Highly constrained optimal gliding guidance

Abstract

A novel highly constrained optimal gliding guidance algorithm, which can satisfy multiple path and terminal constraints in the presence of no-fly zones for hypersonic vehicle, is investigated in this paper. It employs line-of-sight angle to describe the relative location relationship between flight path and no-fly zones, and proposes boundaries selection algorithm for each no-fly zone, which is called avoidance strategy, with minimum energy consumption. The boundaries determined by avoidance strategy divide the flight process and guidance task into several stages. In each stage, it constructs guidance models based on quasi-equilibrium glide condition in longitudinal and lateral directions respectively, and employs optimal control to generate guidance law to satisfy terminal location, altitude, and flight path angle constraints. In addition, all the path constraints, including heating rate, dynamic pressure, and overload, are converted into the angle-of-attack constraint to ensure the guidance mission can be accomplished successfully. This algorithm is independent of standard trajectory, and all the guidance commands, including the bank angle and the angle of attack, can be calculated analytically in real time and adaptively. Finally, the simulation results of CAV-H indicate that the proposed strategy can guide the vehicle to satisfy multiple different constraints with high precision and avoid no-fly zones effectively.

Feasible footprint generation with uncertainty effects

“…Currently, there are two major directions for entry trajectory generation that satisfy various path constraints: based on the standard flight profile [4][5][6][7][8] and the predictor corrector. [9][10][11][12] The trajectory planning method based on standard flight profile aims to design a standard flight profile that satisfies the flight mission demand by parameterization in the entry corridor, which is established by the re-entry path constraints. Common standard flight profiles include the drag acceleration versus velocity profile, the drag acceleration versus energy profile, and the height versus velocity profile.…”

“…9,10 Considering the quasi-equilibrium glide condition (QEGC), Xu et al 11 proposed an adaptive quasi-equilibrium glide guidance method, realizing the direct extraction of the angle of attack and bank. Zhu et al 12 derived a re-entry trajectory realtime planning method based on the optimal control that considers the no-fly zone avoidance.…”

Robust adaptive gliding guidance for hypersonic vehicles

“…7 In this field, Xu takes full advantage of QEGC to predict the terminal states analytically and modify control variables to achieve expected guidance tasks, 7 and we have constructed the optimal guidance model and deduced optimal quasi-equilibrium gliding guidance law with the performance indices of minimum energy consumption in the previous work. 8 The above guidance algorithms work effectively with the accurate model of atmospheric density and aerodynamic coefficient, but the guidance precision will be seriously influenced in the presence of large parametric uncertainties. Consequently, it is necessary to modify the guidance law according to the parametric deviations obtained from on-line identification to improve the robustness.…”

Partial Integrated Guidance and Control Design for Hypersonic Vehicle in Dive Phase

“…The existing literature has done a lot of research on the guidance and control problem, and applied so many theory on it. For example, optimal control [3], sliding mode control [4], backstepping [5] ,dynamic inversion [6], nonlinear control methods, as well as Fuzzy control [7] , predictive control [8] and neural network [9] and other modern control methods. But most of them only focus on one side of the guidance and control problem, this article tries to solve them together.…”