DE102009049410A1 - Missile launcher - Google Patents

Abstract

The invention relates to a missile launching device (2) for suspension on a flying platform (4). In order to achieve a safe launch of the missile (10) on the one hand and external protection of the missile against external influences on the other hand, it is proposed that the missile launching device (2) with at least one container (8) for receiving a missile (10), a suspension 6) for fastening the container (8) on the outside of the flying platform (4) and a release means (24) for releasing the missile (10) from the container (8), which has an opening (18) in the container (8) closes downwards, through which the missile (10) can exit downwards from the container (8) when the release means (26) are open.

Description

The invention relates to a missile starting device for a flying platform.

Guided missiles that are launched from a flying platform, so z. B. from an aircraft or a helicopter, are usually started by a launch rail on which the missile slides in the direction of flight and dissolves after a predetermined distance from her. In this launch process, 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.

It is an object of the invention to provide a missile starting device with which a missile can be safely started.

This object is achieved by 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. In addition, it can be achieved that the missile does not act on the platform when starting or dropping, z. B. by recoil or jet engine, and thus not endangered. Furthermore, the container is not struck by 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 useful 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.

In an advantageous embodiment of the invention, 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.

It is further proposed that the release means has at least one flap closing the opening. A flap is mechanically simple and robust and can be quickly folded down. Advantageously, the flap remains after its release movement for later closing the opening on the container, so that the container is easy to reuse. Conveniently, two mutually symmetrical flaps are present, which release the opening in a common movement.

In order to realize an aerodynamic onward flight of the platform, it is advantageous if 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 with a ripcord to the platform, in particular to the container. As a result, an ignition control of the engine of the missile can be triggered mechanically. The ripcord can also be used as a trigger to close the opening. For this purpose, it is advantageous if 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 train of Ripcord means that the missile is sufficiently far away from the container and this can thus be closed without interference.

In order for the missile to fall undisturbed downward when the release means is opened, it is advantageous if a drive for driving the opening movement of the release means is present. The drive can be motor or pyrotechnic, but is particularly simple and robust when it is spring-driven.

Release of the missile from the container can be done in a two-stage or one-stage process. In a two-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. In a single-stage process, a release movement of the release agent also releases the missile, so that this z. B. can fall down. In such an embodiment of the invention, the release means expediently has a bearing means for supporting the missile from below. This can be moved away from the release agent, 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.

It is also proposed that the bearing means is provided with a damping means for damping a movement of the missile, in particular in the axial direction. As a result, 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.

In a further advantageous variant of the invention, 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.

Advantageously, 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.

In addition, the invention is directed to a system of a missile container as described above and a missile. Appropriately, 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.

In order to realize a compact container, it is expedient if the missile comprises wings, which are folded in the container and are provided for unfolding after an exit from the container.

Further, it is advantageous if in each case 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.

Furthermore, the invention is directed to a system of missile launcher and flying platform, in particular together with the missile.

Furthermore, 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 suggested that the Container is opened by a release agent down, the missile emerges down from the container and learns after completion of a drop route engine-induced feed. The missile can be safely and reliably removed from the platform and ignited only at a safe distance from it.

Advantageously, the missile is connected to the container with a ripcord, and a pull of the ripcord triggers an unfolding of wings of the missile. In this way, 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.

Further advantages emerge from the following description of the drawing. In the drawings, embodiments of the invention are shown. The drawing and the description contain numerous features in combination, which the skilled person expediently consider individually and will summarize meaningful further combinations.

Show it:

1 a missile launcher having a missile in four consecutive states,

2 the missile starting device and the missile in an exploded view,

3 a bearing rail of the missile and a bearing means of the missile starting device in a schematic sectional view,

4 the bearing rail and the bearing means in a schematic side view and

5 The missile in a torpedo tube of a submarine shown in an exploded view.

1 shows a missile starting device 2 in four successive states on a merely schematically indicated flying platform 4 , z. B. a helicopter. Each state is shown by a partial representation. The missile starting device 2 has a suspension also shown only schematically 6 on, with which the missile launcher 2 with the platform 4 can be connected so that they outside and z. B. under the platform 4 hangs freely in the air. Main component of the missile launcher 2 is a container 8th for the storage of a missile 10 which is shown in the lower two partial representations. The missile 10 is a guided missile with rocket engine.

