DE102018133073A1 - Launching device for a rocket with a launcher and with a scissor holder - Google Patents

Abstract

The invention relates to a starting device (1) with a launching container (2) and an ejection mechanism (3), wherein a rocket (5) arranged or to be arranged in the launching container (2) can be ejected from the launching container (2) by means of the ejection mechanism (3) A too high maximum acceleration during the starting process is avoided in that the ejection mechanism (3) has a scissor carrier (8) with an articulated chain (9) with several scissor levers (10a / b, 11a / b, 12a / b, 13a / b) The scissor carrier (8) can be spread by means of an actuator arrangement (18, 19) for ejecting the rocket (5).

Description

The invention relates to a launch device for a rocket with a launching container and an ejection mechanism with the features of claim 1.

The missile is placed in the launcher prior to launch. At launch, the rocket is ejected from the launching container using the ejection mechanism without firing the rocket's own drive. The ejection mechanism pushes the rocket out of the launching container at a sufficiently high speed so that it can align itself in the air and can only ignite its own drive outside the launcher. The interior of the container is less loaded by the propulsion jet of the engine in the rocket, since the drive is not started inside the launching container. Such a starting device can also be referred to as a starting system or a vertical starting system. The ejection mechanism has a gas drive, the rocket being thrown out of the container by means of gas pressure.

From the generic DE 102 12 653 A1 a missile launch device with a launch container in the form of a launch tube for receiving the missile is known. The ejection mechanism has a piston, a tail cone of the missile engaging in the piston. The piston is guided inside the launch tube. The missile, namely a guided missile, is supported radially and axially by the tail cone bearing within the piston. Furthermore, the ejection mechanism has a rocket motor or a gas generator which is embedded in the piston or fastened to it. When the firing of the guided missile is initiated, the gas generator is activated and generates a thrust, as a result of which the piston and thus the guided missile to be accelerated are axially accelerated in the launch tube. The piston is driven by the gas generator until the piston hits a piston stop. The piston is mechanically stopped at the piston stop point, whereby the propellant gases of the gas generator are kept within the launch tube.

From the US 9,605,932 B2 a starting device with a gas generator is known. By means of the gas generator, a piston is accelerated along a longitudinal axis of the launch container, which piston ejects a missile from the launch container.

From the US 2008/0148927 A1 a further starting device with a launching container, a gas generator and a slide is known. The slide is sealingly guided on the inside of the container. When the gas charge is detonated, the resulting gas drives the sled together with the missile and ejects the missile from the container. Near the exit opening, the container has openings from which the gas can exit after the carriage has passed through the opening. This will prevent the carriage from being ejected from the container as well.

The state of the art is not yet optimal. There is a risk that a carrier or the missile can tilt in the launching container. There is a very high acceleration due to the ignition of gas charges in the container, which can strain the starting device. Here, high forces and high loads can act on the launcher and the missile. High forces and high loads act on the rocket floor, namely on the end of the rocket facing away from the flight direction. This requires a complex and costly construction of the rocket floor.

The invention is therefore based on the object of designing the starting device in such a way that excessive acceleration during the starting process is avoided.

This object on which the invention is based is now achieved by a starting device having the features of patent claim 1.

Accordingly, in the case of a starting device with a launching container and an ejection mechanism, wherein a rocket arranged or arranged in the launching container can be ejected from the launching container by means of the ejection mechanism, there is a solution to the problem according to the invention if the ejection mechanism has a scissor carrier with an articulated chain with several scissor levers , wherein the scissor carrier is spreadable by means of an actuator arrangement for ejecting the rocket.

The rocket can in particular be supported on a holder, for example a carrier plate, the articulated chain being supported on the one hand on this holder and on the other hand on the launching container, in particular on the bottom of the launching container. The link chain with the scissor levers can also be referred to as "Nuremberg scissors".

The invention has the advantage that the acceleration path can be increased, and so there is less acceleration to achieve a defined speed, and thus smaller forces act on the rocket and the launching container. This results in a lower load on the starting device and the missile. Through the Lower stability requirements for the launching container and / or the rocket can save costs. There is also a cost saving through the reusability of the starting device.

