Flight state boundary calculation of post-stall maneuver for aircrafts

In order to guarantee the flight safety of aircraft during the post-stall maneuver, different flight state boundaries are calculated by using numerical calculation technique under the condition of high dynamic pressure and low dynamic pressure, respectively. Under the high dynamic pressure, the angle of attack boundary is calculated for the pitching maneuver on the basis of the limit load factor value. For the condition of low dynamic pressure, the boundary of the velocity-vector roll maneuver related to angle of attack and roll rate is obtained by introducing the concept of attainable equilibrium set for the aircraft. Then, the angle of attack boundary over the whole speed range is obtained through integration of the boundaries under high dynamic pressure and low dynamic pressure. For an aircraft, the angle of attack boundary over the whole speed range is calculated and calculation results are presented to illustrate the effectiveness of the developed flight state boundary calculation method of post-stall maneuver.