EP1739384B1 - Coiffe larguable ainsi que corps volant avec coiffe larguable - Google Patents

Coiffe larguable ainsi que corps volant avec coiffe larguable Download PDF

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Publication number
EP1739384B1
EP1739384B1 EP06012006A EP06012006A EP1739384B1 EP 1739384 B1 EP1739384 B1 EP 1739384B1 EP 06012006 A EP06012006 A EP 06012006A EP 06012006 A EP06012006 A EP 06012006A EP 1739384 B1 EP1739384 B1 EP 1739384B1
Authority
EP
European Patent Office
Prior art keywords
parts
missile
connecting pin
nose
hood
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.)
Active
Application number
EP06012006A
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German (de)
English (en)
Other versions
EP1739384A1 (fr
Inventor
Gerald Rieger
Roland Waschke
Gerd Elsner
Klaus Tondok
Peter Gerd Fisch
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.)
Diehl BGT Defence GmbH and Co KG
Original Assignee
Diehl BGT Defence GmbH and Co KG
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
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Application filed by Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP1739384A1 publication Critical patent/EP1739384A1/fr
Application granted granted Critical
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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
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/38—Range-increasing arrangements
    • F42B10/42—Streamlined projectiles
    • F42B10/46—Streamlined nose cones; Windshields; Radomes
    • 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 invention relates to a detachable front hood for a missile, which is divided longitudinally into at least two parts, and which is held together by releasable connecting means.
  • the invention further relates to a missile with such a disposable front hood.
  • Ejectable hoods are used in missiles, for example, to protect the sensitive viewfinder optics, in particular the radransparent dome, during a flight to the site from external influences such as particle impact or heat. Attachment hoods generally hinder the view of the sensitive viewfinder system and can therefore only be used in relatively predefined flight phases or in flight phases in which the missile is not guided through the viewfinder system to the destination. If the missile is to be guided through the viewfinder system to the target, the front hood must be discarded, so that unimpeded target detection is possible.
  • Vorsatzhauben are for example from the CH 525 798 , of the DE 102 11 493 B3 and the DE 196 35 851 C2 known.
  • CH 525 798 is a Vorsatzhaube described, which consists of a prestressed material, in particular toughened glass.
  • a mechanism of action in the missile is actuated pyrotechnically, so that a tip strikes the edge of the intent hood. This shatters the front hood in a variety of small particles.
  • a detachable front hood is known, which is mounted on arranged in grooves radially inwardly resilient retaining members on the missile. To throw off these holding members are deflected by means of unlocking cylinder to the outside and thus out of engagement with the missile.
  • the unlocking cylinders can be operated with an ignitable gas generator, with a gas spring or pyrotechnic.
  • An attachment hood and a missile of the type mentioned are from the DE 102 40 040 A1 known.
  • the front hood at least two parts in the longitudinal direction, wherein the two parts are held together by releasable connecting means. If the connecting means are actuated or released, then the at least two parts open as a result of the back pressure inside the front hood in the manner of a "beak" to the outside and are thereby torn from its anchorage to the missile.
  • this can be provided at the top with an opening.
  • the US 2005/0000383 A1 discloses a split in two parts, ejectable tail cap for a rocket according to the preamble of independent claim 1.
  • To connect the two parts of the front hood inter alia plugged pipe sections are provided.
  • a Plunger and a pyrotechnic material are provided in the cavity formed by the nested tube pieces.
  • a pressure increase is generated, which leads to a movement of the piston and thus to a unfolding of the two parts of the front hood.
  • the DE 101 27 483 A1 shows a separating screw for releasably connecting two components.
  • the separating screw has an outwardly open recess which is intended to receive a preassembled blasting and ignition unit. By activating the ignition unit, the components firmly connected to one another by means of the separating screw can be separated from one another.
  • the object of the invention is to provide a detachable front hood for a missile, which is easy to retrofit and in each phase of the missile easily separable from this, it is an object of the invention to provide a missile with such a designed intent hood, with missile and intent hood in each Flight phase are easily separable from each other.
  • the invention is based on the consideration that a longitudinally split front hood can be thrown off more easily than a one-piece or cross-split front hood.
  • the longitudinal division namely, the individual parts of the attachment hood can be guided past the missile laterally. For this, the individual parts need only be moved apart.
  • the invention is based on the consideration that a safe and easy ejection of the parts of a longitudinally mounted front hood is achieved when the moving apart of the individual parts can take place independently of the respective flight phase of the missile. This is the case when the connecting means which hold together the parts of the longitudinally split front hood are designed to actively disengage the individual parts when triggered.
  • the invention provides that the individual parts of a longitudinally split front hood when dissolving the cohesive connecting means are actively moved apart by this.
  • the longitudinal division of the individual parts of the attachment hood are pressed radially outward with respect to the missile longitudinal axis.
