cooperates with the neck of the corresponding nozzle.
  • the lateral face of the radial vane, facing the neck of the nozzle in the open position of said shutter is concave and curved.
  • said shutters are mounted in a rigid block integral with the structure of said missile.
  • said nozzles are formed in wings of said missile secured to the skin thereof, it is advantageous for the feet of said nozzles to be nested with sliding friction in said rigid block. Thus, the deformations of said nozzles are decoupled from the rest of the missile.
  • Control of the gas flow through a jack is preferably obtained using a linear motor moving a ball, in a flare provided on the circuit of said gas flow.
  • the shutters of the two nozzles are controlled by the same motor.
  • each nozzle comprises a gas stilling chamber, connected to said nozzle, on the opposite side of said neck, by a throttle such that the gas flow inside said nozzle is subsonic.
  • a device for measuring the pressure in each stilling chamber.
  • Figure 1 is a schematic view of an exemplary embodiment of the missile according to the invention, with partial cutaway.
  • FIG. 2 is a partial cross-section, on a larger scale, of the missile according to the invention, along line II-II of FIG. 1.
  • FIG. 3 is a partial longitudinal section of the missile according to the invention, the left and right parts of this figure corresponding respectively to lines III-III and III'-III 'of FIG. 2.
  • FIG. 4 schematically illustrates the means of actuation of each shutter member, said shutter members being in the middle position.
  • FIG. 5 shows an exemplary embodiment of the mechanical coupling connection between said shutter members, in elevation with cutaway and partial section.
  • Figure 6 is a section along line VI-VI of Figure 5.
  • Figure 7 is a view similar to Figure 4, one of the shutter members being completely closed and the other completely open.
  • FIG. 8 schematically shows the application of the system according to the invention to a missile comprising two pairs of nozzles, in longitudinal and orthogonal planes.
  • FIG. 9 shows an alternative embodiment of the control system of FIG. 8.
  • the exemplary embodiment of the missile 1 according to the invention shown diagrammatically in FIGS. 1 to 3, comprises an elongated body 2 of axis LL provided with wings 3 and empennages 4.
  • the wings 3 and the empennages 4 are provided with control surfaces 5 and 6, respectively.
  • the wings 3 are four in number and they are two to two diametrically opposite, the planes of two consecutive wings being orthogonal to each other and passing through the axis LL.
  • the empennages 4 are four in number and they are two to two diametrically opposite, the planes of two consecutive empennages being orthogonal to each other and passing through the axis LL.
  • the tail units 4 are located in the bisector planes of the wings 3.
  • a force piloting device 7 controlling four nozzles 8, two in two diametrically opposite and arranged in the wings 3.
  • the nozzles 8 are placed in the vicinity of the combustion chamber of a gas generator 9, for example with solid propellant, and are connected to said generator 9, by conduits 10.
  • the nozzles 8 can be connected to the conduits 10 through an inlet orifice 11 and they open to the outside through an outlet orifice 12, of larger section than the inlet orifice 11, said orifices 11 and 12 being connected by a divergent 13.
  • the outlet orifices 12 are located at the longitudinal edge 3a of the wings 3, so that the gas jets passing through the nozzles 8 are separated from the body 2 of the missile and only interfere little with the aerodynamic flow around the skin 2a of said body 2.
  • each of the nozzles 8 is equipped, at its inlet 11, with a shutter or rotary shutter 14 (not shown in FIG. 1) making it possible to close off or at least partially clear the corresponding nozzle 8.
  • the action of the force control device 7 is not necessarily necessary, because then the missile 1 can be piloted in a conventional manner thanks to its aerodynamic control surfaces 5 and 6. Consequently, if the gas generator 9 is of the controlled operation type, it may be stopped. If the gas generator 9 is of the continuous operating type, the shutter members 14 of two opposite nozzles are controlled so that the gas jets which they emit exert forces on the missile, the result of which is nothing ; in this case, as will be seen below, the shutter members 14 of the two opposite nozzles are constantly half open to allow the gases produced by the generator 9 to escape.
