Projectile with spin-producing flow passages

• US 4,296,893 A
• Filed: 03/08/1979
• Issued: 10/27/1981
• Est. Priority Date: 07/09/1977
• Status: Expired due to Term

• Current Assignee: Josef Ballmann
• Original Assignee: Josef Ballmann
• Inventors: Ballmann, Josef
• Primary Examiner(s): TUDOR, HAROLD JAY
• Application Number:
  US06/021,606
• Time in Patent Office: 964 Days
• Field of Search: 244/3.23, 244/3.1, 102/93, 102/DIG. 1, 102/92.1, 102/38 R
• US Class Current: 244/3.23
• CPC Class Codes: F42B 10/26 using spin F42B10/04, F42B10/12, F42B10/14, F42B10/24, F42B14/02 take precedence

Abstract

A projectile for shooting from a gun barrel in response to the force of a propellant gas emanating from the aperture of a propellant container, comprising a projectile body having a plurality of spin-producing propellant gas flow passages associated therewith, said passages annularly surrounding, and having their respective axes extending obliquely to, the longitudinal axis of the projectile body, wherein each passage has an inlet portion converging to an adjoining constricted portion, and a diverging portion extending downstream from the constricted portion, the axis of each passage being curved over the entire length of its converging inlet portion and substantially rectilinear over its diverging portion, and the walls of the diverging portion of each passage having a substantially rectilinear form, as viewed in the direction of propellant gas flow.

Claims

1. A projectile for shooting from a gun barrel in response to the force of a propellant gas emanating from the aperture of a propellant container, comprising a projectile body having a plurality of spin-producing propellant gas flow passages associated therewith, said passages annularly surrounding, and having their respective axes extending obliquely to, the longitudinal axis of the projectile body, wherein each passage has an inlet portion converging to an adjoining constricted portion, and a diverging portion extending downstream from the constricted portion, the axis of each passage being curved over the entire length of its converging inlet portion and substantially rectilinear over its diverging portion, and the walls of the diverging portion of each passage having a substantially rectilinear form, as viewed in the direction of propellant gas flow.

2. A projectile as claimed in claim 1, wherein at the outlet end of each flow passage, the pressure side of its bounding wall bears an extension.

3. A projectile as claimed in claims 1 or 2, wherein the distance between the axis of each flow passage and the longitudinal axis of the projectile body is substantially constant over the length of the flow passage, and wherein the flow passages are situated axially.

4. A projectile as claimed in claims 1 or 2, wherein the axis of each flow passage has a widely varying spacing from the longitudinal axis of the projectile body, and wherein the flow passages are situated radially.

5. A projectile as claimed in claim 4, wherein the flow passages are arranged in two or more groups which are spaced apart so as to be successively penetrated by the propellant gas for multi-stage spin production, and wherein the groups are arranged so that the total cross-sectional area of the passages in each group, measured at their narrowest dimension, increases downstream from one group to the next.

6. A projectile as claimed in claim 5, wherein the individual passages of a group have a cross-sectional area, measured at their narrowest dimension, larger than that of the individual passages of the group situated immediately upstream.

7. A projectile as claimed in claim 5, wherein all of the passages have substantially the same cross-sectional area, measured at their narrowest dimension, and wherein the number of passages in each group increases downstream from one group to the next.

8. A projectile as claimed in claim 3, wherein the flow passages are arranged in two or more groups which are spaced apart so as to be successively penetrated by the propellant gas for multi-stage spin production, and wherein the groups are arranged so that the total cross-sectional area of the passages in each group, measured at their narrowest dimension, increases downstream from one group to the next.

9. A projectile as claimed in claim 8, wherein the individual passages of a group have a cross-sectional area, measured at their narrowest dimension, larger than that of the individual passages of the group situated immediately upstream.

10. A projectile as claimed in claim 8, wherein all of the passages have substantially the same cross-sectional area, measured at their narrowest dimension, and wherein the number of passages in each group increases downstream from one group to the next.

11. A projectile as claimed in claim 3, wherein the flow passages are arranged in two or more groups which are spaced apart so as to be successively penetrated by the propellant gas for multi-stage spin production, wherein the total cross-sectional area of the passages in each group, measured at their narrowest dimension, is substantially the same, and wherein each of the groups is provided with propellant gas leakage gaps, with the gaps increasing downstream from one group to the next.

12. A projectile as claimed in claim 4, wherein the flow passages are arranged in two or more groups which are spaced apart so as to be successively penetrated by the propellant gas for multi-stage spin production, wherein the total cross-sectional area of the passages in each group, measured at their narrowest dimension, is substantially the same, and wherein each of the groups is provided with propellant gas leakage gaps, with the gaps increasing downstream from one group to the next.