EP2090859A2 - Lanceur doté d'au moins un tuyau de démarrage pour corps volants actionnés par fusées - Google Patents

Lanceur doté d'au moins un tuyau de démarrage pour corps volants actionnés par fusées Download PDF

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Publication number
EP2090859A2
EP2090859A2 EP20090002082 EP09002082A EP2090859A2 EP 2090859 A2 EP2090859 A2 EP 2090859A2 EP 20090002082 EP20090002082 EP 20090002082 EP 09002082 A EP09002082 A EP 09002082A EP 2090859 A2 EP2090859 A2 EP 2090859A2
Authority
EP
European Patent Office
Prior art keywords
laval nozzle
launcher
starting
sleeve
frame
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
EP20090002082
Other languages
German (de)
English (en)
Other versions
EP2090859A3 (fr
EP2090859B1 (fr
Inventor
Thomas Klaffert
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.)
MBDA Deutschland GmbH
Original Assignee
LFK Lenkflugkoerpersysteme 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 LFK Lenkflugkoerpersysteme GmbH filed Critical LFK Lenkflugkoerpersysteme GmbH
Publication of EP2090859A2 publication Critical patent/EP2090859A2/fr
Publication of EP2090859A3 publication Critical patent/EP2090859A3/fr
Application granted granted Critical
Publication of EP2090859B1 publication Critical patent/EP2090859B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A1/00—Missile propulsion characterised by the use of explosive or combustible propellant charges
    • F41A1/08—Recoilless guns, i.e. guns having propulsion means producing no recoil
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A25/00—Gun mountings permitting recoil or return to battery, e.g. gun cradles; Barrel buffers or brakes
    • F41A25/06—Friction-operated systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket

Definitions

  • the invention relates to a projector according to the preamble of claim 1.
  • start acceleration force and usable start path of the missile depend on its mass ratio to the rejected components as well as the additionally introduced supporting forces or spring and damper forces. If the launch tube is axially fixed or mounted in a spring-damper system results in a recoil, which acts on the attachment of the thrower on the carrier, ie its means of transport and possibly also this overall arrangement moves a piece. If the entire projector arrangement is to be designed as low as possible for the purpose of high mobility, only the variant with a repelled freely flying starting pipe for the projector arrangement can be considered in order to avoid this influence without further modifications.
  • the situation is similar when launching projectiles, where the gas recoil energy of the ignited propellant can be used to operate a recharging mechanism.
  • the additional pipe recoil caused by gas expansion through the mouth after floor exit can be known to reduce so-called muzzle brakes, wherein a portion of the exiting gas flow is deflected at the mouth of the tube for shear compensation.
  • gun barrels which also have an opening behind with a subsequent Laval nozzle. If the geometry of this nozzle is optimally designed for a precisely defined combustion energy, this principle, which is known as a nozzle gun, can theoretically realize a recoilless or return-free gun even for large calibers with comparatively small net mass.
  • the principle of the recoilless launch tube is used to allow it to be fired from the shoulder of a soldier, or a biped or tripod.
  • the recoil at the muzzle after missile outlet is eliminated if it is closed by a moving the missile starting piston.
  • an additional reaction torque is generated about the longitudinal axis of the launch tube that can compensate only for this part of the start path by a defined gas swirl within the Laval nozzle at the rear end of the launch tube , If the missile has left this slotted guide, the gas swirl and the friction of the starting piston cause the starter tube to rotate.
  • the launch tube must therefore be released at this time from its holder so that it can fly away to the rear.
  • This compensation can be a tearing of the launched missile avoid.
  • the total recoil path and thus the rear safety area on the launching frame can be reduced by appropriate dimensioning of the Laval nozzle on application-relevant sizes.
  • the Laval nozzle arrangement may be fixed or pivotally connected to the movable part of the shock absorber or else to the frame-fixed part of the shock absorber, without this eliminating the effect of the new arrangement.
  • a further advantage is that according to the invention the return path between the frame-fixed and the moving parts of the shock absorber by means of the friction ring spring arrangement for the purpose of tuning the force-travel curve of the nozzle part shock absorber combination is adjustable. Also by the occurring friction damping a time-delayed return stroke of the shock absorber can be achieved. With the help of this friction ring spring arrangement torsional moments between start the missile and launcher are also transferred to the launcher frame. With the help of the inventive construction of the arrangement described above, therefore, a first free mobility of the launch tube is achieved within the available distance at the start of the missile, and then slows down the movement of the launch tube to a standstill.
  • a starting pipe 12 is provided, which is part of a thrower, also not shown, in the form of a starting container, which is to be moved by a likewise not shown mobile carrier in the respectively desired starting position.
  • the end of the starting tube 12 facing away from the starting direction 10 carries a Laval nozzle 13, which at the start of the missile serves to discharge the gas volume flow, which is generated by a gas generator 15 operating as a booster.
  • the gas volume flow generated at the start acts on a starting piston 12 located in the starting piston, not shown, via which the missile is accelerated for its launch and is twisted for part of the start path.
  • the gas generator 15 is completed by a load-distribution, located in a recess 14 of an outer guide sleeve 19 for a friction ring spring assembly annular elastic receptacle 16 for the gas generator 15, which is part of a shock absorber 17.
  • the shock absorber 17 comprises two coaxial relative to each other movable sleeves, namely an inner guide sleeve 18 and an outer guide sleeve 19, between which a the return path of a guide sleeve - here the outer guide sleeve 19 - influencing friction ring spring assembly 20 is arranged.
  • the inner guide sleeve 18 is with respect to Fig. 1 assigned at its right end a cap 21, which can be supported on guide surfaces 26 on the indicated frame G.
  • the guide surfaces 26 may also be attached to the outer guide sleeve 19.
  • the cap 21 carries in a central opening 22 which is stepped there at 23 inner guide sleeve 18 fixed and engages with its outer peripheral surface 24 in an axial guide 25 of the outer guide sleeve 19, so that the outer guide sleeve 19 when moving the starting tube 12 against the starting direction 10 over the cap 21 can grip.
  • Strahlablenk vom 31 includes.
  • these lateral nozzle parts 32 carry the same Fig. 1 shows - correspond to the bulkheads 29.
  • Bulkheads 29 and beam deflection surfaces 31 enclose a rectangular cross-section.
  • the bulkheads 29 and beam deflecting surfaces 31 can be introduced into or attached to a starting container, not shown.
  • the starting container is also closed at its front end wall in the transport state by means not shown flaps.
  • the Laval nozzle arrangement 30 corresponds to the Laval nozzle 13 of the starting pipe 12 and extends them so far that due to the braking effect of both nozzle parts a largely recoilless launch of the missile, not shown, can take place.
  • the mutually facing end-side end surfaces of both nozzles overlap at 33 such that the nozzle 13 can engage in the return flow of the start pipe 12 in the nozzle assembly 30.
  • the block length of the friction ring spring determines the maximum return path - braking distance s of the axial guide 25 of the outer guide sleeve - the launch tube 12 at the start of the missile, which is braked by the friction ring spring assembly 20 to a standstill.
  • the running back of the, in the launcher mounted, axially bound starting pipe 12 is limited by the friction ring spring assembly 20 via the shock absorber 17.
  • an advantageous force-displacement characteristic curve of the shock absorber 17 can be tuned taking into account the effect of the Laval nozzle 13 and the Laval nozzle arrangement 30.
  • a time-delayed return stroke is achieved by the friction damping.
  • the Startablenk vom 31 of the Laval nozzle arrangement 30 may also be connected pivotally mounted synchronously to the starting angle in a manner not shown; see. Fig. 3 ,
  • the open flaps are not only "Strahlablenk perennial", they form in open position ie at fire readiness at each elevation angle part of the Laval nozzle contour and are extension part according to the Psi function, ie they form a "pivotal part of the Laval nozzle", which of course also a Beam deflection realized.
  • Psi function ie they form a "pivotal part of the Laval nozzle" which of course also a Beam deflection realized.
  • ballistic protection and weather protection of the launch tube are realized by the same flaps.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
EP09002082.7A 2008-02-18 2009-02-14 Lanceur doté d'au moins un tuyau de démarrage pour corps volants actionnés par fusées Not-in-force EP2090859B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200810009638 DE102008009638B3 (de) 2008-02-18 2008-02-18 Werfer mit mindestens einem Startrohr für raketengetriebene Flugkörper

