Reentry Trajectory Optimization for Hypersonic Glide Vehicle with Flexible Initial Conditions

Dong, Chunyun; Cai, Yuanli

doi:10.1061/(asce)as.1943-5525.0000727

Cited by 13 publications

(8 citation statements)

References 40 publications

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“…In this section, a typical robust trajectory optimization problem of HGV is introduced, and the reference aircraft is chosen as the CAV-H which has been widely used in the research of hypersonic vehicles [9,36].…”

Section: The Robust Trajectory Optimization Problem Of Hgvmentioning

confidence: 99%

“…erefore, it is assumed that the variation in C L and C D is a kind of uncertainty that can be represented by a single random variable [14,26]. Otherwise, for the hypersonic vehicle, it is always not easy to achieve the designed reentry point accurately [36]. As a result, random deviations are also unavoidable at the beginning of the reentry process, i.e., the uncertain initial conditions.…”

Section: The Robust Trajectory Optimization Problem Of Hgvmentioning

confidence: 99%

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Robust Trajectory Planning for Hypersonic Glide Vehicle with Parametric Uncertainties

Dong

Guo

Chen

2021

Mathematical Problems in Engineering

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A hybrid double-loop optimization algorithm combing particle swarm optimization (PSO) and nonintrusive polynomial chaos (NIPC) is proposed for solving the robust trajectory optimization of hypersonic glide vehicle (HGV) under uncertainties. In the outer loop, the PSO method searches globally for the robust optimal control law according to a penalized fitness function that contains the system robustness considerations. In the inner loop, uncertainty propagation of the stochastic system is performed using the NIPC method, to provide statistical moments for the iterative scheme of the PSO method in the outer loop. Only control variables are discretized, and the state constraints are satisfied implicitly through the numerical integration process, which reduces the number of decision variables as well as the huge amount of computation increased by NIPC. In the end, the robust optimal control law is achieved conveniently. Numerical simulations are carried out considering a classical time-optimal trajectory optimization problem of HGV with uncertainties in both initial states and aerodynamic coefficients. The results demonstrate the feasibility and effectiveness of the proposed method.

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Section: The Robust Trajectory Optimization Problem Of Hgvmentioning

confidence: 99%

Section: The Robust Trajectory Optimization Problem Of Hgvmentioning

confidence: 99%

Robust Trajectory Planning for Hypersonic Glide Vehicle with Parametric Uncertainties

Dong

Guo

Chen

2021

Mathematical Problems in Engineering

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“…A recent review [18] on optimization techniques in spacecraft flight trajectory design also showed the effectiveness of pseudo-spectral method. In [19], a Chebyshev pseudo-spectral method (CPM) was introduced and reentry trajectory optimization for hypersonic glide vehicle with flexible initial conditions was also addressed. Among the pseudo-spectral methods, GPM has been proved to be able to maintain relative faster convergence and more accurate solutions during the optimization process.…”

Section: Introductionmentioning

confidence: 99%

Efficient Trajectory Planning for UAVs Using Hierarchical Optimization

Shao

Zhao

et al. 2021

IEEE Access

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Automatic generation of feasible trajectory is one of the key technologies for autonomous flying of unmanned aerial vehicles (UAVs). The existing path planning methods, such as swarm intelligence algorithm and graph-based algorithm, cannot incorporate the flying time and UAV dynamic model into evolution. To overcome such disadvantages, a hierarchical trajectory optimization scheme consisted by improved particle swarm optimization (PSO) and Gauss pseudo-spectral method (GPM) is investigated in this paper. Firstly, considering that traditional GPM is sensitive to initial values, we design an improved PSO for path planning in the first layer. By introducing adaptive parameter adjustment strategy and position mutation updating strategy, the rapidity and optimality of the improved PSO is enhanced. Then in the second layer, a fitted curve based on the path waypoints generated by improved PSO is constructed and served as the initial values for GPM. Comparing with random initial values, the designed curve can significant improve GPM efficiency. A multi-segment strategy is also put forward to further improve the efficiency. Finally, with the consideration of dynamic model and state constraints, the time minimum trajectory planning for quadrotor UAVs is solved. Plenty of simulations are carried out and the results illustrate that the proposed scheme guarantees much better efficiency.

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“…Thus, the past two decades have seen a wide array of research into constrained entry trajectory optimization and guidance for high-speed glide vehicles (for instance, Refs. [2][3][4][5][6][7][8][9][10][11][12][13][14]). The introduction of Ref.…”

Section: Introductionmentioning

confidence: 99%

Rapid Ascent-Entry Vehicle Mission Optimization Using hp-Adaptive Gaussian Quadrature Collocation

Miller

Rao

2017

AIAA Atmospheric Flight Mechanics Conference

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The performance optimization for a combined ascent-entry mission subject to constraints on heating rate and heating load is studied. The ascent vehicle is modeled as a three-stage rocket that places the vehicle onto a suborbital exo-atmopheric trajectory after which the vehicle undergoes an unpowered entry and descent to a vertically downward terminal condition. The entry vehicle is modeled as a high lift-to-drag ratio vehicle that is capable of withstanding high levels of thermal and structural loads. A performance index is designed to improve control margin while attenuating phugoid oscillations during atmospheric entry. Furthermore, a mission corresponding to a prototype launch and target point is used in this study. The trajectory optimization problem is formulated as a multiple-phase optimal control problem, and the optimal control problem is solved using an adaptive Gaussian quadrature collocation method. A key aspect of the optimized trajectories is that, for particular ranges of maximum allowable heating rate and heating load during entry, relatively small adjustments made during ascent can potentially decrease the control effort required during atmospheric entry. Outside of these ranges for maximum allowable heating rate and heating load, however, it is found that the required control effort increases and eventually saturates the commanded angle of attack upon initial descent. The key features of the optimized trajectories and controls are identified, and the approach developed in this paper provides a systematic method for end-to-end ascent-entry trajectory optimization.

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Reentry Trajectory Optimization for Hypersonic Glide Vehicle with Flexible Initial Conditions

Cited by 13 publications

References 40 publications

Robust Trajectory Planning for Hypersonic Glide Vehicle with Parametric Uncertainties

Robust Trajectory Planning for Hypersonic Glide Vehicle with Parametric Uncertainties

Efficient Trajectory Planning for UAVs Using Hierarchical Optimization

Rapid Ascent-Entry Vehicle Mission Optimization Using hp-Adaptive Gaussian Quadrature Collocation

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