KR20050062770A - Fouling-resistant connectors between a military launcher and ammunition - Google Patents

Abstract

The invention relates to the connector technology used between a military ammunition launcher and ammunition. In particular, the invention applies to rocket launchers which are suspended under a helicopter or aircraft. The invention is essentially characterised in that the connectors (5) comprise a locking system (42, 48), such as a pin or bayonet system. Said locking system (42, 48) ensures that the launcher and rocket connectors remain connected after the rocket has been launched from the launcher. In this way, the rocket connector (41) cannot separate from the launcher connector (40) when the rocket leaves the housing thereof. The rocket cable (4) is pulled taut and then breaks while the rocket connector (41) remains in place. As a result, the launcher connector is not affected by fouling or corrosion.

Description

FOULING-RESISTANT CONNECTORS BETWEEN A MILITARY LAUNCHER AND AMMUNITION}

The present invention relates to a technique for connecting ammunition with a military ammunition launcher. The invention applies particularly to rocket launcher mounted under a helicopter or aircraft. ,

When firing ammunition, you must send a firing order from the carrier (helicopter, aircraft) to the ammunition. This launch command is usually transmitted electrically. It is necessary to carry other data from the carrier to the ammunition. In the case of ejector ammunition, for example, after firing, the ammunition (cargo or dars) is distributed by passing the period after the ammunition is opened. In the case of guided ammunition, guided data such as photographs or digital terrain models are delivered. Any data used during the flight of ammunition is thus conveyed.

These data are transferred from the carrier to the ammunition by the data transfer link. This link includes a cable connecting the carrier and the launcher. The link enters the launcher up to the tube containing the ammunition. There is a link between the ammunition and the launcher that leads the data link to the ammo. It is known to use a linkage to connect the ammunition's flexible coaxial cable to the launcher. This connection is formed by a launcher connector disposed at the launcher near the tube outlet and an ammunition connector disposed at the end of the cable. The other end of the cable is connected to the nose of the ammunition. The cable that is part of the ammunition carries the ejection data or guidance data to the nose.

When the ammunition leaves the launcher, the ammunition cable and the ammunition connector fly away with the ammunition and the launcher connector is left open. The launcher connector is in contact with the gas released by the ammunition again, and when the adjacent ammunition is fired, it is also in contact with the gas emitted by the ammunition. Prolonged exposure to these corrosive gases causes the launcher connector to become contaminated and no longer accurately transmit electrical signals.

1 shows an example in which the present invention is applied to a rocket launcher mounted on a helicopter.

2 and 3 are side and front views of launchers capable of firing seven round rockets.

4 is a front view showing an example of the layout of a triangular grid of a rocket housing.

5 is a front view showing a launcher capable of launching nineteen round rockets.

6 illustrates a rocket nose cone with a flexible coaxial cable and a connector.

7 and 8 are cross-sectional and front views showing a rocket connector of the standard type.

9 and 10 are a cross-sectional view and a front view showing an example of the connecting device according to the present invention.

FIG. 11 is an isometric view of a cap that is one element of the connecting device shown in FIGS. 9 and 11.

12, 13 and 14 show another embodiment of the cap.

It is an object of the present invention to avoid such contamination. To this end, the present invention relates to a military ammunition launcher comprising a housing containing an ammunition comprising a cable and an ammunition connector at the end of the cable, and a launcher connector disposed on the launcher and connected to the ammunition connector. It also includes an element of the locking system, characterized in that the locking system maintains the connection of the launcher connector and the ammunition connector after the ammunition leaves the launcher.

Preferably the locking system is a baannut system and the element of the locking system which is part of the launcher is in a lug. Preferably, the lug is disposed on an outer surface of the launcher connector, the lugs are two and disposed opposite each other in the radial direction, and the launcher connector is coaxial.

The present invention also relates to a munition article disposed in a housing of a military ammunition launcher comprising a launcher connector, the munition article comprising a cable and an ammunition connector disposed at an end of the cable and connected to the launcher connector, the munition article being locked. It also includes elements of the system, said locking system characterized by maintaining the connection of the launcher connector and the ammunition connector after the ammunition leaves the launcher.

