International Journal of Aerospace Engineering / 2008 / Article / Fig 6

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 6

Frequency response of AP/HTPB Propellant B, theory ( Δ 𝐻 𝑠 = 7 5 0 0 0  s−1, 𝑟 𝑏 , 𝑜  J/kg) and experiment [23], in terms of real part of pressure-based function (theory & experiment, pressure at 1200 psig).
26070.fig.006

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