Propellant test apparatus and method
US6662629B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 12, 2002 |
| Grant date | Dec 16, 2003 |
| Priority date | — |
| Expiry date | Apr 23, 2022 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01N33/222
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
A test apparatus and method for a solid propellant, comprising a combustion chamber for the solid propellant, an igniter for igniting propellant in the combustion chamber, and an exhaust housing having a primary exhaust channel extending from the combustion chamber to an exit nozzle. A supplemental exhaust channel is connected to the primary exhaust channel, and a valve 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 closed by a burst disk 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 exhaust channel in the event the gas pressure in the primary exhaust channel exceeds the predetermined pressure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.