EP0335761B1 - Flugvehikel mit zumindest einer abwerfbaren Antriebseinheit - Google Patents

Flugvehikel mit zumindest einer abwerfbaren Antriebseinheit Download PDF

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Publication number
EP0335761B1
EP0335761B1 EP89400663A EP89400663A EP0335761B1 EP 0335761 B1 EP0335761 B1 EP 0335761B1 EP 89400663 A EP89400663 A EP 89400663A EP 89400663 A EP89400663 A EP 89400663A EP 0335761 B1 EP0335761 B1 EP 0335761B1
Authority
EP
European Patent Office
Prior art keywords
vehicle
rest
propellant
missile
accelerator
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
Application number
EP89400663A
Other languages
English (en)
French (fr)
Other versions
EP0335761A1 (de
Inventor
Jean Marie Dupuis
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 EP0335761A1 publication Critical patent/EP0335761A1/de
Application granted granted Critical
Publication of EP0335761B1 publication Critical patent/EP0335761B1/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
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the present invention relates to an aerial vehicle provided with at least one releasable thruster. It applies to any device, such as missile, rocket, rocket, provided with one or more releasable thrusters, that this or these thruster (s) is (are) mounted (s) coaxially to said device, or well disposed (s) on the periphery of the latter.
  • releasable thrusters are for example consumable accelerators intended to communicate to said machine a desired speed value.
  • the first which can be described as active, uses mechanical or pyrotechnic elements, such as cutting cords, explosive bolts, extraction springs, etc. controlled by a logic device.
  • Such active separation systems are therefore complex. In addition, their reliability is not perfect.
  • the second of said methods is called natural, because the separation takes place spontaneously under the action of the aerodynamic drag of said propellant.
  • the propellant is connected to the rest of the device by a precise interlocking, constituting a sliding connection parallel to the axis of said propellant, but making the latter integral in rotation with said device.
  • the propulsion force thereof reinforced by the aerodynamic drag of the rest of the vehicle and by the friction forces of the connection slippery, but reduced in the aerodynamic drag of said propellant, secures the propellant on said machine.
  • said propulsion force decreases very sharply (pushing tail) until it cancels out, so that it becomes insufficient to keep said propellant integral with the rest of the machine.
  • the aerodynamic drag of said propellant can then overcome the friction forces of the sliding link and, contrary to the action of aerodynamic drag of the rest of the vehicle, said propellant separates naturally from the rest of the vehicle.
  • the friction forces in a sliding connection depend on the state of the contact surface, on the possible lubrication and on the play, that is to say on the manufacturing tolerances of the engagement of the propellant on the rest of the craft.
  • a gumming phenomenon can appear, when the sliding link is immobilized for a prolonged period, as can be an ammunition in stock.
  • the sliding connection which ensures the rigidity of the whole of the machine and of the propellant, may be subjected to a significant embedding moment during separation. This moment, which can result from the aerodynamics of the machine or from longitudinal mechanical vibrations, significantly affects the level of frictional forces.
  • immobilization in rotation of the sliding link can lead to additional friction due to torsional torques (also of aerodynamic or vibratory origin) in the interlocking.
  • the object of the present invention is to remedy these drawbacks. It allows to obtain, with safety, the natural separation of a temporary propellant from the rest of a machine, without requiring the intervention of auxiliary controllable devices.
  • the air vehicle comprising at least one propellant, temporary and releasable, linked to the rest of said vehicle by an adjustment capable of allowing said propellant to slide parallel to its axis in the direction opposite to said rest of the 'machine, is characterized in that a communication is established between, on the one hand, the internal space to said adjustment and disposed between the front of said propellant and said rest of the machine, and, on the other hand, l aerodynamic flow around said machine.
  • the preamble of claim 1 is based on a known state of the art according to article 54 (2) CBB.
  • this internal space is put under a pressure equal to at least a part of the total pressure of said aerodynamic flow, so that in this internal space is generated a force favorable to the natural separation of the propellant.
  • said propellant has a diameter greater than that of the part of said machine on which it is mounted and said part is connected to said propellant by a divergent wall linked to it, it is preferable that said communication be established through said divergent wall.
