DE102019008539A1 - Missile with pyrotechnic release - Google Patents

Abstract

A missile (2) contains a device (4) for unlocking a component (8) locked by a bolt (6), with the at least one bolt (6) between a block position (PB) locking the component (8) and a the release position (PF) releasing the component (8) is movable, with a pyrotechnic force element (16) with an output (18) which can be moved pyrotechnically from a passive position (PP) into an active position (PA) in response to a trigger signal (SA) , and with a coupling element (27) through which at least one of the bolts (6) is coupled in terms of movement to the output (18) in such a way that a mechanical movement of the bolt (6) from the block position (PB) into the release position (PF) occurs a movement of the output (18) from the passive position (PP) to the active position (PA) or vice versa. During a process to unlock the component (8), the bolt (6) is moved from the block position (PB) to the release position ( PF) moves the output (18) from the Passive position (PP) is moved into the active position (PA), the coupling element (27) moving the bolt (6) with the output (18) so that the movement of the output (18) changes the movement of the bolt (6) from the block position (PB) in the release position (PF) conditionally or vice versa.

Description

The invention relates to a missile.

A certain component of a missile should only be activated / moved / ... at a certain point in time. This should be locked or unlocked for this purpose. For example, the canards of a missile should only emerge from the missile at a desired point in time. It must be ensured that they remain locked in their waiting position until this point in time and are unlocked at the right moment and can stand up.

From previous practice it is known to implement such an unlocking via a locking pin which is pulled via a mechanism. For this purpose, for example, electrical locking bolts or linear actuators are known (https://www.continental-automotive.com/en-GL/Passenger-Cars/Powertrain/Gasoline-T echnologies / Gas-Exchange / Air-Path / Digital-Linear- Actuator).

The object of the invention is to propose a solution for a corresponding missile with such a component.

The object is achieved by a missile according to patent claim 1. Preferred or advantageous embodiments of the invention and other categories of the invention emerge from the further claims, the following description and the attached figures.

The missile contains a device for locking and / or unlocking, in particular only for unlocking, a component locked by a bolt. The device comprises at least one bolt which can be moved between a block position that locks the component and a release position that releases the component, or is moved during unlocking. The device comprises a pyrotechnic force element with an output (output element, output part, ...) which can be or is moved pyrotechnically from a passive position into an active position in response to a trigger signal. The output is therefore moved pyrotechnically. Pyrotechnics is part or the drive element of or in the power element. The device comprises a coupling element through which at least one of the bolts is coupled in motion to the output as follows: A mechanical movement of the bolt from the block position to the release position is caused by a movement of the output from the passive position to the active position or vice versa. A corresponding movement coupling is therefore carried out during operation. In particular, several latches per component can be provided in the missile and / or a multi-part component can be provided, the respective parts of which are held by one or more latches. Several components can also be provided, each of which is locked by at least one of the bolts, etc.

The formulation “or vice versa” is to be understood as follows: The transition from the release position to the block position can also be caused by the transition from the passive to the active position. The variants can in each case - in the case of several bars - be provided identically or mixed differently for all bars. Locking instead of unlocking can also take place, etc.

The missile or the device or the locking / unlocking itself is very robust with respect to environmental influences.

In a preferred embodiment, at least one of the bolts is at least partially moved or movable by a rotary movement between the block position and the release position, or it is moved accordingly during operation. In any case, there is a rotation of the bolt, in particular about a single, preferably also several axes of rotation, optionally combined with a translation. Corresponding movements are particularly favorable for missiles.

In a preferred embodiment, at least one of the bolts is made in one piece with at least one section of the coupling element. In particular, one or more latches are made in one piece with the entire coupling element. In particular, the one-piece object is a stable, rigid, but as intended (due to the movement of the output) deformable object. This leads to a particularly simple and fail-safe design of the device.

In a preferred embodiment, the coupling element is or is moved by the movement of the output and the bolt is moved based on the movement of the coupling element and / or the coupling element is deformed by the movement of the output and the bolt is moved based on the deformation of the coupling element. The output can cause both movements and deformations on the coupling element. Various constructive solutions for the device are thus possible. In particular, a deformation is associated with a movement.

In a preferred variant of this embodiment, the coupling element is or is exclusively moved by the movement of the output and the bolt is moved based on the movement of the coupling element. So there is no deformation here. Such a device is particularly very little force (the output does not have to apply much force) can be realized.

