EP2312256A2 - Dispositif de démarrage d'aéronef - Google Patents

Dispositif de démarrage d'aéronef Download PDF

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Publication number
EP2312256A2
EP2312256A2 EP10013305A EP10013305A EP2312256A2 EP 2312256 A2 EP2312256 A2 EP 2312256A2 EP 10013305 A EP10013305 A EP 10013305A EP 10013305 A EP10013305 A EP 10013305A EP 2312256 A2 EP2312256 A2 EP 2312256A2
Authority
EP
European Patent Office
Prior art keywords
missile
container
launching device
opening
release
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.)
Withdrawn
Application number
EP10013305A
Other languages
German (de)
English (en)
Other versions
EP2312256A3 (fr
Inventor
Jens Wallrabe
Axel Hülsmann
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
Application filed by Diehl BGT Defence GmbH and Co KG filed Critical Diehl BGT Defence GmbH and Co KG
Publication of EP2312256A2 publication Critical patent/EP2312256A2/fr
Publication of EP2312256A3 publication Critical patent/EP2312256A3/fr
Withdrawn legal-status Critical Current

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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
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft
    • 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
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft
    • F41F3/065—Rocket pods, i.e. detachable containers for launching a plurality of rockets

Definitions

  • the invention relates to a missile starting device for a flying platform.
  • a so-called "Hang Fire” can occur, in which the missile jams on the launch rail or another element and the engine of the missile burns without a departure of the missile from the flying platform.
  • a Hang Fire can bring a helicopter into uncontrollable flight attitude.
  • a missile launching device for a flying platform comprising at least one container for receiving a missile, a suspension for mounting the container on the outside of the flying platform and a release means for releasing the missile from the container having an opening of the container closes down, through which the missile can exit with open release agent down from the container.
  • the missile can leave the container and thus the platform initially freely falling and be started only after a predetermined flight time or route, so that a Hang Fire can be safely avoided.
  • the missile does not act on the platform when starting or dropping, z. B. by recoil or jet engine, and thus not endangered.
  • the container is not from the jet of the engine of the missile and thus has a longer life and can be reused without much maintenance.
  • the invention is particularly advantageous applicable to helicopters, which are particularly sensitive to flight disturbances by external forces.
  • the missile is suitably a rocket-propelled guided missile.
  • the container is suitably closed around the missile. It protects the missile from environmental influences such as dust, sand and water. This is particularly advantageous when using on-board helicopters located in a corrosive-aggressive saltwater environment.
  • the downward direction may be dictated by the suspension, which may define attachment of the container to the platform in a gravity predetermined orientation of the container.
  • the hanging can be done upside, sideways or elsewhere of the container. It can be suspended, clamped, screwed, laterally or otherwise bearing or otherwise.
  • the suspension is expediently designed so that the container in a stationary position, for. B. the platform on a floor, or in a mostly occupied attitude in its elongated configuration holds at least substantially in the horizontal direction.
  • the release means allows the missile to exit the container perpendicular to its axial direction.
  • the axial direction may be the direction of a driven flight of the missile.
  • the missile can be held in a horizontal orientation and thus aerodynamically on the platform and fall down in this position from the container.
  • the missile is generally elongated and in particular comprises an at least substantially cylindrical portion whose cylinder axis can coincide with the axial direction.
  • the release means has at least one flap closing the opening.
  • a flap is mechanically simple and robust and can be quickly folded down.
  • the flap remains after its release movement for later closing the opening on the container, so that the container is easy to reuse.
  • two mutually symmetrical flaps are present, which release the opening in a common movement.
  • the release means has a closing device for closing the opening after a missile passage during a flight.
  • the container may be resealed during flight, conveniently by means of a biased means which is biased upon opening, but conveniently pre-tensioned prior to opening to facilitate a smooth opening process.
  • the missile may be connected to the platform with a ripcord, in particular with the missile launcher or the container.
  • an ignition control of the engine of the missile can be triggered mechanically.
  • the missile can remain connected to the missile launcher by means of the rip cord.
  • a tensioning of the ripcord causes a tensile force on the missile, whereby a mechanical triggering of the ignition control of an engine of the missile can be brought about.
  • the ripcord can also be used as a trigger to close the opening.
  • the closing device has a particular biased means for connecting to the ripcord of the missile and is prepared for triggering a closing movement by pulling the ripcord.
  • the pull of the rip cord means that the missile is sufficiently far away from the container and this can thus be closed without interference.
  • the drive can be motor or pyrotechnic, but is particularly simple and robust when it is spring-driven.
  • the release of the missile from the container can be done in a two-stage or one-stage process.
  • the missile is still mounted in the container after opening the release means and is released in a second step from the attachment so that it can fall down.
  • the attachment is suitably a suspension at the top of the missile.
  • a release movement of the release agent also releases the missile, so that this z. B. can fall down.
  • the release means expediently has a bearing means for supporting the missile from below. This can be from the Release means are moved away, in particular downwards, so that the missile is released by the release agent.
  • the bearing means can in this case be moved with the opening of the release means and moved away from the missile.
