GB2154715A

GB2154715A - Aerodynamic stabilisation mechanism for missiles

Info

Publication number: GB2154715A
Application number: GB08501791A
Authority: GB
Inventors: Horst Hutter; Siegfried Bock; Oswald Pepina
Original assignee: Messerschmitt Bolkow Blohm AG
Current assignee: Airbus Defence and Space GmbH
Priority date: 1984-02-18
Filing date: 1985-01-24
Publication date: 1985-09-11
Also published as: DE3405974C1; FR2559894A1; FR2559894B1; GB2154715B; GB8501791D0

Abstract

In an aerodynamic stabilisation mechanism for aircraft-launched missles 10, mechanical means for extending the retracted airfoils 13 simultaneously unlock and extend the rudders, elevators or stabilisation fins 14, 15, without the aid of electrical, pyrotechnical or hydraulic means. A piston (12) on the aircraft load release mechanism operates a plunger 16 or knee joint on the missile to overcome a lock or detent 17, whereupon the airfoils 13 are extended by a piston 23 and cables 21. Extension of the airfoils releases detents 18, 19 for the rudders or fins 14, 15. <IMAGE>

Description

SPECIFICATION Aerodynamic stabilisation mechanism for missiles This invention relates to a mechanism for the mechanical unlocking of swung-in airfoils of a missile, which airfoils communicate with a traction mechanism or linear piston by way of control cables.

It has become apparent that from time to time electrically, pyrotechnically or hydraulically operated swivel and folding (collapsible, hinged) mechanisms of aerodynamic stabilisation mechanisms for missiles fail. Upon functional failure of these stabilisation mechanisms-more especially in the event of emergency releases or jettisonings-the non-stabilised missile becomes, however, a great danger to the transporting aircraft.

An exemplified embodiment of a prior art mechanism is disclosed in German Gebrauchsmuster No. 78 04 927, where it is proposed that the swing-wings (folded wings, swivel wings) of the missile or flying body communicate by way of one control cable each with a linear piston. This linear piston is moved by igniting a gas generator, in which respect by way of the control cables the two swivel wings are swung out simultaneously.

The problem underlying the present invention is to provide a mechanism of the kind mentioned at the beginning hereof which operates purely mechanically and in the process of dropping the missile, more especially in the event of emergency drops, guarantees an automatic stabilisation of the missile.

This problem is solved in a reliable, simple and expenditureless manner in that the present invention provides a mechanism for the mechanical unlocking of swung-in airfoils of a missile, which airfoils communicate with a traction mechanism by way of control cables, characterised in that said mechanism comprises an expansion mechanism that can be actuated by a repulsion mechanism of a load lock of an aircraft carrying the missile, and locking mechanisms for the missile's elevators, rudders or stabilisation fins, the expansion mechanism and the locking mechanisms being associated with the airfoils, which are in the form of swing-wings, and standing in operative connection with one another in such a way that through the expansion mechanisms both airfoils and the rudders, elevators or stabilisation fins are run out or extended simultaneously.

The invention will be described further, by way of example, with reference to the accompanying drawings, in which: Figure 1 is a schematic view of a missile suspended from a wing pylon of an aircraft; Figure 2 is a schematic plan view of the missile illustrating its stabilisation mechanisms in their run-in and run-out state; Figure 3 is a schematic view of a first preferred embodiment of the mechanical unlocking means of the invention; Figure 4 is a schematic elevation of the missile's rear illustrating its detents for its vertical and horizontal rudders; Figure 5 is a schematic view of the stabilisation mechanisms of the missile in the run-in and run-out state; and Figure 6 is a schematic plan view of a second preferred embodiment of the mechanical unlocking means of the invention.