In a preferred embodiment, the coupling element is a joint arrangement with at least one joint, i. H. the coupling element contains at least one joint. This embodiment is particularly suitable in combination with the exclusive movement without deformation, as explained above. However, a combination of deformation and joint arrangement is also conceivable.

In a preferred embodiment, the force element has a base body and the output can be moved relative to the base body between the passive position and the active position or is moved accordingly. The output here in particular performs a linear movement with respect to the base body. Such force elements are commercially available. In particular, the base body is attached to a fixed structure (e.g. base structure / support structure / shell / ...) of the missile, so that the output acts as an actuator that moves relative to the fixed structure.

In a preferred variant of this embodiment, the device contains at least one support that is stationary relative to the base body. The coupling element rests on the support (at least in the active or passive position of the output). The support is or forms a point of rotation and / or displacement for the movement (rotation and / or translation) of the coupling element. This results in devices that are particularly simple and robust in terms of construction. In particular, the support is formed by part of the above-mentioned fixed structure of the missile, so that the output acts as an actuator that moves relative to the support.

In a preferred variant of this embodiment, the device contains at least two supports and the coupling element is a - in particular deformable - body which rests on both supports (at least in the active or passive position of the output). The output is deforming and / or moving (see the options above) between the supports on the coupling element. When the force element is triggered or the output is moved, the coupling element is deformed and / or moved between the two supports. This leads to a particularly robust device. In particular, there is, in particular, a bending of the coupling element between the supports, which serve as a support for the movement / deformation.

In a preferred variant of this embodiment, the coupling element or the body is or will be drawn between the supports when it is deformed and / or moved by the output and at least one of the bars is over one of the supports, in particular outwards ("outside": in particular on the other side with respect to the point of application of the output and / or with respect to the two supports, ie not between these), protruding portion of the coupling element or the body is formed. As a result of the deformation and / or movement of the body between the supports, the part / section of the coupling element that protrudes beyond the supports, and thus the bolt, is also moved. This leads to a structurally particularly simple solution.

In a preferred embodiment, the component is a wing of the missile. The wing is in particular a tail unit, rudder, canard, etc. Corresponding wings can be developed particularly easily thanks to the invention.

• - wird der Riegel von einer das Bauteil verriegelnden Blockposition in eine das Bauteil freigebende Freigabeposition bewegt (oder umgekehrt, siehe oben),
• - wobei ein Abtrieb eines pyrotechnischen Kraftelements auf ein Auslösesignal hin pyrotechnisch aus einer Passivposition in eine Aktivposition bewegt wird,
• - wobei ein Koppelelement den Riegel mit dem Abtrieb derart bewegungskoppelt, dass die Bewegung des Abtriebs von der Passivposition in die Aktivposition die mechanische Bewegung des Riegels von der Blockposition in die Freigabeposition bedingt oder umgekehrt (siehe oben).

The object of the invention is also achieved by a method according to claim 12 for locking and / or unlocking a component of a missile that is locked by a bolt. In the process

• - the bolt is moved from a block position that locks the component to a release position that releases the component (or vice versa, see above),
• - wherein an output of a pyrotechnic force element is moved pyrotechnically from a passive position into an active position in response to a trigger signal,
• - A coupling element coupling the bolt with the output so that the movement of the output from the passive position into the active position causes the mechanical movement of the bolt from the block position into the release position or vice versa (see above).

The method and at least some of its embodiments as well as the respective advantages have already been explained in the same way in connection with the missile according to the invention.

In a preferred embodiment, the bolt is at least rotated, that is to say moved rotationally, in particular moved in a translatory manner. This has already been explained above in connection with the missile.

In a preferred embodiment, the coupling element is moved and / or deformed in order to move the bolt. This has already been explained above in connection with the missile.

In a preferred embodiment, the coupling element is placed on two supports and is deformed and / or moved between them. This has already been explained above in connection with the missile.

The invention is based on the following findings, observations and considerations and also has the following embodiments. The embodiments are sometimes also referred to as “the invention” for the sake of simplicity. The embodiments can also contain parts or combinations of the above-mentioned embodiments or correspond to them and / or optionally also include embodiments not mentioned so far.