  • said communication is constituted by at least one conduit, the external orifice thereof is advantageously directed towards the front of said machine, so that the air intake is favored.
  • said communication is multiple.
  • the communication conduit is extended outside of said machine by an air intake.
  • said air intake is at least substantially parallel to the axis of the machine and directed towards the front thereof.
  • the aerodynamic symmetry of the assembly is respected.
  • the way of arranging the air intakes, to recover the desired pressure, then takes account of the presence of possible shock waves in supersonic flow.
  • Figure 1 is an axial sectional view, schematic and partial, of an exemplary embodiment of a missile to which the invention can be applied, therefore of an example of a known type.
  • Figure 2 is a cross section along the line II-II of Figure 1.
  • Figure 3 is a view similar to Figure 1 illustrating the present invention.
  • FIG. 4 illustrates an alternative embodiment of the invention, in a view similar to FIG. 3.
  • a missile 1 comprising a propellant, or accelerator, temporary 2 (for example powder), the front part of which is mounted on the rear part, the rest 3 of said missile.
  • accelerator 2 is coaxial with the rest 3 of said missile, but it is clear that this feature is not essential for the invention.
  • the axis of the accelerator 2 while being parallel to the axis of said missile, could be eccentric with respect thereto.
  • the front part of the accelerator would not necessarily be connected to the rear extreme part of the remainder 3 of the missile 1.
  • FIGS. 1 and 2 it has also been assumed, which is also not compulsory, that the diameter of the accelerator was greater than that of the rest 3 of missile 1.
  • the rear part of the remainder 3 of said missile (remainder which could possibly include another accelerator) is provided with two ranges cylindrical 4 and 5 coaxial and stepped.
  • the front part of the accelerator 2 comprises a cylindrical portion 6, provided with internal cylindrical surfaces 7 and 8, intended respectively to bear on the cylindrical surfaces 4 and 5.
  • a transverse shoulder 9 of the rear part of the rest 3 of the missile 1 cooperates with the extreme front edge 10 of the cylindrical portion 6 to serve as a stop for the accelerator 2 towards the front.
  • the external contour 11 is also connected to the external contour 13 of the accelerator 2 by a conical skirt 14.
  • a longitudinal groove and rib system 15 makes the accelerator 2 and the rest 3 of the missile 1 integral in rotation with one another.
  • FIG 3 there is shown the missile 1 of Figures 1 and 2 improved according to the present invention.
  • the internal space 16 is then placed in communication with the outside by one or more ducts 17, provided with external air intakes 18.
  • the ducts 17 and the air intakes 18 are arranged in the conical skirt 14.
  • the air intakes 18 are arranged at least substantially parallel to the axis of the propellant and directed towards the front of said missile 1.
  • the thrust thereof acts so as to press the extreme front edge 10 of said accelerator 2 against the shoulder 9.
  • Said accelerator 2 is therefore integral longitudinally with the rest 3 of the missile 1.
  • the longitudinal rib 5 and groove 15 system it is integral with the latter in rotation.
  • the thrust action of the propellant 2 is then reinforced by the aerodynamic drag exerted on the rest 3 of the missile 1, as well as by the friction forces existing respectively between the ranges 4 and 5 and the cylindrical surfaces 7 and 8.
  • this action is counteracted by the aerodynamic drag exerted on the accelerator 2 and by the force, due to the pressure prevailing in the internal space 16.
  • the air intakes 18 and the conduits 17 allow to transmit to the latter at least part of the aerodynamic overpressure prevailing in the vicinity of missile 1 in flight.
  • a sealing lubricant between the surfaces 4 and 5, on the one hand, and the cylindrical surfaces 7 and 8, else go.
  • the volume of the internal space 16 and the diameter of the pressure taps 17, 18 are dimensioned so that the level of the pressure forces remains as long as the missile and the accelerator are in contact during the separation phase.
  • the diameter of the internal space 16 partly determines the level of the pressure forces.
  • the invention makes it possible to greatly increase the reliability of natural separation.
  • the latter is, in fact systematic, thanks to the added forces.
  • the speed of the relative separation movement removes all risk of shock between the rest 3 of the missile 1 and the accelerator 2, after disengagement of the embedding 4,7-5,8-9,10.
  • the instant of separation is no longer subject only to the dispersions inherent in the propulsion, that is to say the combustion time of the acceleration propellant 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Current-Collector Devices For Electrically Propelled Vehicles (AREA)

