A solid rocket motor comprises a pressure vessel, a solid propellant structure within the pressure vessel, and a flight termination system overlying the pressure vessel. The flight termination system comprises a shaped charge configured and positioned to effectuate ignition of an inner portion of the solid propellant structure and a reduction in an ability of the pressure vessel to withstand a change in internal pressure. Another solid rocket motor, a multi-stage rocket motor assembly, and a method of destroying a launch vehicle in flight are also described.
Solid rocket motors including flight termination systems, and related multi-stage solid rocket motor assemblies and methods
22.09.2020
Patent
Elektronische Ressource
Englisch
Combustion termination of solid rocket motors
AIAA | 1965
|Combustion termination of solid rocket motors
AIAA | 1964
|Europäisches Patentamt | 2018
|NTRS | 1993
|