Spin-stabilized training missile

• US 4,520,972 A
• Filed: 06/07/1982
• Issued: 06/04/1985
• Est. Priority Date: 06/05/1981
• Status: Expired due to Fees

• Current Assignee: Dynamit Nobel AG
• Original Assignee: Dynamit Nobel AG
• Inventors: Homburg, Axel, Diesinger, Walter
• Primary Examiner(s): Walsh, Donald P.
• Assistant Examiner(s): Cornwell, D. K.
• Application Number:
  US06/386,072
• Time in Patent Office: 1,093 Days
• Field of Search: 102/444, 102/498, 102/529, 244/3.23, 244/3.24, 244/3.27, 244/3.28, 244/3.29, 244/3.3, 244/3.1
• US Class Current: 244/3.1
• CPC Class Codes: F42B 10/14 using fins spread or deployed after launch, e.g. after leaving the barrel
• CPC Class Codes: F42B 10/54 Spin braking means

Abstract

A spin-stabilized training missile is equipped with a stabilizer device for reducing spinning in order to decrease the flight range. The training missile is designed so that its stabilization attainable solely by the spin upon firing is not sufficient for a stable flight in the practice range. The required additional stabilizing in the practice range is obtained by a stabilizer device or control airfoil effecting simultaneously, after leaving the practice range, such a spin reduction that the training missile becomes unstable and the range of flight is controlled.

Claims

1. A spin-stabilized training missile which comprises a base member shaped as a missile with a stabilizer means for reducing spin in order to decrease the flight range, the base member of the training missile, upon firing, having a stability due to spin that is too low for stable flight, and said stabilizer means comprises at least one element having a stabilizer surface which effects, on the one hand, an additional aerodynamic stabilization providing stable flight in the training range together with the spin stabilization of te base member and, on the other hand, after leaving the training range, such a spin reduction that the training missile becomes unstable;

the stabilization attainable by spin upon firing of the training missile base member, without the stabilizer means, is defined by a stability factor s<

1, said stabilizer means, which is mounted behind the center of gravity of said base member, initially compensating for the lack of stability of the base member and then generating a longitudinal moment which brakes the rotation of said training missile.

2. A training missile according to claim 1, wherein the stabilizer surface is provided by an unfolding or extensible stabilizer element.

3. A training missile according to claim 2, wherein a power element is associated with the stabilizer surface, said power element exerting on the stabilizer surface a radially inwardly directed force in such a way that the surface, with a reduction in the centrifugal force of the rotating training missile, is at least partially retracted again.

4. A training missile according to claim 1, wherein the stabilizer is formed at a separate stabilizer means carrier, which is connected to the remaining training missile, forming a base member and is rotatable relatively to this base member.

5. A training missile according to claim 4, wherein the base member is provided with a rearwardly oriented, axial helical spindle on which the stabilizer carrier is disposed to be rotatable and displaceable between a forward and a rearward position;

and that the spin reduction is effected by mechanical coupling between the stabilizer carrier and the base member.

6. A training missile according to claim 4, wherein for spin reduction, a moment transmission is provided from the stabilizer carrier to the base member during which the stabilizer carrier rotates relatively to the base member.

7. A training missile according to claim 4, wherein the stabilizer carrier is freely rotatable during the spin reduction with respect to the base member, and exhibits a longitudinal moment of inertia of such a size that its braking alone provides the desired spin reduction.

8. A training missile according to claim 7, wherein the stabilizer carrier is extended toward the front and, with this extension, projects into a corresponding axial recess of the base member.

9. A training missile according to claim 7 or 8, wherein the base member, designed with a correspondingly reduced longitudinal moment of inertia, has an auxiliary stabilizer counteracting its spin reduction.

10. A training missile according to claim 1, wherein the center of gravity of the training missile base is displaced towards the rear of the base as compared with a combat missile of like configuration in order to reduce the spin stability of the training missile.

11. A training missile which comprises a base member shaped as a missile with a stabilizer means for reducing spin in order to decrease the flight range, the base member of the training missile, upon firing, having a stability due to spin that is too low for stable flight, and said stabilizer means comprises at least one element having a stabilizer surface which effects, on the one hand, an additional aerodynamic stabilization providing stable flight in the training range together with the spin stabilization of the base member and, on the other hand, after leaving the training range, such a spin reduction that the training missile becomes unstable;

a jet propulsion unit being provided additionally to the stabilizer means, said propulstion unit exerting, during the training flight phase, a torque and a thrust for compensating for the braking effects of the stabilizer means.

12. A training missile according to claim 11, wherein the stabilizer surface is provided by an unfolding or extensible stabilizer element.

13. A training missile according to claim 12, wherein a power element is associated with the stabilizer surface, said power element exerting on the stabilizer surface a radially inward directive force in such a way that the surface, with the reduction in the centrifugal force of the rotating training missile, is at least partially retracted again.

14. A training missile comprises a base member shaped as a missile with a stabilizer means for reducing spin in order to decrease the flight range, the base member of the training missile, upon firing, having a stability due to spin that is too low for stable flight, and said stabilizer means comprises at least one element having a stabilizer surface which effects, on the one hand, an additional aerodynamic stabilization providing stable flight in the training range together with the spin stabilization of the base member and, on the other hand, after leaving the training range, such a spin reduction that the training missile becomes unstable, the adjustment angle of the stabilizer surface of the at least one element of the stabilizer means being selected to be equal to the geometric angle of incidence α

_geom on the training flight path whereby the stabilizer means initially exerts a longitudinal moment on the training missile accelerating the rotation thereof and thereafter exerts a braking longitudinal moment on the training missile thereby reducing the rotation.

15. A training missile according to claim 14, wherein α

_geom, the geometric angle of incidence, is the angle formed by the resultant velocity v_res of the training missile with the longitudinal axis of the training missile.