Preferably the cable has a cable cut point at the exit of the ammunition connector, which is made by locally weakening the cable. Preferably the element of the ammunition locking system is a cap, which is an independent element with a groove for fitting the cable to the cable.

According to another preferred embodiment of the invention, the cap is an element that is molded into the cable.

  Other features and advantages of the invention will be apparent from the accompanying drawings and the description below.

See FIGS. 1-3. The present invention can be applied to any kind of launcher (especially rocket launcher 2). This rocket launcher 2 can be mounted to the helicopter 1. Launcher 2 is shown in side and front view in FIGS. 2 and 3. The launcher includes a housing containing ammunition. In this example the housing forms a tube in which the rocket 3 is arranged. This housing can be for example seven (FIG. 3), twelve or nineteen (FIG. 5). The connection device 5 between the ammunition and the launcher can be arranged in front of the launcher, ie on the side from which the rocket is launched. Launcher connectors may be provided in each housing or in some housings. Each launch connector is connected to a rocket connector which forms the end of the cable 4. The rocket connector cable 4 is integrated with the rocket.

A detailed view of the front of the launcher shows an exemplary layout of the housing. This housing has a circular cross section of the same diameter D1. This diameter D1 is substantially equal to the aperture of the ammunition. To reduce the launcher's footprint, the center of the circle can be equidistant from the triangular grid. Accordingly, the centers of the three housings 6, 7 and 8 adjacent to each other become vertices of the equilateral triangle 9, and the length of the sides 10 of the equilateral triangle becomes equal to the distance D2 between the centers. In such gratings a launcher connector may be disposed between the housings. Thus, the launcher connector 11 can be arranged between the housings 6, 7, 8. There is a narrow space between the three adjacent housings where the linkage between the ammunition and the launcher can be placed.

In front view FIG. 5 is shown a launcher 2 capable of firing nineteen round rockets. The rockets are arranged in a triangular grid. The rocket launcher includes a central housing 12, around which there are six peripheral housings 13-18 and twelve peripheral housings 19-30. Launcher connectors 31 of circular cross section may be arranged between the housings 13-30 of the rocket. More than 24 launchers connectors (24) to be deployed are available. There are several possible arrangements for this. Another launcher connector 32 may be disposed around the housing.

6 is a side view showing a rocket with a flexible coaxial cable 4 and a connector. The cable 4 can be connected to the nose cone 33 of the rocket 3. It is possible to provide the sealing bush 33 at the connection point. The cable may have a length of about 1.5 mm and may be a sheathed coaxial cable. This cable can have a conductive core (not shown), for example, which is connected to the anode and is surrounded by an insulating jacket (not shown). The insulating jacket itself is surrounded by a conductive braid (not shown) that is connected to the cathode. The whole is surrounded by a protective cover (not shown). The free part of the cable has a connector. This connector includes an outer body 34 and a socket 35. The outer body 34 is an outer jacket that allows the connector to be held while protecting the negative circuit. The outer body can be made of silicone such as Geon 83794 Gray.

See FIGS. 7 and 8. The socket 35 is, for example, a coaxial female socket. This socket comprises, for example, a conductive tube 36 in the form of a hollow tube, which core is to be connected to the anode. This tubular core 36 is surrounded by an elastic insulating material 37, which is itself surrounded by a conductive material 38 forming the outside of the socket 35. Conductive material 38 is connected to the cathode. The components 36, 37, 38 of the socket 35 are coaxial with each other. Since there are longitudinal slots 39 (eg three), the cross section of the socket can be reduced with elastic deformation.

9 is a cross-sectional view illustrating the connecting device according to the invention. This connecting device 5 comprises in particular a launcher connector 40 and a rocket connector 41. The rocket connector 41 can be mechanically fixed to the launcher connector 40 with a simple insertion, in particular with the elasticity of the socket 35 of the rocket connector 41.

Launcher connector 40 comprises, for example, a substantially cylindrical body 47 and a conductive rod 44 disposed on the axis of the body 47. This rod 44 is connected to the positive pole and is received in the interior 36 of the socket 35 (see FIGS. 6-8) when the rocket connector 41 is inserted into the launcher connector 40. The rod 44 is in electrical contact with the anode of the rocket. The body 47 includes a conductive element (not shown) on its inner surface. This conductive element may be formed by the body itself and is connected to the cathode. When the rocket connector 41 is inserted into the launcher connector 40, the conductive element is in electrical contact with the outer side 38 of the socket 35 (see FIGS. 6-8).

