Title:
PROPELLANT TEST APPARATUS AND METHOD
Document Type and Number:
WIPO Patent Application WO2003087565
Kind Code:
A3
Abstract:
A test apparatus and method for a solid propellant, comprising a combustion chamber (214) for the solid propellant (212), an igniter (216) for igniting propellant in the combustion chamber, and an exhaust housing (220) having a primary exhaust channel (218) extending from the combustion chamber to an exit nozzle (222). A supplemental exhaust channel (224) is connected to the primary exhaust channel, and a valve (226) controls the size of the supplemental exhaust channel to selectively vary the flow of propellant gases therethrough, thereby to selectively vary the combustion chamber pressure to enable the testing of the burning characteristics of the propellant over a wide pressure range independent of the burning surface area of the propellant. In a further embodiment, an auxiliary exhaust channel (240) closed by a burst disk (244) is connected to the primary exhaust channel. The burst disk is constructed to fail at a predetermined pressure to enable exhaust gases to be vented through the auxiliary channel in the event the gas pressure in the primary exhaust channel exceeds the predetermined pressure.
Inventors:
KHADDURI FARID M
SPEAR GUY BRUCE
SPEAR GUY BRUCE
Application Number:
PCT/US2003/010931
Publication Date:
February 05, 2004
Filing Date:
April 10, 2003
Export Citation:
Assignee:
ATLANTIC RES CORP (US)
International Classes:
G01N25/50; G01N33/22; (IPC1-7): G01N33/22
Foreign References:
| US4554823A | 1985-11-26 | |||
| US5419119A | 1995-05-30 | |||
| US3701278A | 1972-10-31 |
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