针对临近空间大气环境微量气动力风洞试验准确测量需求，研制了微量天平测力系统，实现了微量天平的结构设计和静态校准。采用钝锥简单外形进行试验验证，并对三角翼升力体复杂外形做了探索，结果表明：钝锥外形验证试验中，3次试验时天平各载荷单元的气动数据重复性精度均优于4.8%；探索试验中，三角翼升力体外形采用该风洞目前能达到最低密度状态，试验结果表明：该微量测力天平在极限状态下表现较好。在此基础上，利用数值计算方法对上述外形进行模拟，并将模拟结果与试验结果进行对比，表明数值计算得到的钝锥和三角翼升力体的气动力均与微量天平测力结果吻合较好；对于简单钝锥外形，在其试验条件下，钝锥表面压阻远高于摩阻；对于三角翼升力体外形，其试验条件下环境大气更加稀薄，三角翼表面摩阻占比与压阻相当。

Structural design and static calibration were developed for accurate measurement of micro aerodynamic wind tunnel tests in near space atmospheric environments. Then，the simple blunt cone model was used for the micro-aerodynamic force experiment verification，and the complex shape of the triangular lift body was adopted to explore the ability to measure the micro-aerodynamic force in thinner atmospheric environments. The results show that the repeatability accuracy of aerodynamic data of each balance load unit is better than 4.8% in the three times of the blunt cone shape verification test. In the exploration test，the triangular lift body adopts the lowest density state the wind tunnel can currently achieve，and the test results show that the micro-force balance performs well in the limit state. The numerical simulation results，compared with the experimental results，show that the aerodynamic forces of the blunt cone and the delta wing lift body are in good agreement with those measured by microbalance； for the simple blunt cone，the compressive resistance of the blunt surface is significantly higher than the frictional resistance under its test conditions，while the surface friction ratio of the complex delta wing body is equal to the piezoresistive，with much thinner test conditions.