DE102022003485A1 - Coil unit for a guided missile - Google Patents

Abstract

The invention relates to a coil unit (18) for a guided missile (2) that launches underwater from a launch platform (28), with a missile coil (40) to remain in the guided missile (2) and a coil that is wound onto the missile coil (40) and connected to the launch platform ( 28) data conductor (36) connected in terms of data technology.
In order to increase the unwinding reliability of the data conductor (36) from the missile coil (40), it is proposed that the coil unit (18) has a platform coil (32) wound with the data conductor (36) to remain on the launch platform (28) after the launch of the Guided missile (2) and a housing (48) which keeps the two coils (32, 40) dry when the guided missile (2) is flooded with water.

Description

The invention relates to a coil unit for a guided missile that launches underwater from a launch platform, with a missile coil to remain in the guided missile and a data conductor wound on the missile coil and connected to the launch platform for data technology.

To defend submarines against attacks from rotorcraft from the air, guided missiles are known that launch from a torpedo tube of the submarine, travel through the water to the surface and then head for the aerial target in a subsequent overwater flight. Since the threat situation above the water surface is difficult to track accurately from a submarine, the aerial target can often only be targeted after the guided missile has emerged from the water. A target transfer from the submarine to the guided missile before its launch is not possible.

In order to be able to reliably carry out target selection and target acquisition over water, it makes sense if an operator can recognize and select possible air targets through the seeker head of the guided missile and can hand over the selected air target to the guided missile. However, this is only possible after the launch and after the guided missile has emerged from the water, so a data connection between the guided missile and the launch platform is necessary. Data cables are known for this, which are wound on a spool of the guided missile and unwind during flight, so that the guided missile lays the data cable under water and in the air, via which it remains connected to the launch platform during its flight. Such a guided missile for underwater travel and overwater flight with a coil with a data cable is from the EP2887005A1 known.

It is an object of the present invention to increase the unwinding reliability of the data conductor from the missile coil.

This object is achieved by a coil unit of the type mentioned at the outset, which according to the invention has a platform coil wound with the data conductor for remaining on the launch platform after the guided missile has been launched and a housing which keeps the two coils dry when the guided missile is flooded with water.

The invention is based on the idea that the data cable is heavily stressed when the guided missile is fired from the firing tube if the launch platform moves until the guided missile reaches the aerial target, since the data cable from the launch platform passes through the water is dragged along. With a platform coil that remains on the launch platform and outputs the data cable, the data cable can also be laid from the launch platform in the water, so that the data cable does not have to be dragged and it is protected.

Before a guided missile can launch from a torpedo tube, it must be flooded. Since the data cable runs from the inside of the guided missile to the outside, seawater penetrates into the coil compartment at the start at the latest. At a greater diving depth, if the coil compartment was sealed, it would hit the coil compartment with force during start-up and could damage the cable. It therefore makes sense to keep the coil space open to the outside so that if the torpedo space floods, the sea water can also penetrate into the coil space and create pressure equalization.

During military exercises, a submarine's torpedo tube is flooded for training purposes, even without the missile actually being launched. The same thing happens if a defense against air targets is canceled after the torpedo tube is flooded. The torpedo tube is then pressurized with compressed air and freed from sea water. If necessary, the missile is removed from the torpedo tube for later reuse. The wetting of the missile coil associated with this procedure can lead to corrosion or deposits; in the worst case, repeated flooding can even lead to growth, for example initial barnacles. All of this can endanger the cable being pulled out at high speed during later use. Adverse deposits can be, for example, dried dirt or even initial barnacle formation on the spool or in the spool space. This disadvantage can be countered by keeping the missile coil dry even when the firing tube is flooded. However, if a platform coil is present, this is difficult because the data cable runs from the missile coil of the guided missile to the platform coil of the platform and thus usually through the seawater in the flooded firing tube.

To solve this problem, the invention proposes integrating the platform coil into the coil unit. The platform coil can be part of the guided missile and integrated into it and not, as usual, part of the launch platform. Both coils are combined in the coil unit, which in turn can be part of the guided missile, for example forming a rear section of the guided missile. The housing keeps the coils dry even if the launch platform's firing tube is flooded. So the guided missile can also can be used again after an exercise or after an attack has been aborted, without running the risk of a coil becoming dirty and thus endangering a later cable withdrawal.

