Aircraft stress simulation method used in flight stall state

Abstract

The invention discloses an aircraft stress simulation method used in a flight stall state, which comprises the following steps: S1, establishing an aircraft body coordinate system and a ground inertial coordinate system, and obtaining an aircraft airspeed, an aircraft acceleration, an attitude rotation matrix and a rotation angular speed; S2, calculating to obtain an attack angle and a sideslip angle of the aircraft and an attack angle change rate of the attack angle along with time according to the aircraft airspeed, the aircraft acceleration, the attitude rotation matrix and the rotation angle speed; S3, according to the attack angle and the attack angle change rate, calculating an airflow separation identifier based on the airflow separation hysteresis characteristic of the wing; S4, calculating a corrected lift coefficient and a corrected resistance coefficient according to the airflow separation identifier so as to correct the aerodynamic parameters of the aircraft; and S5, calculating a corrected aerodynamic moment coefficient according to the airflow separation identifier so as to correct the aerodynamic moment parameter of the aircraft. The method has the technical characteristics that the deep tail spin flight characteristic is simulated and displayed, and the simulation result is vivid.

Description

technical field [0001] The invention belongs to the technical field of aircraft simulation, in particular to an aircraft force simulation method used in a flight stall state. Background technique [0002] When the lift force generated by the aircraft moving forward is less than the gravity suffered by the aircraft, the aircraft will fall or crash, that is, the angle of attack of the aircraft is greater than the critical angle, and the aircraft stalls at a high angle of attack. [0003] The following technical problems exist in the existing aircraft simulation technology: the changes in the longitudinal and transverse aerodynamic derivatives of the simulated aircraft at high angles of attack cannot be fully calculated, and the results are mostly given for the local wings of the aircraft; The change of the aerodynamic force and moment of the aircraft at high angles of attack is mostly used in control calculations and experimental analysis, and there is no special calculation m...

AI Technical Summary

Problems solved by technology

[0003]The following technical problems exist in the existing aircraft simulation technology: the changes of the longitudinal and transverse aerodynamic derivatives of the simulated aircraft at high angles of attack cannot be fully calculated, Most of the results are given for the local wings of the aircraft; secondly, the analysis of the changes in the aerodynamic force and moment of the aircraft at high angles of attack is mostly used for control calculations and experimental analysis, and there is no special calculation method for flight simulation; for the delay of aircraft stalling at high angles of attack Back characteristics, the existing technology cannot be simulated in flight simulation, so that the aircraft cannot show the post-stall flight characteristics of deep spin

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