圆锥标模高超声速俯仰自由振动试验与分析

为解决自由振动式动导数试验技术在大尺度高超声速风洞中，高气动载荷环境与低频率模拟要求之间的突出矛盾，进一步提高高超声速飞行器较低气动阻尼的测量精度，发展了基于组合式动导数天平的Ф 1 m量级高超声速风洞自由振动试验技术.设计组合式动导数天平，轴承组件承载模型轴向和法向气动力，弹性应变梁提供系统恢复力矩，并可根据减缩频率的要求调整系统自由振动频率，有效提高了天平承载能力，拓展了试验频率模拟范围.在中国空气动力研究与发展中心Ф 1 m高超声速风洞，利用本系统进行了10°半锥角不同钝度圆锥标模俯仰动导数校测试验，所测俯仰动导数与文献结果最大相对误差在6%以内，验证了试验系统和测试结果具有较好的稳定性与重复性. 

Pitching Free-Oscillation Test and Analysis of Hypersonic Standard Cone Model

To solve the contradiction between high aerodynamic loads and low oscillation frequency in big scale wind tunnel, high-accuracy free-oscillation techniques based on combinatory dynamic derivative balance were developed in the 1 meter scale hypersonic wind tunnel. The designed combinatory balance, whose bearing components bear model's aerodynamic force in axial and normal direction, and the flexible beam provides restoring force and adjusts the system's oscillating frequency, improves the test ability and simulation range greatly. The calibration test with 10° half-angle cone standard model was conducted in Ф 1 m hypersonic wind tunnel of CARDC. The maximum relative error of pitching dynamic derivative between the test and the reference is within 6%, which demonstrates the robustness of the provided technique.