The housing is expediently divided into at least two parts with a missile part that remains on the guided missile and a platform part that remains on the launch platform. When the guided missile is started, the missile part with the missile coil can be separated from the platform part and carried along with the guided missile, whereas the platform part with the platform coil remains on the platform. The platform coil routes the data cable according to the movement of the platform and the missile coil according to the movement of the missile, so that any dragging of the data cable can be avoided.

The coil unit carries both coils and has the housing. The housing of the coil unit advantageously forms part of the outer skin of the guided missile, for example the rearmost part of the outer skin. The data conductor is expediently an optical fiber with external insulation. The data conductor can be wound continuously on both coils and connected to a data interface of the coil unit. Via this data interface, for example a plug on the housing of the coil unit, the data conductor can be connected in terms of data technology to a command post on the launch platform, from which an operator can control the guided missile after it has been launched. The missile coil is expediently an external coil, i.e. with a withdrawal to the radial outside. The platform coil, on the other hand, can be an internal coil with a withdrawal radially inwards. The missile coil should be prepared for air extraction, particularly for air extraction at several 100 m/s. The guided missile can be a sea-air target missile and expediently has a rocket engine, in particular a solid fuel engine. Furthermore, a search head for imaging an environment for an operator is useful, and in particular an active body for combating a target.

In an advantageous embodiment of the invention, the housing has a missile part and a platform part. Both parts can be separated from each other, for example when the missile is launched. It is advantageous if both parts interlock and are sealed against each other, for example with a sealing unit. A suitable sealing unit can be an elastic O-ring. The sealing unit should be mounted on or in at least one of the two housing parts in such a way that when the housing parts are removed from one another, it is mounted in a fall-proof manner, expediently in the platform part of the housing, and does not fall onto the data conductor. Both housing parts can be blocked from being separated from one another with a securing means. The securing means can engage in a groove in both housing parts and can be, for example, a securing pin. Separating the two housing parts is only possible when the securing means is unlocked, for example when the securing pin is removed.

A good aerodynamic property of the guided missile can be maintained if the platform part of the housing radially overlaps the missile part, so that it can be axially pushed onto or pulled off the missile part. The missile part of the housing can form a contact surface on its inner housing wall, against which the data conductor rests during air unwinding, so that it is guided outwards through the contact surface. The inner wall of the housing can also have a rear taper, so that the data conductor must move radially inwards when removed before it leaves the missile part of the housing. This can improve the deduction.

It is further advantageous if the sealing unit rests on an outer cone of the missile part in such a way that pulling the missile part off the platform part squeezes the sealing unit together. This allows the force required to separate both housing parts from each other to be increased, so that a certain degree of security against unwanted separation is maintained even when the safety unit is unlocked. This makes sense if the guided missile is inserted into the firing tube with the safety unit unlocked, so that the housing may be exposed to frictional forces on the firing tube wall.

The missile coil can be a unit with multiple windings or coils. For example, the missile coil includes a starting coil and a marching coil. While the starting coil is used for a trigger during underwater travel, the cruise coil can be designed for a high-speed air trigger. Both coils can be external coils. Geometrically, it makes sense if the platform part of the housing containing the platform coil grips around the missile part of the housing containing the missile coil. A largely friction-free removal of the starting coil can be ensured without increasing the diameter of the platform part of the housing.

It has been shown that, particularly for reliable cable withdrawal of the missile coil, it is better if the coil is wetted, as this makes cable withdrawal easier. This is particularly the case an overwater flight, as the strain on the cable is enormous at unwinding speeds of up to 300 m/s. Therefore, coils should be wetted from the firing tube before launching the guided missile. However, this should not be done without actual sealing in order to protect the coils from barnacles or dried dirt when they are used again. In order to achieve this, it is proposed that the coil unit contains a flooding valve for flooding the housing interior. Before an actual launch, the interior can be flooded and the coils can be prepared for launch. In addition, pressure-induced seawater hitting the coil space during start-up can be avoided.

