Hypersonic Pitching Control Model Development
Nathan Stern, David R Buttsworth, Byrenn Birch, Rishabh Choudhury · 2018
Test of actuated surfaces is currently being performed in a hypersonic wind tunnel for the development of practical control methods for hypersonic vehicles. Hinged flapping plate models with on board electronics for actuation and data-logging were placed into the hypersonic flow and motion of the model was measured through a combination of high-speed camera analysis and on-board inertial measurement electronics. Data from the on-board pitch sensor was then used to actuate a control surface on the rear of the model, for the purpose of controlling the model’s natural flapping motion. Models were fabricated using 3D printed plastics. A custom instrumentation package was developed for the purpose of control, and for the measurement of the time-varying static pressures across the surface of the model. All data was stored on-board for post-run analysis of the model motion and pressures. Amplification and attenuation of the model motion has been demonstrated through actuation of the control surface. Current work is focussed on further improving the speed of actuation of the control surface.