Depressurization Extinguishment of Composite Solid Propellants: Flame Structure, Surface Characteristics, and Restart Capability
DEUTSCHE FORSCHUNGS- UND VERSUCHSANSTALT FUER LUFT- UND RAUMFAHRT E V TRAUEN (GERMANY F R)
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During a rapid depressurization, the intensities of several spectral lines and the pressure are measured, simultaneous to the taking of high speed movie photographs of the flame. The quenched surfaces of all samples are analysed with a scanning electron microscope. The 24 CTBP 76 25 microns AP propellant extinguishes permanently for initial depressurization rates exceeding ca. 7,500 atms, when the initial pressure is 45 atm. At the highest depressurization rates, the gaseous flame quenches immediately due to the adiabatic expansion. Lower rates of fall in pressure allow a second flame to develope after 5 - 7 ms, the relaxation time of the solid phase. This new flame is irregular and partially consumes the AP particles available on the propellant surface, depending on the imposed dPdt. The new flame goes out only at the end of the pressure transient.
- Solid Propellant Rocket Engines
- Solid Rocket Propellants