Research on advanced flight control methods based on actuator constraints for elastic model of hypersonic vehicle

Abstract

Powerful actuators are both indispensable and critical components for the flight control system of hypersonic vehicles. More importantly, the performance of actuators has substantial impact on the control ability; therefore, when designing the control system, one needs to fully take into account actuator restraints in order to meet the efficient and precise control demands under complex flight conditions. In this article, the advanced flight control methods concerned with actuator limitations are discussed for hypersonic vehicles. First, the longitudinal model of hypersonic vehicle is established with consideration of the nonlinear coupling dynamics. Second, the actuator constraints with the effect of elastic deformation are introduced to this built model and then the resulting unstable dynamics characteristic and the control limitation conditions are analyzed for hypersonic vehicle. Furthermore, the advanced flight control laws are designed by using the differential geometry principle and the total energy theory. Finally, simulation results verify the feasibility of the proposed methods for hypersonic vehicle.

Sliding mode synchronization of second order chaotic subsystem based on equivalent transfer function method

“…The traditional synchronization [14][15][16][17][18][19] was realized between two chaotic systems with the same dimension, and there is another kind of synchronization which is called reduced order synchronization and is realized between a high order chaotic system and a less order reduced system. The above two synchronization format were widely investigated.…”

“…A lot of engineering object can be simplified as a second-order system with dual control direction, such as complex missile system or aircraft, and even hypersonic aircraft [15][16][17][18][19][20] , its pitch channel model can be simplified as a second order system. And part of the non minimum phase system control is a world wide difficult problem.…”

Adaptive decoupling control of hypersonic vehicle using fuzzy-neural network observer

“…In addition, aerodynamic parameters, environmental parameters and body structure parameters have large uncertainties during the entire flight envelope, so the designed flight control system should have strong robustness against those uncertainties. 3,4 Although the traditional gain-scheduled control approach has been employed extensively on practical projects of flight control, it needs a large amount of calculation and cannot be used to deal with coupling effects since it does not utilize output information from other channels. A controller in Zeng et al 5 has been proposed based on nonlinear dynamic inversion to achieve decoupling of a MIMO system, but the approach can only be applied to the system of which the model is inaccurate.…”

Continuous Recursive Sliding Mode Control for Hypersonic Flight Vehicle with Extended Disturbance Observer

“…According to the input saturation, a large number of research results can be consulted, such as [18][19][20]. While the articles about antiwindup control for HFV are few, only [21] takes into account actuator restraints under complex flight conditions. Aiming at all the above, a continuous recursive sliding mode control (CRSMC) under control constraints is proposed for HFV in this paper, in which a compensation factor is added in CRSMC for actuator restraints.…”