The articulated chain preferably has a plurality of pairs of scissor levers, in particular connected centrally via articulation points, the scissor lever pairs being connected to one another at the ends of the scissor levers via further articulation points. The scissor levers are each articulated to one another at their ends. The scissor levers are preferably arranged in pairs crossed to each other, the ends of such a pair of scissor levers being connected to the ends of a further pair of scissor levers.

The link chain is folded in the basic state and spread in the end position. The pairs of scissors levers are articulated to one another in different planes, with the ends of the pairs of scissors levers lying in one plane each occupying a maximum distance in the basic state and the pairs of scissors levers being at a minimum distance in the longitudinal direction of the launching container. The scissor ends of a pair of scissors levers lying in one plane are maximally apart. The levels extend transversely to the longitudinal direction of the launch container.

The ejection mechanism also has a gas drive in the form of a gas generator cartridge. The actuator arrangement preferably has at least one actuator which can be actuated by means of the gas drive. The gas drive drives at least one actuator, which preferably compresses the scissor ends of a pair of scissors levers in one plane. The at least one actuator acts in particular transversely to the longitudinal direction of the launch container on at least one pair of scissors levers. By pressing together the scissor ends of a pair of scissors levers, the scissor carrier is pushed apart or spread apart in the longitudinal direction of the launch container and the rocket is accelerated and ejected from the launch container.

In a preferred embodiment, the fully spread scissor carrier is longer than the launch container and extends beyond the upward end of the launch container. The scissor carrier can protrude in the maximally extended state, in particular up to 100% of the length of the launch container, beyond the upward end of the launch container, as a result of which the acceleration path can be extended. In the extended end position, the scissor carrier preferably projects between 20% and 50% of the length of the launch container beyond the end of the launch container.

The launching container is preferably designed as a rectangular or in particular square column or as a round cylinder. The launching container is preferably only as long as is necessary to completely accommodate the scissor carrier and the missile in the basic state.

The compression of the scissor ends is possible in particular by means of the following two different embodiments.

In a first embodiment, the actuator arrangement has two actuators, the actuators being able to compress the ends of the pair of scissor levers in the transverse direction to the launching container. In the first embodiment, two linearly acting, in particular telescopic, actuators are preferably arranged to the side of two scissor ends of a pair of scissors levers, into which the gas generated by the gas drive is simultaneously introduced. The actuator accordingly has a displaceable piston or displaceable telescopic elements. The corresponding pistons or telescopic elements are moved in the direction of the scissor ends by the entering gas and thus press the scissor ends together. The two containers or actuators are each connected to the gas drive, in particular the gas generator cartridge, via a feed line.

In a second embodiment, the actuator arrangement has an actuator, the actuator cooperating with two deflecting members, the deflecting members being displaceable in the transverse direction outward by means of the actuator and the acted upon pair of scissors levers being compressible at its ends via the deflecting members. In the second embodiment, exactly one linearly acting actuator is preferably used. The actuator is driven by the gas drive. The gas drive can be arranged within the actuator. Two deflection members are arranged on both sides of the actuator, each of which rests on the actuator on the outside and on the laterally opposite scissor end of a pair of scissor levers. If the actuator is pushed apart by the gas drive, the deflecting members move against each other in such a way that they act in opposite directions on the ends of the scissors at the same time and compress them, so that the rocket is accelerated over the scissor carrier and ejected from the launching container.

Alternatively, it is of course also conceivable for the scissor carriers to be attached to two universal joints or at the ends of the respective pairs of scissors levers in the longitudinal direction of the To push the launching container apart. It is particularly advantageous for this if a universal joint for this purpose is arranged directly on the bottom of the launching container. The ends of the corresponding bottom pair of scissors joints are slidably arranged on the bottom of the launching container and / or on the holder. In particular, there can be corresponding guides for the bottom-side scissor lever ends of the corresponding bottom-side pair of scissor levers. So that the scissor carrier does not tilt, in a preferred embodiment it is guided in the launching container with a guide, for example in the form of a groove.

The gas generator cartridge preferably contains a powder mixture which can be sublimed directly into a gaseous state by means of an electrical ignition. This creates a large pressure within the actuator or actuators, so that the actuator or actuators can very quickly generate a force in the linear direction.

