EP0447284A1 - Raketensteuerungsanlage mit seitlichem Gasstrahl - Google Patents

Raketensteuerungsanlage mit seitlichem Gasstrahl Download PDF

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Publication number
EP0447284A1
EP0447284A1 EP91400521A EP91400521A EP0447284A1 EP 0447284 A1 EP0447284 A1 EP 0447284A1 EP 91400521 A EP91400521 A EP 91400521A EP 91400521 A EP91400521 A EP 91400521A EP 0447284 A1 EP0447284 A1 EP 0447284A1
Authority
EP
European Patent Office
Prior art keywords
nozzles
shutter
gas
nozzle
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.)
Granted
Application number
EP91400521A
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English (en)
French (fr)
Other versions
EP0447284B1 (de
Inventor
Jean-Pierre Morgand
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.)
Airbus Group SAS
Original Assignee
Airbus Group 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
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0447284A1 publication Critical patent/EP0447284A1/de
Application granted granted Critical
Publication of EP0447284B1 publication Critical patent/EP0447284B1/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
    • F42B10/66—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.
  • 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 controlled shutter is determined, without oscillations, by the corresponding controlled jack, the uncontrolled jacks taking a position determined by the distribution of said incompressible fluid.
  • 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 system comprises two pairs of lateral nozzles, the two nozzles of a pair being diametrically opposite and the nozzles of one pair being arranged in a radial plane perpendicular to the radial plane containing the nozzles of the other pair, at most, one shutter of each pair of nozzles is controlled simultaneously with a shutter of the other pair of nozzles.
  • the two shutters of a pair of nozzles are controlled by the same motor.
  • 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.
  • FIGS. 4 and 5 schematically illustrate the actuating means of each shutter member.
  • FIG. 6 schematically illustrates an application of the actuation means of FIGS. 4 and 5 to the control of four shutter members, two by two diametrically opposite.
  • FIG. 7 is a diagram illustrating the operation of the system of FIG. 6.
  • Figure 8 shows the electrical control diagram of the system in Figure 6.
  • FIG. 9 shows a variant of the control system of FIG. 6.
  • FIGS. 10a and 10b are diagrams illustrating the operation of the device in FIG. 9.
  • 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 tail sections 4.
  • the wings 3 and the tail sections 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 at number of four and they are two to two diametrically opposite, the planes of two consecutive tail units 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 type controlled operation, it can 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 that they emit exert forces on the missile whose result is zero; thus, in this case, the shutter members 14 of the two opposite nozzles are constantly partially 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 1-1, parallel to the axis L-L of the missile, mounted relative to the rigid block 15 on low friction bearings 21, for example bearings.
  • Each shutter member 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 1-1 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, facing 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 said nozzle necks 11.
  • the faces curved lateral 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 1-1 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 large load factor to which the missile 1 is subjected during force piloting maneuvers, deformations which would cause perburbations Operating.
  • each shutter member 14 is associated with a jack 30, the piston 31 of which is connected to the shaft 20 of said member 14 by a mechanical connection 32, comprising, in the 'example shown, a radial arm 33, integral in rotation with said shaft 20 around the axis 1-1, and a link 34, respectively articulated at 35 and 36 on said arm 33 and on the rod 37 of said piston 31.
  • the piston 31 divides the interior of the cylinder 38 of the jack 30 into two chambers 38a and 38b.
  • the chamber 38b opens a conduit 39, introducing an incompressible fluid under pressure intended to push the piston 31 towards the chamber 38a, capable of communicating a position to the piston 31, such that the closure member 14 then closes the neck 11 of the nozzle 8 (see FIG. 4).
  • the piston 31 can come to bear against a stop 40, provided in the chamber 38a and delimiting the minimum volume which 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 38a open an intake duct 41 of calibrated section and an exhaust duct 42 of modular section.
  • the intake duct 41 receives 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 38a.
  • 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 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.
  • a member 46 for example a rotary potentiometer, is linked to the shaft 20, for example by means of a gear 47 linked to the shaft of said potentiometer and a circular rack 48, centered on the axis 1 -1 and integral with the radial arm 33, for measuring the rotational position of said shutter member 14.
  • the system of FIGS. 4 and 5, used for each nozzle 8 of the missile 1, makes it possible to pilot said missile by force.
  • the chamber 38a corresponds to the large driving section of the piston 31 and therefore that, on the side of the chamber 38b, the surface of the piston 31 is smaller than on the side of the room 38a. This is obtained thanks to the presence of the piston rod 37.
