An entry trajectory design methodology for lunar return

Zachary R. Putnam, Gregg H. Barton, Matthew D. Neave

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

A methodology for exploring the design space for lunar return entry trajectories and vehicle design is proposed, using the Orion Crew Exploration Vehicle as an example. This methodology simplifies the vehicle and trajectory design space by focusing on two entry parameters: flight-path angle at entry interface and hypersonic lift-to-drag ratio. Flight-path angle is a governing trajectory design parameter, while lift-to-drag ratio captures entry vehicle performance. Landed accuracy, aeroheating, deceleration, other entry constraints are addressed within the design space. Several entry trajectory scenarios are examined, consistent with the current Orion concept of operations. Analysis and evaluation of parameters is accomplished through high-fidelity six-degree-of-freedom simulation using NASA's ANTATRES simulation. Monte Carlo analysis indicates that the proposed methodology provides a valid means of designing entry trajectories to maximize performance margin while satisfying constraints for a given vehicle capability. Additionally, results indicate that, while performance margin decreases with increasing entry range and lower lift-to-drag ratios, adequate performance margin exists for the Orion Crew Module for the current lunar return concept of operations and vehicle design.

Original languageEnglish (US)
Title of host publicationAIAA Guidance, Navigation, and Control Conference and Exhibit
StatePublished - Dec 1 2009
Externally publishedYes
EventAIAA Guidance, Navigation, and Control Conference and Exhibit - Chicago, IL, United States
Duration: Aug 10 2009Aug 13 2009

Publication series

NameAIAA Guidance, Navigation, and Control Conference and Exhibit

Other

OtherAIAA Guidance, Navigation, and Control Conference and Exhibit
CountryUnited States
CityChicago, IL
Period8/10/098/13/09

Fingerprint

Trajectories
Drag
Flight paths
Vehicle performance
Hypersonic aerodynamics
Deceleration
NASA

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

Cite this

Putnam, Z. R., Barton, G. H., & Neave, M. D. (2009). An entry trajectory design methodology for lunar return. In AIAA Guidance, Navigation, and Control Conference and Exhibit [2009-5773] (AIAA Guidance, Navigation, and Control Conference and Exhibit).

An entry trajectory design methodology for lunar return. / Putnam, Zachary R.; Barton, Gregg H.; Neave, Matthew D.

AIAA Guidance, Navigation, and Control Conference and Exhibit. 2009. 2009-5773 (AIAA Guidance, Navigation, and Control Conference and Exhibit).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Putnam, ZR, Barton, GH & Neave, MD 2009, An entry trajectory design methodology for lunar return. in AIAA Guidance, Navigation, and Control Conference and Exhibit., 2009-5773, AIAA Guidance, Navigation, and Control Conference and Exhibit, AIAA Guidance, Navigation, and Control Conference and Exhibit, Chicago, IL, United States, 8/10/09.
Putnam ZR, Barton GH, Neave MD. An entry trajectory design methodology for lunar return. In AIAA Guidance, Navigation, and Control Conference and Exhibit. 2009. 2009-5773. (AIAA Guidance, Navigation, and Control Conference and Exhibit).
Putnam, Zachary R. ; Barton, Gregg H. ; Neave, Matthew D. / An entry trajectory design methodology for lunar return. AIAA Guidance, Navigation, and Control Conference and Exhibit. 2009. (AIAA Guidance, Navigation, and Control Conference and Exhibit).
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