2 shows the missile starting device 2 in an exploded view, in which the container 8th with an upper half 12 and a lower half 14 is shown. Both halves 12 . 14 enclose the missile 10 complete from all sides, so that it is protected against dust, water and the like. The lower half 14 is with two flaps opening in opposite directions 16 provided, which in its open position an opening 18 ( 1 ), through which the missile 10 with only one translational motion perpendicular to its axial direction 20 down from the container 8th can fall. To allow the pivoting opening movement of the flaps 16 These are hinges 22 at the bottom half 14 of the container 8th stored. The flaps 16 form elements of a release agent 24 to release the missile 10 from the container 8th ,

The release agent 24 also includes a drive 26 for driving the opening movement of the flaps 16 and thus the release agent 24 in itself, with a linkage 28 on one side with the flaps 16 and on the other side connected to a preloaded spring mechanism. This presses in the opening case, the flaps 16 very quickly apart, leaving the missile 10 stored storage equipment 30 at the flaps 16 Move down faster than the missile 10 down from the container 8th fall out. The drive 26 is connected to an additional preloaded spring mechanism, which in the corresponding actuation case, the flaps 16 spring-operated closes again.

The storage means 30 are in 3 and 4 shown in a schematic sectional view and side view. They are considered in the axial direction 20 aligned bearing rails executed, and on them the missile rests 10 with one in the axial direction 20 aligned bearing element 32 , the thus parallel to its associated storage means 30 extends and rests lengthwise on this. To a twisting of the missile 10 to block in the tangential direction in the stored state, the storage means 30 each with at least one in the axial direction 20 extending shape 34 Mistake. In the 3 shown shape 34 blocks a clockwise rotation and the opposing shape on the opposite flap 16 blocks turning counterclockwise.

It is preferable that both for the use of the platform 4 as well as from a tube of a submarine boat or ship from the same missile 10 can be used. It should be remembered that the missile 10 at the platform 4 is exposed to significantly higher shocks and vibrations than that in the tube of the submarine boat or ship. Nevertheless, a shock-sensitive missile 10 from the platform 4 to use off, is the missile 10 stored damped several times. Radial damping is provided by the suspension 6 causes the elastic material, such as rubber or the like, or resilient material, such as a spring comprises, and a platform movement in the radial direction only attenuated to the container 8th passes.

An axial damping is provided by a damping means 36 of the storage facility 30 reached that in 4 is shown. Two bucks 38 are about springs 40 with one attachment each 42 connected, so the bucks 38 in the axial direction 20 slidable on the rail 44 of the storage facility 30 are stored. Slips the missile 10 in the container 8th in the axial direction 20 back and forth, so meet his bearing element 32 against the bucks 38 and are held by them resiliently in a game area in which the missile 10 is movable back and forth. To move the bearing means away 30 and with him the bucks 38 from the bearing element 32 when opening the flaps 16 To simplify, are the bearing element 32 and the bucks 38 beveled to each other relative to the radial direction, so that a movement away of the bearing means 32 from the bearing element 32 in the direction 46 down an axial distance between blocks 38 and bearing element 32 causes.

During the flight of the platform 4 depends on the missile 10 accommodating containers 8th below or to the side of the platform 4 , To start the missile 10 becomes a preparatory signal from a process agent of the platform 4 to a process agent 48 the missile starting device 2 sent, which expediently in the container 8th is arranged. A power supply 50 in the container serves to power the process agent 48 and possibly of sensors and / or a process means 52 of the missile 10 during the transported state. The process agent 48 is activated and takes after an initialization process, eg. As a startup, his work on.

The process agent 48 communicates with the process agent 52 and starts a status query of the missile 10 and check if it is ready to go. The status query can also be done without the process agent 52 respectively. To drop the missile 10 another signal comes from the platform 4 , This signal is the drive 26 of the release agent 24 operated, leaving a preloaded spring mechanism the two flaps 16 opens jerkily. This condition is in the upper right part of the illustration 1 shown. The missile 10 is released and falls down from the container 8th out into the open, as in the lower left partial representation of 1 is shown.

