International Journal of Aerospace Engineering / 2008 / Article / Fig 4

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 4

Frequency response of Propellant A, ๐พ ๐‘ = 1 7 0 0 0 0 โ€‰m/s, ฮ” ๐ป ๐‘  = 0 . 0 โ€‰sโˆ’1, ๐‘Ÿ ๐‘ , ๐‘ž ๐‘  โ€‰J/kg.

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