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为研究吸气式高超声速飞行器新型测力试验技术的可行性,在马赫数Ma=6、高度H=27km模拟飞行环境下开展了风洞试验。以轴对称吸气式高超声速飞行器无舵翼简化构型为研究对象,通过合理的试验系统设计解决内外流解耦关键技术,采用两个环式六分量天平在同一车次上测量模型内外流气动力载荷。试验结果表明:内外流气动力天平测量数据和全模气动力数据准确反映了内外流解耦、内外流窜流、进气道起动/不起动以及溢流影响等物理现象;从物理上实现了内外流解耦;内流气动力对全机气动性能贡献大;内外流解耦、进气道起动时,气动力数据准确、重复性好;窜流产生的传力属于内力。试验证明,同时测力试验技术可行,为解决内外流气动数据源于不同试验所致的不确定性问题提供了有效手段。
In order to study the feasibility of the new force testing technique of the aspirated hypersonic vehicle, a wind tunnel test was carried out under a simulated flight environment with a Mach number of Ma = 6 and a height of H = 27km. Taking the simplified configuration of the rudderless wing of an axisymmetric aspirated hypersonic vehicle as the research object, a key experimental system was designed to solve the key technology of decoupling the inside and outside the flow. Two circular six-component balances were used to measure the aerodynamic forces inside and outside the model Load. The test results show that the measured data and the full-scale aerodynamic data of the internal and external aerodynamic balance accurately reflect the physical phenomena such as the decoupling of internal and external flows, the channeling of internal and external flows, the start / non-start of inlet ports and the influence of overflow. Decoupling; internal aerodynamic force on the whole aerodynamic performance contribution; internal and external decoupling, inlet start, the aerodynamic data is accurate, good repeatability; channeling flow force generated by the internal force. The test proves that the simultaneous force test technology is feasible and provides an effective method to solve the uncertainty of the aerodynamic data of internal and external flow from different experiments.