ROCKET AND PROPELLANT THEREFOR

• US 3,811,380 A
• Filed: 01/23/1968
• Issued: 05/21/1974
• Est. Priority Date: 01/30/1958
• Status: Expired due to Term

• Current Assignee: John P. Glass
• Original Assignee: John P. Glass
• Inventors: Glass, John P.
• Primary Examiner(s): Pendegrass, Verlin R.
• Application Number:
  US04/720,429
• Time in Patent Office: 2,310 Days
• Field of Search: 102/99-103,34,34.5,40,49.3,49.7 60/253-256
• US Class Current: 102/380
• CPC Class Codes: F02K 9/82 by injection of a secondary fluid into the rocket exhaust gases
• CPC Class Codes: F02K 9/94 Re-ignitable or restartable rocket- engine plants; Intermittently operated rocket-engine plants

Abstract

A rocket and propellant therefor comprising a body portion formed of a plurality of rings arranged in abutting relationship to form an enclosing wall having a nose and a tail end, a rocket motor positioned within the wall and including a solid propellant arranged in layers with each layer connected to one of the rings, a series of foraminous screens embedded in the propellant and presenting a concave surface to the tail end of the rocket and focusing the propellant gases on the tail end which is adapted to have a burning surface that travels toward the nose end when the rocket is in flight, said screens also controlling the shape of the burning surface by spreading it laterally. The rocket also includes means for controlling the distance of travel by extinguishing the burning surface, means for re-igniting the extinguished rocket including an electrical circuit having wires which connect with a slow-burning fuse layer, and steering means which includes an auxiliary propellant that is discharged through clusters of pipes to change the mass or energy at one side of the rocket tail to swing the tail around and change the direction of rocket travel.

Claims

2. The rocket defined in claim 1, wherein said screens are made of a slower burning material than said propellant to thereby retard hot spots.

3. The rocket defined in claim 1, wherein said screens are made of a faster-burning material than said propellant to quickly spread laterally the flame from any hot spots.

4. The rocket defined in claim 1, wherein said screens are made of metal.

5. The rocket defined in claim 1, wherein a layer of slow-burning fuse material is positioned in the rocket propellant between the screens with electrical leads imbedded in said fuse material and extending therefrom to a re-ignition means chamber.

6. A rocket comprising an enclosing wall having a nose and a tail end, a solid rocket propellant contained within said wall and presenting a burnable surface to said tail end, a series of foraminous screens imbedded in said propellant and extending transversely across the interior of each of said rings, said screens presenting a concave surface to said tail end, and a separate re-ignition layer of slow-burning fuse material located between said screens, said rocket propellant comprising a plurality of charges of rapid burning propellant which are spherical in shape with a cone-shaped opening leading to a detonator so as to expel their burning gases in one direction when burning and are dispersed between said nose and tail end to burn successively, and a matrix of slower-burning cushioning material in which said charges are supported and oriented so that their burning gases are expelled toward said tail end, whereby the average rate of burning of said rocket propellant as a whole is intermediate the rate of burning of said charges and said matrix.

7. The combination defined in claim 6, wherein said charges are provided with fuses, and fuse wire extending from said fuses to a control system chamber.

8. A solid propellant for rockets and the like comprising a matrix of a solid burnable material, and pellets dispersed within said matrix, said pellets being made of a faster-burning material than said matrix material, said pellets being spherical in shape with a cone-shaped opening leading to a detonator, said propellant being arranged in identically shaped concave segments positioned to focus the gas toward the tail.

9. A rocket comprising a series of rings arranged in abutting relationship to form an enclosing wall having a nose and a tail end, a solid rocket propellant contained within said wall and presenting a burnable concave surface to said tail end, said solid propellant comprising a matrix of solid burnable material, and pellets dispersed within said matrix, said pellets being made of a faster-burning material than said matrix material, said pellets including a resilient coating which protects the pellets against being detonated by pressure waves, said resilient coating having fuzzy fibers that add structural strength to the propellant, and a separate layer of slow-burning fuse material located in said propellant and connected to a re-ignition means chamber.

10. A rocket comprising an enclosing wall having a tail end, a solid rocket propellant contained within said wall and presenting a burnable surface to said tail end, a series of foraminous screens imbedded in said propellant and extending transversely across the interior of each of said rings, said screens presenting a concave surface to said tail end, and a separate re-ignition layer of slow-burning fuse material located between said screens, said rocket propellant comprising a plurality of pellets of explosive embedded in a matrix, with each pellet containing a nucleus which detonates in response to heat.

11. A rocket comprising an enclosing wall having a tail end, a solid rocket propellant contained within said wall and presenting a burnable surface to said tail end, a series of foraminous screens imbedded in said propellant and extending transversely across the interior of each of said rings, said screens presenting a concave surface to said tail end, and a separate re-ignition layer of slow-burning fuse material located between said screens, said rocket propellant comprising a plurality of pellets of explosive embedded in a matrix, with each pellet having a resilient coating which includes fuzzy fibers that add structural strength to the propellant.

12. A rocket comprising an enclosing wall having a tail end, a solid rocket propellant contained within said wall and presenting a burnable surface to said tail end, a series of foraminous screens imbedded in said propellant and extending transversely across the interior of each of said rings, said screens presenting a concave surface to said tail end, and a separate re-ignition layer of slow-burning fuse material located between said screens, said rocket propellant comprising a plurality of pellets of explosive imbedded in a matrix, said matrix having fibers of refractory material imbedded therein to provide added structural strength to the propellant.

13. A solid propellant for rockets and the like comprising a matrix of solid burnable material, and pellets dispersed within said matrix, said pellets being spherical in shape with a cone-shaped opening leading to a detonator.

14. The propellant defined in claim 13, wherein said pellets are provided with fuses, and fuse wire extending from said fuses to a control system chamber.

15. A solid propellant for rockets and the like comprising a matrix of solid burnable material, and pellets dispersed within said matrix, each of said pellets containing a nucleus which detonates in response to heat.