  • the nozzles 8 have the shape of a flattened funnel.
  • the outlet 12 is oblong, the large dimension of its section being parallel to the longitudinal axis L-L of the missile 1, while the small dimension of this section is transverse to said axis L-L. This small transverse dimension is advantageously constant and the ends of the outlet orifice 12 can be rounded.
  • the inlet or neck 11 located on the inner side of the missile 1, is also oblong, of constant width and with rounded ends.
  • the section of said neck 11 is similar to that of the outlet orifice 12, but smaller than that of the latter.
  • the divergent 13 is connected to the two orifices 11 and 12 by a regulated surface.
  • the section ratio necessary to sufficiently relax the combustion gases coming from the generator 9 is largely obtained by determining the respective lengths of the orifices 11 and 12.
  • the lateral control jets have the form of plies having a small frontal dimension for aerodynamic flow.
  • the interactions between said lateral control jets and said aerodynamic flow are, if not totally eliminated, at least even more reduced, so that the aerodynamic elements 3, 4, 5 and 6 can continue to fulfill their function by cooperating with the aerodynamic flow, even when the lateral control jets are used at their maximum power.
  • the force control device 7 is composed of two parts 7a and 7b, namely a part 7a in which the shutter members 14 are mounted and a part 7b intended for controlling the said elements obturation organs.
  • Part 7a of the force control device 7 comprises a central rigid block 15, coaxial with the axis LL and forming a housing inside which the movable closure members 14 are disposed.
  • the rigid block 15 is rigidly connected to the internal structure of the body 2 of the missile 1 by end rings 16, 17.
  • This rigid block 15 is hollow and has an internal recess 18 in communication with the conduits 10 by peripheral openings 19.
  • the rigid block 15 has other peripheral openings, forming the nozzle necks 11 and in communication with the internal recess 18, depending on the obturation members 14.
  • the rotary shutter members 14 each comprise a shaft 20 of axis ll, parallel to the axis LL of the missile, mounted relative to the rigid block 15 on low friction bearings 21, for example bearings.
  • Each organ shutter 14 comprises a radial pallet 22, integral with the corresponding shaft 20 and projecting outwardly relative to the latter.
  • the outer longitudinal face 22a of the radial vanes 22 cooperates with the corresponding nozzle neck 11 either to close the latter (see the position of the shutter members 14 from the left and from above in FIG. 2), or to release at least partially said nozzle neck 11 (see the position of the shutter members 14 on the right and at the bottom in FIG. 2).
  • the shutter members 14 When the shutter members 14 are in this shutter position, they isolate the internal recess 18 of the nozzles 8 and therefore the latter from the conduits 10. On the other hand, when the shutter members 14 are in their release position necks 11, they put the nozzles 8 in communication with the conduits 10, through said nozzle necks 11, the internal recess 18 and the peripheral openings 19.
  • the axes l-l of the shutter members 14 are respectively arranged in the median longitudinal plane of the nozzles 8.
  • the lateral face 22b of the pallets 22, opposite the nozzle necks 11 in the open position of said closure members 14, is concave and curved, profiled to form with the internal wall 18a of the internal recess 18 a convergent in the direction of said nozzle necks 11.
  • the curved lateral faces 22a serve as bearing faces for the setting in speed of the gases and report the depression generated at a distance from the axes of rotation ll of the shutter members 14.
  • each closure member 14 has very little rotational inertia and maneuvering movement, so as to obtain a very short response time with a power of minimum order. It is thus seen that, thanks to such an embodiment of the shutter members 14, these have a very low inertia, which allows them to have a very reduced response time, and limit the torque which is opposed at the opening of the nozzle necks, which avoids having to provide complex compensation systems.
  • the outer face 22a of the closure members 14 has a minimum clearance relative to the internal wall 18a of the block 15, in order to reduce leaks in the closed position, while allowing the expansions caused by the high temperature of the gases. , for example when these come from a gas generator 9 of the powder type.
