运载火箭振型斜率测量系统研制

结构动力学分析是运载火箭研制必不可少的环节，动力学分析的基础是建立一个准确的数学分析模型，这个数学模型需要通过一些试验测量获取的动特性参数来充分验证。运载火箭的振型斜率是运载火箭稳定控制系统设计的重要参数，该参数受舱段结构局部变形影响较大，无法通过数学仿真计算得到。因此，新型运载火箭必须进行全箭模态试验以获取振型斜率参数。通过全箭模态试验，完成了通过速率陀螺+加速度计直接测量的方式获取箭体结构振型斜率值。同时，根据不同频率下的模态试验，给出了速率陀螺标度因数在不同频率下的修正因子。试验结果表明，本测量方法有效提高了振型斜率的测量精度。

Development of Launch Vehicle Vibration Slope Measurement System

Structural dynamics analysis is an indispensable link in launch vehicle development. The basis of dynamic analysis is to establish an accurate mathematical analysis model. It needs to be fully verified by an experiment measurement of the parameter characteristics. The vibration slope of the launch vehicle is an important parameter of its stability control system. This parameter is greatly affected by the partial deformation of the cabin structure, and it can''t be calculated by mathematical simulation. Therefore, the new launch vehicle must carry out the whole modal experiment to obtain the vibration slope parameters. Through the whole modal experiment, the slope value of arrowhead structure is obtained by direct measurement of the speed gyroscope and accelerometer. According to the modal experiments at different frequencies, the correction factors of rate gyroscope scale factor at different frequencies are given. The experiment results show that this method can effectively improve the measurement accuracy of vibration slope.