  • the position of the shutter member 14 relative to the nozzle neck 11 results from the balance of forces between the piston and the corresponding shutter.
  • FIG 6 there is shown schematically the application of the system of Figures 4 and 5, piloting a missile 1 provided with four nozzles, two in two diametrically opposite and distributed at 90 ° around the axis LL of said missile .
  • each nozzle 8.i is associated with a closure member 14.i, a cylinder 30.i, the piston 31 of which is connected to the corresponding closure member 14.i by a link 32.i, and a position measuring device 46.i.
  • a single motor 45 is associated for two diametrically opposite nozzles: this is how the motor 45.13 controls the shutter members 14.1 and 14.3, respectively associated with nozzles 8.1 and 8.3, while the motor 45.24 controls the closure members 14.2 and 14.4, respectively associated with the nozzles 8.2 and 8.4.
  • Each of these motors 45.13 and 45.24 is for example a linear motor of the type described in patent FR-A-2 622 066, comprising an elongated core 50 movable in translation parallel to itself.
  • a ball 44 is carried by each end of the core 50, in order to be able to cooperate with the funnels 43 associated with the exhaust conduits 42 of the cylinders 30.1 and 30.3, or 30.2 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.
  • conduits 39 of the four cylinders 30.1 to 30.4 are interconnected, the hydraulic fluid trapped in the conduits 39 and in the chambers 38b of the cylinders 30.i being under pressure.
  • the overall gas discharge section through the four pairs of nozzle 8 - shutter 14, fixed by the volume of the incompressible hydraulic fluid comprised between the four jacks 30.1 to 30.4 , is chosen equal to the complete opening of a neck 11 of nozzle 8.
  • two shutter members 14 assume controlled opening positions, which are a function of the controls, while the other two shutter members assume identical partial shutter positions , because of the equal distribution of said incompressible hydraulic fluid in the circuit of the chambers 38b and of the conduits 39.
  • the overall opening of the two closed shutters corresponds at most to the complete opening of a single shutter, when the two other shutter members are closed, each of said members then being able to release at most half of the corresponding nozzle neck, configuration which is shown in FIG. 2.
  • the vertices of square 51 are on the axis of the nozzles 8.1, 8.2, 8.3 and 8.4 and they correspond to the maximum thrusts F1M, F2M, F3M and F4M likely to be supplied by each of said nozzles, when the other three are completely closed , each of these maximum thrusts being equal to the thrust P capable of being delivered by the generator 9.
  • the circle 52 of radius P which corresponds to a homogeneous theoretical distribution of the thrust of the generator 9 around the LL axis. We see that to get closer to this theoretical distribution and therefore further optimize the system of the invention, it is advantageous to increase the number of pairs of diametrically opposite nozzles, so that the square 51 is transformed into an inscribed polygon, according closer to said circle 52.
  • calculation means 53 intended to control the motors 45.13 and 45.24 to obtain, for the piloting in force of the missile 1, any desired transverse thrust, registered in the square 51
  • the calculation means 53 receive (from a control device not shown), the intensity and the orientation of this desired thrust. Referring also to FIG. 7, it is assumed that this intensity must be equal to f and that the orientation is given by the angle ⁇ made by said thrust with respect to the axis of the nozzle 8.1.
  • F1, F2, F3 and F4 the transverse thrusts, respectively due to the nozzles 8.1 to 8.4.
  • the calculation means 53 therefore have a system of four equations with four unknowns and they calculate F1, F2, F3 and F4 from f, ⁇ and P. They then issue orders to the motors 45.13 and 45.24, which respectively control cylinders 30.1 to 30.4. These in turn, through the shutters 14.1 to 14.4, move the position measuring devices 46.1 to 46.4. The measurements of these are representative of the opening of said shutter members and therefore of the thrusts actually controlled F1 to F4, so that said measurements are addressed to the calculation means 53 which can thus control the proper execution of their orders.
  • a reserve 55 of incompressible fluid capable of being connected to the circuit 39 is also provided, through a distributor 56.
  • the reserve 55 has for example the form of a jack whose piston 57 is subjected to a pressure, for example by virtue of a part of the gases coming from the generator 9.
  • a pressure for example by virtue of a part of the gases coming from the generator 9.
  • an orifice 58 allows the entry of said gases.
  • the piston 57 is pressed towards the distributor 56 and pressurizes the incompressible fluid contained in the jack 55.
  • the distributor 56 in addition to its connection 59 to the reserve 55 has a connection 60 to the circuit 39 and an orifice 61 to the exhaust.
  • the distributor 56 isolates the reserve 55 from the circuit 39.
  • the distributor 56 is in a position for which, the reserve 55 can introduce incompressible fluid into the circuit 39.
  • the distributor makes it possible to connect the circuit 39 with the exhaust 61.
  • the reserve 55 associated with the distributor 56, makes it possible to ensure a constant volume of incompressible fluid in the circuit 39, over a wide range of temperatures.
  • this speed can be reduced, by exhausting through the distributor 56, when said generator 9 operating, we are in a piloting phase requiring no transverse thrust of piloting in force.
  • the distributor 56 is controlled by the output 62 of the computer 53.

