International Journal of Aerospace Engineering / 2008 / Article / Fig 5

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 5

Frequency response of Propellant A, ฮ” ๐ป ๐‘  = 0 . 0 โ€‰m/s, ๐‘Ÿ ๐‘ , ๐‘œ โ€‰J/kg.

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