The flooding valve can have a sealing position and a flooding position for flooding the two coils with water flowing around the guided missile, so that the valve can be actively adjusted or the flooding can be initiated at a selectable time after flooding the firing tube and before the launch of the guided missile. The flooding valve is expediently arranged in a front region of the missile coil, for example in an axial position within the front third of the missile coil. However, the flooding valve does not have to be directly next to a coil and can also be located in a housing section in front of the missile coil, in particular up to half the axial coil length in front of the front end of the missile coil. The coil unit then extends to the flooding valve. In order to achieve uniform flooding of the coil space, it makes sense if there are several flooding valves, which are distributed in particular tangentially along the circumference of the housing, for example two or four flooding valves.

The flooding valve can be opened shortly before start. Quick opening is advantageous here. For this purpose, the flooding valve can be a pyrotechnic valve. In addition, the simplicity and reliability speak for a pyrotechnic valve. However, an electromechanical or electromagnetic valve is also possible.

During the flight of the guided missile, it is conducive to the reliability of the unwinding of the data cable from the missile coil if air flows through the coil space, expediently in the unwinding direction, i.e. from front to back, since the data cable is output to the rear. For this purpose, an air opening in the front area of the coil chamber makes sense, which connects the coil chamber with the surroundings of the guided missile. If a flooding valve is present, it is advantageous if the flooding valve is designed as an air purging opening in the open state for flushing around the missile coil during an overwater flight with outside air from outside the guided missile.

The speed of the guided missile under water and also above water influences the inflow behavior of water or air through the flooding valve into the coil space around the winding of the coil. In order to obtain the most even inflow possible, the flooding valve should be designed in terms of its geometry and the geometry of the environment in such a way that the fluid - water or air - flows well into the flooding valve even at low speed. However, at high speed it may then flow too quickly into the spool space and have an undesirable effect on unwinding. In order to keep the flow as uniform and moderate as possible, it is advantageous if the flooding valve has a labyrinth for braking the inflowing fluid, in particular water. A labyrinth can be seen in the fact that the fluid flow is deflected in the tangential direction at least 2 x at least 45°, for example from the axial direction - independent of a radial direction component - at least 45° in the tangential direction and back again. A distribution from one opening of the flooding valve into at least two openings in the coil space can also be viewed as a labyrinth.

In order to allow sufficient fluid to flow through the coil space even at low driving or flight speeds, it is advantageous if the coil unit has a guide vane and a flooding valve in front of the guide vane, which are arranged relative to one another in such a way that the guide vane prevents fluid from flowing in through the flooding valve favored. The forward direction is to be seen in relation to the guided missile or its direction of flight. One possibility is that the geometry of the steering vane increases the fluid pressure, i.e. that of water or air, in the area of the flooding valve compared to a situation without the guiding vane. One way to achieve the higher pressure is for the vane to have a deflector that directs the fluid into the flooding valve. For example, the guide vane can be concave towards the front. However, the deflection means can also be present without the guide vane, so that when the guided missile moves through a fluid, the deflection means directs part of the fluid into the flooding valve.

The invention is also directed to a guided missile with a coil unit as described above. This expediently forms a tail part of the guided missile. By means of a data interface for connection to the launch platform, for example when inserting the guided missile into a firing tube of the launch platform, the data cable can be easily connected to a The command post in the launch platform can be connected for data purposes. The data interface can be a plug which is inserted into a counterpart of the plug in the firing tube when the guided missile is arranged in the firing tube. The interface is expediently arranged in or on the platform part of the housing. If the guided missile moves forward in the firing tube during launch, the platform part is pulled backwards from the missile part of the housing from the missile's perspective and remains in the tube, so that the data connection between the launch platform and, for example, the seeker head of the guided missile via the interface and that connected to it Data cable is retained.

The guided missile is expediently equipped with an engine which can have a central gas guide pipe or at least a side exhaust nozzle. If a side blow-out nozzle is present, it is advantageous if a flooding valve arranged behind the blow-out nozzle is arranged tangentially offset from the blow-out nozzle for flushing the missile coil with outside air during an overwater flight. As a result, the flow of purge air into the coil compartment is not or only slightly influenced by the exhaust jet of the engine and the hot exhaust jet of the engine does not flow into the coil compartment or only flows slightly, so that the data cable is not heated.

