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本文根据火箭发动机推力等于作用在火箭发动机内外表面上压力的合力这一基本公式,引入在一定条件下喷管扩张段内的燃气压力与喷管截面半径成线性变化的关系,导出大料切角时斜切喷管火箭发动机的轴向推力和侧向力理论计算的近似公式。计算结果与六分力推力试验的测试结果相比颇为接近,说明该公式具有较好的计算精度,可以用于涡轮式火箭弹推力和转矩计算以及某些反推发动机的推力计算。
According to the basic formula that the rocket engine thrust is equal to the resultant force of the pressure acting on the inner and outer surfaces of the rocket engine, the relationship between the gas pressure and the radius of the nozzle cross section under certain conditions is introduced. Approximate Formulas for Theoretical Calculation of Axial Thrust and Lateral Forces of Beveling Rocket Motor. The calculated result is quite close to the test result of the six component thrust test, which shows that the formula has good calculation accuracy and can be used for the thrust and torque calculation of turbo rocket propellant and the thrust calculation of some reverse thrust engines.