To assist and accelerate the escape of the missile 10 from the container are two ejection elements 68 an ejection means 70 for ejecting the missile 10 down from the container 8th available. These ejection elements 68 can be spring-loaded or equipped with a pyrotechnic propellant and press the missile 10 down and out of the container 8th out.

While falling, the missile remains 10 first by a ripcord 54 with the missile starting device 2 connected. After a given fall distance, the length of the ripcord 54 corresponds, the ripcord spans 54 and causes a pulling force on both the missile 10 as well as on the missile launcher 2 ,

By the tensile force on the missile starting device 2 becomes a locking device 56 operated, the one before an opening operation of the flaps 16 Contains preloaded drive in the drive 26 can be integrated. The drive operates via the linkage 28 a closing of the flaps 16 and thus closing the opening 18 of the container 8th , allowing an aerodynamic onward flight of the flying platform 4 is guaranteed.

Due to the tensile force on the missile 10 become wings 58 of the missile 10 operated, which fold out on this mechanical signal and the missile 10 maneuverable. Inside the container 8th are these wings 58 , of which at least one can also serve as a rudder, to an outer shell of the missile 10 folded, as in 2 is shown. After all the wings 58 fully unfolded, becomes the engine of the missile 10 started, either by a mechanical signal of the unfolded wings 58 or an electrical signal of the process agent 52 of the missile 10 ,

By the mechanism of the ripcord 54 , who folds out the wings 58 and coupled thereto or advantageously only later ignition of the engine causes only after a tensioning of the ripcord, it is ensured that ignition of the engine takes place only when the missile 10 a fixed distance to the container 8th has taken. This allows a safe onward flight of the platform 4 and a damage-free obtaining the missile starting device 2 and the container 8th be achieved.

Upon further removal of the missile 10 from the missile launcher 2 towards and after the signal to close the flaps 16 and unfolding the wings 58 tears the ripcord 54 as in the lower right illustration of the 1 is shown. The missile 10 is ready for action and flies rocket-powered to a destination that z. B. the process agent 52 is known.

5 shows the same missile 10 in a tube 60 a ship or an underwater boat. The following description is essentially limited to the differences from the exemplary embodiment in 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.

Instead of the flaps 16 is the pipe 60 with a front flap 62 provided by z. B. pivoting - as in 5 is indicated - or a translational movement can be opened. This will cause the missile 10 released to the front. A drive 64 holding a holding means 66 attacks, the missile can 10 now in the axial direction 20 a little way out of the pipe 60 pull, allowing an initial acceleration of the missile 10 is supported.

When moving in the axial direction through the pipe 60 becomes the missile 10 through its bearing elements 32 on the storage grounds 30 of the pipe 60 slide, in the pipe 60 guided, so that a trouble-free exit of the missile 10 out of the pipe 60 is ensured in the surrounding water. After a short flight through the water, the missile dives 10 out of the water and completes most of the flight in the air.

LIST OF REFERENCE NUMBERS

2

Missile launcher

4

platform

6

suspension

8th

container

10

missile

12

half

14

half

16

flap

18

opening

20

axially

22

hinge

24

release means

26

drive

28

linkage

30

bearing means

32

bearing element

34

formation

36

damping means

38

buck

40

feather

42

attachment

44

rail

46

direction

48

process means

50

power supply

52

process means

54

ripcord

56

closing device

58

wing

60

pipe

62

flap

64

drive

66

holding means

68

ejection element

70

ejection means

Claims (24)

