Optimization and Implementation of Periodic Cruise for a Hypersonic Vehicle

Wang

Proceedings of the 33rd Chinese Control Conference

et al. 2014

This paper concentrates on optimization of the steady-state cruise for a hypersonic vehicle.The steady-state cruise is a state with constant altitude and velocity during the flight.The ratio of fuel consumption to the range over a given period of time is defined as the fuel rate,which is the objective of this fuel optimized problem in this work.The optimal steady-state cruise is determined by minimizing the fuel rate with multi-constraints including boundary constraints of states and path constraints.Since this work needs to find the global solution satisfying the nonlinear constraints,we can apply particle swarm optimization(PSO) combined with the sequential quadratic programming(SQP) to find the optimal solution.Thus,this strategy takes the advantage of intelligent optimization algorithms with global search ability and SQP with high precision and handled constraint ability.A demonstration example results show good performance of fuel savings on the nonlinear model of the hypersonic vehicle.

Section: Introductionmentioning

confidence: 73%

Optimization on steady-state cruise for a hypersonic vehicle

Wang

Proceedings of the 33rd Chinese Control Conference

et al. 2014

“…As a result, the engine and airframe become one [36]. In a real application, the periodic flight trajectory can be designed to widen the cruise range and to save the consumed energy [12]. For this reason, an illustrative example is provided for this study in a similar manner to the actual situation for waveriders [37].…”

Section: Illustrative Examplementioning

confidence: 99%

“…Therefore, feasible trajectory generation is critical for the design of guidance and control of waveriders to improve the flight performance and minimize the control power [11]. The periodic cruise can typically save more fuel than the steady-state cruise in the hypersonic flight phase [12]; thus, applying the periodic flight trajectory helps improve the hypersonic flight performance. Nevertheless, tracking such a trajectory is difficult for the guidance and control system while guaranteeing the respected control qualities, such as fast setting time, small overshot, and robustness during the hypersonic flight.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Trajectory Controller with Improved Performances for Waveriders

2019

This paper presents a nonlinear trajectory controller with improved performances for a general model of the waverider based on feedback linearization theory and composite nonlinear feedback (CNF) technique. First, a nonlinear controller is presented using the dynamic inversion and CNF technique for the MIMO Model, and the robust stability of the proposed controller is proved. Then, the nonlinear model is established on the basis of hypersonic aerodynamic principle, and the dynamic characteristics are analyzed accordingly, and the periodic trajectory is designed and optimized in combination with a fuel optimization problem. Furthermore, the nonlinear controller is applied to the trajectory tracking of the waverider model, and the general design steps are provided the flight controller using this nonlinear control method. Finally, an illustrative example is given to verify the effectiveness of the nonlinear controller of the waverider, and the flight performances are improved accordingly, including system stability, robustness, and tracking ability.

“…(2) the sinusoidal signal reflects the periodic motion process of hypersonic vehicle, such trajectory design can decrease stagnation heat load and improve the fuel efficiency. 26…”

Section: Simulation Casementioning

confidence: 99%

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

Proceedings of the Institution of Mechanical Engineers, Part G:

Xiao

2013

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.