In an alternative embodiment, the gas generator cartridge is arranged outside the firing container and the gas generated when the cartridge is ignited is introduced into the actuator by means of a connecting line. Alternatively, several gas cartridges can also be used. The multiple gas cartridges can be fired at the same time or with a slight time delay so that they can interact for the launch of the rocket.

• 1 in einer schematischen Seitenansicht eine Startvorrichtung mit einem Auswurfmechanismus in einer Grundstellung und einer Rakete,
• 2 in einer schematischen Seitenansicht die Startvorrichtung mit dem Auswurfmechanismus in einer ausgefahrenen Stellung,
• 3 in einer schematischen Schnittansicht eine erste Aktoranordnung in einer ersten Stellung,
• 4 in einer schematischen Schnittansicht die Aktoranordnung aus 3 in einer zweiten Stellung, sowie
• 5 in einer schematischen Schnittansicht eine alternative Aktoranordnung in einer ersten Stellung, sowie
• 6 in einer schematischen Schnittansicht die alternative Aktoranordnung aus 5 in einer zweiten Stellung.

There are now a multitude of possibilities for further developing and developing the starting device according to the invention. For this purpose, reference may first be made to the claims subordinate to claim 1. Preferred embodiments of the invention are explained in more detail below with reference to the drawing and the associated description. The drawing shows:

• 1 a schematic side view of a starting device with an ejection mechanism in a basic position and a rocket,
• 2nd a schematic side view of the starting device with the ejection mechanism in an extended position,
• 3rd a schematic sectional view of a first actuator arrangement in a first position,
• 4th in a schematic sectional view of the actuator arrangement 3rd in a second position, as well
• 5 in a schematic sectional view an alternative actuator arrangement in a first position, and
• 6 in a schematic sectional view of the alternative actuator arrangement 5 in a second position.

In 1 and 2nd is a starting device 1 with a launcher 2nd and an ejection mechanism 3rd shown. The launcher 2nd can be designed as a tube, in particular with a round cross section or as a sleeve with a rectangular, in particular square, cross section.

The launcher 2nd has a first upper end 4th on, one here in the launcher 2nd ordered missile 5 from this end 4th of the launcher 2nd is ejectable. The end 4th can be closed by a lid or cover. It is conceivable that the lid is opened before the ejection or that the lid of the rocket 5 is broken or punctured when ejected.

Furthermore, the launch container 2nd a second lower end 6 on that with a bottom 7 is closed. The ejection mechanism 3rd is on the ground 7 supported. The ejection mechanism 3rd is between the missile 5 and the end 6 of the launcher 2nd arranged. The ejection mechanism 3rd supports itself on the one hand in the end 6 and on the other hand on the rocket 5 from.

The ejection mechanism 3rd now has a scissor holder 8th with an articulated chain 9 on. The link chain 9 is through several scissor levers 10a / b , 11a / b , 12a / b , 13a / b educated. The scissor levers 10a / b , 11a / b , 12a / b , 13a / b are about hinge points 14 pivotally connected to each other in the middle. These unspecified ends of the scissor levers 10a / b , 11a / b , 12a / b , 13a / b are with the next adjacent pair of scissors levers 10a / b , 11a / b , 12a / b , 13a / b connected. The scissors lever 10a / b is with the pair of scissors levers 11a / b via hinge points 15 , 16 and the pair of scissors levers 11a / b is a pair of scissors levers 12a / b via further hinge points 15 , 16 connected. There are a total of four pairs of scissors levers 10a / b , 11a / b , 12a / b , 13a / b available. It is conceivable that more or less pairs of scissors levers 10a / b , 11a / b , 12a / b , 13a / b available. Preferably there are more than two pairs of scissors levers 10a / b , 11a / b , 12a / b , 13a / b available. The scissor bearer 8th is folded in its basic state, so that the scissor ends of a pair of scissors levers 10a / b , 11a / b , 12a / b , 13a / b each in the transverse direction to the longitudinal axis of the launch container 2nd are maximally spaced, as shown in 1 is shown.

The ejection mechanism 3rd now has a gas drive 17th preferably with a gas generator cartridge. This gas drive 17th serves to actuate an actuator arrangement 18th or alternatively an actuator arrangement 19th .

