A thermally initiated variable venting system may comprise a first linear shape charge (LSC) coupled to a first sensor and a second LSC coupled to a second sensor. An upper apex of the second LSC may be disposed within a lower apex of the first LSC. The output of the system may vary depending on whether the event is fast cook-off (FCO) or slow cook-off (SCO).
Thermally initiated variable venting system for rocket motor
2020-11-10
Patent
Elektronische Ressource
Englisch
Venting of sounding - Rocket payloads
AIAA | 1982
|ADDITIVELY MANUFACTURED, THERMALLY OPTIMIZED ROCKET MOTOR NOZZLE DESIGN
Europäisches Patentamt | 2024
|