Global Stability and Control Analysis of Aircraft at High Angles-of-Attack.

摘要: Abstract : High angle-of-attack phenomena have been of interest to aerodynamicists, aircraft designers, pilots and control system analysts ever since the advent modern high performance aircraft. Due concentration inertia along fuselage, jet fighters are highly susceptible poststall departures spin. In spite extensive design effort, still inadvertently enter spins which sometimes result in loss life and/or property. Extensive wind-tunnel testing radio-controlled flight has done over last 20 years gain a better understanding dynamic instabilities at angles-of-attack. A basic problem existed interpreting these data making predictions behavior so as achieve close agreement with test data. Most work on this project involved study second model, F-4. detailed description modeling aircraft, correlation time history runs, analysis utilizing equilibrium bifurcation surfaces, is included report. The spin regimes were found be rather insensitive aerosurface deflections, consistent observed performance. Studies conducted well stall/post-stall/spin entry regime, synthesis approach was initiated, thrust effects analyzed.