A stopper 45 may be provided to protect the rod 44 when the rocket connector 41 is not in the launcher connector 40. This cylindrical stopper includes a central through hole, which can slide on the rod 44. There is a spring 46 behind the stopper in the body 47 of the launcher connector 40. When the rocket connector 41 is inserted into the launcher connector 40 the spring 46 is compressed by the rocket connector. When there is no rocket connector 41 in the launcher connector 40, the spring 46 exerts a force on the stopper 45, by which the stopper is pushed back to protect the rod. However, when there is a rocket connector 41, the spring 46 pushes the rocket connector 41 slightly out of the launcher connector 40 so that a good electrical connection is no longer made.

According to an essential feature of the present invention, the connecting device comprises a locking system 42, 48, such as a pin or bayonet system. This locking system 42, 48 allows the launcher connector and the rocket connector to remain connected after the rocket is launched from the launcher. Thus, the rocket connector 41 no longer leaves the launcher connector 40 when the rocket leaves its housing. The cable 4 of the rocket is tense and broken and the rocket connector 41 remains in place. In this way, contamination and corrosion of the launcher connector will no longer occur.

The present invention has many advantages. The rocket connector 41 is held in place because of the locking system 42, 48 when an adjacent rocket is launched before one rocket is launched. Moreover, the rocket connector 41 no longer accidentally falls out of the launcher connector 40 even in difficult vibration environments. This ensures complete transmission of the electrical signal. Finally, the rocket leaves its launcher leaving its connector 41 alone, resulting in less aerodynamic drag.

When the rocket leaves the housing, the first portion of the cable follows the rocket and the second portion remains fixed to the launcher. The second part of the cable risks breaking when the adjacent rocket leaves and can damage the carrier. To avoid this risk, a cable cut point can be placed at the outlet 49 of the rocket connector. This cut point can be made, for example, by locally weakening the cable or by removing part of the conductive braid.

According to an advantageous embodiment, the locking systems 42, 48 are of a bakenut system. This system includes, for example, a cap 42 and a lug 48. This cap 42 is in contact with the rocket connector 41. Lug 48 forms part of launcher connector 40. When the rocket connector 41 is inserted into the launcher connector 40, the cap 42 is pushed toward the launcher connector 40 and rotated to engage the lug 48. The cap 42 includes a fixing groove to which the lug 48 is coupled. Once engaged, the cap 42 can keep the rocket connector 41 in connection with the launcher connector 40. The lug 48 of the launcher connector 40 holds the cap 42 in the axial direction, and the cap itself supports the rocket connector 41 to the launcher connector 40.

The bakenut system has many advantages. It is easy to operate and has a reduced footprint. This allows the locking system to be placed in the space between three adjacent housings of the launcher.

Referring again to FIG. 4, there is room for the launcher connector 11 and the locking system. The locking system and the connector 11 occupying the surface area of the disk having the diameter D3 can be arranged in the space. This diameter is limited to the following relationship (the disc abuts the adjacent housing).

Reference is now made to FIG. 10. According to a practical embodiment, the cap 42 covers the rocket connector 41 and the launcher connector 40. The footprint is determined by the diameter of the cap 42. For example, when the aperture D1 is 70 mm and the center distance D2 is 76 mm, the diameter D3 of the cap is 13 mm.

See FIGS. 9 to 11. The locking system can include one or more lugs 48 disposed on the launcher connector 40. Preferably the lugs are two and arranged radially.

