DE2815799C2 - Device for stabilizing a missile - Google Patents

Description

30th

The invention relates to a device for stabilizing a missile on its flight path during the start phase or the initial phase of its flight by a center attacking the rear of the missile Pull rope, the rope forces of which turn back when the missile longitudinal axis deviates from the path tangent Generate moments, a rope brake being used to generate the aforementioned rope forces.

When launching in particular jet-propelled missiles such. B. to fight tanks, step after the start disturbances in the form of pitch and yaw angle movements up to an order of magnitude of ± 30 ° per second. Due to the missile's flight speed, which is still slow after take-off These start-up disturbances cannot be compensated for by aerodynamic means such as stabilizing fins alone because the aerodynamic pressure forces are still too small for this. Even if one doesn't aerodynamic steering method is chosen, so z. B. a deflection of the engine jet with spoilers, so Although these start-up disturbances could in principle be compensated for; with conventional steering methods However, the guided missile only after a certain approach distance of z. B. steered 20 to 30 m at all, because after the start it is only used by the steering gate or by an automatic goniometer as a steering stand must be detected.

Another way of compensating for start-up disruptions, consists, as is apparent from DE-OS 21 44 140, that in the start phase at the tail of the missile A pull rope attached to the take-off point engages the guided missile, so to speak, in the desired direction of flight draws in.

According to DE-OS 19 50 930 it is known to use missiles of the type described above during their launch phase by a rope brake arranged on the missile tail,

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65 the z. B. intervenes temporarily braking in the running steering wire to give a stability aid and thus inevitably stabilize it by a continuous pull to the rear.

It is the object of the invention to provide a safe functioning for the purpose in question, in their To create tensile forces predictable stabilization device with a simple structure.

This object is achieved in that a calibrated drawing nozzle in the rear of the fiugkörper as a cable brake or is provided on the launching system, with a narrowest cross-section that is necessary to produce the desired Cable braking forces in diameter is correspondingly smaller than the diameter of the in the drawing nozzle incoming brake wire.

The device according to the invention enables a to be generated in advance with great accuracy calculable tractive force at the tail of the missile to stabilize its flight during its launch or Initial flight phase. In this case, deflections of the missile are dampened by the turning back stabilization torque of the braking forces, as the deflections a momentary increase in the retracting moments through a temporary increase in the material displacement in the drawing nozzle, which in turn increases the amplitude of the deflections quickly To subside. The braking force on the drawing nozzle can be easily determined by the wire material and the degree of deformation in the drawing nozzle, the so-called drawing die.

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

In an embodiment of the invention, the individual turns of the brake wire are on the bobbin by a known thermoplastic which is in a solid state at normal temperature Adhesive held during the drawing process by the frictional heat occurring in the drawing nozzle melts and serves as a coolant and lubricant. This adhesive can be a special lubricant, z. B. graphite, be added.

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

The F i g. 1 shows a jet-propelled missile FK during the launch phase from a launch tube 1 of a launch system A. B üt denotes the trajectory on which the missile FK is to move tangentially. At the moment, shortly after leaving the launch tube 1 , the missile FK assumes its angle of attack α due to a disturbance torque M \ caused by rotation about its center of gravity.

A drawing nozzle device 3 is installed in the tail 2 of the missile FK and accommodates a coil body 4 and a drawing nozzle 5. On the bobbin 4 turns 6a of a brake wire 6 are wound by a thermoplastic adhesive 7, which is solid at normal temperature Drawing nozzle 5, a tensile force Z occurs in the specified direction, which exerts a turning-back moment Af 2 on the missile FK. In other words, the tensile force, which can be predetermined in terms of its size, has a permanent stabilizing effect on the flight movement of the missile FK and ensures that there are no significant deflections

comes and if, then these are immediately suppressed and the missile FK restabilized

According to the F i g. 1 and 2, the missile-side end 66 of the brake wire 6 is attached to the bobbin 4 so that it can be easily torn off, while the bottom end 6c of the brake wire 6 is inextricably linked to the firing system A at 8, so that after the end of the initial stabilization phase, the wire end 66 from the bobbin 4 tears off and the brake wire 6 remains on the launching system A or on the ground

In Figure 3, the nozzle device 3a is the

Firing system A and the wire end 6c firmly connected to the coil body there, while the wire end 66 is attached to the rear wing 2 so that it can be easily torn off, so that in this case too the brake wire 6 remains on the launch system A or on the ground in the present case z. B. soft-annealed high-alloy chrome-nickel steel.

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

1 sheet of drawings

Claims (3)

Patent claims: 1. Device for stabilizing a missile on its trajectory during the take-off phase or the initial phase of its flight by means of a pulling rope that acts centrally on the tail of the flag body, the rope forces of which cause backward torques when the missile's longitudinal axis deviates from the path tangent, a rope brake being used to generate the rope forces, characterized in that that a calibrated pulling nozzle (5) is provided as a rope brake in the missile tail (2) or on the launching system (A) , with a narrowest cross-section, the diameter of which is smaller than the diameter of the pulling nozzle (5) in order to generate the desired rope braking forces incoming pull rope or brake wire (5). 2. Device according to claim 1, characterized in that the individual turns of the brake wire (6) on the bobbin (4) by a known 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 3. Device according to claim 2, characterized in that the thermoplastic adhesive (7) a special lubricant is added.