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主要针对惯性制导火箭橇试验中惯性测量装置力学环境要求严格的难题,提出采用斜劈面外形控制和发动机斜置的方式对火箭橇系统进行减振处理,对减振平台施加柔性预紧力的方式进行隔振处理,有效控制惯性测量装置在火箭橇运行过程中所处的加速度环境。通过模拟仿真与试验验证,该方法有效地将惯性制导段切向加速度控制在3g以下,竖向加速度控制在4g以下,大幅度减小试验过程中切向和竖向振动值。为以后惯性制导火箭橇试验力学环境控制提供重要支撑。
In order to solve the problem of rigorous mechanical environment of inertial measurement device in the inertial guidance rocket sledge test, a method of reducing the vibration of the rocket sled system by means of wedge surface shape control and engine skew is proposed. The method of applying flexible pre-tightening force to the damping platform Vibration isolation processing, effective control of the inertial measurement device in the rocket run in the acceleration of the environment. Through simulation and experimental verification, this method effectively controls the tangential acceleration of the inertial guidance section below 3g and the vertical acceleration below 4g, which greatly reduces the tangential and vertical vibration values during the test. It will provide important support for inertial guidance rocket test mechanical environment control.