Index Approach Law Based Sliding Control for A Hypersonic Aircraft
A universal improved nonlinear longitudinal model of hypersonic developed by Langley lab is adopted. For the I/O linearizing model, a sliding mode controller is designed. This method can solve the uncertainty problem and insensitive to disturbance of outside. The index approach law used to drive the sliding mode to reach the sliding surface is adopted to eliminate the quiver. The simulation for tracking the height step and velocity step order at cruise condition show that the sliding mode controller with index approach law acquires satisfying tracking ability and strong robustness. The controller can not only track the single height step order or velocity step order accurately, but track the height step order and velocity step order together fleetly with zero error. In addition, the sliding controller with index law is better than the one with sign function in track speed and precision. Another result is also proved that the index approach law can eliminate the quiver perfectly.
Li Hui-feng Sun Wen-chong Li Zhao-ying
Beijng university of aeronautics and astronautics Institute Road No.37,Haidian District,Beijing
国际会议
深圳
英文
862-866
2008-12-10（万方平台首次上网日期，不代表论文的发表时间）