用内式六分量应变天平实测导弹挂飞载荷

 本文研究了导弹挂飞载荷的飞行实测技术。研制了两套由导弹模拟壳体和内式六分量应变天平组成的测力系统，在进行多项飞行环境适应性、安全性、测试功能性地面试验后，将其左右对称安装在载机截尖三角形翼下，在国内首次对三挂点、大长细比导弹的挂飞载荷进行了飞行实测，试验结果可信可靠。采用与实弹相同的挂装连接方式模拟壳体气动外形和几何尺寸，采用框式双天平一体结构、集中传力、天平校心与测力系统质心重合以及测力系统整体校准等，实现对导弹质心处航向、侧向和法向3个方向上力和力矩的直接测量，测量不确定度小于5%。为导弹挂飞载荷的安全、精准实测提供了一种重要技术途径。

Measuring Missile's Suspension Flight Loads Using Built-in Six-component Strain-gage Balance

This article reports a study of the flight measurement technology of a missile’s suspension flight loads. Two sets of dynamometric systems are developed which consist of a simulated missile shell and a built-in six-component strain-gage balance. Suspension flight load measurements of the missile with three suspension points and high-fineness ratio are conducted for the first time in China, and the test results are reliable and valid. The tests are performed by the dynamometric systems installed symmetrically and laterally under the clipped delta wing of an aircraft after numerous ground tests on flight circumstance adaptability, security and functionality. Direct measuring of three direction forces and moments on the center of the missile mass is realized, and measurement uncertainty is less than five percent, which is guaranteed by using the same suspension joint, the same simulant shell aerodynamic configuration and geometrical size as the real missile，the integrative structure with frame double balances, concentrated force transfer, the superposition of balance calibration center with the dynamometric system centroid, the dynamometric system calibration as a whole, etc. The test may provide an important technical approach to measuring suspension flight loads of missiles safely and accurately.