SUPPORTED HIGH-SURFACE-AREA PROPELLANT CHARGES FOR HIGH-ACCELERATION ROCKETS

• US 3,807,171 A
• Filed: 04/27/1972
• Issued: 04/30/1974
• Est. Priority Date: 04/27/1972
• Status: Expired due to Term

• Current Assignee: Stanley E. Anderson
• Original Assignee: Stanley E. Anderson
• Inventors: Anderson, Stanley E.
• Primary Examiner(s): Stahl, Robert F.
• Application Number:
  US05/249,453
• Time in Patent Office: 733 Days
• Field of Search: 102/101,102,103,49.3 60/35.6RS,255
• US Class Current: 60/255
• CPC Class Codes: F02K 9/36 Propellant charge supports

Abstract

A high-acceleration rocket motor in which the propellant is bonded to supporting structure in a thin and substantially uniform layer to enable the propellant to withstand high acceleration forces. High-surface-area propellant is accomplished by the shape of the supporting structure.

Claims

1. A rocket motor comprising a motor case that has a chamber therein, said motor case having an end wall at a forward end of said motor case and an open end opposite said end wall;

a solid support structure mounted in said motor case by being secured at said end wall to said motor case, said support structure extending the full length of said motor case, said support structure having a plurality of radiating fins that are integral with, uniformly spaced about the support structure, and extend the full length of the support structure; and

a substantially uniform thickness layer of propellant on the outer surfaces of said fins and the exposed surfaces on said support structure between said fins to provide a continuous and uninterrupted propellant layer that is structurally supported and has a highsurface-area.

2. A rocket motor as set forth in claim 1, wherein said support structure has from 8 to 12 radiating fins of a thickness from About 30 to about 70 thousandths of an inch thick, and wherein said solid propellant layer is about 30 to about 100 thousandths of an inch thick.

3. A rocket motor as set forth in claim 2, wherein said motor case has a substantially uniform thickness layer of propellant about the inner surface of said motor case.

4. A rocket motor as set forth in claim 3, wherein said propellant about the inner surface of said motor case has substantially the same thickness as the propellant about said fins.

5. A rocket motor as set forth in claim 4, wherein said fins are 10 in number and have a thickness of 30 to 60 thousandths of an inch.

6. A rocket motor as set forth in claim 5, wherein said propellant about said fins is approximately 30 to 60 thousandths of an inch thick, and the propellant about said inner surface is approximately 30 to 60 thousandths of an inch thick.