PYROTECHNIC DEVICES

• US 3,715,984 A
• Filed: 06/09/1970
• Issued: 02/13/1973
• Est. Priority Date: 06/09/1969
• Status: Expired due to Term

• Current Assignee: Dudley Charles Murray
• Original Assignee: Dudley Charles Murray
• Inventors: Murray, Dudley Charles
• Primary Examiner(s): Borchelt, Benjamin A.
• Assistant Examiner(s): Bent, D. A.
• Application Number:
  US05/044,725
• Time in Patent Office: 980 Days
• Field of Search: 102/34.2,37.4 149/19
• US Class Current: 60/256
• CPC Class Codes: C06B 45/10 the organic component containing a resin

Abstract

In a rocket with plastic propellant, which includes a solid oxidizing agent, a fuse means is used to directly ignite the propellant, and copper chromate is associated with the propellant by either being distributed within the propellant and/or on the surface of the propellant to be ignited.

Claims

1. A rocket comprising:

a. a combustion chamber;

b. a mass of propellant located within said chamber, said propellant being a plastic gas-producing composition and said composition comprising;

i. a solid oxidizing agent and ii. a binder which is a visco-elastic liquid comprising a Polymeric aliphatic hydrocarbon having side groups and a viscosity in the range of from 250,000 to 7,000,000 poises at 25* C.; and

c. means for igniting said propellant comprising the combination of iii. copper chromate associated with the propellant in the region where it is desired that initial ignition occur, and iv. fuse means of quickmatch material having a portion thereof juxtaposed to the propellant in said region for igniting the same directly with the aid of said copper chromate.

2. A rocket according to claim 1, wherein at least part of said copper chromate is exposed on a portion of the propellant surface in the region to be ignited.

3. A rocket according to claim 2, wherein there is a discontinuous distribution of copper chromate exposed over substantially the whole of the said surface.

4. A rocket according to claim 2, wherein the said surface has a sprinkling of copper chromate thereon.

5. A rocket according to claim 1, wherein said copper chromate is of a particle size such that substantially all of it will pass through a 120 mesh (B.S.S.) screen.

6. A rocket according to claim 1, wherein the said binder comprises a polyisobutene.

7. A rocket according to claim 1, wherein the said composition includes from 1 to 2 percent by weight of said copper chromate.

8. A rocket according to claim 1, wherein the said plastic gas-producing composition has admixed therein at least 0.5 percent by weight of said copper chromate.

9. A rocket according to claim 8, wherein at least part of said copper chromate is exposed on a portion of the propellant surface in the region to be ignited.

10. A rocket according to claim 8, wherein there is a discontinuous distribution of copper chromate over substantially the whole of the said surface.

11. A rocket according to claim 8, wherein the propellant mass has a sprinkling of copper chromate thereon.

12. A rocket according to claim 8, wherein the particle size of the copper chromate is such that substantially all of it will pass through a 120 mesh (B.S.S.) screen.