Missile launching device ( 2 ) for suspension to a flying platform ( 4 ) with at least one container ( 8th ) for receiving a missile ( 10 ), a suspension ( 6 ) for fastening the container ( 8th ) on the outside of the flying platform ( 4 ) and a release agent ( 24 ) for releasing the missile ( 10 ) from the container ( 8th ), which has an opening ( 18 ) of the container ( 8th ) down, through which the missile ( 10 ) with the release agent ( 26 ) down from the container ( 8th ) can escape. Missile launching device ( 2 ) according to claim 1, characterized in that the container ( 8th ) around the missile ( 10 ) is closed. Missile launching device ( 2 ) according to claim 1 or 2, characterized in that the release agent ( 24 ) an exit of the missile ( 10 ) perpendicular to its axial direction ( 20 ) from the container ( 8th ) allowed. Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the release agent ( 24 ) at least one the opening ( 18 ) closing flap ( 16 ) having. Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the flap ( 16 ) after its release movement for later closing the opening ( 18 ) on the container ( 8th ) remains. Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the release agent ( 24 ) a locking device ( 56 ) for closing the opening ( 18 ) after a missile passage during a flight. Missile launching device ( 2 ) according to claim 6, characterized in that the closing device ( 56 ) means for connecting to a ripcord ( 54 ) of the missile ( 10 ) and for triggering a closing movement by pulling the ripcord ( 54 ) is prepared. Missile launching device ( 2 ) according to one of the preceding claims, characterized by a drive ( 26 ) for driving the opening movement of the release agent ( 24 ). Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the release agent ( 24 ) a storage means ( 30 ) for storing the missile ( 10 ) from below. Missile launching device ( 2 ) according to claim 9, characterized in that the bearing means ( 30 ) with the opening of the release agent ( 24 ) and moved by the missile ( 10 ) is moved away. Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the bearing means ( 30 ) with a damping agent ( 36 ) for damping a movement of the missile ( 10 ) in the axial direction ( 20 ) of the missile ( 10 ) is provided. Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the suspension ( 6 ) with a damping means for damping a relative movement between the container ( 8th ) and the flying platform ( 4 ) is provided. Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the bearing means ( 30 ) one in the axial direction ( 20 ) of the missile ( 10 ) extending bearing rail, which is a movement of the missile ( 10 ) in the axial direction ( 20 ), and a blocking agent ( 34 ) for blocking a movement of the missile ( 10 ) in the tangential direction of the missile ( 10 ) having. Missile launching device ( 2 ) according to one of the preceding claims, characterized by an ejection means ( 70 ) for ejecting the missile ( 10 ) from the container ( 8th ). Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the container ( 8th ) a power supply ( 50 ) for a process agent ( 48 ) of the container ( 8th ) contains. Missile launching device ( 2 ) according to one of the preceding claims, characterized in that the container ( 8th ) a process agent ( 48 ) for determining a status of the missile ( 10 ) is prepared. System of a missile starting device ( 2 ) according to one of the preceding claims and a missile ( 10 ), the at least one radially outwardly shaped and aligned in the axial direction bearing element ( 32 ) for supporting on at least one axially aligned bearing means ( 30 ) of the missile starting device ( 2 ) having. System according to claim 17, characterized in that the missile ( 10 ) Wings ( 58 ) contained in the container ( 8th ) are folded and to unfold after an exit from the container ( 8th ) are provided. System according to claim 17 or 18, characterized in that in the container ( 8th ) and in the missile ( 10 ) a process agent ( 48 . 52 ) and the two process agents ( 48 . 52 ) are prepared for communication with each other. Method for starting a missile ( 10 ) from a flying platform ( 4 ), in which the missile ( 10 ) in a container ( 8th ) is held and for starting from the container ( 8th ), characterized in that the container ( 8th ) by a release agent ( 24 ) is opened down, the missile ( 10 ) down from the container ( 8th ) and experiences an engine-induced feed after completion of a drop distance. Method according to claim 20, characterized in that the missile ( 10 ) with a ripcord ( 54 ) with the container ( 8th ) and a pull of the ripcord ( 54 ) an unfolding of wings ( 58 ) of the missile ( 10 ) triggers. A method according to claim 21, characterized in that starting of an engine of the missile ( 10 ) after unfolding the wings ( 58 ) he follows. Method according to one of claims 20 to 22, characterized in that a to missile ( 10 ) in its exterior design identical executed further missile ( 10 ) from a pipe ( 60 ) of a submarine is fired. A method according to claim 23, characterized in that the missile ( 10 ) in the pipe ( 60 ) by means of at least one radially outwardly shaped and aligned in the axial direction bearing element ( 32 ) in its execution movement out of the pipe ( 60 ) and the missile ( 10 ) in the container ( 8th ) with the bearing element ( 32 ) at least one in the axial direction ( 20 ) bearing means ( 30 ) of the container ( 8th ) is held.

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