用扭摆测量导弹主惯性参数的方法研究  

Error Analysis for Testing Main Inertia Parameters of Missile Using Torsion Pendulum

作　　者：黄德东[1] 吴斌[1] 张蓓[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《计量学报》2010年第3期234-237,共4页Acta Metrologica Sinica

摘　　要：介绍了用扭摆测量导弹惯性积的方法。通过6个不同的安装位置测量导弹转动惯量，进而计算导弹全部惯性张量、惯性主轴方向和主转动惯量。推导了计算惯性主轴夹角和主转动惯量的解析式，并进行了误差分析。由误差公式，可见该方法仅适用于大长细比试件测量。实例表明，当转动惯量测量误差小于0．5％时，惯性主轴夹角误差小于15’，主转动惯量测量误差小于2％。A method of determining missile＇ s product of inertia using torsion pendulum is introduced . This method can test a series of moment of inertia with the missile oriented in six different positions. If the six different positions are certain（paper mentioned）, six certain inertia tensors have been measured . Then the main parameters of inertia can be calculated. The position of the principle inertia axes and the main movement of inertia for the missile would be shown. And error analysis for the missile＇ s main parameters of inertia is proved,which caused by measurement errors for the six inertia tensors. Error analysis expressions show this method can measure products having large ratio of longitude and latitude. A product is measured using the method mentioned above, and the errors are calculated. The measured and calculated data proves when the error of the measured moment of inertia is less than 0. 5% ,the error for the position of the principle inertia axes is less than 15＇, the error for the main movement of inertia is less than 2%.

关 键 词：计量学 主转动惯量 惯性主轴 扭摆 误差分析 

分 类 号：TB931[一般工业技术—计量学]