DE1213760B - Self-propelled hollow charge projectile - Google Patents

Description

FEDERAL REPUBLIC OF GERMANY

GERMAN

PATENT OFFICE

EDITORIAL

Int. CL:

F07f

German class: 72 d- 19/01

Number: 1213 760

File number: R33038Ic / 72d

Filing date: June 30, 1962

Opening day: March 31, 1966

The invention relates to a shaped charge projectile with self-propulsion and twist stabilization.

The high speed required for perfect spin stabilization is common to all known Self-propelled hollow charge projectiles, however, are disadvantageous in that these projectiles a sharp drop in penetration performance when a certain circumferential speed is exceeded demonstrate. The task was therefore to be solved without damaging the shaped charge effect the greatest possible accuracy, d. H. with the smallest possible twist rotation a sufficient one Stabilization, to achieve.

The stability factor of a spin-stabilized projectile is proportional to the square of the axial moment of inertia and the angular velocity, inversely proportional to the transverse moment of inertia and the moment of air force around the transverse axis of the projectile, which tries to twist the projectile out of a trajectory position and thus _{initiates the pre-ao} assignment movement.

The stability number is

σ =

/ α ² ω ²

When using the Munk airship formula for the air attack point, the approximation equation is obtained

σ =

Λζ ² ω ²

4 Jq-ρ- ν ² [Va- F _g (Ig -x.)]

Here means

Yes the axial moment of inertia, Jq the transverse moment of inertia, ω the angular velocity,

c _{m is} the moment coefficient around the transverse axis of the storey,

ρ is the air density,

ν the projectile velocity, Fg the projectile cross-section, D the projectile diameter, V ₀ the projectile volume,
Ig the length of the projectile,

x _{s is} the distance from the center of gravity from the tip of the projectile.

The invention is based on the idea by limiting the speed as a function of the for

Self-propelled hollow charge projectile

Applicant:

Rheinmetall G. mb H.,
Düsseldorf, Ulmenstr. 125

Named as inventor:

Dr.-Ing. Karl-Otto Wehlow,
Ratingen-Tief enbroich;
Fritz Woyt, Erkrath (District Düsseldorf);
Hermann Renner, Düsseldorf

a hollow charge still permissible circumferential speed to keep all other influencing variables on the stability number of the bullet within the given limits (caliber, etc.) large or small and finally to choose a comparatively large moment of inertia ratio Ja: Jq in order to achieve adequate stabilization of the with the lowest possible twist rotation To achieve projectile.

The inventive solution to the problem is that the engine and combustion chamber existing engine is arranged in a known manner in a ring around the active part and that to achieve the greatest possible stability with the smallest possible twist rotation on the bullet jacket and in the plane of the overall center of gravity a known ring of moments of inertia of high specificity Weight is arranged.

In connection with these constructive measures can be used to reduce the denominator the stability number equation quadratic incoming airspeed the thrust program of the rocket by using a marching engine to compensate for the drop in speed after burning out the launch engine can be designed so that the projectile has a relatively low maximum speed achieved. This can be achieved in an advantageous embodiment of the invention that the cruise engine arranged in the outer shell is designed and arranged in such a way that that it supplements or replaces the effect of the moment of inertia ring.

In a further advantageous embodiment of the invention, this can be done concentrically outside the take-off engine arranged cruise engine as ramjet

609 540/138

engine be trained. This training has the advantage that the projectile is held more easily or at more explosives can be carried with the same weight.

The proposed engine arrangement offers particular advantages when used with shaped charges, but it is also readily available on other projectiles that are sensitive to swirl, e.g. B. Supply floors, applicable.

Some exemplary embodiments for shaped charge projectiles are shown in the drawing. It shows

1 shows a shaped charge projectile with an engine,

2 shows a shaped charge projectile with separate launch and cruise engines,

F i g. 3 a shaped charge projectile with a starter and a ramjet engine as a cruise engine.

The rocket projectile shown in FIG. 1 has the wanking part which is arranged in the longitudinal axis and consists of a hollow charge. The combustion chamber 2 with the propellant charge 3 is arranged in a ring around the active part. With 4 nozzles are designated, which are also arranged in a ring around the active part at the rear end of the combustion chamber and are slightly employed to generate the swirl. The overall structure of the projectile is made in such a way that the centers of gravity of the engine and the active part practically coincide and form the common center of gravity S.

A moment of inertia ring 5 made of a material of high specific weight, for example made of iron, copper or lead, which is firmly connected to the combustion chamber shell, is arranged in such a way that its center of gravity also coincides approximately with the center of gravity S within the combustion chamber.

According to the invention, it is also possible to have an additional inside or outside the combustion chamber To provide a cruise engine, paying attention to the choice of the individual design values must be that despite a shift in the center of gravity and a change in the axial moment of inertia through the burn-up of the engines and through the influence of the airspeed over the entire operating range the stability criterion <5> 1 is also met.

It is also possible to use the propellant for the March engine in the common combustion chamber in a corresponding expedient form to arrange the outer shell of the combustion chamber, so that this, under certain circumstances using Ballast powder that has the effect of the described moment of inertia ring or its effect increased in the critical speed range to maintain a sufficient stability figure.

The missile projectile shown in Fig. 2 also has one consisting of a shaped charge Active part. The active part 1 is concentrically surrounded by a launch engine 3 and a cruise engine. Otherwise, the same applies to the position of the focal points as to FIG. 1 described became.

The same applies to that in FIG. 3 rocket projectile shown. In this version is the cruise engine 6 arranged concentrically around the take-off engine 3 is designed as a ramjet engine.

Claims (3)

Patent claims: 1. Shaped charge projectile with self-propulsion and twist stabilization, characterized in that that the engine and combustion chamber consisting of the engine is arranged in a known manner in a ring around the active part and that for Achieving the greatest possible stability with the smallest possible twist rotation on the bullet jacket and in the plane of the overall center of gravity a known moment of inertia ring (5) high specific gravity is arranged. 2. Shaped charge projectile self-propelled according to claim 1 with a start and a cruise engine, characterized in that the cruise engine (6) mounted in the outer casing is designed and arranged so that it complements the action of the inertia ring or replace it. 3. Self-propelled hollow charge projectile according to claim 2, characterized in that the Cruising engine (6) arranged concentrically outside the take-off engine (3) as a ramjet engine is trained. Considered publications:
German Patent No. 1097 321;
Austrian Patent No. 6796;
French patent specification No. 1265 295,
1052450, 816083;
British Patent No. 669,008;
U.S. Patent No. 2968,244. 1 sheet of drawings 609 540/138 3.66 © Bundesdruckelei Berlin