本文叙述了测量俯仰阻尼导数的试验装置及其数据处理方程。
The test mechanism for measuring pitching damping derivatives and data reduction equations for obtaining pitching dynamic derivatives have been outlined.
角振幅增大会使返回舱的平均俯仰阻尼增加，马赫数增大使俯仰阻尼降低。
The average effective pitch damping increases with increasing Angle of oscillation amplitude and decreases with increasing Mach number.
重复性实验结果表明，该装置可用在跨超音速风洞中测量飞行器模型的俯仰阻尼导数。
The results obtained in repeated tests show that this test mechanism can be used to measure the pitching damping derivatives for the vehicle models in the transonic and supersonic wind tunnel.
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