  • the choice of the constituent materials of the block 15 and of the shutter members 14, as well as the choice of their shape can also contribute to the minimization of friction: for example, carbon or molybdenum is used, protected or not by coatings or sleeves thermal protection.
  • the feet 8a of the nozzles 8 are fitted into indentations 23, of corresponding shape, provided in the external wall of the rigid block 15, so that the connection between said said nozzles 8 and said rigid block 15 is of the sliding adjustment type.
  • the nozzles 8, which are integral with the skin 2a of the body 2 can follow the deformations thereof.
  • the deformations between the internal rigid structure of the missile 1 and the external skin 2a of the body 2 are thus dissociated, due in part to the significant load factor to which the missile 1 is subjected during the force piloting maneuvers, deformations which would cause operating disturbances.
  • FIG 4 there is shown a pair of opposite nozzles 8, respectively bearing the references 8.1 and 8.2 and associated with respective shutters 14.1 and 14.2. Similarly, the devices respectively associated with said nozzles 8.1 and 8.2 have the same references assigned indices 1 or 2 respectively.
  • each closure member 14.1 or 14.2 is associated with a cylinder 30.1 or 30.2, the piston 31 of which is connected to said member 14.1 or 14.2 for example by a rod 34, respectively articulated at 35 and 36 on said closure member 14.1 or 14.2 and on the rod 37 of said piston 31.
  • each cylinder 30.1 or 30.2 divides the interior of the corresponding cylinder 38 into two chambers 38a and 38b of different sections.
  • a conduit 39 for example connected to a conduit 10, introducing the pressure of the generator 9 and tending to push the piston 31 towards the chamber 38b of larger section, possibly up to a position such that the shutter member 14.1 or 14.2 then seals the neck 11 of the corresponding nozzle 8.1 or 8.2.
  • the piston 31 can come to bear against a stop 40, provided in the chamber of larger section 38b and delimiting the minimum volume that the latter can occupy.
  • an intake duct 41 of calibrated section and an exhaust duct 42 of modular section In this minimum volume of the chamber of larger section 38b of a cylinder 30.1 or 30.2 open an intake duct 41 of calibrated section and an exhaust duct 42 of modular section.
  • the intake duct 41 receives, like the duct 39, a portion, for example of the order of 1%, of the gas flow generated by the generator 9 by being for example connected to a duct 10.
  • the exhaust duct 42 is vented, for example by being connected to the outside of the missile 1, so that a slight pressure po prevails in the chamber of larger section 38b.
  • the free end of the latter is extended by a part 43 flared in a funnel and a refractory ball 44 is provided so as to be able to move inside said flared part 43, in the axis thereof.
  • a motor 45.1 or 45.2 for example a linear electric motor, is provided for such displacement of said ball 44. It can be seen that with such a device, ball 44 is automatically centered relative to conduit 42 in the closed position.
  • the positions of the shutter members 14.1 or 14.2 do not depend solely on the pressures prevailing in the chambers 38a and 38b of the jacks 30.1 and 30.2, because said shutter members are mechanically coupled to each other in rotation by a mechanical link 50, which is shown diagrammatically in FIG. 4, but an exemplary embodiment of which is illustrated by FIGS. 5 and 6.
  • said mechanical connection 50 comprises a connecting rod 51, integral in rotation with the shaft 20 of the shutter member 14.1, and a connecting rod 52, integral in rotation with the shaft 20 of the shutter member 14.2, said connecting rods 51 and 52 being directed towards one another and articulated to one another.
  • the connecting rod 52 comprises a yoke 53 in which is engaged one end 54 of the connecting rod 51.
  • This end 54 is pierced with an oblong opening 55, in which a roller 56 can be rolled, rotatably mounted around an axis 57, integral with the connecting rod 52 and passing through the yoke 53, said axis 57 being parallel to the axes ll of the shafts 20.
