A major hazard posed by the propulsion system of hypersonic and space vehicles is the possibility of fire or explosion in the vehicle environment. The hazard is mitigated by minimizing or detecting, in the vehicle environment, the three ingredients essential to producing fire: fuel, oxidizer, and an ignition source. The Linear Aerospike SR-71 Experiment (LASRE) consisted of a linear aerospike rocket engine integrated into one-half of an X-33-like lifting body shape, carried on top of an SR-71 aircraft. Gaseous hydrogen and liquid oxygen were used as propellants. Although LASRE is a one-of-a-kind experimental system, it must be rated for piloted flight, so this test presented a unique challenge. To help meet safety requirements, the following propulsion hazard mitigation systems were incorporated into the experiment: pod inert purge, oxygen sensors, a hydrogen leak detection algorithm, hydrogen sensors, fire detection and pod temperature thermocouples, water misting, and control room displays. These systems are described, and their development discussed. Analyses, ground test, and flight test results are presented, as well as findings and lessons learned.
Linear Aerospike SR-71 Experiment (LASRE): Aerospace Propulsion Hazard Mitigation Systems
1998
22 pages
Report
Keine Angabe
Englisch
Rocket Engines & Motors , Rocket Propellants , Astronautics , Spacecraft Trajectories & Flight Mechanics , Aerospike engines , Sr-71 aircraft , Spacecraft propulsion , Propulsion system performance , Propulsion system configurations , Liquid oxygen , Lifting bodies , Hypersonic vehicles , Flight tests , Thermocouples , Rocket engines , Pods(External stores) , Propellants , Propulsion , Oxidizers , Leakage , Ground based control , Algorithms