EP0215185B1 - Bloc de guidage - Google Patents

Bloc de guidage Download PDF

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Publication number
EP0215185B1
EP0215185B1 EP86105759A EP86105759A EP0215185B1 EP 0215185 B1 EP0215185 B1 EP 0215185B1 EP 86105759 A EP86105759 A EP 86105759A EP 86105759 A EP86105759 A EP 86105759A EP 0215185 B1 EP0215185 B1 EP 0215185B1
Authority
EP
European Patent Office
Prior art keywords
control
valve
cross
block
fact
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
EP86105759A
Other languages
German (de)
English (en)
Other versions
EP0215185A1 (fr
Inventor
Klaus Unterstein
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.)
Rheinmetall Industrie AG
Original Assignee
Rheinmetall GmbH
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 Rheinmetall GmbH filed Critical Rheinmetall GmbH
Publication of EP0215185A1 publication Critical patent/EP0215185A1/fr
Application granted granted Critical
Publication of EP0215185B1 publication Critical patent/EP0215185B1/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 control block for an end-phase-guided projectile according to the preamble of patent claim 1.
  • Such a control block is known from USA-A-3 139 725, which is provided for controlling a second rocket stage.
  • a valve is assigned to each control nozzle for control purposes, but its actuating mechanism is arranged in the longitudinal direction of the projectile.
  • the payload volume is disadvantageously limited on the one hand by the comparatively large space requirement of this control block, on the other hand acceleration forces deploying in the longitudinal direction can have a disadvantageous effect on the opening and closing function of the valves.
  • Projectiles that are fired from barrel weapons contain a correction impulse in order to fight point targets over very long distances in the final phase of their trajectory in order to be able to hit the point target.
  • control blocks are required which work extremely reliably despite the highest acceleration and temperature stresses and which also require the smallest possible construction volume so that they can still be accommodated in storeys of conventional caliber values of 155 mm or 203 mm.
  • the invention has for its object to provide a control block that meets these requirements.
  • FIG. 1 shows in longitudinal section a part of a projectile 10 in the area of the control block 100.
  • the projectile 10 comprises an essentially hollow cylindrical envelope 11, which also includes the control block 100.
  • the control block 100 comprises a hot gas generator with a combustion chamber 101 and propellant charge 102, as well as control nozzles 12 and valve arrangements 13.
  • a hot gas with temperatures in the order of 1400 K to 2000 K is generated in the combustion chamber 101, with which valve arrangements 13 control nozzles 12 are applied.
  • the control nozzles 12 lie in a cross-sectional plane of the sleeve 11, a total of four control nozzles 12 being provided, which are arranged at an even distance from one another on the circumference of a circle.
  • a valve arrangement 13 is assigned to each control nozzle 12, wherein all valves 13 are also arranged lying in a cross-sectional plane of the casing 11 in such a way that their longitudinal axes 130 are aligned along a chord of the casing cross section.
  • the valves 13 lie on one side of a square within the cross-sectional plane.
  • control nozzles 12 and valves 13 also leads in the area of the control block 100 to a very uniform mass distribution with respect to the longitudinal axis 10 a of the projectile, which is advantageous with regard to a possibly required swirl application of the projectile 10. Since the direction of action of the valve arrangements 13 extends in a cross-sectional plane perpendicular to the longitudinal axis 10 a of the projectile 10, acceleration forces which develop primarily in the longitudinal axis direction cannot adversely affect the opening or closing function of the valves 13.
  • the hot gas generated in the combustion chamber 101 passes through bores 12 a, which can be acted upon by the valves 13 in the opening or closing direction, to the control nozzles 12.
  • a control pulse can be provided via the control nozzles 12, which are arranged diametrically opposite each other in four directions for trajectory correction.
  • the actuator 13 c actuating the piston 13 a of the valve 13 consists of a metal with shape memory.
  • Metals of this type can be activated electrothermally, ie by applying heat, an existing martensite structure is converted into an austenite structure in a relatively short time of approximately 100 ms, and this is reversible, so that the process is reversed when heat is removed.
  • the actuator 13 c executes, for example, a stroke between one and 10 mm, whereby it can exert a force of up to 300 N.
  • Such actuators are characterized in comparison to conventional electromagnets with the same performance by a much smaller size and weight.
  • Actuators of the type mentioned or suitable metals with shape memory are sold, for example, by Raychem.
  • the one with the actuator 13 c Connected piston 13 a suitably made of a material with low thermal conductivity, preferably ceramic or silicon nitride.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (3)