Claims (8)

  1. Flugkörper (1) mit wenigstens einem temporären und abwerfbaren, mit dem Rest (3) des Flugkörpers durch eine Passung (4,7-5,8-9,10) verbundenen Triebwerk (2), die es diesem erlaubt, parallel zu seiner Achse in entgegengesetzter Richtung zu der des besagten Restes (3) des Triebwerks zu gleiten,
    dadurch gekennzeichnet, daß eine Verbindung (17) zwischen einerseits dem Innenraum (16) der besagten Passung, angeordnet zwischen dem Vorderteil des besagten Triebwerkes und dem besagten Rest (3) des Flugkörpers, und andererseits der aerodynamischen Strömung um den besagten Flugkörper (1) geschaffen wird
  2. Flugkörper nach Anspruch 1,
    dadurch gekennzeichnet, daß die besagte Verbindung durch das Triebwerk (2) hindurch geschaffen wird.
  3. Flugkörper nach Anspruch 2, wobei das besagte Triebwerk (2) einen größeren Durchmesser als der Teil (3) des besagten Flugkörpers hat, auf dem es angebracht ist, und wobei der besagte Teil (3) mit dem besagten Triebwerk (2) durch eine divergente Wand (14) verbunden ist,
    dadurch gekennzeichnet, daß die besagte Verbindung durch die besagte divergente Wand hindurch geschaffen wird.
  4. Flugkörper nach einem der Ansprüche 1 bis 3,
    dadurch gekennzeichnet, daß die besagte Verbindung eine Vielfachverbindung ist.
  5. Flugkörper nach einem der Ansprüche 1 bis 4,
    dadurch gekennzeichnet, daß er wenigstens eine in der Peripherie des besagten Flugkörpers mündende Leitung (17) aufweist.
  6. Flugkörper nach Anspruch 5,
    dadurch gekennzeichnet, daß die besagte Leitung (17) durch einen Luftanschluß (18) zum Außenraum des besagten Flugkörpers verlängert ist.
  7. Flugkörper nach Anspruch 6,
    dadurch gekennzeichnet, daß der besagte Luftanschluß (18) im wesentlichen parallel zur Achse des Flugkörpers verläuft und zum Vorderteil desselben gerichtet ist.
  8. Flugkörper nach einem der Ansprüche 1 bis 7,
    dadurch gekennzeichnet, daß die Dichtheit der besagten Gleitpassung mittels eines Schmiermittels erreicht wird.
EP89400663A 1988-03-30 1989-03-09 Flugvehikel mit zumindest einer abwerfbaren Antriebseinheit Expired - Lifetime EP0335761B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8804213A FR2629583B1 (fr) 1988-03-30 1988-03-30 Engin aerien pourvu d'au moins un propulseur largable
FR8804213 1988-03-30

Publications (2)

Publication Number Publication Date
EP0335761A1 EP0335761A1 (de) 1989-10-04
EP0335761B1 true EP0335761B1 (de) 1993-01-20

Family

ID=9364806

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89400663A Expired - Lifetime EP0335761B1 (de) 1988-03-30 1989-03-09 Flugvehikel mit zumindest einer abwerfbaren Antriebseinheit

Country Status (7)

Country Link
US (1) US4903605A (de)
EP (1) EP0335761B1 (de)
JP (1) JP2954948B2 (de)
CA (1) CA1332537C (de)
DE (1) DE68904453T2 (de)
ES (1) ES2037972T3 (de)
FR (1) FR2629583B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3663704B1 (de) * 2016-07-22 2022-06-15 Raytheon Company Stufentrennungsmechanismus

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE508475C2 (sv) 1993-03-30 1998-10-12 Bofors Ab Sätt och anordning för spridning av stridsdelar
FR2791130B1 (fr) 1999-03-19 2001-05-04 Celerg Engin muni d'un ejecteur pyrotechnique largable
EP2002198B1 (de) * 2006-03-30 2013-04-24 Raytheon Company Verfahren und vorrichtung für ein integriertes sperrverschlusssystem
JP5634785B2 (ja) * 2010-07-30 2014-12-03 株式会社Ｉｈｉエアロスペース 飛翔体

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA572824A (en) * 1959-03-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Combined ram-jet and rocket unit
US2899898A (en) * 1959-08-18 Auxilliary carriage arrangement for a missile
DE1122380B (de) * 1960-04-16 1962-01-18 Boelkow Entwicklungen K G Flugkoerper mit Rueckstosstriebwerk
US3190221A (en) * 1961-12-27 1965-06-22 John M Gariboldi Rocket stage coupling
US3260204A (en) * 1964-06-08 1966-07-12 Jr John W Wilkey Velocity package
US3262266A (en) * 1964-08-31 1966-07-26 James F Howison Rocket interstage adapter
US3310947A (en) * 1965-12-10 1967-03-28 George F Shryock Safety apparatus for tandem-connected rockets
US4348956A (en) * 1980-08-29 1982-09-14 The United States Of America As Represented By The Secretary Of The Army Artillery shell comprising two sections having complementary coupling members for connecting the sections together
US4625649A (en) * 1983-04-05 1986-12-02 British Aerospace Plc Projectiles
US4628821A (en) * 1985-07-05 1986-12-16 The United States Of America As Represented By The Secretary Of The Army Acceleration actuated kinetic energy penetrator retainer
EP0228781B1 (de) * 1985-10-31 1992-08-05 British Aerospace Public Limited Company Ausstossantrieb für Flugkörper

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3663704B1 (de) * 2016-07-22 2022-06-15 Raytheon Company Stufentrennungsmechanismus

Also Published As

Publication number Publication date
DE68904453T2 (de) 1993-06-03
FR2629583A1 (fr) 1989-10-06
DE68904453D1 (de) 1993-03-04
CA1332537C (fr) 1994-10-18
ES2037972T3 (es) 1993-07-01
FR2629583B1 (fr) 1993-06-18
EP0335761A1 (de) 1989-10-04
US4903605A (en) 1990-02-27
JP2954948B2 (ja) 1999-09-27
JPH0210100A (ja) 1990-01-12

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