To solve the maneuvering control problem

a new adaptive sliding mode control combined with thrust vector is proposed

and a closed-loop optimal control allocation system is built to realize the optimal allocation of aerodynamic rudder and vector nozzle ensuring stable maneuvering flight of the near space vehicle. To cope with the complex uncertainty in the maneuvering flight environment

a new adaptive sliding mode controller is designed to relax the limit of uncertainty boundedness assumption of the typical adaptive sliding mode control

and obtain the expected control torque to ensure the stable tracking of attitude angle. Control allocation is the key to maneuver flight control because there are many control inputs for the near-space vehicle with thrust vector technology. To ensure the stability and safety of maneuvering flight

an optimal closed-loop optimal control distribution system was designed to improve the distribution performance from the perspective of stability. The expected control torque is accurately and stably distributed to actuators

completing the coordinated control of the aerodynamic rudders and the vector nozzles

and achieving the stable tracking of the reference command by the attitude angle during the maneuvering flight. The simulation results verify the effectiveness of thrust vector technology for expanding the range of attitude angles in the horizontal and vertical directions of near space vehicles

and prove that the designed controller can ensure flight attitude stability under the influence of complex uncertainties.