Title:
HIGH PRESSURE, HIGH PERFORMANCE SOLID ROCKET HYDROXY-TERMINATED POLYBUTADIENE PROPELLANT FORMULATIONS
Document Type and Number:
WIPO Patent Application WO1999018051
Kind Code:
A3
Abstract:
A solid rocket propellant formulation with a burn rate slope of less than about 0.15 ips/psi (2.54cm/69.10<2>Pas) over a substantial portion of a pressure range of about 1,000 psi (69.10<2>Pa) to about 7,000 psi (69.10<2>pa) and a temperature sensitivity of less than about 0.15 %/ DEG F is provided. The solid propellant formulation contains from 35 % to 55 % by weight ammonium perchlorate particles having an average size of 200 mu m, from 25 % to 40 % by weight ammonium perchlorate particles having an average size in the range of from 2 mu m to 50 mu m, from 7 % to 10 % by weight hydroxy-terminated polybutadiene binder and at least one member selected from the group consisting of a co-oxidizer, a ballistic additive, and a polyisocyanate curative. A high performance solid propellant rocket motor including the solid rocket propellant formulation is also provided. The rocket motor is encased in a high strength low weight motor casing which is further equipped with a nozzle throat constructed of material that has an erosion rate of about 2 to about 3 mils per second during motor operation. The solid rocket propellant formulation can be cast in a grain pattern such that an all-boost thrust profile is achieved.
Inventors:
HAWKINS DAVID K
CAMPBELL CAROL J
CAMPBELL CAROL J
Application Number:
PCT/US1998/020891
Publication Date:
June 17, 1999
Filing Date:
October 02, 1998
Export Citation:
Assignee:
CORDANT TECH INC (US)
International Classes:
C06B23/00; C06B29/22; C06B45/10; (IPC1-7): C06B45/10; C06B23/00; C06B29/22
Foreign References:
| US4391660A | 1983-07-05 | |||
| US5334270A | 1994-08-02 | |||
| US5472532A | 1995-12-05 | |||
| DE2718013A1 | 1977-11-17 | |||
| US4776993A | 1988-10-11 | |||
| US3986910A | 1976-10-19 |
Other References:
CHEMICAL ABSTRACTS, vol. 111, no. 20, 13 November 1989, Columbus, Ohio, US; abstract no. 177405x, B. WANG: "Effect of additive HMX upon burning rate behavior of AP/HTPB composite propellants" page 202; XP000156193
J. MAMIE: "Feststoffraketenantriebe", SCHWEIZERISCHE TECHNISCHE ZEITSCHRIFT, vol. 62, no. 44, 1965, pages 889 - 896, XP002096765
CHEMICAL ABSTRACTS, vol. 114, no. 4, 28 January 1991, Columbus, Ohio, US; abstract no. 26763y, R.G. STACER ET AL.: "Polymeric binder and the combustion of solid propellants" page 153; XP000188157
CHEMICAL ABSTRACTS, vol. 129, no. 12, 21 September 1998, Columbus, Ohio, US; abstract no. 150869m, T.T. NGUYEN: "New insights into the combustion of AP/HTPB rocket propellants:" page 695; XP000789751
J. MAMIE: "Feststoffraketenantriebe", SCHWEIZERISCHE TECHNISCHE ZEITSCHRIFT, vol. 62, no. 44, 1965, pages 889 - 896, XP002096765
CHEMICAL ABSTRACTS, vol. 114, no. 4, 28 January 1991, Columbus, Ohio, US; abstract no. 26763y, R.G. STACER ET AL.: "Polymeric binder and the combustion of solid propellants" page 153; XP000188157
CHEMICAL ABSTRACTS, vol. 129, no. 12, 21 September 1998, Columbus, Ohio, US; abstract no. 150869m, T.T. NGUYEN: "New insights into the combustion of AP/HTPB rocket propellants:" page 695; XP000789751
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