The invention is based on the idea of a rigid and / or articulated structure (output / coupling element / bolt) which holds a component, in particular canards, in a waiting position (locked position) via a bolt, in particular a retaining lug (nose). If the release of the component, e.g. B. the canards, initiated, a pyrotechnic force element is ignited and deformed and / or shifts this structure. The retaining lugs (latch) move away from the component (canard) and unlock it, giving this z. B. the opportunity to line up.

The invention is very robust against environmental influences. There are no freely movable parts required, which can become loose due to vibrations or shocks. There are no bearing points necessary or available that could solidify due to corrosion.

In particular, the invention has no gears or freely moving parts. The required movement is generated in particular by a deformation and / or displacement. This results in a high level of resistance to incorrect behavior and environmental influences. The system is hardly subject to tolerances and is easy to manufacture. The system can be used where space is limited.

The invention is based on the basic idea or works by deforming and / or shifting a structure (output / coupling element / bolt). The structure is shown in particular as a beam with two supports, which are located away from the ends of the beam and within the length of the beam. A force is applied to the beam between the supports by means of a pyrotechnic force element (its output). When the structure is loaded, the free ends of the beam are raised and unlock the canards attached there. A self-locking force element (the output is secured in the active position in particular) and a plastic deformation of the structure (of the coupling element) means that the unlocking remains active and prevents it from being locked again.

According to the invention there is a pyrotechnic unlocking. According to the invention, a structure (coupling element) is forced into a desired deformation by a pyrotechnic force element and the structure thereby releases the lock.

The invention can be used in a floor to prevent accidental unlocking of the component or the canards and to achieve a desired unlocking via an electrical impulse from the electronics. In this way, the component / canards can be unlocked / step out of the projectile at a desired point in time.

• 1 eine Vorrichtung eines Flugkörpers zur Entriegelung eines Bauteils mit dem a) verriegelten und b) entriegelten Bauteil,
• 2 eine alternative Vorrichtung mit gelenkigem Koppelelement im a) verriegelten und b) entriegelten Zustand,
• 3 eine Draufsicht auf die Vorrichtungen aus den 1 und 2 in Richtung des Pfeils III,
• 4 einen Flugkörper mit alternativer Vorrichtung und ver- und entriegelten Flügeln.

Further features, effects and advantages of the invention emerge from the following description of a preferred exemplary embodiment of the invention and the attached figures. They show, in each case in a schematic principle sketch:

• 1 a device of a missile for unlocking a component with the a) locked and b) unlocked component,
• 2 an alternative device with an articulated coupling element in a) locked and b) unlocked state,
• 3rd a plan view of the devices from FIG 1 and 2 in the direction of arrow III,
• 4th a missile with an alternative device and locked and unlocked wings.

1 shows a schematic diagram of a section from a missile, not shown in detail 2 holding a fixture 4th contains. The missile 2 extends along a central longitudinal axis 3rd . The device 4th is used to unlock four (see also 3rd ), each with a latch 6th locked, not shown components 8th , of which in 1 only one is indicated by way of example. 1a shows the component 8th in the locked state when a nose 10 of a bolt 6th a head start 12th of the component 8th engages behind and so a movement of the component 8th in the direction of the arrow 14th prevented. Overall, the device has 4th over four bars 6th , of which in 1a only two are visible. 1a shows a block position PB the latch 6th in which you can find the respective components 8th lock. The latch 6th can be moved into a release position FP in which they hold the respective component 8th released as in 1b is shown. The component 8th can then move in the direction of the arrow 14th move.

The device 4th contains a pyrotechnic power element 16 with one output 18th in the form of an output element, here a tension bolt. The power element 16 contains a basic body 20th , which is in a cup-shaped recess here 22nd a supporting structure 24 the device 4th or the missile 2 is fixed. The downforce 18th is relative to the body 20th linear in the direction of an arrow 26th to a trigger signal SA (here only indicated symbolically) pyrotechnically from a passive position PP ( 1a) in an active position PA ( 1 b) moveable.

