Optimal phase-angle design for the powered-descent phase of lunar lander

Cited 5 time in webofscience Cited 0 time in scopus
  • Hit : 39
  • Download : 0
In the optimal trajectory design problem for the lunar powered-descent phase, the periapsis of the de-orbit burn phase is usually chosen as a starting point or an initial state. The resultant trajectory in these cases shows that the altitude of the lander increases to gain more sufficient time to reduce large initial horizontal velocity. However, the periapsis of the de-orbit burn phase is not the optimal choice. In this study, the optimal initial phase angle can be found by applying the modified trajectory-optimization problem, where the initial state is considered as a free variable. In this problem, any additional assumption and change in hardware compared with the traditional optimal lunar-landing problem are not imposed except for the initial phase angle. Using the proposed numerical approach, we show that the optimal phase angle is not always equivalent to the periapsis, and fuel consumption can be reduced by changing the starting point of the powered descent phase.
Publisher
SAGE PUBLICATIONS LTD
Issue Date
2016-09
Language
English
Article Type
Article
Citation

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING, v.230, no.11, pp.2036 - 2047

ISSN
0954-4100
DOI
10.1177/0954410016632015
URI
http://hdl.handle.net/10203/317522
Appears in Collection
AE-Journal Papers(저널논문)
Files in This Item
There are no files associated with this item.
This item is cited by other documents in WoS
⊙ Detail Information in WoSⓡ Click to see webofscience_button
⊙ Cited 5 items in WoS Click to see citing articles in records_button

qr_code

  • mendeley

    citeulike


rss_1.0 rss_2.0 atom_1.0