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 language | English (US) |
|---|---|
| Title of host publication | AIAA Guidance, Navigation, and Control Conference and Exhibit |
| State | Published - Dec 1 2009 |
| Externally published | Yes |
| Event | AIAA Guidance, Navigation, and Control Conference and Exhibit - Chicago, IL, United States Duration: Aug 10 2009 → Aug 13 2009 |
Publication series
| Name | AIAA Guidance, Navigation, and Control Conference and Exhibit |
|---|
Other
| Other | AIAA Guidance, Navigation, and Control Conference and Exhibit |
|---|---|
| Country | United States |
| City | Chicago, IL |
| Period | 8/10/09 → 8/13/09 |
Fingerprint
ASJC Scopus subject areas
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
Cite this
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 proceeding › Conference contribution
}
TY - GEN
T1 - An entry trajectory design methodology for lunar return
AU - Putnam, Zachary R.
AU - Barton, Gregg H.
AU - Neave, Matthew D.
PY - 2009/12/1
Y1 - 2009/12/1
N2 - 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.
AB - 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.
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M3 - Conference contribution
AN - SCOPUS:78049276391
SN - 9781563479786
T3 - AIAA Guidance, Navigation, and Control Conference and Exhibit
BT - AIAA Guidance, Navigation, and Control Conference and Exhibit
ER -