EP0064433B1 - Projectile guidé - Google Patents

Projectile guidé Download PDF

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Publication number
EP0064433B1
EP0064433B1 EP82400634A EP82400634A EP0064433B1 EP 0064433 B1 EP0064433 B1 EP 0064433B1 EP 82400634 A EP82400634 A EP 82400634A EP 82400634 A EP82400634 A EP 82400634A EP 0064433 B1 EP0064433 B1 EP 0064433B1
Authority
EP
European Patent Office
Prior art keywords
projectile
nozzles
gas
pipes
valve
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
Application number
EP82400634A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0064433A1 (fr
Inventor
Roger Crepin
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Priority to AT82400634T priority Critical patent/ATE18096T1/de
Publication of EP0064433A1 publication Critical patent/EP0064433A1/fr
Application granted granted Critical
Publication of EP0064433B1 publication Critical patent/EP0064433B1/fr
Expired 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 invention relates to a guided projectile, the flight path of which can be modified by the controlled ejection of lateral gas jets in the flight plans.
  • a guided projectile such as a missile, comprises in particular propulsion means, guidance means intended to measure the deviations from the trajectory relative to the position of the targeted target and piloting means making it possible to reduce these deviations for the purpose minimize its passing distance to the right of the target.
  • Control of the flight path of a guided projectile can be accomplished by the application of a lateral thrust force supplied by jets of material whose flow and direction can be changed.
  • a thrust force can be obtained from numerous energy sources, such as liquid propellants or compressed gases which supply suitable control means.
  • the energy source necessary for piloting in the direction and jointly with maintaining the flight speed is it constituted by a solid propellant whose combustion provides a flow of gas continued.
  • a solid propellant whose combustion provides a flow of gas continued.
  • the projectile comprises a gas generator, of the solid propellant type, which feeds a pair of diametrically opposite fixed nozzles.
  • the invention therefore relates to a projectile guided by lateral gas jets, comprising an energy source constituted by a solid propellant whose combustion provides a gas flow of substantially constant flow to a plurality of equally spaced lateral nozzles, each of these nozzles comprising a valve for regulating the flow of gas passing through, characterized in that it comprises two pairs of diametrically opposite nozzles situated respectively in two mutually orthogonal guide planes, and in which each of the adjustment valves comprises a pivoting pallet, one of which of the faces constitutes a wall of the nozzle, and in that the pallets corresponding to each pair of nozzles are secured and positioned by parallelogram mechanisms whose transverse elements are the driving elements.
  • Another object of the invention is a guided projectile, the two positioning jacks of the valves for adjusting the relative flow rate of the gas jets are mutually nested in their middle part.
  • Another object of the invention is a guided projectile in which the control means are combined with the propulsion means.
  • Another object of the invention is a guided projectile in which the total effective passage section of the nozzles is kept constant while the unitary passage section of the nozzles is modified.
  • Figure 1 relates to the prior art. It represents, in partial view, a projectile equipped with a piloting section using lateral gas jets.
  • This piloting section 1 comprises a pair of diametrically opposite fixed ejection nozzles 2 located in the piloting plane of the projectile. These ejection nozzles are supplied with gas by divergent conduits 3 whose common inlet constitutes the nozzle throat and receives a continuous flow of gas supplied by a primary source of energy.
  • the means for adjusting the relative flow rate of gases passing through the nozzles comprise a single valve positioned by a pneumatic cylinder.
  • the adjustment valve essentially comprises a pivoting vane 5, of triangular shape, articulated around an axis 6 perpendicular to the plane containing the nozzles.
  • This pivoting pallet is partially engaged in the nozzle neck 4 and its lateral faces 7 constitute one of the walls of the divergent conduits, it is provided with a lug 8 which is housed in a notch 9 formed in the piston of the jack 10.
  • the position of the jack is controlled by a servovalve 11 comprising an air inlet 12 for supply and electromagnets excited by electrical signals representative of the control commands.
  • FIG. 2 represents, in a schematic form, the basic concepts of a guided projectile according to the invention.
  • This projectile comprises, in particular, a piloting section proper, in which are arranged two pairs of fixed nozzles T 1 , T 3 and T 2 , T 4 respectively , all identical.
  • the thrust forces F 1 to F 4 supplied by the ejection nozzles converge at the same point P located on the longitudinal axis XX 'of the projectile, this point P being substantially coincident with the center of gravity G of the projectile .
