吸气式空空导弹FADS系统标定研究

针对自主研发的吸气式空空导弹FADS系统，利用FD-12风洞对其进行了标定研究。分析了风洞标定试验的技术特点，提出一种采用变支杆长度方法避开风洞试验台阶波的标定方案，包括支杆设计、模型加工、安装以及测压管路气密性检测等，在风洞中完成标定试验。试验结果表明:在Ma2.0~3.5范围内，FADS系统的测量误差精度全部达到设计目标，其中静压误差≤490Pa（≤3%）、马赫数误差≤0.1、迎角和侧滑角误差≤0.5°；与首次标定相比，各来流参数测量误差均减小，特别是Ma2状态下，静压最大相对误差由11.5%降低到3.0 %，马赫数最大误差由0.15下降到0.10，迎角最大误差由2.5°降低到0.5°，侧滑角最大误差由1.2°降低到0.5°。研究结果可为FADS系统设计提供技术参考。

Study on calibration of FADS system for air-breathing air-to-air missile

Aiming at the independently developed FADS system of the air-breathing air-to-air missile, the calibration is carried out by FD-12 wind tunnel. The technical characteristics of the wind tunnel calibration test are analyzed. The wind tunnel calibration scheme is proposed to avoid the step shock wave by using the variable length pole, mainly including the pole design, machining and installation of the model and the air tightness detection of the pressure pipe. The second calibration is done in FD-12 wind tunnel.The experimental results show that:in the range of Mach number from 2.0~3.5, the measurement error of FADS system achieves the design goal:the error of the static pressure is less than 490Pa (less than 3%), the error of Ma is less than 0.1, and both errors of the angle of attack and the angle of side slip are less than 0.5°. Compared with the calibration at first time, the errors of the flow parameter measurements are all reduced, especially for the Ma2 status where the maximum relative error of the static pressure decreases from 11.5% to 3.0%, the maximum error of Ma decreases from 0.15 to 0.10, the maximum error of angle of attack decreases from 2.5° to 0.5°, and the maximum error of angle of side slip decreases from 1.2° to 0.5°. The research results can provide technical reference for the design of FADS system.