• Die Aktoranordnung 18 weist zwei linear wirkende, insbesondere teleskopierbare Aktoren 20, 21 auf. Die Aktoren 20, 21 wirken dabei quer zur Längsrichtung des Abschussbehälters 2 und dienen dazu die Scherenenden, insbesondere des untersten Scherenpaares 10a/b zusammenzudrücken und so die Rakete 5 aus dem Abschussbehälter 2 auszuwerfen. Die Aktoren 20, 21 sind jeweils über eine Verbindungsleitung 22, 23 mit dem Gasantrieb 17 verbunden. Wenn der Gasantrieb 17 gezündet wird, wirken die Aktoren 20, 21 nach innen in Richtung der Scherenenden und drücken die Scherenenden zusammen. Hierdurch wird der Scherenträger 8 in Längsrichtung gestreckt, wobei die auf einer Grundplatte 24 stehende Rakete 5 in Längsrichtung beschleunigt wird und aus dem Abschussbehälter 2 ausgeworfen wird.

First, the first actuator arrangement 18th based on 3rd and 4th are explained in more detail:

• The actuator arrangement 18th has two linear acting, in particular telescopic actuators 20 , 21st on. The actuators 20 , 21st act transversely to the longitudinal direction of the launch container 2nd and serve the ends of the scissors, especially the bottom pair of scissors 10a / b squeeze and so the missile 5 from the launcher 2nd eject. The actuators 20 , 21st are each via a connecting line 22 , 23 with the gas drive 17th connected. If the gas drive 17th is ignited, the actuators act 20 , 21st inwards towards the scissor ends and press the scissor ends together. This will make the scissors holder 8th stretched in the longitudinal direction, being on a base plate 24th standing missile 5 is accelerated in the longitudinal direction and from the launcher 2nd is ejected.

• Die Aktoranordnung 19 weist ebenfalls einen Gasantrieb auf, der innerhalb eines Aktors 25 angeordnet ist. Der Aktor 25 wirkt ebenfalls quer zur Längsrichtung des Abschussbehälters 2. Es sind jeweils zwei Umlenkglieder 26, 27 vorhanden, die doppelt gekröpft ausgebildet sind. Ein sich in Längsrichtung des Abschussbehälters 2 erstreckender Endbereich 28 des Umlenkglieds 26 liegt dabei am Aktor 25 und der andere, sich in Längsrichtung des Abschussbehälters 2 erstreckender Endbereich 29 wirkt dabei mit einem der Scherenenden zusammen. Das Umlenkglied 27 weist entsprechend gekröpfte Endbereiche 30, 31 auf, wobei der Endbereich 30 an der anderen Seite des Aktors 25 anliegt und der Endbereich 31 an dem anderen Scherenende des beaufschlagten Scherenhebelpaares anliegt. Die Endbereiche 30, 31 erstrecken sich in Längsrichtung des Abschussbehälters 2. Wenn nun durch die Gaserzeugung der Aktor 25 auseinander geschoben wird, verschieben sich die Umlenkglieder 26, 27 derart, dass diese entgegengesetzt von außen auf die entsprechenden Scherenenden einwirken, wodurch diese zusammengedrückt werden, so dass die Rakete 5 über den Scherenträger 8 beschleunigt und aus dem Abschussbehälter 2 ausgeworfen wird.

The alternative actuator arrangement is shown below 19th based on 5 and 6 explains:

• The actuator arrangement 19th also has a gas drive, which is within an actuator 25th is arranged. The actuator 25th also acts transversely to the longitudinal direction of the launching container 2nd . There are two deflection links each 26 , 27 available, which are double cranked. One in the longitudinal direction of the launcher 2nd extending end region 28 of the deflecting member 26 is due to the actuator 25th and the other, in the longitudinal direction of the launcher 2nd extending end region 29 interacts with one of the scissor ends. The deflection link 27 has correspondingly cranked end areas 30th , 31 on, with the end area 30th on the other side of the actuator 25th is applied and the end area 31 abuts the other end of the scissors lever pair. The end areas 30th , 31 extend in the longitudinal direction of the launching container 2nd . If the actuator generates gas 25th is pushed apart, the deflection members move 26 , 27 such that they act in opposite directions on the corresponding ends of the scissors, thereby compressing them so that the rocket 5 over the scissors holder 8th accelerated and out of the launcher 2nd is ejected.

