Publication Date:
2019-07-13
Description:
An integrated approach for entry trajectory design, guidance, and simulation is proposed. The key ingredients for this approach are an on-line 3 degree-of-freedom entry trajectory planning algorithm and the entry guidance algorithm that generates the guidance gains automatically. When fully developed, such a tool could enable end-bend entry mission design and simulations in 3DOF and 6DOF mode from de-orbit burn to the TAEM interface and beyond, all in one key stroke. Some preliminary examples of such a capability are presented in this paper that demonstrate the potential of this type of integrated environment.
Keywords:
Spacecraft Design, Testing and Performance
Type:
AIAA Paper 2004-0702
,
42nd AIAA Aerospace Sciences Meeting and Exhibit; Jan 05, 2004 - Jan 08, 2004; Reno, NV; United States
Format:
application/pdf
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