Trajectory Optimization of Hypersonic Vehicle Using Gauss Pseudospectral Method

Rahman, Tawfiqur; Zhang, Hao; Sheng, Yong Zhi; Younis, Ya Min; Zhang, Ke Nan

doi:10.4028/www.scientific.net/amm.110-116.5232

Cited by 10 publications

(5 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…There are many effective methods to solve NLP availability. Among them, sequential quadratic programming (SQP) is widely used because of its maturity (23,24) .…”

Section: The Basic Principle Of Gpmmentioning

confidence: 99%

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Zhang¹,

Sun²,

Cheng³

et al. 2019

Aeronaut. j.

View full text Add to dashboard Cite

The takeoff-mass of a two-stage-to-orbit Rocket-Based Combined Cycle Engine-Rocket (RBCC-RKT) launch vehicle is a crucial factor in its comprehensive performance. This paper optimizes the takeoff-mass together with the trajectory by reformulating it to a nonlinear optimal control problem. The range of the second stage rocket mass is considered as a process constraint. When the scopes of initial and terminal states are specified, the problem can be solved by using the Gauss pseudo-spectral method (GPM). In order to reduce the convergent difficulty caused by using table data, the data in different stages are utilized by employing an integrated interpolation strategy through the optimization. Simulation results show that the mass can be effectively optimized to meet the inertia mass ratio constraint of the first-stage, and the separation of Mach number and altitude can be optimized at the same time.

show abstract

“…There are many effective methods to solve NLP availability. Among them, sequential quadratic programming (SQP) is widely used because of its maturity (23,24) .…”

Section: The Basic Principle Of Gpmmentioning

confidence: 99%

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Zhang¹,

Sun²,

Cheng³

et al. 2019

Aeronaut. j.

View full text Add to dashboard Cite

show abstract

“…Zhang and Chen [ 24 ] introduced an easy GPM for optimizing the reentry trajectory of common aero vehicle (CAV) satisfying all of the path constraints and control authority. Tawfiqur et al [ 25 ] and Xie et al [ 26 ] obtained the flight profile using multiphase implementation of the GPM. Yang and Sun [ 27 ] improved the GPM to solve the problem of minimum total heat and demonstrated that the approach is not sensitive to the initial value.…”

Section: Brief Reviewmentioning

confidence: 99%

Reentry Trajectory Optimization Based on a Multistage Pseudospectral Method

Zhao

Zhou

Jin

2014

The Scientific World Journal

View full text Add to dashboard Cite

Of the many direct numerical methods, the pseudospectral method serves as an effective tool to solve the reentry trajectory optimization for hypersonic vehicles. However, the traditional pseudospectral method is time-consuming due to large number of discretization points. For the purpose of autonomous and adaptive reentry guidance, the research herein presents a multistage trajectory control strategy based on the pseudospectral method, capable of dealing with the unexpected situations in reentry flight. The strategy typically includes two subproblems: the trajectory estimation and trajectory refining. In each processing stage, the proposed method generates a specified range of trajectory with the transition of the flight state. The full glide trajectory consists of several optimal trajectory sequences. The newly focused geographic constraints in actual flight are discussed thereafter. Numerical examples of free-space flight, target transition flight, and threat avoidance flight are used to show the feasible application of multistage pseudospectral method in reentry trajectory optimization.

show abstract

“…In order to solve the optimal control problems, indirect method and direct method have been applied. By indirect method, the ascent trajectory optimization problem is transformed into Hamilton two‐point boundary value problem (TPBVP), which can be solved by finite difference, 17 finite element, 18 or Gauss pseudospectral method 19 . By contrast, indirect method can be applied onboard for ascent trajectory planning of spacecrafts.…”

Section: Introductionmentioning

confidence: 99%

Improved guidance algorithm considering terminal attitude constraints for spacecrafts via optimal control theory

Wei

2020

Optim Control Appl Methods

View full text Add to dashboard Cite

Summary Motivated by new aerospace applications, the condition of minimum‐energy achieving high accuracy of both terminal orbital injection and attitude angle is required for better navigation and observation. The stability of guidance command also needs to be improved considering the control system. In this article, an optimal guidance algorithm with an advanced numerical method of spacecrafts is proposed. In order to ensure the continuity of the attitude angle and its terminal constraints, the thrust vector is treated as the state variable in the optimal control problems, and the rate of attitude angle change is regarded as the control variable. Then the optimal ascent problem of spacecrafts based on a nondimensional dynamical model is derived in detail, including performance index considering energy consumption, optimal conditions, and terminal conditions. To improve the computational efficiency of optimal ascent problems, a numerical method and a solution strategy are proposed. Simulation results show that the terminal attitude angle error of proposed method is much less than that of the traditional guidance method, and the continuity and stability of the guidance command is also better, which demonstrates the high accuracy and strong adaptability of the guidance algorithm developed in this article.

show abstract

Trajectory Optimization of Hypersonic Vehicle Using Gauss Pseudospectral Method

Cited by 10 publications

References 10 publications

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

Reentry Trajectory Optimization Based on a Multistage Pseudospectral Method

Improved guidance algorithm considering terminal attitude constraints for spacecrafts via optimal control theory

Contact Info

Product

Resources

About