Effect of Radiation on the Rate of Burning of Solid Fuel Rocket Propellants

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Abstract
The temperature rise of powder grains in different rocket motors, resulting from the absorption of radiant energy, has been computed by the method of Avery. The calculated results show that more radiant energy is absorbed by the powder grains in large service rockets than in small experimental test motors. The increase in powder temperature before burning, associated with the absorption of radiant energy, leads to an increase in the average rate of burning of the solid fuel charge. The differences in burning rate produced by the absorption of radiant energy amount to less than four percent for the rocket motors commonly employed. Thus burning rate results obtained in small test motors may be applied to predict the approximate behavior of the same propellant in a large service rocket.

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