DE2815799A1 - DEVICE FOR THE STABILIZATION OF A PARTICULAR RADIATED AIRCRAFT - Google Patents

Description

Device for stabilizing a particularly jet-propelled missile

The invention relates to a device for stabilizing a particular jet-driven plug body on its plug path during the start phase or initial phase of its flight by means of the missile, in particular Cable forces acting centrally on the missile tail, which occur when the missile longitudinal axis deviates from of the rail tangent cause reversing moments, whereby a rope brake is used to generate the aforementioned rope forces serves.

When launching missiles, for example to combat tanks, disturbances in the form of pitch and yaw angle movements up to a magnitude of + _ 30 per second occur after take-off. Due to the flight speed of the missile, which is still slow after take-off, these take-off disturbances cannot be compensated for by aerodynamic means alone, such as stabilizing fins, since the aerodynamic pressure forces are still too small for this. Even if a non-aerodynamic steering method is selected, for example a deflection of the engine jet with spoilers, these start-up disturbances could in principle be compensated for; With conventional steering methods, however, the guided missile is only _{steered at all after a certain approach w} distance of, for example, 20 to 30 m, since it is only steered after the start by the guards or by an automatic goniometer or steering system.

25 stand must be recorded.

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Another way to compensate for start-up disruptions, consists, xvie from the DT-OS 21 44 140, is that in the start phase at the tail of the guided missile a pull rope attached to the take-off point attacks the guided missile, so to speak, into the Target flight direction pulls in.

According to DT-OS 19 50 930 it is known to use plug bodies of the type described above during their start-up phase by a rope brake arranged on the plug body rear, which z. B. in the expiring steering wire temporarily brakes intervenes to give a stability aid and this by a continuous pull backwards inevitably stabilize.

It is the object of the invention to provide a pulling force that works safely for the purpose in question To create predictable stabilization device with a simple structure and one for it to realize the intended rope brake.

This object is achieved in that a calibrated drawing nozzle in the plug body, in particular, as a cable brake is provided centrally in the plug body rear or on the launch system, with a narrowest cross-section, which is used for Generation of the desired rope braking forces in the diameter is correspondingly smaller than the diameter of the brake wire entering the drawing nozzle.

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The device according to the invention enables with the generation of a tensile force that can be calculated in advance at the tail of the missile with great accuracy its plug stabilization during its take-off or initial flight phase. There are deflections of the missile dampened by the turning back stabilization torque of the braking forces, since the deflections a momentary increase in the retracting moments due to a temporary increase in the material displacement cause in the drawing nozzle, which in turn quickly reduce the amplitude of the deflections. The braking force at the drawing nozzle can be easily determined by the wire material and the degree of Deformation in the drawing nozzle or the so-called drawing die.

In the context of the invention, there is the possibility of using the steering wire transmitting the electrical steering command To train in its initial part as a brake wire, so reinforced.

A preferred embodiment of the invention, however, consists in that in the missile, in particular centrally A special brake wire in the rear of the missile with one corresponding to the start or initial phase of the flight Length is stored in the wound state, the bottom-side brake wire end with the launching frame is inextricably linked, while the missile-side Brake wire end is easily torn off attached to a missile tail associated coil body.

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According to another embodiment of the invention can a special brake wire can be stored in the coiled state on the launching frame, the bottom-side Brake wire end is inextricably connected to a bobbin associated with the launching frame, while the other Brake wire end is easily torn off attached to the missile tail.

In an embodiment of the invention, the individual turns of the Eremsdrahtes on the bobbin are through one thermoplastic adhesive, which is in a solid state at normal temperature, which is retained during the drawing process due to the frictional heat that occurs in the drawing nozzle, it melts and serves as a coolant and lubricant. A special lubricant, e.g. graphite, can be added to this adhesive.

In the drawing, an embodiment according to the invention is shown.

