International Journal of Aerospace Engineering / 2008 / Article / Fig 10

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 10

Frequency response of AP/HTPB Propellant D, theory ( Δ 𝐻 𝑠 = 1 0 0 0 0 0 0  s−1, 𝑟 𝑏  J/kg) and experiment [24], in terms of real part of pressure-based function (theory and experiment, pressure at 200 psig).
26070.fig.010

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