惯性测量装置火箭橇试验过载曲线设计方法

在3 km火箭撬轨道的试验背景下,提出了一种适合惯性测量装置火箭撬试验的过载曲线设计方法。首先对火箭撬运动过程中的主要受力进行了受力分析,在此基础上将火箭撬运动分为三段,包括主动段、自由滑动段和水刹车段,并建立了火箭撬基本运动方程。为确保过载曲线设计方法的精度,进行了仿真误差分析,修正了火箭发动机熄火时间和空气阻力系数,保证了过载曲线设计方法的合理正确。最后对此曲线设计方法又进行了一次验证试验,模型修正后速度仿真结果与实测速度结果基本重合,最大误差也不超过3 m/s,从而验证了提出的火箭撬试验过载曲线设计方法的正确性。本文的研究对惯性测量装置开展精度验证和误差系数的分离奠定了良好的基础。

Designing method of sled overload based on SIMU rocket sled testing

Based on the 3 km sled track,a method for designing sled test overload curve is put forward.After analyzing the main forces on the sled,the whole movement process is divided into three parts: rocket thrust part,free sliding part and water braking part.To guarantee the exactness of the overload curve,the simulation error analysis is made,and two coefficients,i.e.rocket engine stalling time and air resistance coefficient,are corrected.At last a validation test is made to verify this method.The results are essentially coincident with that of the real test for velocity,and the maximum error is less than 3 m/s,therefore the result validates the correctness of the method.