International Journal of Aerospace Engineering / 2008 / Article / Fig 8

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 8

Frequency response of AP/PBAN Propellant C, theory ( Δ 𝐻 𝑠 = 1 1 5 0 0 0  s−1, 𝐾 𝑏 = 1 8 0 0 0  J/kg; Δ 𝐻 𝑠 = 6 8 0 0 0  s−1, Ω  J/kg) and experiment [24, 26], in terms of real part of pressure-based function (theory & experiment, pressure at 300 psig).
26070.fig.008

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