The invention is further directed to a method for preparing an underwater launch of a guided missile from a firing tube of a launch platform, the guided missile having a coil unit with a missile coil to remain in the guided missile and a data conductor wound on the missile coil, in which the firing tube is flooded with water and the Guided missile is surrounded by water.

In order to increase the unwinding reliability of the data conductor from the missile coil, it is proposed that, according to the invention, the coil unit also contains a platform coil for remaining on the launch platform and both coils are sealed against the water by a housing of the coil unit and remain dry. The firing tube can be flooded without the coils getting wet, protecting them from deposits.

To protect against sudden intrusion of seawater into the housing, it is advantageous if after the flooding of the firing tube and before the launch of the missile in the firing tube and independently of the flooding of the firing tube, the coil unit is flooded by opening a flooding valve of the coil unit. Water in the sealing tube flows into the coil unit in a controlled manner and ensures pressure equalization between the outside space around the housing and the interior space in the housing.

When the guided missile is started, it is expediently first ejected from the firing tube without starting the engine and then the engine ignites and the guided missile begins its self-propelled underwater journey. After surfacing, overwater flight begins. During all of these phases, there is a data connection between the launch platform and the guided missile, e.g. its seeker head, with a command post for manual control of the guided missile, e.g. through manual target acquisition and target transfer.

During an overwater flight of the guided missile, the missile coil can be surrounded by ambient air flowing in through the flooding valve, so that unwinding of the data cable from the missile coil, in particular from a marching coil of the missile coil, is promoted.

The description given so far of advantageous embodiments of the invention contains numerous features, some of which are summarized in several dependent claims. However, the features can also expediently be considered individually and combined into meaningful further combinations, especially when referring back to claims, so that a single feature of a dependent claim can be combined with a single, several or all features of another dependent claim. In addition, these features can each be combined individually and in any suitable combination both with the method according to the invention and with the device according to the invention according to the independent claims. Thus, process features can also be seen as objectively formulated as properties of the corresponding device unit and functional device features can also be seen as corresponding process features.

The characteristics, features and advantages of this invention described above, as well as the manner in which these are achieved, will be more clearly and clearly understood in connection with the following description of the exemplary embodiments, which will be explained in more detail in connection with the drawings. The exemplary embodiments serve to explain the invention and do not limit the invention to the combination of features specified therein, not even with regard to functional features. In addition, suitable features of each exemplary embodiment can also be viewed explicitly in isolation, from one Embodiment removed, introduced into another embodiment to supplement it and / or combined with any of the claims.

• 1 einen Lenkflugkörper zur Bekämpfung eines Luftziels und für einen Verschuss unter Wasser,
• 2 ein Heckteil des Lenkflugkörpers mit einer Spuleneinheit mit mehreren Datenkabelspulen und
• 3 eine mögliche Ausführung des Heckteils aus 2.

Show it:

• 1 a guided missile for combating an aerial target and for firing underwater,
• 2 a tail part of the guided missile with a coil unit with several data cable coils and
• 3 a possible version of the rear section 2 .

1 shows a guided missile 2 with a seeker head 4, an active part 6 for explosively combating an air target, an engine 8 with at least one side exhaust nozzle 10, which is in 1 is only indicated schematically, a control section 12 with steering wings 14, sliding wings 16 and a tail part in the form of a coil unit 18 with a front missile part 20 and a rear platform part 22. The missile part 20 carries two guide wings 24, of which in 1 only one is visible, and is provided with an inlet opening 26 of a flooding valve.

2 shows the tail part of the guided missile 2 in more detail. For a launch from a launch platform 28, the guided missile 2 is introduced into a launch tube 30 of the launch platform 28, for example a torpedo tube if the launch platform 28 is a submarine. To do this, the sliding wings 16 can be folded backwards, as in 1 is shown in dashed lines, and place it on the fuselage of the guided missile 2. The steering wings 14 can also be created so that the geometry of the guided missile 2 is adapted to the firing tube 30.