  • the individual parts of the attachment hood are guided past the missile laterally.
  • a longitudinally split hood can be mounted on the missile in such a way that its joint gap is aligned vertically during the flight of the missile.
  • This offers the advantage that during a dropping the two parts of the front hood are always passed laterally on the missile during a sinking or climb flight.
  • the risk of a collision of a missile in the climb or descent with an up or down discarded part of an intent hood does not exist.
  • the effective angle of attack of the parts of the hood which depends on the angle of incidence of the missile to the flow, minimized. This requires a minimization of the risk of collision of parts of the front hood with the missile.
  • the releasable connection means are arranged in the front hood, a simple retrofitting of existing missiles with such a front hood is possible. As a result of the active moving apart of the parts of the front hood this can be safely dropped both at low and at high Fluggeschwindigkelten the missile.
  • the triggering of the parts holding together the connecting means can be activated at any time on the existing electronics in the missile time. Also, a remote release is possible.
  • a metal or a plastic can be used as material for the front hood.
  • a metal is particularly suitable steel.
  • the plastic may optionally be reinforced or jacketed with carbon or glass fibers.
  • the connecting means comprise a pyrotechnically activatable connecting pin with a bore into which a propellant charge is used, wherein upon ignition of the propellant, the at least two parts driving apart, gases are released.
  • the high energy releasing propellant within a short time is integrated directly into the connecting pin that holds the parts of the front hood together.
  • the spontaneously released at ignition of the propellant gases are used to divide the parts of the front hood.
  • the integration of the propellant charge in the connecting pin allows the tripping speed to be adapted to the external parameters predetermined by the missile or by the conditions of use. This can be done for example by the choice of material of the connecting pin or by the composition of the propellant.
  • the at least two parts of the auxiliary cap are held together by means of the connecting pin via an axially hollow cylinder which forms an inner cavity, wherein the bore of the connecting pin has an opening to the inner cavity through which the gases released upon ignition of the propellant, the hollow cylinder axially apart, to flow into the inner cavity.
  • the at least two parts are inserted into one another via hollow cylinders in the manner of a piston. The gases flowing through the opening into the internal cavity when the propellant is ignited push the two hollow cylinders apart, as a result of which the parts of the ancillary hood are moved apart.
  • the connecting pin ruptures in this disassembly movement in half.
  • the moving apart of the parts of the front hood can be adjusted according to the conditions of use and for an existing type of missile.
  • an axial movement apart of the hollow cylinders means that they drift apart in the transverse direction of the missile longitudinal axis.
  • the at least two parts are held together directly by means of the connecting pin, wherein the bore extends in the longitudinal direction and in addition to the propellant has a fitted piston, and wherein the piston is driven by ignition of the propellant in the longitudinal direction.
  • the connecting pin which holds the two parts together generates a pulse directed outwards or in the longitudinal direction of the connecting pin, whereby the parts of the front hood are moved apart.
  • the propellant charge of the longitudinally aligned bore is ignited, the gases propel the piston fitted in this bore longitudinally, thereby tearing the connecting pin apart.
  • the two parts of the connecting pin then have an opposite impulse.
  • the parts against header hood need only be configured so that they can be connected to each other via the connecting pin. This can be done, for example, that the parts each have openings mounted in a web, and are held together via these openings by means of the connecting pin formed as a screw or rivet. This technique also allows easy installation of the front hood on the missile.
  • the connecting pin has a predetermined breaking point.
  • About the predetermined breaking point is ensured that the connecting pin tearing at ignition of the propellant charge at a predetermined location.
  • the front hood is conical, ogiven or paraboloid.
  • Other aerodynamic shapes of the front hood which have, for example, a comparison with the hemisphere shape better aerodynamics, are conceivable. These forms have a favorable aerodynamics and thus help to reduce the aerodynamic drag of the missile.
  • the front hood thus serves as an aerodynamic fairing and reduces the aerodynamic drag of the basic configuration of the missile without Vorsatzhaube.
  • an aerodynamically designed intent hood forms the possibility of the shot from an aircraft range also launched from the ground to reach.
  • this end is connectable by means of a convex groove with the missile. If the pulse for actively moving apart of the parts of the front hood is transmitted in the front region of the hood, this embodiment allows the parts of the front hood to tilt over this convex groove radially from the missile.
  • a kinking groove for guiding a arranged on the missile pin is introduced.
  • two such grooves offset by 180 ° are introduced, in which the corresponding pins protruding from the structure of the missile are guided along.