FIG. 1 shows a missile FK during the launch phase from a launch tube 1 of a launch system A. With B is the trajectory on which the missile FK is to move tangentially. Right now the missile is taking off FK shortly after leaving the launch tube 1 as a result of a disturbance torque Ml caused by rotation around his Center of gravity S an angle of attack OC.

In the tail 2 of the missile FK, a drawing nozzle device is installed, which receives a bobbin 4 and a drawing nozzle 5. On the bobbin 4, turns 6a of a brake wire 6 are made by a thermoplastic adhesive 7, which is firm at Norma! temperature, wound up. The brake wire 6 runs through the drawing nozzle 5, which has a smaller cross-section than the wire cross-section, so that when Passage of the brake wire 6 through the drawing nozzle 5 in the

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indicated direction a tensile force Z occurs, which exerts a turning back moment M2 on the plug body FK. In other words, the tensile force Z, which can be predetermined in size, has a permanent stabilizing effect on the Flight movement of the missile FK and ensures that there are no significant deflections and if so, then these are immediately suppressed and the missile FK is restabilized.

According to Figures 1 and 2, the missile end is 6b of the brake wire 6 attached to the bobbin 4 so that it can be easily torn off, while the bottom end 6c of the brake wire 6 is permanently connected to the launching system A at 8, so that after the end of the initial stabilization phase the wire end 6b tears off the bobbin 4 and the brake wire 6 remains on the launching system A or on the ground.

In FIG. 3, the drawing nozzle device 3a is assigned to the launching system A and the wire end 6c with the one there Coil body firmly connected, while the wire end 6b is attached to the missile tail 2 so that it can be easily torn off In this case, too, the brake wire 6 remains on the launching system A or on the ground. As a brern wire 6 is suitable in In the present case, e.g. soft-annealed high-alloy chrome-nickel steel.

The steering wire 9 transmitting the electrical command is attached to the outside of the body of the drawing nozzle device 3. \ tfolds and runs from the missile FK to the launching system A.

The device according to the invention is not only applicable for recoil-propelled missiles, i.e. those with their own propulsion, but also for projectiles without their own

_ 9 _ 909842/0412

Drive that are shot from pipes, such. B. Melee missiles (recoilless guns) or mortar shells.

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Claims (5)

Patent claims 1. Device for stabilizing a particular jet-propelled missile on its trajectory during the launch phase or initial phase of its
Flight by means of rope forces acting centrally on the missile, in particular on the missile tail, which cause back-rotating moments when the missile longitudinal axis deviates from the path tangent, a rope brake serving to generate the mentioned rope forces, characterized in that a calibrated pulling nozzle (5) in the missile (FK ), especially centrally in the rear of the missile (2) or on the launching system (A) 90984 OWQWAL. INSPECTED is provided, with a narrowest cross-section, which is used to generate the desired rope braking forces in the The diameter is smaller than the diameter of the brake wire (6) entering the drawing nozzle (5). 2. Device according to claim 1, characterized in that in the missile (FK), in particular in the missile tail (2) a special brake wire (6) with one of the start phase or initial phase of the flight corresponding length is stored in the wound state, with the bottom-side Eremsdrahtende (6c) with the launching system (A) is inextricably linked, while the missile-side brake wire end (6b) attached to a coil body (4) assigned to the missile tail (2) so that it can be easily torn off is. 3. Device according to claim 1 and partly according to claim 2, characterized in that that a special brake wire (6) is stored in the coiled state on the launching system (A), wherein the bottom-side brake wire end (6c) cannot be detached from a coil former assigned to the launching system (A) is connected, while the other end of the brake wire (6b) on the missile (FK) can be easily torn off is attached. 4. Device according to claim 1 to 3, characterized in that the individual turns the brake wire (6) on the bobbin (4) by a thermoplastic, at normal temperature in the solid state adhesive (7) are held, which when heated during the drawing process melts and serves as a coolant and lubricant. 909847/0412 5. Device according to claim 5, characterized in that the thermoplastic Adhesive (7) a special lubricant is added. 909842/0412