Investigation On Dynamic Derivative Test Technique In Φ1m Hypersonic Wind Tunnel

Dynamic derivatives are the indispensable aerodynamic parameters for flightcontrol system and dynamic characteristic assessment of aircraft, which describesaerodynamic characteristics about the aircraft when received disturbance or gettingmaneuvering. The aerodynamic forces of hypersonic vehicles are sensitive to attitudeand disturbance, and the control system has to adjust within a short time, as a result, toget dynamic derivatives correctly is a major concern. In order to meet the needs ofdevelopment of hypersonic vehicles, an investigation of dynamic derivatives testtechniques has been conducted in1m Hypersonic Wind Tunnel of CARDC, and afree-oscillation and forced-oscillation dynamic derivative testing equipment has beendeveloped. The main works of this paper are listed as below.First, necessity and possibility have been demonstrated by the domestic andforeign references about the aerodynamic derivatives’ research actuality, introducedprinciples of the free free-oscillation and forced-oscillation dynamic derivative test andmethod of data processing.Secondly, to ensure a smooth experiment, debugging of two sets of test devicewas accomplished, and the problems encountered were solved. Calibration offree-oscillation and forced-oscillation balances was conducted on the ground, andcalibration precision of the forced-oscillation balance was improved by reforming thecalibration method.Thirdly, capacities of the equipment were verified by experiments of a set of10-deg sharp cones and OV-102standard model. Results indicate that test data isreasonable and agrees well with that of literature, which means that the device isreliable and could be applied in project testing.Finally, this paper analyzed effect of influence factors on numerical simulationresults of10-deg sharp cone. It shows that both frequency and amplitude influence thedynamic stability results by different level.