  • the connecting rods 51 and 52 are articulated respectively on the connecting rods 34 associated with the jacks 30.1 and 30.2 by articulations 35, represented in the form of 'ball joint.
  • the oblong opening 55 and the roller 56 form, between the connecting rods 51 and 52, an articulation whose axis 57 is capable of moving longitudinally relative to the connecting rod 51, when said connecting rods rotate with the associated shafts 20 .
  • the two motors 45.1 and 45.2 are in their neutral position for which their respective balls 44 are spaced from the funnel 43 with which they cooperate and at equal distance from them, the sections exhaust of the two conduits 42 are identical, so that in the chambers 38b of large section of the cylinders 30.1 and 30.2 prevails the same pressure, equal to the value po defined above. Furthermore, the chambers 38a of small section of the jacks 30.1 and 30.2 receive the same pressure of gas coming from the generator 9, so that, in these chambers also, the same pressure prevails, equal to that of the gas stream derived from the conduits 10.
  • FIG. 8 the application of the system of FIGS. 4 and 7 is shown diagrammatically, for piloting a missile 1 provided with four nozzles, two with two diametrically opposite and distributed at 90 ° around the axis LL of said missile .
  • the nozzles 8.3 and 8.4 are associated respectively with closure members 14.3 and 14.4 and jacks 30.3 and 30.4.
  • the shutter members 14.1 and 14.2 are coupled by the mechanical link 50.12, while the shutter members 14.3 and 14.4 are linked by the mechanical link 50.34.
  • the mechanical connections 50.12 and 50.34 are similar to the connection 50, described above. They intersect in the vicinity of their articulation, and that is why they have a central recess 60 (see FIG. 6).
  • each pair of shutter members 14.1-14.2 and 14.3-14.4 is associated with a position measuring member of one of said shutter members, bearing the references 61.12 and 61.34 respectively.
  • These position measuring members can be of the potentiometer type and they are intended to communicate, when controlling the shutter members (not shown), the exact position reached by said shutter members. It will be noted that, because of the mechanical connections 50.12 and 50.34. each position measuring member 61.12 and 61.34 delivers signals representative, at the same time, of the positions of the two associated shutter members.
  • a single motor 45 is associated for two diametrically opposite nozzles: this is how the motor 45.12 controls the shutter members 14.1 and 14.2, respectively associated with the nozzles 8.1 and 8.2, while the motor 45.34 controls the shutter members 14.3 and 14.4, respectively associated with the nozzles 8.3 and 8.4.
  • Each of these motors 45.12 and 45.34 is for example a linear motor of the type described in patent FR-A-2 622 066, comprising an elongated core 62 movable in translation parallel to itself.
  • a ball 44 is carried by each end of the core 62, in order to be able to cooperate with the funnels 43 associated with the exhaust conduits 42 of the jacks 30.1 and 30.2, or 30.3 and 30.4, corresponding, so that when a ball 44 approaches its associated funnel, the other ball 44 moves away from its own and vice versa.
  • the position of the balls 44 can be such that the force provided by a piston 31 is equal to the torque which tends to close each shutter member 14.
  • the connections mechanical 50 which guarantee operating safety, are little used.
  • these mechanical connections 50 arranged in part 7b of the system, are outside the gas flows (passing through part 7a), so that they are subjected to moderate temperatures.
  • the rollers 56 can have the shape of a barrel, so that the mechanical connections 50 tolerate reverse bending.
  • the servo-control in transverse thrust of piloting can be done, in known manner, by a feedback loop (not shown) ensuring the measurement of the position of each pair of shutter members, using members 61.12 and 61.34 . Operation can be stabilized by regulating the speed of the motors 45, fitted for this purpose with tachometric generators (not shown), over the difference between the positions requested and achieved.