  • the bearing means is provided with a damping means for damping a movement of the missile, in particular in the axial direction.
  • a shock-sensitive missile, z As a missile for a launch from a pipe of a water or underwater vehicle, for a start from the flying platform use, which is usually exposed to greater vibration and vibration.
  • Shocks may be damped differently or additionally when the suspension is provided with a damping means for damping relative movement between the container and the flying platform, in particular for damping radial movement of the missile.
  • a stable and yet simple storage of the missile in the container can be achieved if the bearing means, which may be a bearing rail extending in the axial direction of the missile, permits movement of the missile in the axial direction, and blocking means for blocking movement of the missile in the tangential direction of the missile Missile has.
  • the bearing means which may be a bearing rail extending in the axial direction of the missile, permits movement of the missile in the axial direction, and blocking means for blocking movement of the missile in the tangential direction of the missile Missile has.
  • the missile starting device is provided with an ejection means for ejecting the missile down from the container.
  • the missile can be quickly removed from the platform and can be quickly detonated and moved towards a target accordingly.
  • the drive can be pyrotechnic or spring-driven.
  • the container contains a power supply for a processing means of the missile.
  • the power supply may be used to power up the process means, to operate it, to activate other electronic elements of the missile, e.g. As a sensor, and / or be prepared for determining a status of the missile, z. B. whether he is ready to start or has a defect, the missile contains corresponding elements.
  • the corresponding function is expediently realized by a data processing program to which the process agent has access.
  • the invention is directed to a system of a missile container as described above and a missile.
  • this is provided with at least one radially outwardly shaped and aligned in the axial direction bearing member for supporting on at least one axially aligned bearing means of the missile container. Due to the axial orientation of the bearing element, this is also suitable for guiding in a launch from a pipe, so that the missile is multifunctional in terms of its starting capabilities.
  • the missile comprises wings, which are folded in the container and are provided for unfolding after an exit from the container.
  • a process agent is present in the container and in the missile and the two process means are prepared for communication with each other.
  • Both process agents can, for. B. with respect to interface and software can be easily adapted to each other, so that can be dispensed with a corresponding adjustment between platform and missile.
  • the invention is directed to a system of missile launcher and flying platform, in particular together with the missile.
  • the invention is directed to a method for launching a missile from a flying platform, wherein the missile is mounted in a container and exits for discharging from the container. It is proposed that the container is opened by a release agent down, the missile exits down from the container and undergoes an engine-induced feed after completion of a fall distance. The missile can be safely and reliably removed from the platform and ignited only at a safe distance from it.
  • the missile is connected to the container with a ripcord, and a pull of the ripcord triggers an unfolding of wings of the missile.
  • a container-bound and thus safe storage of the missile can be connected to a secure deployment of the missile at a designated distance from the platform.
  • the unfolding of the wings is expediently preceded by starting of an engine of the missile, so that the propulsion takes place only after a maneuverability of the missile.
  • a multifunctional applicability of the missile is achieved when a missile executed in its exterior design identical missile from a tube of a submarine can be fired. This multifunctionality can be assisted if the missile in the tube is guided out of the tube by means of at least one radially outwardly oriented and axially aligned bearing element and the missile in the missile container is held with the bearing element on at least one axially aligned bearing means of the missile container, is held in particular axially displaceable.
  • FIG. 1 shows a missile starting device 2 in four successive states on an only schematically indicated flying platform 4, z. B. a helicopter. Each state is shown by a partial representation.
  • the missile starting device 2 has a likewise only schematically illustrated suspension 6, with which the missile starting device 2 with the platform. 4 can be connected so that they outside and z. B. suspended under the platform 4 in the air.
  • Main component of the missile starting device 2 is a container 8 for supporting a missile 10, which is shown in the lower two partial views.
  • the missile 10 is a guided missile with rocket engine.
  • FIG. 2 shows the missile starting device 2 in an exploded view, in which the container 8 with an upper half 12 and a lower half 14 is shown. Both halves 12, 14 completely surround the missile 10 from all sides, so that it is protected against dust, water and the like.
  • the lower half 14 is provided with two mutually opposite opening flaps 16, which in its open position, an opening 18 (FIG. FIG. 1 ), through which the missile 10 can fall down from the container 8 with only one translational movement perpendicular to its axial direction 20.
  • the flaps 16 form elements of a release means 24 for releasing the missile 10 from the container 8.
  • the release means 24 further comprises a drive 26 for driving the opening movement of the flaps 16 and thus the release means 24 per se, with a linkage 28 which is connected on one side with the flaps 16 and on the other side with a biased spring mechanism. This presses in the opening case, the flaps 16 apart very quickly, so that the missile 10 superimposed storage means 30 move faster at the flaps 16 down as the missile 10 falls down from the container 8.
  • the drive 26 is connected to an additional preloaded spring mechanism which closes the flaps 16 spring-driven again in the corresponding actuation case.
  • the bearing means 30 are in FIG. 3 and FIG. 4 shown in a schematic sectional view and side view. They are designed as axially aligned bearing rails 20, and on them the missile 10 rests with one aligned in the axial direction 20 bearing element 32, which thus extends parallel to its associated bearing means 30 and rests lengthwise on this.