According to an advantageous embodiment, the lug 38 is arranged on the outer surface of the launcher connector 40. If the lug is thus disposed on the outer surface of the launcher connector, it is not necessary to fit the shape of the rocket connector to the lug 48. Specifically, the shape of the rocket connector 41 is determined only by the inner surface of the launcher connector 40. In this way, a launcher connector compatible with all kinds of rocket connectors can be used, which is compatible with a predetermined standard. Representative shapes of the cap are described in more detail. The cap 42 has a substantially cylindrical inner surface. The fixing groove 50 is disposed inside the inner surface. Each groove defines an arc of angle A in a plane perpendicular to the axis of the cylinder forming the inner surface. The angle A is for example 309 °. The fixing groove 50 receives the lug 48 of the launcher connector to prevent the cap 42 from falling out in the axial direction. Each fixing groove 50 is connected to the inlet groove 51 at one end. When the cap 42 is disposed in the launcher connector 40, each inlet groove 51 is opposite the lug 48. When the cap is pushed towards the launcher connector 40, each lug can move inward of the associated inlet groove 51 to reach the fixing groove 50. At the other end of each fixing groove 50 is a hole 52. This hole may be a through hole as shown in FIGS. 9 and 11. When the cap is rotated by an angle A, the lug 48 moves inside the associated fixing groove 50 to reach the hole 52 at the end of the fixing groove. Thanks to the hole 52 at the end of the fixing groove, the rotation of the cap 42 can be stopped in a stable position.

Of course, other types of bakenut systems with more or less grooves and lugs are conceivable. The position of the lugs and the grooves can also be swapped, i.e. with lugs on the cap and grooves on the launcher connector. The lug becomes part of the rocket connector and the cap comes into contact with the launcher connector.

According to an advantageous embodiment, the cap 42 forms an independent element. This independent element comprises a groove 53 for fitting the cap 42 to the cable 4. In this way, a locking system compatible with all kinds of rocket connectors can be used, whereby the invention can also be implemented in rockets having a predetermined standard.

See FIGS. 12-14. According to another advantageous embodiment, the cap 54 is molded on the cable 4.

Of course, the invention can be applied to any type of ammunition fired from a launcher. In this example, the cable is secured to the nose cone in front of the ammunition. The present invention can be applied to other locations of ammunition.

For example, the present invention can be used to deliver a launch command. It is known to use a linkage that directly connects the ammunition and the tube to deliver a firing command. This linkage is formed by a cleanpage system placed at the bottom of the tube at the height of the propellant of the ammunition. The present invention can be used to transmit a firing command to a cable outside the ammunition. This cable can be connected to the rear of the ammunition at the height of the propulsion system. In other words, the present invention can be used at the rear of the ammunition to convey a start command to the propulsion device. This has many advantages in terms of cost and reliability compared to conventional techniques using the cleanpage system.

Claims (13)

As a military ammunition launcher 2 A housing in which an ammunition 3 comprising a cable 4 and an ammunition connector 41 at the end of the cable is received; In the military ammunition launcher (2) comprising a launcher connector 40 disposed in the launcher and connected to the ammunition connector, Also includes an element 48 of the locking system 42, 48, The ammunition launcher (2), characterized in that the locking system maintains the connection of the launcher connector and the ammunition connector after the ammunition leaves the launcher. 2. The launcher of claim 1, wherein said locking system is a bayonet system. 3. Launcher according to claim 2, wherein the element of the locking system is a lug (48). 4. The launcher of claim 3, wherein the lug is disposed on an outer surface of the launcher connector. 5. Launcher according to any one of claims 3 to 4, wherein the lugs are two and arranged opposite each other in the radial direction. The launcher of claim 1, wherein the launcher connector is coaxial. A munitions 4 disposed in a housing of a military ammunition launcher 2 comprising a launcher connector 40, comprising a cable 4 and an ammunition connector 41 disposed at the end of the cable and connected to the launcher connector. In the said munitions, Also includes an element 42 of the locking system 42, 48, And the locking system maintains the connection of the launcher connector and the ammunition connector after the ammunition leaves the launcher. 8. The munition of claim 7, wherein the cable has a cable break point (49) at the outlet of the ammunition connector. 9. The munition of claim 8, wherein the cable break point is made by locally weakening the cable. 10. The munition of any of claims 7 to 9, wherein the locking system is a bayonet system. A munition according to claim 10, wherein said element of the locking system is a cap (42). 12. The munition of claim 11 wherein the cap is an independent element having a groove for fitting the cap to the cable. 12. The munition of claim 11 wherein the cap is comprised of elements molded into the cable.