Hypersonic reentry trajectory optimization by using improved sparrow search algorithm and control parametrization method

2021 ◽  
Author(s):  
XU Hui ◽  
CAI Guangbin ◽  
ZHANG Shengxiu ◽  
YANG Xiaogang ◽  
HOU Mingzhe
Keyword(s):  
Trajectory Optimization ◽  
Search Algorithm ◽  
Control Parametrization ◽  
Parametrization Method ◽  
Reentry Trajectory ◽  
Reentry Trajectory Optimization ◽  
And Control

Reentry Trajectory Optimization of Airbreathing Hypersonic Vehicles Based on Gauss Pseudospectral Method

2011 ◽  
Vol 383-390 ◽  
pp. 7375-7380 ◽  
Author(s):  
Bo Yang ◽  
Shang Sun
Keyword(s):  
Trajectory Optimization ◽  
Optimization Problems ◽  
Kinetic Equations ◽  
Pseudospectral Method ◽  
Hypersonic Vehicles ◽  
Gauss Pseudospectral Method ◽  
Suboptimal Solution ◽  
Reentry Trajectory ◽  
Reentry Trajectory Optimization ◽  
And Control

According to the nonlinear, multivariable and multi-constraint features of the reentry trajectory optimization problem of airbreathing hypersonic vehicles, a suboptimal solution method is developed. The reentry trajectory generation is converted to a nonlinear programming (NLP) problem by using Gauss pseudospectral method (GPM). The state and control variables on Gauss nodes are chosen as parameters to be optimized and the minimum total heat absorption is chosen as the optimal performance index. Then the sequential quadratic programming (SQP) method is used to solve the NLP problem. The states of optimized trajectory are compared with the states obtained by the integral of kinetic equations. By simulating on an example of airbreathing hypersonic vehicles, it is demonstrated that the above method is not sensitive to the estimate of motion states and is easier to converge. And the method is effective to solve trajectory optimization problems.

Coupled Shape and Reentry Trajectory Optimization of Entry Vehicle for Lunar Return

2012 ◽  
Vol 591-593 ◽  
pp. 2624-2627
Author(s):  
Xu Zhong Wu ◽  
Sheng Jing Tang ◽  
Jie Guo
Keyword(s):  
Trajectory Optimization ◽  
Body Shape ◽  
Optimization Problem ◽  
Population Based ◽  
Impact Theory ◽  
Peak Heat Flux ◽  
Reentry Trajectory ◽  
Reentry Trajectory Optimization ◽  
Semi Empirical ◽  
Pareto Frontiers

This paper deals with the reentry trajectory optimization problem for lunar return with consideration of entry vehicle’s fore-body shape. Three performance objectives are applied in this work: cross range, peak heat flux and total heat load. Aerothermodynamic models are based on modified Newtonian impact theory and semi-empirical correlations for convective and radiative stagnation-point heat transfer. A population based evolutionary algorithm has been executed to optimize the multidisciplinary problem. At last the numerical example showed the Pareto frontiers for spherical segment and sphere cone respectively, one of optimal trajectory designs selected from the Pareto frontiers are showed in this paper. The mission requirements are satisfied through the aerothermodynamic balance.

scholarly journals Reentry Trajectory Optimization using Gradient Free Algorithms

2018 ◽  
Vol 51 (1) ◽  
pp. 650-655 ◽  
Author(s):  
G. Naresh Kumar ◽  
Md Shafeeq Ahmed ◽  
A.K. Sarkar ◽  
S.E. Talole
Keyword(s):  
Trajectory Optimization ◽  
Reentry Trajectory ◽  
Reentry Trajectory Optimization

A Novel Migrant PSO Algorithm for Vehicle Reentry Trajectory Optimization

2012 ◽  
Vol 9 (2) ◽  
pp. 276-285 ◽  
Author(s):  
Fu-Qiang Xie ◽  
Yong-Ji Wang ◽  
Cheng-Yu Hu ◽  
Zong-Zhun Zheng ◽  
Quan-Min Zhu
Keyword(s):  
Trajectory Optimization ◽  
Pso Algorithm ◽  
Reentry Trajectory ◽  
Reentry Trajectory Optimization

Reentry Trajectory Optimization Based on Time-Domain Improved Particle Swarm Optimization

2015 ◽  
Vol 734 ◽  
pp. 482-486
Author(s):  
Bo Yang ◽  
Hai Xiao Wang
Keyword(s):  
Time Domain ◽  
Trajectory Optimization ◽  
Pso Algorithm ◽  
Basis Functions ◽  
Final Time ◽  
Swarm Optimization ◽  
Reentry Vehicle ◽  
Time Optimal ◽  
Reentry Trajectory ◽  
Reentry Trajectory Optimization

A new time-domain improved PSO algorithm is proposed to solve the problem of reentry trajectory optimization. The approach uses time-domain basis functions fitting the control variables, solves free final time optimal control directly, and sets parameters by using vehicle's dynamic characteristics. Simulation of a reentry vehicle with no-fly zone constraints is used to demonstrate the effectiveness and veracity of algorithm in reentry trajectory optimization. The final condition error is less than 1%.

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