  • Each pair of diametrically opposite nozzles is situated in the corresponding piloting plane, the two piloting planes being advantageously orthogonal.
  • Each of the nozzles is supplied through divergent conduits 20, of rectangular section, by a gas source (not shown) which provides a continuous gas flow resulting from the combustion of a solid propellant placed in a combustion chamber;
  • the gas source can comprise two substantially identical gas generators arranged on either side of the piloting section and operating in parallel, by means of gas conduits arranged parallel to the axis XX , of the projectile and between the nozzles.
  • Each of the four nozzles; and more precisely each of the divergent conduits 20 is provided with a valve for adjusting the flow rate of gas passing through; these valves being essentially constituted by a pivoting pallet 30, one of the lateral faces 31 of which supplies, at least partially, one of the walls of these divergent conduits.
  • the pivot axes 32 of these pallets are located in the same plane perpendicular to the longitudinal axis XX 'of the projectile.
  • the diametrically opposite pallets are physically joined by an articulated mechanism forming a deformable parallelogram whose transverse branch 40 constitutes the driving element; the longitudinal branches 41 constitute the connecting elements, the fourth branch 42, shown in dotted lines and passing through the pivot axes of the pallets, being provided by the structure itself of the projectile.
  • the ejection nozzles are inclined more or less on the longitudinal axis of the projectile, to create a thrust force F whose components provide longitudinal thrust forces F L and transverse F T allowing respectively d '' maintain the flight speed of the projectile and modify its flight direction.
  • the transverse branches 40 of the operating mechanism of the pallets are made concurrent by nesting their middle part.
  • Figures 3a to 3d show an embodiment of the piloting section of a guided projectile according to the invention.
  • the four ejection nozzles are oriented towards the rear of the projectile to provide a longitudinal thrust component and the positioning cylinders of the gas flow adjustment valves are nested in their middle part.
  • FIG. 3a represents a front view of the piloting section; this section comprises two elements: a first element 1a including the four nozzles provided with their respective valves and a second element 1b carrying the positioning cylinders of the valves.
  • FIG. 3a shows the relative positions of the two pairs of nozzles, respectively T I , T 3 and T 2 , T 4 which are arranged at the periphery of the first element 1 a of the piloting section.
  • These nozzles all identical, have a rectangular section and the divergent conduits 20 open onto convergent conduits 21 which constitute the gas flow inlets.
  • the pivot axes 32 of the pivoting pallets are located in the same plane and are parallel to the larger walls of the nozzles.
  • FIG. 3a also shows the gas passage conduits 50 ensuring the connection between the gas generators located on either side of the piloting section.
  • one of the pallets is shown in the open position and the other in the closed position; however, it should be understood that these pallets can occupy all the intermediate symmetrical positions.
  • the jack body has two gas inlets E 1 and E ' ⁇ connected to the outlet of a servovalve not shown. The pneumatic energy necessary for the operation of the cylinders can be borrowed from the gas flow supplied by the gas generators.
  • Figure 3c shows, in a sectional view, the elements that make up the control means according to the second control plane. These elements are essentially identical to those described in the previous figure, only the difference between the embodiment of the piston 40 of the pneumatic cylinder for positioning the corresponding pivoting pallets.
  • This piston 40 is a cylindrical part in the middle part of which is formed an opening 40d allowing the free translational movement of the cylindrical element 40c already described in Figure 3b.
  • the gas inlets E 2 and E ' 2 are connected to a second control solenoid valve, not shown.
  • Figure 3d shows an embodiment of the pallet 30 aimed at reducing its inertia; for this purpose, the non-active parts of the pallet are hollowed out so as to leave only a stiffening “wing” 35 in which the notch 33 is formed.
  • the parts subjected to the action of gases must be made of a refractory material and resistant to erosion, for example, graphite or molybdenum.
  • the invention is not strictly limited to the embodiment described and shown; for example, the notch 33, formed in the pallets 30, can be transferred to the pistons 40 of the pneumatic cylinders and the rods 41 can be integral with the pallets.
  • the pistons 40 can comprise a rack driven by a bidirectional rotary motor of the electric or pneumatic type and means can be provided on these pistons for coupling a position sensor.
  • the profiles of the nozzles, gas conduits and vanes have been given for illustrative purposes only. Finally, it is by no means essential that the center of thrust P of the ejection nozzles be confused with the center of gravity G of the projectile.
  • the invention applies, in particular, to missiles stabilized in roll or in autorotation.