  • a gas stilling chamber 63 is provided between the nozzle necks 11 and said nozzles 8, these stilling chambers 63 themselves being connected to the nozzles 8 by a constriction 64 of section known, one can ensure that the gas flow in said nozzles is subsonic. By measuring, using devices 65, the pressure in each chamber 63, it is easy to determine the thrust of each nozzle 8 and the resulting value per pair of nozzles.

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  • 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)
  • Nozzles (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Claims (14)

  1. System zur Steuerung eines Flugkörpers mittels seitlicher Gasstrahlen, mit einem Gasgenerator (9), der mittels rotierenden Absperrmittel (14), welche unter der Einwirkung von Bewegungsmitteln (30)beweglich sind und den Durchfluß der Gase durch die besagten Düsen steuern, mit mindestens einem Paar seitlicher Düsen (8) verbunden werden kann, wobei jede Düse (8) mit einem rotierenden Verschluß (14) verbunden ist und die besagten Verschlüsse (14) in der Drehung durch einen Kolben (31), der einen Zylinder (30) in zwei Kammern (38a, 38b) mit verschiedenen Querschnitten teilt, gesteuert werden, wobei jede der besagten Kammern einen Teil des vom Gasgenerator (9) erzeugten Gases erhält und die Stellung des besagten Kolbens durch die Kontrolle des Durchflusses des besagten Gases durch die Kammer mit dem größten Querschnitt (38b) gesteuert wird, wobei die beiden Verschlüsse (14) über eine mechanische Verbindung (50) so miteinander verbunden sind, daß, wenn ein Verschluß sich dreht, um die damit verbundene Düse zu verschließen, der andere Verschluß sich um die gleiche Winkelamplitude dreht, mit dem Bestreben, die damit verbundene Düse freizugeben,
    dadurch gekennzeichnet, daß
    - jedem einzelnen Verschluß (14) ein solcher Zylinder (30) zugeordnet ist, wobei die Kontrolle der besagten Durchflüsse durch die Kammern mit großem Querschnitt der beiden Zylinder eines seitlichen Düsenpaares so gestaltet ist, daß in einem gewissen Augenblick nur einer der besagten Durchflüsse verringert werden kann, eventuell bis zur vollständigen Schließung; und
    - die besagte mechanische Verbindung (50) zwei jeweils in Drehung mit einem Verschluß (14) fest verbundene Pleuelstangen (51, 52) enthält, wobei besagte Pleuelstangen über ihre sich gegenüberliegenden freien Enden mittels eines Gelenkes (55, 56, 57), dessen Achse sich der Länge nach in Bezug auf eine der besagten Pleuelstangen bewegen kann, miteinander verbunden sind.
  2. System nach Anspruch 1,
    dadurch gekennzeichnet, daß die besagte mechanische Verbindung (59) in einem gewissen Abstand der vom besagten Gasgenerator (9) ausgestrahlten Gasströme angeordnet ist.
  3. System nach einem der Ansprüche 1 oder 2,
    dadurch gekennzeichnet, daß jede Pleuelstange in Drehung fest mit der Welle (20) des entspechenden Verschlusses (14) verbunden ist, und daß mit ihrem dem besagten Gelenk mit der anderen Pleuelstange gegenüberliegenden Ende jede Pleuelstange an den Kolben (31) des entsprechenden Zylinders (30) angelenkt ist.
  4. System nach dem Anspruch 3, für ein sich diametral gegen-überliegendes Düsenpaar,
    dadurch gekennzeichnet, daß in neutraler Stellung die beiden Anlenkungen (35) der Pleuelstangen an die besagten Zylinder und die Gelenke zwischen den besagten Pleuelstangen fluchten und daß die beiden Verschlüsse (14) die entsprechenden Düsen halb verschließen.
  5. System nach irgend einem der Ansprüche 1 bis 4,
    dadurch gekennzeichnet, daß wenigstens in Höhe ihres Halses (11), der mit einem Verschluß (14) zusammenwirkt, jede Düse (8) einen länglichen Querschnitt aufweist.
