International Journal of Aerospace Engineering / 2008 / Article / Fig 9

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 9

Frequency response of AP/PBAN Propellant C, theory ( Δ 𝐻 𝑠 = 6 8 0 0 0  s−1, 𝜇  J/kg) and experiment [22], in terms of real part of pressure-based function, at differing pressures.
26070.fig.009

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