Spin stabilized projectile for smoothbore barrels

• US 10,309,755 B1
• Filed: 05/30/2018
• Issued: 06/04/2019
• Est. Priority Date: 05/30/2018
• Status: Expired due to Fees

• Current Assignee: Michael Sean Bradbury
• Original Assignee: Michael Sean Bradbury
• Inventors: Bradbury, Michael Sean
• Primary Examiner(s): Johnson, Stephen
• Application Number:
  US15/993,346
• Time in Patent Office: 370 Days
• CPC Class Codes: F42B 10/28 induced by gas action
• CPC Class Codes: F42B 14/06 Sub-calibre projectiles having sabots; Sabots therefor
• CPC Class Codes: F42B 19/18 of turbine type

Abstract

The Spin-stabilized Projectile for Smoothbore Barrels would provide for improved accuracy and a flatter trajectory in comparison tot current Foster design projectiles or statically stabilized finned projectiles. The method achieved for spin stabilization here can easily be up-scaled for larger caliber artillery projectiles for when a spin-stabilized projectile is desired from a smoothbore weapon.

Claims

1. An Assembly for a sub-caliber rotationally stabilized projectile for use in a smoothbore barrel firearm comprising:

a. a projectile having a fore-end portion, an aft-end portion, and a sufficiently uniform distribution of mass extending radially from its longitudinal axis whereby said projectile is capable of spin stabilization; and

b. a turbine having a turbine clutch, a turbine bearing, and at least one turbine blade, said turbine clutch can be mated to said aft-end portion of said projectile; and

c. a gas seal having a gas seal bearing, and at least one gas seal port, said gas seal bearing can be mated to said turbine bearing whereby said turbine bearing is supported by and is and rotationally independent of said gas seal bearing, said gas port converts burning propellant into a gas jet imposing a force onto said turbine blade; and

d. said turbine blade converts said gas jet force into a rotational force causing said turbine to rotate whereby said turbine imposes a rotational force onto said projectile whereby both said turbine and said projectile rotate while being supported by said gas seal and sabots; and

e. at least one said sabot each having an inner surface that can be mated with and is rotationally independent from said projectile fore-end portion, each of said sabot has at least one sabot gas port whereby said gas jet is vented through said sabot and forward of said assembly, said sabots, said turbine, and said gas seal are eject-able from said projectile when said projectile exits said barrel.