年間 6 号発行
ISSN 印刷: 2150-766X
ISSN オンライン: 2150-7678
Indexed in
CONTAINED LOW PRESSURE COMBUSTION OF NIKE AND IMPROVED HAWK ROCKET MOTORS: EXPERIMENTAL TECHNIQUES AND EMISSIONS MEASUREMENTS
要約
Results obtained from three rocket motor propellant burn tests conducted in a large, sealed, underground cavern are described. These tests made use of a runnel complex at the U.S. Department of Energy's Nevada Test Site, Mercury, NV, USA. The NIKE rocket motor containing double base propellant was used in two tests (two and four motors, respectively), and a third test used two Improved HAWK rocket motors containing composite propellant. In each test, relatively small quantities of explosive were used to initiate non-propulsive propellant bums that lasted approximately 20 seconds. An extensive suite of both time-resolved and time-averaged data was collected for several hours after each test. These data include pressure and temperature transients in the test chamber as well as concentrations and compositions of the gas species and aerosols generated by the combustion process.
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Koch Ernst‐Christian, Insensitive High Explosives: V. Ballistic Properties and Vulnerability of Nitroguanidine Based Propellants, Propellants, Explosives, Pyrotechnics, 46, 2, 2021. Crossref