FIGURE 11-12. Effect of axial spin on the thrust-time behavior of a rocket motor with composite propellant using aluminum and PBAN (polybutadiene acrylonitrile) as fuels. (Adapted with permission from Ref. 11-7.)
staples (short bent wires) mixed with the propellant prior to the casting operation.
Intense radiation emissions from the hot gases in the grain cavity transfer heat to the burning propellant surfaces. More energetic radiation causes an increase in burning rate. Radiation of the exhaust plume (outside of the nozzle) and the effect of particles in the gas are discussed in Chapter 18.
Combustion instability, also called oscillatory combustion, can affect the burning rate of the propellant because of increased heat-transfer rate, gas velocity, and high pressure. This is discussed in Chapter 13.
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