Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 4

Frequency response of Propellant A, 𝐾 𝑏 = 1 7 0 0 0 0  m/s, Δ 𝐻 𝑠 = 0 . 0  s−1, 𝑟 𝑏 , 𝑞 𝑠  J/kg.
26070.fig.004