As illustrated in Figs. 1 and 2, missile 10 is held by way of the suspension eyes or lugs 26 in load lock 11 of an aircraft, only part of which is shown. Upon dropping of the missile 10, pistons of a repulsion, (push-off or release) mechanism 1 2 of the load lock 11 release or push the missile 10 away from the aircraft. In this respect, a repulsion piston 12a (illustrated in Fig. 3) presses on an expansion plunger 1 6 which has, in a bore, a compression spring 1 6c.The two side surfaces of the expansion plunger 1 6 are provided with slopes or recesses which act in each case on one end of a tappet 1 6a which stands under the pressure of a spring 1 6b and which tappet 1 6a for its part acts on a respective one of two airfoils 1 3 of the missile 1 0. The force of the pressure transmitted from the repulsion piston 1 2a onto the expansion plunger 16 and from the expansion plunger 1 6 by way of the tappets 1 6a onto the airfoils 13 is so great that lock or detect 1 7 of each of the airfoils 1 3 is overcome and the airfoils 1 3 are drawn by draw or traction mechanism 24, by way of linear piston 23 and control or traction cable 21 thereof, into the deployed or run-out operating position. Cable guides in the form of guide rollers 22 are arranged for the reliable guidance of the traction cables 21. The swing-out angle of the airfoils 1 3 is limited by a run-up or ramp brake 20.

At the same instant when the airfoils 1 3 leave the so-called rest position, they release both a detent mechanism 1 8 for horizontal rudders or stabilisation fins 1 4 and detent 1 9 for vertical rudders 1 5. Since the rudders 1 5 or fins 1 4 respectively stand in their retracted or run-in state under the bias of associated spring elements 25 or spring mechanisms respectively, their swing-out into the operating position automatically ensues with the release of the detents 18 and 19.

As a result of the proposals of the present invention, an automatic swing-out of all the supporting and stabilisation surfaces 13, 14, 1 5 is achieved in a purely mechanical way in that the repulsion force acting on the missile 10 releases the airfoils 13, standing under spring pressure, so that they swing-out and this releases the other stabilisation surfaces similarly standing under spring pressure.

Herewith a reliable component-saving and space-saving mechanism for the unfurling or deployment of swung-in supporting and stabilisation surfaces have been provided, as is made clear schematically by Fig. 5.

In Fig. 6 there is illustrated a further preferred embodiment of mechanical unlocking means for the deployment of swung-in airfoils, said means comprising draw or traction mechanism 23, 24. A pair of traction cables 21 of the traction mechanism 23, 24 act by way of respective guide rollers 22 on the airfoils 1 3 and put these under a certain bias.

A knee joint 16d, which is locked by way of the dead-centre, is moved by a pedal 1 6 t-on which the repulsion piston of the repulsion mechanism acts-and at the same time locking pins 1 6h standing under the pressure of springs 1 6g are drawn out of locking or detect bores or respectively bearings 1 3a of the airfoils 1 3 and thus release both airfoils simultaneously. The release of the remaining rudders and stabilisation surfaces is effected as aforedescribed by airfoil swivel movement.

Claims

1. A mechanism for the mechanical unlocking of swung-in airfoils of a missile, which airfoils communicate with a traction mechanism by way of control cables, characterised in that said mechanism comprises an expansion mechanism, that can be actuated by a repulsion mechanism of a load lock of an aircraft carrying the missile, and locking mechanisms for the missile's elevators, rudders or stabilisation fins, the expansion mechanism and the locking mechanisms being associated with the airfoils, which are in the form of swing-wings, and standing in operative connection with one another in such a way that through the expansion mechanism both the airfoils and the rudders, elevators or stabilisation fins are run out or extended simultaneously.

2. A mechanism as claimed in claim 1, characterised in that the airfoils in the run-in state act on locking mechanisms standing under the bias of spring elements for the horizontal and vertical rudders and thus the rudders are similarly held in the run-in state.

3. A mechanism as claimed in claims 1 and 2, characterised in that the horizontal and vertical rudders in the run-in state stand under the bias of associated spring elements which, after a detent unlocking bring the rudders into the operating position.

4. A mechanism as claimed in any one of claims 1 to 3, characterised in that the expansion mechanism is composed of an expansion plunger, which is mounted on a spring ele ment and which can be actuated by a repulsion piston, and of tappets which co-operate with the expansion plunger and which are provided with spring elements and which act on the airfoils.

5. A mechanism as claimed in any one of claims 1 to 3, characterised in that the expansion mechanism is a knee joint which can be actuated by way of a pedal and which acts on the tappets which are locking pins for the airfoils and which stand under the pressure of compression springs.

6. A mechanism for the mechanical unlocking of swung-in airfoils of a missile substantially as hereinbefore described with reference to and as illustrated in Figs. 1 to 5, or in Figs.1, 4, 5 and 6 of the accompanying drawings.