  • the hood can be mounted on the missile or dismantled they will first be pushed axially onto a arranged on the circumference of the missile federal government , In this case, the end-side convex groove of the attachment hood engages with a collar-oriented, forwardly directed concave groove. At the same time, the pin or pins attached to the missile engage in the corresponding kinked grooves of the hood which are attached to the inner circumference. By a slight rotation of the attachment hood this is then clamped between the pins and the collar on the missile, the circumferential collar continues to fulfill an axial support function during acceleration of the missile.
  • the second-mentioned object with regard to a missile is achieved in that according to the invention the missile has a detachable front hood as described above.
  • the front hood engages the end in a circumferentially extending raised collar on the missile, It has been shown in particular that it is sufficient for attaching the front hood and also for dropping their parts when the raised collar is partially interrupted in the circumferential direction.
  • the interruption can also be designed generously.
  • Fig. 1 shows a perspective view of a two-part split in the longitudinal direction ejectable front hood 10 for a missile.
  • the front hood 10 extends from a tip 12 to one end 13.
  • the front hood 10 has two covers 20 circumferentially partially revolving, which are removable in order to mount the two parts 15, 16 together.
  • Fig. 2 shows in a section an attachment hood 10, which forms no part of the invention. It can be seen the two parts 15, 16 and the longitudinally extending joint gap 18. Also provided for connecting the two parts 15, 16 webs 22, 23 are clearly visible. About a respectively mounted in the web 22 and 23 bore the two halves 15, 16 are held together by means of a connecting pin 25.
  • the connecting pin 25 is designed for this purpose as a screw with a screw head 26 and a thread 27.
  • a thread 27 patch nut 28 the two parts 15, 16 of the cap 10 can be easily connected to each other with a suitable tool.
  • the part 15 is connected to the impulse transmission upon release of the connecting pin 25 via a bolted by means of the external thread 71 end piece 29 fixed to the connecting pin 25.
  • In the part 16 of the screw head 26 is also screwed by means of an external thread 70.
  • the connection pin 25 can also be designed as a connecting pin.
  • the two parts 15, 16 of the cap 10 according to Fig. 2 cohesive connecting pin 25 is in detail Fig. 3 removable.
  • the connecting pin 25 has the already in Fig. 2 recognizable screw head 26 and at the other end also in Fig. 2 already shown thread 27.
  • Inside the connecting pin 25 is a longitudinal direction extending bore 30 introduced.
  • a piston 32 and a propellant 33 is introduced inside the connecting pin 25 .
  • a squib 35 which is ignited via outgoing leads 36.
  • a predetermined breaking point 38 is introduced in the form of a circumferential groove.
  • Fig. 4 again shows a perspective view of the inside of a portion 15 of the longitudinally split front hood 10 according to Fig. 1 or 2 ,
  • the web 22 can be seen, via which the part 15 with the other part 16 of the attachment hood 10 is connectable.
  • a bore 38 is introduced into the web 22.
  • the part 15 has a circumferential convex groove 40, which is provided for engagement in a correspondingly mounted on the missile concave groove.
  • a kinking groove 42 is introduced on the inner circumference. This kinking groove 42 serves to guide a protruding from the contour of the missile pin (52).
  • the front hood For mounting the front hood it is pushed axially, wherein the corresponding pin is initially guided in the axial direction along the groove 42. Subsequently, the front hood can be clamped in the manner of a bayonet lock by turning against the missile, in which case the corresponding pin 52 is guided in the part of the groove 42 bent in the circumferential direction of the part 15.
  • Fig. 5 shows in perspective the tip 45 of a for receiving a front hood 10 according to the Fig. 1 or 2 prepared missile.
  • a hemispherical dome 47 of IR radiation permeable material arranged at the tip 45 of the missile.
  • Behind the dome 47 is a gimbaled IR seeker that scans a large solid angle area for target signatures.
  • the tip 45 of the missile has a circumferential collar 49, at the end toward the dome towards the front end a circumferential concave groove 50 is introduced.
  • two protruding from the contour of the missile 52 are mounted on the circumference of the tip 45 by 180 °, which in the in Fig. 4 shown kinking groove 42 of the respective parts 15, 16 of the attachment hood 10 engage.
  • a foam body can be inserted between this and the front hood.
  • Fig. 6 again shows a corresponding one in a section Fig. 1 formed intent hood 10.
  • the two parts 15, 16 and the longitudinally extending joint gap 18 can be seen.
  • the two parts 15 and 16 are connected to each other via plug-in hollow cylinder 54, 55 together.
  • the hollow cylinders are held together by a connecting pin 60.
  • the two hollow cylinders form an inner cavity 57 in the interior, into which the released gases expand when the connecting pin 60 is triggered.
  • Fig. 7 shows the connection of the two halves 15, 16 via the plug-in hollow cylinder 54 and 55 in detail.
  • a first hollow cylinder 54 of the part 15 engages in a second hollow cylinder 55 of the part 16.
  • the hollow cylinders 54, 55 are movable into each other.
  • the created by the nested hollow cylinder 54, 55 inner cavity 57 is clearly visible.
  • the two parts 15, 16 of the front hood 10 are held together by a connecting pin 60, to which this has a thread 61.
  • a connecting piece 62 is screwed into the part 16.
  • the connecting pin 60 has a predetermined breaking point 63 in the form of a circumferential groove.
  • the connecting pin 60 shows two opening into the inner cavity 57 openings 64.
  • In the interior of the connecting pin 60 has a bore 65 is introduced, which is completely filled with a propellant 66.
  • the propellant 66 can be ignited via a squib 62 introduced in the squib 62, to which the squib 67 has a contact 73 for transmitting an ignition pulse.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (8)

