Abstract
Results are presented on the response of a solid propellant to pressure and velocity fluctuations. Two different experimental techniques have been developed. The first makes use of devices known to be unstable (L* or T rocket motors). Comparison of cold and hot tests shows the poor credibility of the results obtained with T rocket motors; furthermore the temperature heterogeneity is scale dependent. In the second technique, research rockets with a modulated throat section are used. These methods are discussed in some detail from the experimental and theoretical standpoints. Here again cold gas comparative tests emphasize the effect of combustion on the observed gain. A linearized theory predicts the observed trends.
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