The platform part 22 of the coil unit 18 carries a platform coil 32, which contains a winding package 34 of a data conductor 36, which is designed as an optical waveguide with a sheath for external insulation. This continues in the missile part 20 in a winding package 38 of a missile coil 40 and is connected in terms of data technology to a control unit 42 in the control section 12. On the platform side, the data conductor 36 is connected to a command post 46 of the starting platform 28 via a data interface 44. The platform coil 32 is an inner coil for an internal withdrawal of the data conductor 36 and the missile coil 40 is an external coil for an external withdrawal of the data conductor 36. Around both coils 32, 40 there is a housing 48, which is divided into the missile part 20 and the platform part 22. The missile part 20 carries the missile coil 40 and the platform part 22 carries the platform coil 32. Between the coils 32, 40 lies the coil space 50, which is the part of the housing interior filled with air.

In the front area of the coil unit 18, the housing 48 is provided with the inlet openings 26 of the flooding valves 52. The flooding valves 52 are pyrotechnic valves that are controlled by the control unit 42 and open by means of an explosion, i.e. are brought from a sealing position into a flooding position. This opens the inlet opening 26 of the housing 48 and water or air can penetrate into the coil space 50 from outside the guided missile 2. The coil unit 18 is equipped with two flooding valves 52. Just for clarification is in 2 A third flooding valve 52 is shown in the middle, since the flooding valves 52 are each equipped with a labyrinth 54, which is difficult to show in the side view. The labyrinth 54 divides a fluid flow flowing in from the radial outside through the inlet opening 26, i.e. water flow or air flow, into two flows and deflects them laterally tangentially by approximately 60 °, with a second deflection by again 60 ° in the axial direction, so that the Fluid can flow through the coil space 50. As a result, the fluid flow is firstly braked and secondly distributed in the coil space 50. To better introduce the fluid into the inlet openings 26, a deflection means 56 is placed behind each inlet opening 26, which is part of a guide vane 24 and is concavely shaped. The concave shape is created by the deflection means 56 in connection with the housing 48, so that the deflection means 56 presses the fluid into the inlet opening 26, as shown by the outer arrows at the side inlet openings 26.

To prepare for a launch of the guided missile 2, it is inserted into the firing tube 30. With its tail part, the guided missile 2 is guided to the rear end of the firing tube 30, so that the interface 44 of the coil unit 18 is coupled to an interface of the firing tube 30 and the data connection between the control unit 42 and the command post 46 via the data conductor 26 via the two coils 32, 40 will be produced. If an imminent launch of the guided missile 2 is planned, the firing tube 30 is flooded with seawater and opened to the front so that the guided missile 2 can leave the firing tube 30 to the front. Now the guided missile 2 is surrounded with seawater in the firing tube 30. However, the housing 48 seals the two coils 32, 40 against water so that they remain dry. For this purpose, a particularly circumferential sealing unit 58 is arranged between the two housing parts 20, 22, which seals the two housing parts 20, 22 against one another, so that the housing 48 forms a watertight unit. The sealing unit 58 may be an O-ring in a groove. Becomes a If the launch of the guided missile 2 is aborted, the firing tube 30 can be ventilated and the two coils 32, 40 remain dry despite the firing tube 30 being flooded.

However, if the guided missile 2 is to be launched, the interior of the housing is flooded shortly before launch. For this purpose, the control unit 42 controls the pyrotechnic propellants of the flooding valves 52, which ignite and release their inlet opening 26, so that seawater in the flooded firing tube 30 now also floods the coil space 50 and thus wets the two coils 32, 40. This results in a pressure equalization between the coil space 50 and the water surrounding the launch platform 28, so that when the guided missile 2 is launched, no further water shoots into the coil space 50 from behind due to pressure. The flooding of the coil unit 18 is independent of the flooding of the firing tube 30, since both floodings are triggered by an independent command. The command to flood the firing tube 30 is given when the guided missile 2 is to be launched later, even if it is not certain whether it will actually be launched. The coil unit 18 is only flooded when the guided missile 2 is actually started, for example with or connected to the start signal for the guided missile 2.

The launch of the guided missile 2 takes place at the command of the launch platform 28. For this purpose, the guided missile 2 is ejected from the firing tube 30, for example by mechanical claws which force the guided missile 2 out of the firing tube 30. During this underwater launch of the guided missile 2 from the firing tube 30, the missile part 20 of the coil unit 18 separates from the platform part 22 of the coil unit 18. While the missile part 20 is carried along on the guided missile 2, the platform part 22 remains in the firing tube 30 and thus on the starting platform 28. For this purpose the two housing parts 20, 22 are arranged and shaped relative to one another in such a way that the missile part 20 can be pulled forward from the platform part 22. The sealing unit 58 slides along the missile part 20 and remains on the platform part 22. By removing the missile part 20 from the platform part 22, the data conductor unwinds from one or both coils 32, 40, so that the data connection between the command post 46 and the control unit 42 remains .

