Abstract
Symmetrical aerospace configuration design has greatly increased currently. Compare with conventional aerospace vehicles, those aerospace vehicles’ aerodynamic forces have the characteristics of strong unsteady, nonlinear and longitudinal/directional/lateral coupling. To study those characteristics, accurate prediction and accurate measurement the dynamic stability derivatives of the vehicles is strongly needed. One important tool is dynamic derivative wind tunnel test. With these issues in method, the difficulties of dynamic derivative wind tunnel test in hypersonic wind tunnel will be solved, and a forced oscillation test rig for measure dynamic derivative of hypersonic vehicle will be built here. The test rig has been completed with a symmetrical hypersonic aerospace model under Mach number 5.0 to 8.0, and the direct dynamic derivative and coupling dynamic derivative has been obtained. The test result shows that: comparing the direct dynamic derivative results of forced oscillation test with free oscillation test, the relative deviation is less than 10%. The new test technique can meet the requirement of the dynamic derivative test of hypersonic vehicles.
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Liu, J., Song, Y., Hu, J. (2019). Investigation on Dynamic Derivative Test Technique in Hypersonic Wind Tunnel. In: Zhang, X. (eds) The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018). APISAT 2018. Lecture Notes in Electrical Engineering, vol 459. Springer, Singapore. https://doi.org/10.1007/978-981-13-3305-7_69
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DOI: https://doi.org/10.1007/978-981-13-3305-7_69
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