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根据火箭橇动态试验非线性和非定常特点,以及火箭橇与轨道的摩擦特性,对某型火箭橇系统进行了动力学分析、建模和流场数值模拟,界定了不同运动状态的动力学特点,得到了系统的气动力特性。研究结果表明:在60~90m/s速度条件下,该型火箭橇阻力系数约为0.58,升力系数约为0.003,气动力主要表现为气动阻力,升力与火箭橇自重相比相对较小,约占自重的0.5%~1.2%。同时结果表明,火箭橇运动速度是影响摩擦因数的主要因素,摩擦因数随运动速度的增大而减小。在数值模拟和试验数据基础上,确定了幂函数形式的摩擦因数计算公式,公式以运动速度为底数,系数为2.554,指数为-0.756。并在多种工况下,对火箭橇运动参数进行预测和验证,与试验数据符合良好。
According to the nonlinear and unsteady characteristics of the rocket sled dynamic test and the frictional characteristics of the rocket sled and the orbit, the dynamics analysis, modeling and flow field numerical simulation of a rocket sled system are carried out to define the dynamic characteristics of different rocket kinematics , Got the aerodynamic characteristics of the system. The results show that the drag coefficient of this type of rocket sled is about 0.58 and the lift coefficient is about 0.003 at the speed of 60 ~ 90m / s. The aerodynamic force is mainly aerodynamic drag, and the lift is relatively small compared with the self-weight of the rocket sled. The weight of 0.5% ~ 1.2%. The results show that the velocity of rocket sled is the main factor affecting the friction coefficient, and the friction coefficient decreases with the increase of velocity. Based on the numerical simulation and experimental data, the formula of friction coefficient in the form of power function is determined. The formula is based on the velocity of movement with a coefficient of 2.554 and an exponent of -0.756. And in a variety of conditions, the rocket sled motion parameters are predicted and verified, which is in good agreement with the experimental data.