A few meters in front of the firing tube 30, the engine 8 of the guided missile 2 ignites and accelerates it underwater to an underwater journey. After reaching the water surface, the engine 8 further accelerates the guided missile 2 so that it flies in the air towards its aerial target. For this purpose, there is an image connection to the command post 46 in the starting platform 28 by means of search head 4 and data conductor 36, so that an operator can see the view of the search head 4 on a screen in the command post 46. The operator identifies the aerial target, hands it over to the seeker head 4 and the guided missile 2 independently steers towards the aerial target. The visual or data connection between the search head 4 and the command post 46 is maintained, so that the operator can also control the flight manually, change it to another target or cancel it.

During air flight, the data conductor 36 unwinds from the missile coil 40 at the flight speed of the guided missile 2 and is thereby laid in the air. When the launch platform 28 moves during this flight, the data conductor 36 unwinds from the platform coil 32 and is laid in the water so that it is not pulled behind by the launch platform 28. Immediately after surfacing, the seawater flows out of the coil room 50. Here, air is sucked through the open inlet openings 26, which are now air purging openings of the coil unit 18. The deflection means 56 also forces air into the inlet openings 26, so that the coil space 50 is flushed with outside air, which promotes the unwinding of the data cable 36. So that no hot exhaust gases get into the coil space 50 through the inlet openings 26, the inlet openings 26 are arranged tangentially offset from the blow-out nozzle or nozzles 10, as shown in 1 is shown, so that the hot exhaust gas jet blows past the inlet openings 26.

3 shows a possible design of the rear part of the coil unit 18 2 . The missile coil 40 is divided into a starting coil 60 and a marching coil 62, both of which are external coils. The starting coil 60 is used for underwater unwinding, i.e. for unwinding during the underwater travel of the guided missile 2 and during overwater flight until the water has flowed out of the coil space 50. The marching coil 62 is used for winding up when the coil space 50 is essentially water-free during overwater flight of the guided missile 2. The data cable 36 runs from the data interface 44 through the platform coil, from there - as in 3 is visible - to the starting coil 60 and through a groove, not shown, to the marching coil 62 and from there to the control unit 42. Due to the high withdrawal speed from the marching coil 62, the data cable 36 is pressed from the inside by the centrifugal force onto the inner wall of the missile part 20 of the housing 48 and lies on the inside of this. When executed as in 3 Central exhaust of the engine exhaust gases in a central gas guide pipe 64 is possible.

The platform part 22 encompasses the housing 48 - as in 2 - The missile part 20 of the housing 48, both parts 20, 22 being sealed against one another by means of a sealing unit 58, which is designed as a circumferential O-ring. The sealing unit 58 is held captively in a groove 66 in the platform part 22 of the housing 48, so that it does not rest on the data cable 36 when the two parts 20, 22 are separated. When the two parts 20, 22 are separated, the missile part 20 is pulled out of the platform part 22, so that the rear housing wall of the missile part 20 slides along the sealing unit 58. By designing this housing wall as a cone 68, the sealing unit 58 is squeezed together, which requires a certain amount of force. This effort provides additional security that the missile part 20 does not accidentally slip off the platform part 22. Before the guided missile 2 is introduced into the firing tube 30, the missile part 20 and platform part 22 are connected to one another with a securing means 70, which engages in a non-circumferential groove 72 in both housing parts 20, 22 and thereby blocks an axial displacement of the two parts 20, 22 relative to one another . The securing means 70 is a securing pin that can be manually pulled out of the two grooves 72, so that the separation is unlocked and is only prevented by the sealing unit 58 on the cone 68.