  • the bearing means 30 are each provided with at least one shaping 34 extending in the axial direction 20. In the FIG. 3 Shaping 34 blocked a clockwise rotation and the opposite shaping on the opposite flap 16 blocks a counterclockwise rotation.
  • the same missile 10 can be used for both the use of the platform 4 and a tube of a submarine boat or ship. It should be noted that the missile 10 is exposed to the platform 4 significantly higher shock and vibration than that in the tube of the submarine boat or ship. Nevertheless, in order to be able to use a shock-sensitive missile 10 from the platform 4, the missile 10 is mounted so as to damp several times. Radial damping is effected by the suspension 6, which comprises elastic material, such as rubber or the like, or resilient material, such as a spring, and transmits platform movement in the radial direction only to the container 8 in a damped manner.
  • the suspension 6 which comprises elastic material, such as rubber or the like, or resilient material, such as a spring
  • An axial damping is achieved by a damping means 36 of the bearing means 30, which in FIG. 4 is shown.
  • Two blocks 38 are connected by springs 40, each with a fastening 42, so that the blocks 38 are slidably mounted in the axial direction 20 on the rail 44 of the bearing means 30. If the missile 10 slides back and forth in the container 8 in the axial direction 20, its bearing element 32 abuts against the blocks 38 and are resiliently held by the latter in a play area in which the missile 10 can be moved back and forth.
  • the bearing element 32 and the blocks 38 are each beveled relative to the radial direction to each other, so that a movement away of the bearing means 32 from the bearing element 32 in Direction 46 downward causes an axial distance between blocks 38 and bearing element 32.
  • the container 8 accommodating the missile 10 hangs below or laterally of the platform 4.
  • a preparatory signal is sent by a processing means of the platform 4 to a processing means 48 of the missile launcher 2, which expediently is in the container 8 is arranged.
  • a power supply 50 in the container is used to power the process means 48 and possibly of sensors and / or a processing means 52 of the missile 10 during the transported state.
  • the process means 48 is activated and takes after an initialization process, for. As a startup, his work on.
  • the process means 48 communicates with the processing means 52 and starts a status query of the missile 10 and checks whether it is ready to start.
  • the status query can also be carried out without the process means 52.
  • To eject the missile 10 is another signal from the platform 4.
  • the drive 26 of the release means 24 is actuated, so that a biased spring mechanism, the two flaps 16 opens jerkily. This condition is in the upper right part of the illustration FIG. 1 shown.
  • the missile 10 is released and falls down out of the container 8 out into the open, as in the lower left partial representation of FIG. 1 is shown.
  • ejection elements 68 of ejection means 70 for ejecting the missile 10 downwardly from the container 8.
  • ejection elements 68 may be spring-loaded or equipped with a pyrotechnic propellant and push the missile 10 down and out of the container 8.
  • a rip cord 54 With the missile starting device 2. After a predetermined fall distance, which corresponds to the length of the ripcord 54, the rip cord 54 tensions and causes a tensile force on both the missile 10 and the missile launcher 2.
  • a closing device 56 is actuated, which contains a pre-tensioned pre-opening operation of the flaps 16 drive, which may be integrated in the drive 26.
  • the drive causes via the linkage 28, a closing of the flaps 16 and thus closing the opening 18 of the container 8, so that an aerodynamic continuation flight of the flying platform 4 is ensured.
  • wings 58 of the missile 10 are actuated, which fold out in response to this mechanical signal and make the missile 10 maneuverable.
  • these wings 58 of which at least one can also serve as a rudder, folded on an outer shell of the missile 10, as in FIG. 2 is shown.
  • the engine of the missile 10 is started, either by a mechanical signal of the deployed wings 58 or an electrical signal of the processing means 52 of the missile 10.
  • the mechanism of the ripcord 54 which causes an unfolding of the wings 58 and coupled thereto, or advantageously only later ignition of the engine after a tensioning of the ripcord, it is ensured that an ignition of the engine takes place only when the missile 10 a fixed distance to the container 8 has taken. In this way, a safe onward flight of the platform 4 and a damage-free obtaining the missile starting device 2 and the container 8 can be achieved.
  • the ripcord 54 tears as shown in the lower right hand illustration of FIG. 1 is shown.
  • the missile 10 is ready for use and flies rocket-driven to a destination that z. B. the process means 52 is known.
  • FIG. 5 shows the same missile 10 in a tube 60 of a ship or underwater boat.
  • the following description is essentially limited to the differences from the exemplary embodiment in FIGS FIGS. 1 to 4 which is referred to with regard to features and functions that remain the same.
  • Substantially identical components are basically numbered with the same reference numerals, and features not mentioned are adopted in the following exemplary embodiments without being described again.
  • the tube 60 is provided with a front flap 62 which is replaced by z.
  • pivoting - as in FIG. 5 is indicated - or a translational movement can be opened.
  • a drive 64 which acts on a holding means 66, can now pull the missile 10 somewhat out of the tube 60 in the axial direction 20, so that an initial acceleration of the missile 10 is supported.
  • the missile 10 During its movement in the axial direction through the tube 60, the missile 10 is guided by its bearing elements 32 which slide on the bearing means 30 of the tube 60 in the tube 60, so that a trouble-free exit of the missile 10 from the tube 60 ensures in the surrounding water is. After a short flight through the water, the missile 10 emerges from the water and completes most of the route in the air.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
EP10013305.7A 2009-10-14 2010-10-05 Dispositif de démarrage d'aéronef Withdrawn EP2312256A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200910049410 DE102009049410A1 (de) 2009-10-14 2009-10-14 Flugkörperstartvorrichtung

