自旋飞行器角速率和过载测量数据拟合修正方法  

Method of Angular Rate and Acceleration A Fitting and Revising Measurement Data for Spinning Vehicle

作　　者：严东升[1] 童伟[1] 唐林卡[1] 贾平会 郭珂[1] Yan Dong-sheng;Tong Wei;Tang Lin-ka;Jia Ping-hui;Guo Ke(Beijing Institute of Space Long March Vehicle, Beijing, 100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术》2017年第5期29-32,48,共5页Missiles and Space Vehicles

摘　　要：为正确分析飞行试验飞行器迎角和气动参数偏差等飞行动力学特性,根据具有非零惯性积旋转飞行器在大气层外的运动规律,推导飞行器角速率和过载分量的解析表达式。利用测量数据拟合估计相应的系数,给出测量数据系统偏差修正解算公式。计算实例表明,经拟合、系统偏差修正和过载质心换算的测量数据更接近实际飞行状况,可用于确定飞行器大气层初始段飞行迎角变化范围和大气层内气动系数辨识等的飞行动力学特性结果分析。试验数据结果分析实例验证了该方法的有效性,研究结果对测量数据处理和误差修正具有现实指导意义。In order to analyze the flight dynamic characteristics of hypersonic vehicles,including angle of attack and aerodynamicparameter error,the analytic expressions for angular rate and acceleration of hypersonic vehicles were deduced base on the motion lawof exoatmospheric vehicle possessing nonzero product of inertia.The corresponding coefficients and deviation correction formulas ofdata measurement system were estimated using the measured data.The proposed method can treat the measured data effectively,andthen the actual flight dynamic characteristics of hypersonic vehicles can be analyzed exactly based on the revised data.Thecomputational result shows that the proposed fitting and revising method is effective and the research results are helpful on dataprocessing and error correction.

关 键 词：数据拟合 偏差修正 自旋飞行器 

分 类 号：V412.5[航空宇航科学与技术—航空宇航推进理论与工程]