DE3405974C1 - Aerodynamic stabilization device for missiles - Google Patents

Description

The invention relates to a device for mechanical unlocking and swiveling out pivoted Wings of a missile hanging in an aircraft cargo lock, which are connected via cables are connected to a linear piston.

It has been shown that electrical, pyrotechnic or hydraulically operated pivoting and folding devices of aerodynamic stabilization devices for missiles fail on various occasions. In the event of a functional failure of these stabilization devices - especially in the case of emergency drops - the non-stabilized Missiles, however, pose a great danger to the transporting aircraft.

An embodiment of this prior art is disclosed in DE-GM 78 04 927, where proposed is that the swivel wings of the missile are connected to a linear piston via a cable stand. This linear piston is moved by igniting a gas generator, the two of which are operated via the cables Swivel blades can be folded out at the same time.

DE-OS 21 37 766 is a projectile for a bazooka with a stabilizing wing assembly became known, in which the wing under spring pressure in the propellant charge case is pivoted State are maintained and after firing and ejection from this case by an ejector wedge be swiveled out. For projectiles that hang from aircraft locks and that need to be released etc. this version cannot be used.

The invention is based on the object of creating a device of the type mentioned at the beginning the purely mechanical elements for swiveling out and locking the elevator and rudder and for unlocking them and to support the wing swiveling

ίο Should be used to in the event of a drop, in particular to ensure automatic stabilization of the missile in the event of emergency drops.

This task is made more reliable, simpler and less complicated by the measures indicated in claim 1 Way solved. Advantageous configurations are specified in the subclaims and in the figures shown in the drawing. It shows

F i g. 1 is a schematic view of the missile suspended from the hydrofoil pylon;

F i g. 2 is a schematic plan view of the stabilizing devices the missile in the retracted and extended state,

F i g. 3 a schematic view of an exemplary embodiment of a mechanical unlocking device,

F i g. 4 a schematic view of the locking device for the rudder and elevator,

F i g. 5 shows a schematic view of the stabilization devices of the missile in the retracted and extended position State,

F i g. 6 a further embodiment of a mechanical unlocking in a schematic plan view.

As the F i g. 1 and 2 show, the missile 10 is via the suspension eyes 26 in the load lock 11 of the aircraft held. When the missile 10 is dropped, the pistons of the repelling device 12 of the load lock hit 11 this away from the aircraft. Here, the pushing piston 12a pushes in the position shown in FIG. 3 shown embodiment on an expansion ram 16 which has a compression spring 16c in a bore. The two side faces this expansion ram are provided with bevels, each on one under the pressure of a spring 16Z> act standing plunger 16a, which in turn acts on the wings 13 of the missile 10. The force of the push-off piston 12a on the expansion ram 16 and from there via the plunger 16a on the wings 13 transmitted pressure is so great that the locking 17 of the wings 13 is overcome and this is overcome by the pulling device 24 via the linear piston 23 and its pull cables 21 are pulled into the extended operating position. For the safe management of the Pull ropes 21 are rope guide or deflection pulleys 22 arranged. The pivoting angle of the wings 13 is limited by an overrun brake 20.

At the same time that the wings leave the so-called rest position, they give both the Locking device 18 for the elevator or stabilizing fins 14 as well as the lock 19 for the rudder free and since this rudder or fins in the retracted state under bias of associated Spring elements 25 or spring devices are available, with this release the swiveling takes place automatically in the operating position.

The proposed concept now automatically swings out all wing and stabilization surfaces 13,14,15 achieved in a purely mechanical way in that the acting on the missile 10 Repulsion force releases the wings 13, which are under spring pressure, to pivot and these,

the other stabilization surfaces, which are also under spring pressure. This is a reliable, component-saving and space-saving device for unfolding Support and stabilization surfaces have been created, as shown in FIG. 5 illustrated schematically.

In FIG. 6 shows a further exemplary embodiment for the mechanical unlocking of pivoted-in supporting surfaces via a pulling device 23, 24. The traction ropes 21 of the traction device 23, 24 engage the support surfaces 13 via deflection rollers 22 and place them under a certain pretension. A knee joint 16c /, which is locked above dead center, is moved by a pedal i6f - on which the pushing piston of the pushing device acts - and at the same time the locking pins 16Λ, which are under the pressure of springs 16g, are removed from the locking bores or bearings 13a of the Wing 13 pulled and thus release both wings at the same time. The remaining rudder and stabilizing surfaces are released, as described above, by this pivoting movement of the wing.

For this purpose 3 sheets of drawings

25th

30th

35

40

45

50

55

60

65

- blank page -

Claims (4)

Patent claims: 1. Device for mechanical unlocking and pivoting of swiveled-in wings of a in an aircraft cargo lock hanging missile, which via cables with a linear piston in Are connected, characterized in that the repelling device (12) of the aircraft cargo lock (11) acts on a spreading device (16, 16a, 16i ^ and thus on the wings (13), their locking device (17) and the one (18, 19) for the elevator (14) and rudder or stabilizing fins (15) also via the force of the push-off piston (12a,) and its mechanical transmission elements (18a, 19a, 21) can be unlocked and extended at the same time. 2. Device according to claim 1, characterized in that that the wings (13) in the retracted state under the bias of spring elements (18a, 19a,) standing locking devices (18,19) for the elevator (14) and rudder (15) act and so the oars (14,15) are also kept in the retracted state. 3. Device according to claims 1 to 3, characterized in that the spreading device from one, on a spring element (16c ^ superimposed and expansion ram to be actuated by the push-off piston (12a,) (16) and with it cooperating, provided with spring elements (166,) plungers (16a,), the act on the wing (13) is composed. 4. Devices according to claims 1 to 3, characterized in that the spreading device is designed as a knee joint (16c /,) to be actuated via a pedal (16 /?) Which is formed on the locking pins (t6h) for the wings (13) , acts under the pressure of compression springs (16g) plunger.