  6. System nach dem Anspruch 5,
    dadurch gekennzeichnet, daß jeder Verschluß eine Welle (20) enthält, die mit einem herausragenden radialen Flügel (22) fest verbunden ist, dessen äussere Langsfläche (22a) mit dem Hals (11) der entsprechenden Düse (8) zusammenwirkt.
  7. System nach Anspruch 6,
    dadurch gekennzeichnet, daß die Seitenfläche (22b) des radialen Flügels (22) gegenüber dem Hals (11) der Düse (8) in offener Stellung des besagten Verschlusses (14) konkav und gebogen ist.
  8. System nach einem der Ansprüche 1 bis 7,
    dadurch gekennzeichnet, daß die besagten Verschlüsse in einem mit der Struktur des besagten Flugkörpers (1) fest verbundenen starren Block (15) montiert sind.
  9. System nach dem Anspruch 8, in welchem die besagten Düsen (8) in den Flügeln (3) des besagten Flugkörpers untergebracht sind, die mit der Haut (2a) desselben fest verbunden sind,
    dadurch gekennzeichnet, daß die Füße (8a) der besagten Düsen (8) mit gleitender Reibung in den besagten starren Block (15) eingefaßt sind.
  10. System nach einem der Ansprüche 1 bis 9,
    dadurch gekennzeichnet, daß die Kontrolle des Gasdurchflusses durch einen Zylinder mittels eines Linearmotors (45) erreicht wird, welcher eine Kugel (44) in einer im Kreislauf des besagten Gasflusses vorgesehenen Erweiterung (43) bewegt.
  11. System nach Anspruch 10,
    dadurch gekennzeichnet, daß die Verschlüsse der beiden Düsen durch den selben Motor (45.12 oder 45.34) gesteuert werden.
  12. System nach einem der Ansprüche 1 bis 11,
    dadurch gekennzeichnet, daß unterhalb ihres Halses (11), der mit dem entsprechenden Rotationsverschluß (14) zusammenwirkt, jede Düse (8) eine Gasberuhigungskammer (63) enthaält, die mit der besagten Düse, auf der dem besagten Hals (11) gegenüberliegenden Seite, über eine Drosselung (64) verbunden ist, so daß der Gasfluß innerhalb der besagten Düse subsonisch ist.
  13. System nach dem Anspruch 12,
    dadurch gekennzeichnet, daß eine Meßvorrichtung (65) vorgesehen ist, zur Messung des Druckes in jeder Beruhigungskammer (63).
  14. Flugkörper, dadurch gekennzeichnet, daß er ein Steuersystem nach irgend einem des Ansprüche 1 bis 13 enthält.
EP91400520A 1990-03-14 1991-02-26 Raketensteuerungsanlage mit seitlichem Düsen Expired - Lifetime EP0447283B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR909003252A FR2659733B1 (fr) 1990-03-14 1990-03-14 Systeme pour le pilotage d'un missile au moyen de tuyeres laterales.
FR9003252 1990-03-14

Publications (2)

Publication Number Publication Date
EP0447283A1 EP0447283A1 (de) 1991-09-18
EP0447283B1 true EP0447283B1 (de) 1993-10-06

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EP91400520A Expired - Lifetime EP0447283B1 (de) 1990-03-14 1991-02-26 Raketensteuerungsanlage mit seitlichem Düsen

Country Status (8)

Country Link
US (1) US5074492A (de)
EP (1) EP0447283B1 (de)
JP (1) JP3181930B2 (de)
AU (1) AU631969B2 (de)
CA (1) CA2038091C (de)
DE (1) DE69100454T2 (de)
ES (1) ES2046862T3 (de)
FR (1) FR2659733B1 (de)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2659734B1 (fr) * 1990-03-14 1992-07-03 Aerospatiale Systeme pour le pilotage d'un missile au moyen de jets gazeux lateraux.