1. Bloc de commande (100) pour un projectile commandé en phase finale comportant une chambre de combustion (101) pour brûler une charge propulsive (102) comprenant un générateur de gaz chauds, des tuyères de commande (12) soumises aux gaz chauds, et des dispositifs à clapet (3) pour agir sur le courant des gaz chauds, quatre tuyères de commande (12) espacées régulièrement se trouvant dans un plan transversal du corps de projectile (11) et un clapet (13) associé à chaque tuyère (12), caractérisé en ce que chaque clapet (13) est disposé avec son axe longitudinal (130) le long d'une corde de la section de corps de projectile formant l'un des côtés d'un quadrilatère, dans le plan de section droite.
2. Bloc de commande selon la revendication 1, caractérisé en ce que le clapet (13) comprend un organe de commande (13c) en métal à mémoire de forme dont la longueur peut être modifiée sous l'effet d'une action électro-thermique grâce à un élément chauffant (13b).
3. Bloc de commande selon la revendication 1 ou 2, caractérisé en ce qu'un piston (13a) constitué de céramique ou de nitrure de silicium est lié à l'organe de commande (13c).
EP86105759A 1985-09-05 1986-04-25 Bloc de guidage Expired EP0215185B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19853531686 DE3531686A1 (de) 1985-09-05 1985-09-05 Steuerblock
DE3531686 1985-09-05

Publications (2)

Publication Number Publication Date
EP0215185A1 EP0215185A1 (fr) 1987-03-25
EP0215185B1 true EP0215185B1 (fr) 1989-07-12

Family

ID=6280187

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86105759A Expired EP0215185B1 (fr) 1985-09-05 1986-04-25 Bloc de guidage

Country Status (3)

Country Link
US (1) US4726544A (fr)
EP (1) EP0215185B1 (fr)
DE (2) DE3531686A1 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4951901A (en) * 1985-11-22 1990-08-28 Ship Systems, Inc. Spin-stabilized projectile with pulse receiver and method of use
FR2686687B1 (fr) * 1987-04-22 1994-05-13 Thomson Brandt Armements Procede et dispositif de pilotage d'un projectile selon ses trois axes de roulis tangage et lacet.
US4817377A (en) * 1987-05-07 1989-04-04 Morton Thiokol, Inc. Head end control and steering system: using a forward end maneuvering gas generator
GB8803164D0 (en) * 1988-02-11 1988-08-24 British Aerospace Reaction control system
FR2632722B1 (fr) * 1988-06-10 1993-09-03 Thomson Brandt Armements Dispositif destine a modifier la trajectoire d'un projectile par impulseurs pyrotechniques
US5158246A (en) * 1988-11-15 1992-10-27 Anderson Jr Carl W Radial bleed total thrust control apparatus and method for a rocket propelled missile
US5028014A (en) * 1988-11-15 1991-07-02 Anderson Jr Carl W Radial bleed total thrust control apparatus and method for a rocket propelled missile
DE3901041A1 (de) * 1989-01-14 1990-07-26 Messerschmitt Boelkow Blohm Lenkgeschoss
US5129604A (en) * 1989-07-17 1992-07-14 General Dynamics Corporation, Pomona Div. Lateral thrust assembly for missiles
FR2684723B1 (fr) * 1991-12-10 1995-05-19 Thomson Csf Propulseur a propergol solide a poussee modulable et missile equipe.
US5294079A (en) * 1992-04-01 1994-03-15 Trw Inc. Space transfer vehicle
DE4415259C1 (de) * 1994-04-30 1995-06-08 Daimler Benz Aerospace Ag Schuberzeugungsvorrichtung
US5755401A (en) * 1995-10-31 1998-05-26 Thiokol Corporation Missile diverter integration method and system
US6478250B1 (en) * 1999-10-12 2002-11-12 Raytheon Company Propulsive torque motor
IL167721A (en) 2005-03-29 2008-06-05 Israel Aerospace Ind Ltd Steering system and method for guided flying apparatus
US8618455B2 (en) * 2009-06-05 2013-12-31 Safariland, Llc Adjustable range munition
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
DE102017130117A1 (de) * 2017-12-15 2019-06-19 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Um eine Achse drehbarer Ventilkörper für ein regelbares Querschubtriebwerk

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2509037A1 (fr) * 1981-07-03 1983-01-07 Diehl Gmbh & Co Dispositif de surete pour fusee de projectile

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2509037A (en) * 1948-07-10 1950-05-23 Flicker Jakob Edging for table tops
US3057581A (en) * 1959-06-25 1962-10-09 United Aircraft Corp Rocket vectoring arrangement
US3139725A (en) * 1961-10-31 1964-07-07 James E Webb Steerable solid propellant rocket motor
US3807660A (en) * 1971-11-08 1974-04-30 Aerospatiale Missile flight control system
EP0060726A3 (fr) * 1981-03-17 1983-02-09 Normalair-Garrett (Holdings) Limited Systèmes de poussée par gaz
DE3144532A1 (de) * 1981-11-10 1983-05-19 Rheinmetall GmbH, 4000 Düsseldorf Fluegelstabilisiertes geschoss

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2509037A1 (fr) * 1981-07-03 1983-01-07 Diehl Gmbh & Co Dispositif de surete pour fusee de projectile

Also Published As

Publication number Publication date
US4726544A (en) 1988-02-23
DE3531686A1 (de) 1987-03-12
EP0215185A1 (fr) 1987-03-25
DE3664379D1 (en) 1989-08-17

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