Large Angle Of Attack Stall / Spin And Simulation Of Anti-tail Spin Umbrella

Combined with prototype aircraft flight testing, a research and simulation of the following main topics are completed in this dissertation.1.Based upon the aerodynamic data tested and measured by six component static balance, oscillation balance and rotary balance, a high angle of attack (AOA) database is established.2.Under direct link (DL) mode, which belongs to high AOA control law, a numerical simulation of aircraft enter into and recovery from stall/spin is completed.3.The mechanism of anti-spin parachute is analyzed and mathematical model of anti-spin parachute is built. The dynamic behavior of using anti-spin parachute to recover from spin is also simulated.4.Using the simulation results mentioned above, the spin retrieve effects of using different kind of parachute sizes are determined.5.The numerical simulation results are compared with real model free flight test results and the comparison shows that the consistency between the two results is fairy good.