A self - excited low - frequency oscillatory combustion was analyzed theoretically, which occurred during the pressure decay in a nozzleless rocket motor. Based on the L* oscillation theory in which a stability of a closed - loop model of a pressure - coupled response function of a propellant burning rate and a time delay factor of a motor mass conservation was examined, critical conditions of the oscillation were clarified. Conversely, with the analytical results obtained, combustion experiments of nozzleless rocket motors could determine the combustion response function. And supply the infornation of the propellant burning properties, such as an activation energy of surface deoomposition, etc. It should be noted that, in a case that a burning rate characteristic in the motor deviates from the steady - state one, predicting combustion properties would produces some errors.
ノズルレスロケットモータで圧力降下中に発生する自励的低周波振動燃焼を理論的に解析した｡ 推進薬の圧力変動に対する燃焼速度応答関数とモータの質量保存による時間遅れ要素との連成を考慮する, いわゆるL*振動理論で振動発生条件が明らかになった。 これを利用すればノズルレスロケットモータ燃焼実験より逆に推進薬固有の応答関数を求めることができ, さらに表面反応活性化エネルギー等の推進薬燃焼特性量を推定できる｡ また提案された解析手法ではモータ内の燃焼速度が定常特性からずれるような場合, 特性量が大きく誤差を生じることが予見された｡