Integrated design method for gliding section guidance and attitude control of hypersonic aircraft

The invention discloses an integrated design method for gliding section guidance and attitude control of a hypersonic aircraft. The method comprises the steps of taking the geocentric distance of thecurrent moving target and the latitude and longitude of the moving target as the input of a gliding section guidance and attitude control integrated model of the hypersonic aircraft; and generating acontrol rudder deflection angle according to a control scheme of the gliding section guidance and attitude control integrated control model of the hypersonic aircraft, inputting the control rudder deflection angle into a six-degree-of-freedom motion model of the hypersonic aircraft, and enabling the hypersonic aircraft to fly to a motion target to complete a flight task. According to the method, acontrol scheme of a hypersonic aircraft gliding section guidance and attitude control integrated model is designed based on a block dynamic surface method; according to the method, the attitude control task requirement of the