Portal de Periódicos da CAPES

Research on Guidance and Control Law Design of Decelerating Transition and Vertical Landing for a STOVL UAV

2021; IOP Publishing; Volume: 1875; Issue: 1 Linguagem: Inglês

10.1088/1742-6596/1875/1/012008

1742-6596

Zixu Dong, Yang Ren, Kun Chen, Yaohui Chen,

Spacecraft Dynamics and Control

Abstract In this paper, an integrated design method for guidance and control laws for a short takeoff and vertical landing (STOVL) unmanned aerial vehicle (UAV) during decelerating transition and vertical landing phases under thrust vector control is studied. Based on the principle of time-scale separation, the outer-loop guidance law adopts an implicit dynamic inverse method to provide attainable overload vector control instructions for decelerating transition and vertical landing phases. Meanwhile, the inner-loop control law adopts an improved eigen-structure assignment method, which tracks guidance instructions and maintains a stable attitude. The attitude nozzles are joined to the attitude control with the dropping of dynamic pressure, thereby assisting aerodynamic surfaces to stabilize attitudes. Subsequently, the feasibility and effect of the control methods for a STOVL UAV during decelerating transition and vertical landing phases are verified by a 6-DOF flight simulation platform. The simulation results demonstrate that the integrated design method is beneficial for a quick evaluation of the overall scheme.