Reference symbol list

2

Guided missiles

4

Search head

6

active part

8th

engine

10

blow-out nozzle

12

Tax section

14

Steering wing

16

Sliding wing

18

Coil unit

20

Missile part

22

Platform part

24

Guiding wing

26

Inlet opening

28

Launch platform

30

Firing tube

32

Platform coil

34

Wrap package

36

Data conductor

38

Wrap package

40

Missile coil

42

Control unit

44

Data interface

46

Command post

48

Housing

50

Coil room

52

Flooding valve

54

labyrinth

56

Distractants

58

Sealing unit

60

Starting coil

62

marching coil

64

Gas guide pipe

66

Nut

68

cone

70

security means

72

Nut

QUOTES INCLUDED IN THE DESCRIPTION

This list of documents listed by the applicant was generated automatically and is included solely 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.

Cited patent literature

• EP 2887005 A1 [0003]

Claims (15)

Coil unit (18) for a guided missile (2) that launches underwater from a launch platform (28), with a missile coil (40) to remain in the guided missile (2) and a missile wound onto the missile coil (40) and connected to the launch platform (28) for data technology Data conductor (36), characterized by a platform coil (32) wound with the data conductor (36) to remain on the launch platform (28) after the guided missile (2) has been launched and a housing (48) which contains the two coils (32, 40 ) keeps dry when the guided missile (2) is flooded with water. Coil unit (18). Claim 1 , characterized in that the housing (48) has a missile part (20) and a platform part (22), which interlock and are sealed against each other with a sealing unit (58). Coil unit (18). Claim 2 , characterized in that the sealing unit (58) rests on an outer cone (68) of the missile part (20) in such a way that pulling the missile part (20) from the platform part (22) squeezes the sealing unit (58). Coil unit (18) according to one of the preceding claims, characterized in that the missile coil (40) contains a starting coil (60) and a marching coil (62), both of which are external coils, and the platform coil (32) is an internal coil, and a Platform part (22) of the housing (48) containing the platform coil (32) engages around a missile part (20) of the housing (48) containing the missile coil (40). Coil unit (18) according to one of the preceding claims, characterized by a flooding valve (52) with a sealing position and a flooding position for flooding the two coils (32, 40) with water flowing around the guided missile (2). Coil unit (18). Claim 5 , characterized in that the flooding valve (52) is a pyrotechnic valve. Coil unit (18). Claim 5 or 6 , characterized in that the flooding valve (52) in the open state is designed as an air purging opening for flushing the missile coil (40) with outside air during an overwater flight. Coil unit (18) according to one of the Claims 5 until 7 , characterized in that the flooding valve (52) has a labyrinth (54) for braking the inflowing fluid. Coil unit (18) according to one of the preceding claims, characterized by a guide vane (24) and a flooding valve (52) in front of the guide vane (24), which are arranged relative to one another in such a way that the guide vane (24) prevents fluid from flowing in through the flooding valve ( 52) favored. Coil unit (18). Claim 9 , characterized by a deflection means (56) which, when the guided missile (2) moves through fluid, directs part of the fluid into the flooding valve (52). Guided missile (2) with a coil unit (18) forming its tail part according to one of the preceding claims, which has a data interface (44) for connection to the launch platform (28) when the guided missile (2) is inserted into a firing tube (30) of the launch platform (28). Guided missile (2). Claim 11 , characterized by an engine (8) with at least one side blow-out nozzle (10) and a flooding valve (52) arranged behind the blow-out nozzle (10) for flushing the missile coil (40) with outside air during an overwater flight, which is tangentially offset to the blow-out nozzle (10) is arranged. Method for preparing an underwater launch of a guided missile (2) from a firing tube (30) of a launch platform (28), the guided missile (2) having a coil unit (18) with a missile coil (40) to remain in the guided missile (2) and one on the Missile coil (40) has wound data conductor (36), in which the firing tube (30) is flooded with water and the guided missile (2) is flushed with water, characterized in that the coil unit (18) also has a platform coil (32) to remain on the starting platform (28) and both coils (32, 40) are sealed against the water by a housing (48) of the coil unit (18) and remain dry. Procedure according to Claim 13 , characterized in that after the flooding of the firing tube (30) and before the launch of the guided missile (2) in the firing tube (30) and independently of the flooding of the firing tube (30), the coil unit (18) is flooded by opening a flooding valve (52 ) of the coil unit (18). Procedure according to Claim 14 , characterized in that the missile coil (40) is surrounded by ambient air flowing in through the flooding valve (52) during an overwater flight of the guided missile (2).

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