WO1994010527A1 (en) * 1992-10-23 1994-05-11 Arkhangelsky Ivan I Method of steering a missile and device for carrying out the same
FR2699610B1 (fr) * 1992-12-22 1995-02-10 Aerospatiale Dispositif d'actionnement d'un organe mécanique, notamment pour le pilotage en force d'un missile, et missile équipé dudit dispositif.
US6254031B1 (en) * 1994-08-24 2001-07-03 Lockhead Martin Corporation Precision guidance system for aircraft launched bombs
US5631830A (en) 1995-02-03 1997-05-20 Loral Vought Systems Corporation Dual-control scheme for improved missle maneuverability
US6308911B1 (en) 1998-10-30 2001-10-30 Lockheed Martin Corp. Method and apparatus for rapidly turning a vehicle in a fluid medium
US7287725B2 (en) * 2005-04-25 2007-10-30 Raytheon Company Missile control system and method
US7856806B1 (en) * 2006-11-06 2010-12-28 Raytheon Company Propulsion system with canted multinozzle grid
US7872215B2 (en) * 2008-02-29 2011-01-18 Raytheon Company Methods and apparatus for guiding a projectile
US8269156B2 (en) 2008-03-04 2012-09-18 The Charles Stark Draper Laboratory, Inc. Guidance control system for projectiles
US8117847B2 (en) 2008-03-07 2012-02-21 Raytheon Company Hybrid missile propulsion system with reconfigurable multinozzle grid
US8338768B2 (en) 2008-10-15 2012-12-25 Honeywell International Inc. Actuation assembly
US8362408B2 (en) * 2009-10-22 2013-01-29 Honeywell International Inc. Steerable projectile charging system
FR2980265B1 (fr) * 2011-09-21 2017-02-24 Mbda France Systeme pour le pilotage d'un engin volant a l'aide de paires de tuyeres laterales
RU2485342C1 (ru) * 2012-02-20 2013-06-20 Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации Силовой блок двигательной установки ракеты-носителя
US9068808B2 (en) * 2013-01-17 2015-06-30 Raytheon Company Air vehicle with bilateral steering thrusters
KR102134354B1 (ko) * 2020-04-16 2020-07-15 국방과학연구소 화염 차단 장치 및 이를 포함하는 유도 무기

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2620812A1 (fr) * 1987-09-18 1989-03-24 Thomson Brandt Armements Dispositif de commutation de jets de gaz lateraux destine au pilotage d'engins

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3136250A (en) * 1962-05-04 1964-06-09 Samuel A Humphrey Integrated auxiliary power unit
US4085909A (en) * 1976-10-04 1978-04-25 Ford Motor Company Combined warm gas fin and reaction control servo
FR2504252B1 (fr) * 1981-04-21 1987-03-06 Thomson Brandt Projectile guide
FR2536720A1 (fr) * 1982-11-29 1984-06-01 Aerospatiale Systeme pour le pilotage d'un missile au moyen de jets gazeux lateraux et missile comportant un tel systeme
FR2538098B1 (fr) * 1982-12-17 1987-11-20 Thomson Brandt Dispositif de pilotage par jets de gaz lateraux
FR2622066B1 (fr) * 1987-10-16 1995-08-25 Rossi Rinaldo Machine electrique a entrefers radiaux

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2620812A1 (fr) * 1987-09-18 1989-03-24 Thomson Brandt Armements Dispositif de commutation de jets de gaz lateraux destine au pilotage d'engins

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DE69100454D1 (de) 1993-11-11
JPH04222399A (ja) 1992-08-12
DE69100454T2 (de) 1994-03-03
US5074492A (en) 1991-12-24
AU7136991A (en) 1991-09-19
JP3181930B2 (ja) 2001-07-03
CA2038091A1 (fr) 1991-09-15
EP0447283A1 (de) 1991-09-18
AU631969B2 (en) 1992-12-10
CA2038091C (fr) 2000-08-29
FR2659733A1 (fr) 1991-09-20
ES2046862T3 (es) 1994-02-01
FR2659733B1 (fr) 1994-07-01

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