  1. Coiffe largable (10) pour un corps volant, qui est divisée longitudinalement en au moins deux parties (15, 16), et qui est solidarisée par des moyens d'assemblage détachables, dans laquelle les moyens d'assemblage
    a) sont réalisés de façon à séparer activement les au moins deux parties (15, 16) lors du largage,
    b) comprennent une tige d'assemblage (60) pouvant être activée par pyrotechnie, avec un alésage (65) dans lequel un bloc de propergol (66) est introduit, l'allumage du bloc de propergol (66) entraînant le dégagement de gaz qui provoquent la séparation des aux moins deux parties (15, 16),
    et dans laquelle
    c) les au moins deux parties (15, 16) sont solidarisées au moyen de la tige d'assemblage (60) par des cylindres creux (54, 55) pouvant s'engager axialement l'un dans l'autre et formant un espace intérieur creux (57),
    caractérisée en ce que
    d) l'alésage (65) de la tige d'assemblage (60) présente une ouverture (64) vers l'espace intérieur creux (57), par laquelle les gaz dégagés lors de l'allumage du bloc de propergol (66) s'écoulent dans l'espace intérieur creux (57) en écartant axialement les cylindres creux (54, 55) l'un hors de l'autre.
  2. Coiffe largable (10) selon la revendication 1, caractérisée en ce que la tige d'assemblage (25, 60) présente un point destiné à la rupture (63).
  3. Coiffe largable (10) selon l'une quelconque des revendications précédentes, caractérisée en ce qu'elle présente une forme de cône, d'ogive ou de paraboloïde.
  4. Coiffe largable (10) selon l'un quelconque des revendications précédentes, caractérisée en ce qu'elle peut, du côté de l'extrémité, être assemblée au corps volant au moyen d'une rainure convexe (40).
  5. Coiffe largable (10) selon l'une quelconque des revendications précédentes, caractérisée en ce qu'une rainure coudée (42) est formée sur la périphérie intérieure en vue du guidage d'une tige (52) disposée sur le corps volant pour l'assemblage avec le corps volant.
  6. Corps volant avec une coiffe largable (10) selon l'une quelconque des revendications précédentes.
  7. Corps volant selon la revendication 6, caractérisé en ce que la coiffe largable (10) s'engage du côté de l'extrémité dans un bourrelet surélevé (49) orienté dans la direction périphérique.
  8. Corps volant selon la revendication 7, caractérisé en ce que le bourrelet surélevé (49) est partiellement interrompu dans la direction périphérique.
EP06012006A 2005-06-27 2006-06-10 Coiffe larguable ainsi que corps volant avec coiffe larguable Active EP1739384B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102005030090A DE102005030090B4 (de) 2005-06-27 2005-06-27 Abwerfbare Vorsatzhaube sowie Flugkörper mit abwerfbarer Vorsatzhaube