The device 4th contains a coupling element 27 . The coupling element 27 is through a screw connection (thread in the output 18th , Hole in the coupling element 27 screwed-in screw with washer) at the output 18th fixed. Through the coupling element 27 are the bars 8th with the downforce 18th Movement-coupled as follows: a movement of the output 18th from the passive position PP in the active position PA in the direction of the arrow 26th causes the latch to move 6th from the block position PB in the release position PF . This is achieved by the above-mentioned tensile screw connection of the output 18th on the coupling element 27 causes. The corresponding movement coupling is through the 1a, b shown. The latch 6th are integral with the coupling element 27 or its respective sections 32 , here end sections (see also 3rd ). The coupling element 27 is designed here in the form of a cross or two crossed bars.

The movement of the latch 6th takes place here by a combination of a rotary or rotary movement (arrow 28 ) and a translational or shifting movement (arrow 30th ), in the 1b is indicated. The movement takes place on or around a support 36 or its pivot and shift point 38 .

1b it can be seen that due to the movement of the output 18th in the direction of the arrow 26th the coupling element 27 is both moved and deformed. The deformation occurs in the form of a bend in the area 34 of the coupling element 27 on. Due to the deformation and bending, the latches become 6th emotional. In 1b is opposite thanks to the deformation that has taken place 1b now also the (end) section 32 of a third arm / beam of the coupling element 27 and a third bolt is molded onto it 6th has become visible in the middle of the image in its release position FP.

The device 4th contains a total of four supports 36 on which the coupling element 27 rests. The supports 36 form a respective point of rotation and displacement 38 for the movement of the coupling element 27 . The supports 36 are here together as a ring-shaped collar 37 the supporting structure 24 , the central longitudinal axis 3rd executed ring-shaped surrounding, wherein 1a, b shows alternative variants (left and right in the picture) of a collar cross-section. In reality, the collar is 37 in particular uniformly formed.

The coupling element 27 is one in itself in positions PB , PF or states PA , PP more rigid, but at the transition between these through the output 18th deformable body resting on the four supports 36 rests. The downforce 18th is thus deforming between the supports 36 on the coupling element 27 connected, here by the above-mentioned screw connection in the output 18th . The coupling element is deformed 27 (in 1 centered and down) between the supports 36 drawn. The latch 6th form over the supports 36 each to the outside, i.e. from the connection point of the output 18th seen from beyond the supports 36 , protruding sections 32 of the coupling element 27 .

In a process of unlocking the through the bolt 6th locked components 8th of the missile 2 is proceeded as follows: The latch 6th are of the the components 8th locking block position PB in which the components 8th releasing release position PF emotional. The downforce 18th of the pyrotechnic power element 16 will respond to the trigger signal SA pyrotechnically from the passive position PP in the active position PA emotional. The coupling element 27 couples the bolt 6th with the downforce 18th according to a movement coupling such that the movement of the output 18th from the passive position PP in the active position PA the mechanical movement of the bolt 6th from the block position PB in the release position PF conditionally. The component 8th is off the bolt 6th released or unlocked.

The latch 6th is rotated (arrow 28 ) and moved (arrow 30th ). The coupling element 27 is moved and deformed to the latch 6th to move. The coupling element 27 is for this on four supports 36 placed and deformed between them, i.e. in 1 pulled down and thereby bent.

2 shows the arrangement 1 , but with an alternative coupling element 27 . This is now a joint arrangement and has a total of four joints 40 on. During the movement of the output 18th becomes the coupling element 27 no longer deformed, but the coupling element 27 or its joints 40 are only moved. So are the bars 6th also exclusively through the movement, no longer through the deformation of the coupling element 27 emotional. Otherwise the above apply too 1 statements made analogously for the embodiment according to 2 .

3rd shows the plan view in the direction of arrow III of the arrangements from 1 and 2 . The joints 40 with their respective axes of rotation 42 according to 2 are as a variant of the deformable coupling element 27 indicated by dashed lines. The circular collar is clearly visible again 37 , the one in the area of the coupling element 27 the supports 36 and pivot and displacement points 38 trains. The coupling element 27 with four arms and four integrally molded bars 6th is designed as a holding cross.

4th shows in a view according to FIG 1 and 2 a section from an alternative missile 2 . The components 8th are wings here 44 in the form of canards. 4th shows the block position when pulled out PB or liability position PP the latch 6th as well as a locked wing in the picture on the right 44 . In the picture on the left there is also a dashed line for an active position PA the release position PF of the bolt 6th and the associated position / state of the coupling element 27 shown. In addition, an unlocked and thus out of the missile is shown in dashed lines on the left for this case 2 or its shell 46 or outer contour of worn sash 44 shown. The coupling element 27 is shown here again without a joint and is therefore deformed when unlocking. Alternatively and not shown, the coupling element can also be used here 27 out 2 can be used.