Publications (2)

Publication Number Publication Date
EP2312256A2 true EP2312256A2 (fr) 2011-04-20
EP2312256A3 EP2312256A3 (fr) 2014-04-02

Family

ID=43111417

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10013305.7A Withdrawn EP2312256A3 (fr) 2009-10-14 2010-10-05 Dispositif de démarrage d'aéronef

Country Status (2)

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EP (1) EP2312256A3 (fr)
DE (1) DE102009049410A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104729367A (zh) * 2015-03-11 2015-06-24 北京航天发射技术研究所 一种重载桁架
WO2018046445A1 (fr) * 2016-09-06 2018-03-15 Thyssenkrupp Marine Systems Gmbh Dispositif de retenue d'un canon d'arme à feu
CN110775277A (zh) * 2019-12-06 2020-02-11 中国工程物理研究院总体工程研究所 一种具有同步性的无人机机载微小型导弹投放分离装置

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022000496A1 (de) 2022-02-09 2023-08-10 Diehl Defence Gmbh & Co. Kg Trägerplattform zum Abschießen oder Abwerfen eines unbemannten Flugkörpers auf ein Ziel und Verfahren zum Betrieb einer solchen Trägerplattform

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3347770A1 (de) * 1982-06-16 1986-10-23 Hunting Engineering Ltd., Ampthill, Bedfordshire Auswerfvorrichtung
US4702145A (en) * 1986-06-17 1987-10-27 Northrop Corporation Stores magazine and launch system
DE4304563C1 (de) * 1993-02-16 1994-04-28 Deutsche Aerospace Vorrichtung zum Lagern eines Flugkörpers in einem Abschußrohr
US6679454B2 (en) * 2002-04-15 2004-01-20 The Boeing Company Radial sonobuoy launcher
DE10342565B4 (de) * 2003-09-15 2007-12-27 Michael Grabmeier Vorrichtung und Verfahren für das Absetzen von Marschflugkörpern mittels Airdrop-Launchern aus Transportflugzeugen

Non-Patent Citations (1)

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

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104729367A (zh) * 2015-03-11 2015-06-24 北京航天发射技术研究所 一种重载桁架
CN104729367B (zh) * 2015-03-11 2017-03-08 北京航天发射技术研究所 一种重载桁架
WO2018046445A1 (fr) * 2016-09-06 2018-03-15 Thyssenkrupp Marine Systems Gmbh Dispositif de retenue d'un canon d'arme à feu
CN110775277A (zh) * 2019-12-06 2020-02-11 中国工程物理研究院总体工程研究所 一种具有同步性的无人机机载微小型导弹投放分离装置
CN110775277B (zh) * 2019-12-06 2024-04-19 中国工程物理研究院总体工程研究所 一种具有同步性的无人机机载微小型导弹投放分离装置

Also Published As

Publication number Publication date
EP2312256A3 (fr) 2014-04-02
DE102009049410A1 (de) 2011-04-28

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