Evaluation of Aircraft Model Upset Behaviour Using Wind Tunnel Manoeuvre Rig

This paper discusses the development of a novel multi-degree-of-freedom dynamic manoeuvre rig aimed at investigation of aircraft upset/LOC-related behaviour in the wind tunnel. The motivation behind the development and characteristics of the rig are first described, along with example behaviour of an aircraft model exhibiting nonlinear time-dependent aerodynamics in an open-jet low-speed wind tunnel. Test objectives for assessment of upset onset scenarios - both for parameter estimation purposes and to 'physiccally simulate' the behaviour - are then described, as is the design of the upgraded instrumentation system to facilitate experimental investigation. Finally, examples of relevant behaviour involving real-time control of the rig to explore nonlinear conditions leading to upset are presented; these are evaluated in terms of prospects for such testing in aircraft development and analysis projects.