Review and prospect of guidance and control for Mars atmospheric entry

S Li, X Jiang - Progress in Aerospace Sciences, 2014 - Elsevier
The Mars atmospheric entry phase plays a vital role in the whole Mars exploration mission-
cycle. It largely determines the success of the entire Mars mission. In order to achieve a pin …

Barrier Lyapunov function based sliding mode control for Mars atmospheric entry trajectory tracking with input saturation constraint

J Long, S Zhu, P Cui, Z Liang - Aerospace Science and Technology, 2020 - Elsevier
The nature of the bank angle modulation technique based on the low lift-to-drag
aerodynamic configuration of the entry vehicle inevitably introduces the problem of input …

Optimal information filtering for robust aerocapture trajectory generation and guidance

CR Heidrich, MJ Holzinger, RD Braun - Journal of Spacecraft and …, 2022 - arc.aiaa.org
Entry flight is a critical mission phase of planetary aeroassist problems. During atmospheric
flight, aleatory-epistemic uncertainty and environmental factors reduce the accuracy of …

[HTML][HTML] Disturbance observer-based robust guidance for Mars atmospheric entry with input saturation

Y Zheng, H Cui - Chinese Journal of Aeronautics, 2015 - Elsevier
With low-lifting capability taken into account, a robust guidance law for Mars entry vehicles
with low lift-to-drag ratios, such as Mars Science Laboratory (MSL), is presented. Consider …

Terminal altitude maximization for Mars entry considering uncertainties

P Cui, Z Zhao, Z Yu, J Dai - Acta Astronautica, 2018 - Elsevier
Uncertainties present in the Mars atmospheric entry process may cause state deviations
from the nominal designed values, which will lead to unexpected performance degradation if …

Mars atmospheric entry guidance for optimal terminal altitude

J Long, A Gao, P Cui, Y Liu - Acta Astronautica, 2019 - Elsevier
Maximizing the terminal altitude for Mars atmospheric entry has long been investigated on
trajectory design to allow a sufficient timeline margin for subsequent operations and the …

Constrained numerical predictor–corrector guidance for Mars precision landing

Y Zheng, H Cui, Y Ai - Journal of Guidance, Control, and Dynamics, 2017 - arc.aiaa.org
ONE of the state-of-the-art entry technologies considered to significantly improve the
accuracy of Mars landing is the numerical predictor–corrector (NPC) guidance. There are …

Aerothermodynamics and thermal design for on-ground and in-flight testing of a deployable heat shield capsule

A Fedele, R Gardi, G Pezzella - CEAS Space Journal, 2020 - Springer
The article deals with the aerothermodynamic and thermal analysis of two technological
demonstrators suitable for research activities on deployable heatshield entry capsules …

[PDF][PDF] 火星进入减速器技术综述与展望

李爽, 江秀强 - 航空学报, 2015 - researchgate.net
随着火星着陆探测任务的不断推进, 火星采样返回, 载人登火星和火星基地等任务要求能将更大,
更重的探测器着陆到火星表面, 这就需要在火星大气进入阶段进行高效减速 …

Robust trajectory design scheme under uncertainties and perturbations for Mars entry vehicle

H Xu, H Cui - 2015 IEEE International Conference on …, 2015 - ieeexplore.ieee.org
For improving landing accuracy on future Mars missions, robust entry guidance schemes are
required to improve landing accuracy. This paper analyzes the desensitized optimal …