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)
  • Control Of Turbines (AREA)
  • Sliding Valves (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Telephone Function (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
  • Burglar Alarm Systems (AREA)
  • Surgical Instruments (AREA)
  • Soft Magnetic Materials (AREA)
  • Electromagnets (AREA)
EP82400634A 1981-04-21 1982-04-06 Projectile guidé Expired EP0064433B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82400634T ATE18096T1 (de) 1981-04-21 1982-04-06 Lenkbarer flugkoerper.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8107916A FR2504252B1 (fr) 1981-04-21 1981-04-21 Projectile guide
FR8107916 1981-04-21

Publications (2)

Publication Number Publication Date
EP0064433A1 EP0064433A1 (fr) 1982-11-10
EP0064433B1 true EP0064433B1 (fr) 1986-02-19

Family

ID=9257617

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82400634A Expired EP0064433B1 (fr) 1981-04-21 1982-04-06 Projectile guidé

Country Status (7)

Country Link
US (1) US4441670A (ja)
EP (1) EP0064433B1 (ja)
JP (1) JPS57181953A (ja)
AT (1) ATE18096T1 (ja)
CA (1) CA1185479A (ja)
DE (1) DE3269123D1 (ja)
FR (1) FR2504252B1 (ja)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2504252B1 (fr) * 1981-04-21 1987-03-06 Thomson Brandt Projectile guide
FR2538098B1 (fr) * 1982-12-17 1987-11-20 Thomson Brandt Dispositif de pilotage par jets de gaz lateraux
EP0131573B1 (en) * 1983-01-20 1988-12-28 FORD AEROSPACE & COMMUNICATIONS CORPORATION Ram air combustion steering system for a guided missile
DE3317583C2 (de) * 1983-05-13 1986-01-23 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Vorrichtung mit einer von einer Treibmittelquelle versorgten Düsenanordnung
DE3340037A1 (de) * 1983-11-05 1985-05-23 Diehl GmbH & Co, 8500 Nürnberg Stellsystem fuer gelenkte, mit ueberschallgeschwindigkeit fliegende flugkoerper
FR2557926B1 (fr) * 1984-01-06 1986-04-11 Brandt Armements Propulseur a gaz pour projectile guide.
US4889699A (en) * 1987-05-19 1989-12-26 Texaco Inc. Partial oxidation process
FR2620812B1 (fr) * 1987-09-18 1992-04-17 Thomson Brandt Armements Dispositif de commutation de jets de gaz lateraux destine au pilotage d'engins
FR2659734B1 (fr) * 1990-03-14 1992-07-03 Aerospatiale Systeme pour le pilotage d'un missile au moyen de jets gazeux lateraux.
FR2659733B1 (fr) * 1990-03-14 1994-07-01 Aerospatiale Systeme pour le pilotage d'un missile au moyen de tuyeres laterales.
US6499696B1 (en) * 2001-03-16 2002-12-31 Lockheed Martin Corporation Rocket engine with reduced thrust and stagable venting system
US8319162B2 (en) 2008-12-08 2012-11-27 Raytheon Company Steerable spin-stabilized projectile and method
GB2473187B (en) * 2009-09-02 2016-05-11 Lynley Ashley Adrian Air intake stabilizing system
US8362408B2 (en) * 2009-10-22 2013-01-29 Honeywell International Inc. Steerable projectile charging system
US9279651B1 (en) 2014-09-09 2016-03-08 Marshall Phillip Goldberg Laser-guided projectile system

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE568066C (de) * 1930-08-02 1933-01-13 Elek Sche App M B H Ges Steuerung fuer Raketen- und aehnliche Geschosse
FR916692A (fr) * 1945-10-31 1946-12-12 App Controleurs Procédé et dispositif de combustion gazeuse par infusion à travers une masse réfractaire
US2726510A (en) * 1952-03-26 1955-12-13 Daniel And Florence Guggenhcim Flight-control apparatus involving steering combustion chambers
GB916692A (en) * 1958-06-19 1963-01-23 Snecma Improvements in jet control apparatus
FR1293654A (fr) * 1961-04-07 1962-05-18 Snecma Dispositif de distribution de fluide applicable notamment à la gouverne par jet desavions à décollage vertical
DE1232030B (de) * 1961-05-18 1967-01-05 Dornier Gmbh Steuerduesenkopf fuer die Strahlsteuerung von Luftfahrzeugen
US3273825A (en) * 1961-10-30 1966-09-20 Emerson Electric Co Guidance systems
US3245620A (en) * 1961-12-13 1966-04-12 Gen Motors Corp Missile steering control
GB1073075A (en) * 1964-12-30 1967-06-21 Carter Day Company Distributor valve for controlling the distribution of a solids-gas mixture
US3530886A (en) * 1967-12-04 1970-09-29 Sperry Rand Corp Hydraulic control valve
US3986683A (en) * 1974-03-27 1976-10-19 The United States Of America As Represented By The Secretary Of The Air Force Jet tab steerable missile
US3927693A (en) * 1974-10-11 1975-12-23 Minnesota Mining & Mfg High-pressure valve
US4131246A (en) * 1977-02-04 1978-12-26 Textron Inc. Thrust vector control actuation system
FR2386802A1 (fr) * 1977-04-08 1978-11-03 Thomson Brandt Dispositif de pilotage pour projectile du genre missile, et projectile equipe de ce dispositif
US4375276A (en) * 1980-06-02 1983-03-01 General Electric Company Variable geometry exhaust nozzle
FR2504252B1 (fr) * 1981-04-21 1987-03-06 Thomson Brandt Projectile guide

Also Published As

Publication number Publication date
FR2504252A1 (fr) 1982-10-22
JPS57181953A (en) 1982-11-09
FR2504252B1 (fr) 1987-03-06
EP0064433A1 (fr) 1982-11-10
DE3269123D1 (en) 1986-03-27
ATE18096T1 (de) 1986-03-15
CA1185479A (en) 1985-04-16
US4441670A (en) 1984-04-10

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