Publications (2)

Publication Number Publication Date
EP1739384A1 EP1739384A1 (fr) 2007-01-03
EP1739384B1 true EP1739384B1 (fr) 2008-04-16

Family

ID=37027575

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06012006A Active EP1739384B1 (fr) 2005-06-27 2006-06-10 Coiffe larguable ainsi que corps volant avec coiffe larguable

Country Status (4)

Country Link
US (1) US7661625B2 (fr)
EP (1) EP1739384B1 (fr)
DE (1) DE102005030090B4 (fr)
IL (1) IL176446A (fr)

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FR2966919B1 (fr) * 2010-10-29 2013-11-01 Tda Armements Sas Coiffe aerodynamique secable pour munition guidee et munition guidee comportant une telle coiffe.
FR2966920B1 (fr) * 2010-10-29 2013-05-17 Tda Armements Sas Coiffe aerodynamique ejectable pour munition guidee et munition guidee comportant une telle coiffe.
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US9857154B2 (en) * 2014-07-30 2018-01-02 The United States Of America As Represented By The Secretary Of The Army Steerable munitions projectile
US10030952B1 (en) 2017-03-30 2018-07-24 The United States Of America As Represented By The Secretary Of The Army Thermally deployable shroud for affordable precision guided projectile
FR3065798A1 (fr) * 2017-04-28 2018-11-02 Mbda France Dispositif d'actionnement pour l'ejection d'au moins une partie amovible de missile, en particulier d'une coiffe
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Also Published As

Publication number Publication date
US20070074636A1 (en) 2007-04-05
EP1739384A1 (fr) 2007-01-03
DE102005030090A1 (de) 2006-12-28
IL176446A0 (en) 2007-08-19
IL176446A (en) 2012-05-31
DE102005030090B4 (de) 2007-03-22
US7661625B2 (en) 2010-02-16

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