DE10230687B4 - Method for improving the ability to penetrate a missile - Google Patents

Abstract

Method for improving the penetration capability of a self-propelled aerodynamically supported missile, at least in the final approach approach,
- Which is designed as a distance weapon against fixed targets and largely flies completely to the finish and
- Which contains as a system of action a kinetically penetrating penetrator with a substantial mass fraction of the total system
- Is pivoted by means of servo drive (s) within the missile deviating from the longitudinal axis of the missile.

Description

A Distance weapon with a kinetically penetrating impact point Active system share (= penetrator) must after prolonged approach to the target area on the intended impact point as possible stable and precisely aligned. In this case, the penetrator in the final phase, just before hitting the target, with its longitudinal axis in the direction of the earth-fixed speed vector on the intended Show the point of impact. In addition to a sophisticated construction are one high speed of the penetrator and the orientation described above Prerequisite to the desired to achieve maximum kinetic penetration.

Lie for the Penetrator at the moment of impact side movements, pivoting movements across from the earth-fixed velocity vector or in particular static Deviations from this before, can this for kinking or rebounding and thus the destruction of the Penetrators still prevent penetration, prevent its penetration, or at least hinder it. Because crosswind and gravity aerodynamic only with sliding angle and angle of attack of the distance weapon can be met is proposed, the penetrator in the distance weapon against sliding angle and angle of attack by means of servo drives in the direction of the earth Pan speed vector.

Penetrators are known, which are tilted from a litter and relatively primitive steered, that is, without compensation of Anstell- and sliding angle, crash on the runway of an airfield ( DE 40 37 787 A1 ).

Also known at the moment of impingement are the projectile-forming charges (= pivotally mounted) which adapt to the surface inclination ( DE 198 13 376 A1 ), which are also used as a replacement or precursor for kinetically penetrating penetrators.

In no patent, however, are kinetically penetrating penetrators pivoted and / or rotated within its aerodynamic shell and so aimed at goal directed to the finish.

Largely Completely to the target flying distance weapons with one by means of kinetic Energy penetrating penetrator, have relatively small wings, which represent a compromise between the advantageous for the longer approach Asymmetry and her for the orientation of the penetrator adverse effect in the final phase, which are just enough compensated by means of controllable fins can. However, this is also a known with all known distance weapons the performance data limiting compromise between reach and Penetration.

• – in der Endphase den Auftreffpunkt,
• – die optimale Ausrichtung der Penetratorachse
• – und eine maximale kinetische Autreffenergie möglichst
• – ohne geschwindigkeitsmindernde Lenkflächen zu erreichen und nicht knicksichere, das heißt, dickere und damit weniger eindringfähige Penetratoren, einsetzen zu müssen.

The underlying task of the application is

• - in the final phase, the point of impact,
• - the optimal alignment of the penetrator axis
• - And a maximum kinetic auto-incident energy possible
• - To achieve without speed-reducing steering surfaces and not kink-proof, that is, thicker and thus less penetrating penetrators to use.

These Task is, as stated in claim 1, initially achieved by the fact that the penetrator by means of servo drives within the distance weapon deviating from longitudinal axis of the missile is pivoted.

The figure shows a penetrator 1 in a guide tube 2 is held. In the lower part of the distance weapon 3 inserted, in the embodiment, the front end of the guide tube in a vertically and horizontally displaceable backdrop 4 held. The rear end of the guide tube can not be moved in the embodiment. Is, as shown to explain the principle, the scenery 4 with the servo drive 5 horizontal and the servo drive 6 shifted vertically, aerodynamically necessary sliding angle and angle of attack of the spacer weapon for the penetrator can be reset and so, as set for the task, the penetrator are pivoted in the direction of the earth-fixed speed vector.

At the leadership the backdrop, or storage of the penetrator in the distance weapon are, due to the high mass forces during maneuvers in the wing flight, free flight and Final approach, to make high demands, - in the direction to be stabilized acting on the stationary target actuating forces of the servo drives during the By contrast, the last phase of the final approach may be relatively weak.

For the mechanical Design of storage and adjustment is the in the figure shown by other positive (eccentric rings, hydraulic or pneumatic tensioning devices, etc), for stabilization the last phase but also by non-positive elements (adjustable magnetic fields) executable (not shown in the figure).

The penetrator is at least an essential, sometimes the dominant mass of the missile. The described in claim 1 and 2 movement of the penetrator within the spacer weapon then has substantial reaction movements of the distance weapon itself result, the first can also be returned from known position controls and steering over relative to the missile movable steering surfaces. The reaction movement can be avoided in advance according to claim 3 by the respective expected definable reaction of the missile is fed as a dynamic control variable in the regulation of its movable steering surfaces.

• – Schiebewinkel und Anstellwinkel für die Lenkung des Flugkörpers werden durch dosierte Schwenkbewegungen der Penetratorachse zur Flugachse eingestellt,
• – wie umgekehrt die Penetratorachse im Endanflug in Richtung des erdfesten Geschwindigkeitsvektors gestellt und geregelt wird.
• – Rollbewegungen werden durch dosierte Gegendrehbewegungen des Penetrators aufgehoben.

The continuation of the problem solution is given in claim 4:

• - Sliding angle and angle of attack for the steering of the missile are adjusted by metered pivoting movements of the penetrator axis to the axis of flight,
• - Conversely, as the Penetratorachse is set and regulated in the final approach in the direction of the fixed earth speed vector.
• - Rolling movements are canceled by metered counter-rotating movements of the penetrator.

For the aerodynamic support suffice smaller steering surfaces or can ultimately satisfy the fixed missile profile.

Claims (4)

Method for improving the penetration ability a self-propelled and aerodynamic at least in Zielendanflug supported Missile, - the as Distance weapon is designed against stationary targets and largely Completely flies to the finish and - of the as an active system a kinetically penetrating penetrator with a contains substantial mass fraction of the overall system - by means of servo drive (s) inside the missile deviating from the longitudinal axis the missile pivoted becomes. Method for improving the penetration ability a self-propelled and aerodynamic at least in Zielendanflug supported Missile, - the as Distance weapon is designed against stationary targets and largely Completely flies to the finish and - of the as an active system a kinetically penetrating penetrator with a contains substantial mass fraction of the overall system - by means of servo drive (s) inside the missile around its own longitudinal axis is turned. Method according to claim 1 and 2, characterized that the expected dynamic repercussions The introduced by servo drives penetrator movements in the Control of the steering surfaces of the missile fed as control variables become. Method according to claim 1 and 2, characterized that the dynamic repercussions the penetrator movements that can be introduced by servo drives for the steering and stabilization of the missile be used.