Skip to main content
Disciplines
Automotive Business IT + Informatics Construction + Real Estate Electrical Engineering + Electronics Energy + Sustainability Insurance + Risk Finance + Banking Management + Leadership Marketing + Sales Mechanical Engineering + Materials
Events
DE
EN
Books
Journals
Topic Page
Marketing
Start single access now
Access for companies
EXTENDED SEARCH
Log in
Top

2024 | Book

Introduction Read chapter Read first chapter

Trajectory Optimization and Guidance Methods for Mars Entry

Authors: Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng

Publisher: Springer Nature Singapore

Part of: Springer Professional "Wirtschaft+Technik" , Springer Professional "Technik" , Springer Professional "Wirtschaft"

Login to get access
insite
SEARCH

About this book

This book systematically investigates the Mars entry problem from the perspectives of deterministic optimization, uncertainty optimization, and guidance. Began with a detailed review of the robotic missions and human-scaled exploration plans to Mars, theories or concepts of optimal control, uncertainty quantification, robust optimization, model predictive control, sequential convex programming, and computational guidance are subsequently introduced. Correspondingly, this book presents a series of trajectory planning and guidance algorithms to improve the robustness, reliability, and safety of the Mars missions. Because the Mars entry problem is studied using advanced mathematics, including probability theory, optimization theory, and cybernetics, thus the book is primarily designed as a textbook for graduate students in aerospace engineering, aeronautics, and astronautics departments. Engineers and researchers may also use this book as a reference or tutorial to help with the modeling and simulation of the Mars entry problem due to its thorough simulations and analyses.

Table of Contents

Frontmatter

Fundamental Knowledge

Frontmatter
Chapter 1. Introduction
Abstract
This chapter provides an overview of the progress of unmanned and manned landing exploration missions to Mars, along with a summary of the methods associated with Mars entry, descent, and landing guidance.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Chapter 2. Preliminaries
Abstract
This chapter mainly discusses the dynamics of Mars entry and theories related to convex optimization, uncertainty quantification, and robust optimization.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng

Deterministic Optimization

Frontmatter
Chapter 3. Improved Gauss Pseudospectral Method for Mars Entry Trajectory Planning
Abstract
Aiming to improve the desired high efficiency under the initial state uncertainty, this chapter is to develop a hybrid trajectory optimization strategy for Mars entry by using PSO and Gauss Pseudospectral Method (GPM).
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Chapter 4. Improved Sequential Convex Optimization for Mars Entry Trajectory Planning
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Chapter 5. Pseudospectral Model Predictive Convex Programming for Mars Entry Trajectory Planning
Abstract
This chapter develops two approaches to the Mars entry trajectory optimization problem. The pseudospectral model predictive convex programming (PMPCP) method allows for the establishment of a pseudospectral sensitivity relation, which reduces the computational load. And the mapped Chebyshev-Gauss-Lobatto pseudospectral model predictive convex programming (MCGL-MPCP) method introduces Kosloff-Tal-Eaer conformal mapping and barycentric Lagrange interpolation, ensuring both computational efficiency and numerical accuracy.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Chapter 6. Indirect Sequential Convex Programming for Mars Entry Trajectory Planning
Abstract
This chapter proposes indirect sequential convex programming (ISCP) to maximize the Mars entry terminal altitude.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Chapter 7. Mars Entry and Powered Descent Using Collaborative Optimization
Abstract
This chapter employed reinforcement learning and hp-adaptive pseudospectral method to investigate the interplay between entry guidance and powered descent guidance. The study demonstrates how did they integrated working can bring dramatic reduction in propellant consumption of several tons in powered descent phase for a mid-lift high-mass Mars landing mission.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng

Uncertainty Optimization

Frontmatter
Chapter 8. Mars Entry Trajectory Optimization with Desensitized Optimal Control
Abstract
This chapter describes the Mars entry trajectory optimization in presence of uncertainties and control saturation by use of desensitized optimal control (DOC) methodology and Direct Collocation and Nonlinear Programming (DCNLP). The final height and the state sensitivities are simultaneously included into the weighted performance index. Monte Carlo simulations show that the optimization algorithm developed in this paper can effectively reduce the sensitivity of the final state at the end of entry phase with respect to the uncertainties on the initial state variables and the disturbances on the Mars atmospheric density and aerodynamic parameters.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Chapter 9. Uncertainty Quantification for Mars Entry
Abstract
In this chapter, the propagation of high-dimensional uncertainty in Mars atmospheric entry dynamics is investigated. Based on spectral decomposition and random space decomposition, generalized polynomial chaos is modified to efficiently address the uncertainty quantification task. Comparison simulations demonstrate its effectiveness in quantifying the high-dimensional uncertainty propagated along Mars atmospheric entry trajectories, exhibiting a higher level of accuracy than generalized polynomial chaos as well as better computational efficiency than Monte-Carlo simulations.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Chapter 10. Robust Trajectory Optimization for Mars Entry
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng

Robust Optimal Guidance Method

Frontmatter
Chapter 11. Direct Model Reference Adaptive Tracking Guidance for Mars Entry
Abstract
This chapter addresses the Mars atmospheric entry guidance by use of command generator tracker based direct model reference adaptive controller to eliminate the effect of the bounded uncertainties on atmospheric density and aerodynamic coefficients. The proposed strategy is easily implemented on low-cost, low-weight entry vehicle from a practical point of view, because it requires only storing on board a pre-computed set of DMRAC control gains and a reference trajectory. The feasibility and robustness of the guidance algorithm developed in this paper is validated by Monte Carlo simulation and analysis.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Chapter 12. Computational Guidance Method for Mars Entry
Abstract
In this chapter, the pseudospectral discretization and modified objective function with penalty terms are used to develop a new P-QCQP entry tracking guidance algorithm to fundamentally reduce the scale of the problem, improve the computational efficiency, and smoothen the control profile based on the original U-QCQP algorithm. Compared with the existing LQR and ETPC algorithms, the QCQP-based method is less sensitive to the initial state error, atmospheric density perturbation, and aerodynamic coefficient bias because it takes path constraints into account. The results demonstrate the potential of the improved P-QCQP algorithm for real-time onboard applications.
Shuang Li, Xu Liu, Xiu-qiang Jiang, Yu-ming Peng
Backmatter
Metadata
Title
Trajectory Optimization and Guidance Methods for Mars Entry
Authors
Shuang Li
Xu Liu
Xiu-qiang Jiang
Yu-ming Peng
Copyright Year
2024
Publisher
Springer Nature Singapore
Electronic ISBN
978-981-9962-82-2
Print ISBN
978-981-9962-81-5
DOI
https://doi.org/10.1007/978-981-99-6282-2

Premium Partner

    Image Credits