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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)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Nozzles (AREA)
EP91400521A 1990-03-14 1991-02-26 Raketensteuerungsanlage mit seitlichem Gasstrahl Expired - Lifetime EP0447284B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9003253A FR2659734B1 (fr) 1990-03-14 1990-03-14 Systeme pour le pilotage d'un missile au moyen de jets gazeux lateraux.
FR9003253 1990-03-14

Publications (2)

Publication Number Publication Date
EP0447284A1 true EP0447284A1 (de) 1991-09-18
EP0447284B1 EP0447284B1 (de) 1993-09-08

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EP91400521A Expired - Lifetime EP0447284B1 (de) 1990-03-14 1991-02-26 Raketensteuerungsanlage mit seitlichem Gasstrahl

Country Status (8)

Country Link
US (1) US5123611A (de)
EP (1) EP0447284B1 (de)
JP (1) JP3199764B2 (de)
AU (1) AU631970B2 (de)
CA (1) CA2037939C (de)
DE (1) DE69100339T2 (de)
ES (1) ES2044692T3 (de)
FR (1) FR2659734B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2730303A1 (fr) * 1995-02-03 1996-08-09 Loral Vought Systems Corp Procede pour changer rapidement la direction de deplacement d'un vehicule, notamment d'un missile et machine pour sa mise en oeuvre
FR2767382A1 (fr) * 1997-08-14 1999-02-19 Bayern Chemie Gmbh Flugchemie Dispositif de commande de poussee transversale pour missiles, comportant un generateur de gaz chauds a matiere solide
US6308911B1 (en) 1998-10-30 2001-10-30 Lockheed Martin Corp. Method and apparatus for rapidly turning a vehicle in a fluid medium

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WO1994010527A1 (en) * 1992-10-23 1994-05-11 Arkhangelsky Ivan I Method of steering a missile and device for carrying out the same
US5505408A (en) * 1993-10-19 1996-04-09 Versatron Corporation Differential yoke-aerofin thrust vector control system
US6254031B1 (en) * 1994-08-24 2001-07-03 Lockhead Martin Corporation Precision guidance system for aircraft launched bombs
FR2730302B1 (fr) * 1995-02-03 1997-03-14 Tda Armements Sas Controle d'un projectile par impulseur multi-chambre et mono-tuyere
US5662290A (en) * 1996-07-15 1997-09-02 Versatron Corporation Mechanism for thrust vector control using multiple nozzles
US6752351B2 (en) * 2002-11-04 2004-06-22 The United States Of America As Represented By The Secretary Of The Navy Low mass flow reaction jet
US7416154B2 (en) * 2005-09-16 2008-08-26 The United States Of America As Represented By The Secretary Of The Army Trajectory correction kit
US7851732B2 (en) * 2006-03-07 2010-12-14 Raytheon Company System and method for attitude control of a flight vehicle using pitch-over thrusters
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
US8362408B2 (en) * 2009-10-22 2013-01-29 Honeywell International Inc. Steerable projectile charging system
US10717550B1 (en) 2011-03-09 2020-07-21 United Launch Alliance, L.L.C. Integrated vehicle fluids
US8884202B2 (en) 2011-03-09 2014-11-11 United Launch Alliance, Llc Integrated vehicle fluids
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
US8975565B2 (en) * 2012-07-17 2015-03-10 Raytheon Company Integrated propulsion and attitude control system from a common pressure vessel for an interceptor
US9068808B2 (en) * 2013-01-17 2015-06-30 Raytheon Company Air vehicle with bilateral steering thrusters
KR101681992B1 (ko) 2015-02-13 2016-12-02 국방과학연구소 연동 메커니즘을 적용한 다축 핀틀 추력기 시스템
DE102017102160A1 (de) * 2016-02-05 2017-08-10 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Vorrichtung und System zur Steuerung von Flugkörpern und Kill-Vehicles, die mit gelförmigen Treibstoffen betrieben wird
US10718294B1 (en) 2017-10-27 2020-07-21 United Launch Alliance, L.L.C. Integrated vehicle fluids
RU2767645C1 (ru) * 2020-10-19 2022-03-18 Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации Зенитная управляемая ракета 9м96

