Rocket projectile

• US 3,349,708 A
• Filed: 12/13/1965
• Issued: 10/31/1967
• Est. Priority Date: 12/16/1964
• Status: Expired due to Term

• Current Assignee: Withers Paget Win
• Original Assignee: Withers Paget Win
• Inventors: WITHERS PAGET WIN
• Application Number:
  US04/513,461
• Time in Patent Office: 687 Days
• US Class Current: 102/374
• CPC Class Codes: F02K 9/32 Constructional parts; Details not otherwise provided for
• CPC Class Codes: F02K 9/86 using nozzle throats of adjustable cross- section F02K9/978 takes precedence
• CPC Class Codes: F42B 14/06 Sub-calibre projectiles having sabots; Sabots therefor
• CPC Class Codes: F42B 15/00 Self-propelled projectiles or missiles, e.g. rockets; Guided missiles F42B10/00, F42B12/00, F42B14/00 take precedence; for practice or training F42B8/12; rocket torpedoes F42B17/00; marine torpedoes F42B19/00; cosmonautic vehicles B64G; jet-propulsion plants F02K

Claims

1. A ROCKET PROJECTILE LAUNCHED BY A FIREARM AND HAVING AN ADDITIONAL PROPULSION DEVICE CONSTITUTED BY SOLID FUEL ROCKET MOTOR HOUSED IN THE PROJECTILE, A CALIBRATED NOZZLE IN THE REAR OF THE PROJECTILE FOR THE ESCAPE OF COMBUSTION GASES OF THE SOLID FUEL OF THE ROCKET, A CENTERING SLEEVE DISPOSED IN THE PROJECTILE, A SOLID BODY CARRIED IN CENTERED RELATIONSHIP BY SAID CENTERING SLEEVE, SAID CALIBRATED NOZZLE BEING DISPOSED IN SAID SOLID BODY, A TRANSVERSE PLATE DISPOSED IN THE REAR OF THE PROJECTILE, SAID PLATE HAVING HOLES THERETHROUGH, SAID CENTERING SLEEVE HAVING A SHOULDER THEREON, MEANS DEFINING AN ADDITIONAL CONDUIT FROM THE REAR OF THE PROJECTILE INTO THE VICINITY OF SAID TRANSVERSE PLATE, SAID ADDITIONAL CONDUIT BEING CLOSED WHEN SAID TRANSVERSE PLATE ABUTS AGAINST SAID SHOULDER, AND MEANS DEFINING A CHANNEL ISSUING AT THE REAR OF SAID SOLID FUEL AND COMMUNICATING WITH SAID ADDITIONAL CONDUIT.