TY - GEN
T1 - Computational guidance for Mars entry and power descent
AU - Jiang, Xiuqiang
AU - Li, Shuang
AU - Furfaro, Roberto
N1 - Funding Information:
This work is supported by the National Natural Science Foundation of China (Grant No. 11672126), the Opening Grant from the Key Laboratory of Space Utilization, Chinese Academy of Sciences (Grant No. LSU-2016-07-01), State Scholarship from China Scholarship Council (Grant No. 201706830055), Postgraduate Research and Practice Innovation Funding of Jiangsu Province (Grant No. KYZZ16_0170), and Funding for Outstanding Doctoral Dissertation in NUAA (Grant No. BCXJ16-10). The authors fully appreciate their financial supports.
Publisher Copyright:
© 2018 Univelt Inc. All rights reserved.
PY - 2018
Y1 - 2018
N2 - Traditional studies on Mars entry, descent, and landing usually take a divide- and-conquer approach where each phase is investigated separately. This paper proposed a new computational approach to generate optimal guidance for mid-lift high-mass Mars entry and powered descent. First, optimal Mars atmospheric entry and optimal powered descent problems are respectively modeled. Second, optimal handover problem is formulated to integrate the Mars entry and powered descent phases in a collaborative optimization manner. Third, optimal guidance for Mars entry and powered descent is produced through online solving energy-optimal entry, propellant-optimal powered descent, and optimal handover problems iteratively. Finally, numerical simulations verified the collaborative work of the proposed computational guidance framework, and the results demonstrated the significant benefit of the optimal integrated guidance.
AB - Traditional studies on Mars entry, descent, and landing usually take a divide- and-conquer approach where each phase is investigated separately. This paper proposed a new computational approach to generate optimal guidance for mid-lift high-mass Mars entry and powered descent. First, optimal Mars atmospheric entry and optimal powered descent problems are respectively modeled. Second, optimal handover problem is formulated to integrate the Mars entry and powered descent phases in a collaborative optimization manner. Third, optimal guidance for Mars entry and powered descent is produced through online solving energy-optimal entry, propellant-optimal powered descent, and optimal handover problems iteratively. Finally, numerical simulations verified the collaborative work of the proposed computational guidance framework, and the results demonstrated the significant benefit of the optimal integrated guidance.
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M3 - Conference contribution
AN - SCOPUS:85069490872
SN - 9780877036579
T3 - Advances in the Astronautical Sciences
SP - 3387
EP - 3402
BT - AAS/AIAA Astrodynamics Specialist Conference, 2018
A2 - Singla, Puneet
A2 - Weisman, Ryan M.
A2 - Marchand, Belinda G.
A2 - Jones, Brandon A.
PB - Univelt Inc.
T2 - AAS/AIAA Astrodynamics Specialist Conference, 2018
Y2 - 19 August 2018 through 23 August 2018
ER -