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DE2743371A1 (de) * 1976-10-04 1978-04-13 Ford Aerospace & Communication Kombiniertes heissgas-servosteuersystem fuer ruder und rueckstoss bei flugkoerpern
EP0064433A1 (de) * 1981-04-21 1982-11-10 Thomson-Brandt Armements Lenkbarer Flugkörper
US4531693A (en) * 1982-11-29 1985-07-30 Societe Nationale Industrielle Et Aerospatiale System for piloting a missile by means of lateral gaseous jets and missile comprising such a system

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US3136250A (en) * 1962-05-04 1964-06-09 Samuel A Humphrey Integrated auxiliary power unit
US3721402A (en) * 1971-06-25 1973-03-20 Us Army Missile roll control mechanism
FR2538098B1 (fr) * 1982-12-17 1987-11-20 Thomson Brandt Dispositif de pilotage par jets de gaz lateraux
FR2620812B1 (fr) * 1987-09-18 1992-04-17 Thomson Brandt Armements Dispositif de commutation de jets de gaz lateraux destine au pilotage d'engins
FR2622066B1 (fr) * 1987-10-16 1995-08-25 Rossi Rinaldo Machine electrique a entrefers radiaux
FR2659733B1 (fr) * 1990-03-14 1994-07-01 Aerospatiale Systeme pour le pilotage d'un missile au moyen de tuyeres laterales.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2743371A1 (de) * 1976-10-04 1978-04-13 Ford Aerospace & Communication Kombiniertes heissgas-servosteuersystem fuer ruder und rueckstoss bei flugkoerpern
EP0064433A1 (de) * 1981-04-21 1982-11-10 Thomson-Brandt Armements Lenkbarer Flugkörper
US4531693A (en) * 1982-11-29 1985-07-30 Societe Nationale Industrielle Et Aerospatiale System for piloting a missile by means of lateral gaseous jets and missile comprising such a system

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2730303A1 (fr) * 1995-02-03 1996-08-09 Loral Vought Systems Corp Procede pour changer rapidement la direction de deplacement d'un vehicule, notamment d'un missile et machine pour sa mise en oeuvre
FR2779246A1 (fr) * 1995-02-03 1999-12-03 Loral Vought Systems Corp Procede et systeme pour changer rapidement la direction de deplacement d'un vehicule se deplacant dans un milieu fluide
USRE37331E1 (en) 1995-02-03 2001-08-14 Lockheed Martin Corporation Dual-control scheme for improved missile maneuverability
FR2767382A1 (fr) * 1997-08-14 1999-02-19 Bayern Chemie Gmbh Flugchemie Dispositif de commande de poussee transversale pour missiles, comportant un generateur de gaz chauds a matiere solide
US6308911B1 (en) 1998-10-30 2001-10-30 Lockheed Martin Corp. Method and apparatus for rapidly turning a vehicle in a fluid medium

Also Published As

Publication number Publication date
JP3199764B2 (ja) 2001-08-20
AU631970B2 (en) 1992-12-10
CA2037939A1 (fr) 1991-09-15
FR2659734B1 (fr) 1992-07-03
AU7137191A (en) 1991-09-19
DE69100339T2 (de) 1994-01-27
US5123611A (en) 1992-06-23
CA2037939C (fr) 2000-11-28
FR2659734A1 (fr) 1991-09-20
ES2044692T3 (es) 1994-01-01
JPH04227495A (ja) 1992-08-17
DE69100339D1 (de) 1993-10-14
EP0447284B1 (de) 1993-09-08

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