Furthermore, it is conceivable that the scissor levers are pressed apart vertically at two articulation points by means of an actuator (not shown). In particular, it is advantageous here if a universal joint is directly attached to the bottom of the launch container 2nd is arranged.

The gas generator cartridge contains a powder mixture which can be sublimed directly into the gaseous state by means of an electrical ignition. This creates a great deal of pressure within the actuator 20 , 21st or. 25th so these actuators 20 , 21st , 25th can generate force in the linear direction very quickly. So that the scissor holder 8th not tilted, this is in a preferred embodiment in the launching container 2nd guided with a guide, for example in the form of a groove.

In an alternative embodiment, the gas generator cartridge is outside the firing container 2nd arranged and the gas generated during ignition is connected to the corresponding actuator by means of a connecting line 20 , 21st , 25th initiated. Alternatively, several gas cartridges can also be used and fired simultaneously or with a time delay, so that these are used to launch the rocket 5 can work together.

Reference list

1

Starting device

2nd

Launch container

3rd

Ejection mechanism

4th

The End

5

rocket

6

The End

7

ground

8th

Scissors holder

9

Link chain

10a / b

Scissor lever or pair of scissor levers

11a / b

Scissor lever or pair of scissor levers

12a / b

Scissor lever or pair of scissor levers

13a / b

Scissor lever or pair of scissor levers

14

Hinge point

15

Hinge point

16

Hinge point

17th

Gas drive

18th

Actuator arrangement

19th

Actuator arrangement

20

Actuator

21

Actuator

22

Connection line

23

Connection line

24th

Carrier plate

25th

Actuator

26

Deflector

27

Deflector

28

End area

29

End area

30th

End area

31

End area

QUOTES INCLUDE IN THE DESCRIPTION

This list of documents listed by the applicant has been generated automatically and is only included for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent literature cited

• DE 10212653 A1 [0003]
• US 9605932 B2 [0004]
• US 2008/0148927 A1 [0005]

Claims (8)

Starting device (1) with a launching container (2) and an ejection mechanism (3), wherein a rocket (5) arranged or arranged in the launching container (2) can be ejected from the launching container (2) by means of the ejection mechanism (3), characterized in that that the ejection mechanism (3) has a scissor carrier (8) with an articulated chain (9) with a plurality of scissor levers (10a / b, 11a / b, 12a / b, 13a / b), the scissor carrier (8) using an actuator arrangement (18 , 19) for ejecting the rocket (5) is expandable. Starting device according to the above Claim 1 , characterized in that the articulated chain has a plurality of scissor lever pairs (10a / b, 11a / b, 12a / b, 13a / b), in particular connected centrally via articulation points (14), the scissor lever pairs (10a / b, 11a / b, 12a / b, 13a / b) at the ends of the scissors levers (10a / b, 11a / b, 12a / b, 13a / b) are connected to one another via further articulation points (15, 16). Starting device according to one of the preceding claims, characterized in that the actuator arrangement (18, 19) has at least one actuator (20, 21, 25) which can be actuated by means of a gas drive (17). Starting device according to the preceding claim, characterized in that the actuator (20, 21, 25) acts on at least one pair of scissors levers (10a / b) transversely to the longitudinal direction of the launching container (2). Starting device according to the above Claim 3 or 4th characterized in that the actuator arrangement (18) has two actuators (20, 21), the actuators (20, 21) being able to compress the ends of the pair of scissor levers (10a / b) in the transverse direction to the firing container (2). Starting device according to one of the preceding claims, characterized in that the actuator arrangement (19) has an actuator (25), the actuator (25) cooperating with two deflecting members (26, 27), the deflecting members (26 , 27) can be displaced outwards in the transverse direction and the acted upon pair of scissors levers (10a / b) can be compressed at its ends via the deflection members (26, 27). Starting device according to one of the preceding claims, characterized in that the fully spread scissor carrier (8) is longer than the launch container (2) and extends beyond the upwardly directed end (4) of the launch container (2). Starting device according to the above Claim 7 , characterized in that, in the extended end position, the scissor holder (8) projects between 20% and 50% of the length of the launch container beyond the end of the launch container.

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