List of reference symbols

2

Missile

3

Central longitudinal axis

4th

contraption

6th

bars

8th

Component

10

nose

12th

head Start

14th

Arrow (triggering component)

16

Power element

18th

Downforce

20th

Base body

22nd

Recess

24

Support structure

26th

Arrow (movement output)

27

Coupling element

28

Arrow (rotation)

30th

Arrow (translation)

32

section

34

Area

36

In stock

37

collar

38

Pivot and shift point

40

joint

42

Axis of rotation

44

wing

46

Shell

PB

Block position

PF

Release position

PA

Asset position

PP

Passive position

SA

Trigger signal

Claims (15)

Missile (2) with a device (4) for locking and / or unlocking a component (8) locked by a bolt (6), - With the at least one bolt (6) which can be moved between a block position (PB) that locks the component (8) and a release position (PF) that releases the component (8), - With a pyrotechnic force element (16) with an output (18) which can be moved pyrotechnically from a passive position (PP) into an active position (PA) in response to a trigger signal (SA), - With a coupling element (27) through which at least one of the bolts (6) is coupled in motion to the output (18) in such a way that a mechanical movement of the bolt (6) from the block position (PB) into the release position (PF) is effected by a Movement of the output (18) from the passive position (PP) to the active position (PA) or vice versa. Missile (2) after Claim 1 , characterized in that at least one of the bolts (6) is at least partially moved by a rotary movement between the block position (PB) and the release position (PF). Missile (2) according to one of the preceding claims, characterized in that at least one of the bolts (6) is made in one piece with at least one section (32) of the coupling element (27). Missile (2) according to one of the preceding claims, characterized in that the coupling element (27) is moved and / or deformed by the movement of the output (18) and the bolt (6) is based on the movement and / or deformation of the coupling element ( 27) is moved. Missile (2) after Claim 4 , characterized in that the coupling element (27) is moved exclusively by the movement of the output (18) and the bolt (6) is moved based on the movement of the coupling element (27). Missile (2) according to one of the preceding claims, characterized in that the coupling element (27) is a joint arrangement with at least one joint (40). Missile (2) according to one of the preceding claims, characterized in that the force element (16) has a base body (20) and the output (18) can be moved relative to the base body (20) between the passive position (PP) and the active position (PA). Missile (2) after Claim 7 , characterized in that the device (4) contains at least one support which is stationary relative to the base body (20) and on which the coupling element rests, the support (36) being a point of rotation and / or displacement (38) for the movement of the coupling element ( 27) is. Missile (2) according to one of the Claims 7 to 8th , characterized in that the device (4) contains at least two supports (36) and the coupling element (27) is a body which rests on both supports (36), the output (18) between the supports (36) on the coupling element (27) is connected. Missile (2) after Claim 9 , characterized in that the coupling element (27) is drawn between the supports (36) during the deformation and / or movement and at least one of the bolts (6) is a section (32) of the coupling element (27) protruding beyond one of the supports (36) ) is trained. Missile (2) according to one of the preceding claims, characterized in that the component (8) is a wing (44) of the missile (2). Method for locking and / or unlocking a component (8) of a missile (2) locked by a bolt (6), in which - The bolt (6) is moved from a block position (PB) that locks the component (8) into a release position (PF) that releases the component (8), - wherein an output (18) of a pyrotechnic force element (16) is moved pyrotechnically from a passive position (PP) into an active position (PA) in response to a trigger signal (SA), - A coupling element (27) coupling the bolt (6) with the output (18) in such a way that the movement of the output (18) from the passive position (PP) to the active position (PA) changes the mechanical movement of the bolt (6) from the block position (PB) to the release position (PF) or vice versa. Procedure according to Claim 12 , characterized in that the bolt (6) is at least rotated. Method according to one of the Claims 12 to 13th , characterized in that the coupling element (27) is moved and / or deformed in order to move the bolt (6). Method according to one of the Claims 12 to 14th , characterized in that the coupling element (27) is placed on two supports (36) and is deformed and / or moved between them.

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