International Journal of Aerospace Engineering / 2008 / Article / Fig 11

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 11

Frequency response of double-base Propellant E, theory ( Δ 𝐻 𝑠 = 4 5 0 0 0  s−1, Δ 𝐻 𝑠 = 9 0 0 0 0  J/kg [800 psig], 𝑅 𝑝  J/kg [1600 psig]) and experiment [30], in terms of real part of pressure-based function.
26070.fig.011

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