Publications (3)

Publication Number Publication Date
EP2090859A2 true EP2090859A2 (fr) 2009-08-19
EP2090859A3 EP2090859A3 (fr) 2013-05-29
EP2090859B1 EP2090859B1 (fr) 2015-06-03

Family

ID=40578863

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09002082.7A Not-in-force EP2090859B1 (fr) 2008-02-18 2009-02-14 Lanceur doté d'au moins un tuyau de démarrage pour corps volants actionnés par fusées

Country Status (2)

Country Link
EP (1) EP2090859B1 (fr)
DE (1) DE102008009638B3 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2354751A3 (fr) * 2010-02-02 2014-10-29 Diehl BGT Defence GmbH & Co.KG Conteneur pour missile à réaction
CN112644801A (zh) * 2020-09-21 2021-04-13 中山市哈工朗德智能科技有限公司 一种新型横封导向装置
CN116006360A (zh) * 2022-12-03 2023-04-25 中国科学院力学研究所 一种异形拉瓦尔微喷管

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE695584C (de) * 1933-11-05 1940-08-28 Mauser Werke Ag Maschinenwaffe mit beweglichem Lauf
DE716385C (de) * 1939-03-04 1942-01-19 Mauser Werke Ag Reibungsringfeder mit vergroesserter Arbeitsvernichtung, insbesondere fuer den Waffenbau
FR1604112A (fr) * 1964-02-26 1971-07-12
CH450228A (fr) * 1965-10-22 1968-01-15 Transurvey Holding Company Inc Dispositif de lancement d'un projectile
GB1560881A (en) * 1976-05-14 1980-02-13 British Aircraft Corp Ltd Aircraft weapon mountings
GB2121149B (en) * 1982-05-27 1985-07-24 British Aerospace Missile housing and launch arrangement
US6352030B1 (en) * 1998-11-12 2002-03-05 Cordant Technologies Inc. Gas generating eject motor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2354751A3 (fr) * 2010-02-02 2014-10-29 Diehl BGT Defence GmbH & Co.KG Conteneur pour missile à réaction
CN112644801A (zh) * 2020-09-21 2021-04-13 中山市哈工朗德智能科技有限公司 一种新型横封导向装置
CN116006360A (zh) * 2022-12-03 2023-04-25 中国科学院力学研究所 一种异形拉瓦尔微喷管
CN116006360B (zh) * 2022-12-03 2024-04-09 中国科学院力学研究所 一种异形拉瓦尔微喷管

Also Published As

Publication number Publication date
DE102008009638B3 (de) 2009-09-03
EP2090859A3 (fr) 2013-05-29
EP2090859B1 (fr) 2015-06-03

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