Abstract
The Orion crew module utilizes skip entry to significantly increase entry range capability when returning from the moon. This extended range capability allows the vehicle to achieve accurate landings at various land and coastal water landing sites in close proximity to the continental United States throughout the lunar month. Six-degree-of-freedom computer simulation coupled with Monte Carlo and deterministic analysis techniques were used to evaluate the guided range capability of the Orion crew module over a range of navigation, environment, and vehicle uncertainties. Additionally, the effects of hypersonic lift-to-drag ratio and flight-path angle at entry interface on vehicle entry range capability were evaluated. Results indicate that skip entry trajectories provide a significant increase in entry range capability over that of the direct entry and loft trajectories of the Apollo program. Crossrange capability degrades as vehicle lift-to-drag ratio is decreased, but substantial capability remains for vehicle lift-to-drag ratios lower than the Apollo entry vehicle. Accuracy degrades in both downrange and crossrange with steeper entry interface flight-path angles. However, higher lift-to-drag ratios partially mitigate these effects, allowing greater freedom in selection of entry interface flight-path angles. The ability to perform long-range entries and accurate landings over the range of design lift-to-drag ratios currently under consideration may provide significant benefits in operational complexity and cost to the Orion program. However, these benefits must be balanced with increased mass and entry system complexity.
| Original language | English (US) |
|---|---|
| Title of host publication | 2008 IEEE Aerospace Conference, AC |
| DOIs | |
| State | Published - Aug 19 2008 |
| Externally published | Yes |
| Event | 2008 IEEE Aerospace Conference, AC - Big Sky, MT, United States Duration: Mar 1 2008 → Mar 8 2008 |
Publication series
| Name | IEEE Aerospace Conference Proceedings |
|---|---|
| ISSN (Print) | 1095-323X |
Other
| Other | 2008 IEEE Aerospace Conference, AC |
|---|---|
| Country | United States |
| City | Big Sky, MT |
| Period | 3/1/08 → 3/8/08 |
Fingerprint
ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science
Cite this
Entry range capability analysis of the Orion crew module. / Putnam, Zachary R.; Barton, Gregg H.
2008 IEEE Aerospace Conference, AC. 2008. 4526287 (IEEE Aerospace Conference Proceedings).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Entry range capability analysis of the Orion crew module
AU - Putnam, Zachary R.
AU - Barton, Gregg H.
PY - 2008/8/19
Y1 - 2008/8/19
N2 - The Orion crew module utilizes skip entry to significantly increase entry range capability when returning from the moon. This extended range capability allows the vehicle to achieve accurate landings at various land and coastal water landing sites in close proximity to the continental United States throughout the lunar month. Six-degree-of-freedom computer simulation coupled with Monte Carlo and deterministic analysis techniques were used to evaluate the guided range capability of the Orion crew module over a range of navigation, environment, and vehicle uncertainties. Additionally, the effects of hypersonic lift-to-drag ratio and flight-path angle at entry interface on vehicle entry range capability were evaluated. Results indicate that skip entry trajectories provide a significant increase in entry range capability over that of the direct entry and loft trajectories of the Apollo program. Crossrange capability degrades as vehicle lift-to-drag ratio is decreased, but substantial capability remains for vehicle lift-to-drag ratios lower than the Apollo entry vehicle. Accuracy degrades in both downrange and crossrange with steeper entry interface flight-path angles. However, higher lift-to-drag ratios partially mitigate these effects, allowing greater freedom in selection of entry interface flight-path angles. The ability to perform long-range entries and accurate landings over the range of design lift-to-drag ratios currently under consideration may provide significant benefits in operational complexity and cost to the Orion program. However, these benefits must be balanced with increased mass and entry system complexity.
AB - The Orion crew module utilizes skip entry to significantly increase entry range capability when returning from the moon. This extended range capability allows the vehicle to achieve accurate landings at various land and coastal water landing sites in close proximity to the continental United States throughout the lunar month. Six-degree-of-freedom computer simulation coupled with Monte Carlo and deterministic analysis techniques were used to evaluate the guided range capability of the Orion crew module over a range of navigation, environment, and vehicle uncertainties. Additionally, the effects of hypersonic lift-to-drag ratio and flight-path angle at entry interface on vehicle entry range capability were evaluated. Results indicate that skip entry trajectories provide a significant increase in entry range capability over that of the direct entry and loft trajectories of the Apollo program. Crossrange capability degrades as vehicle lift-to-drag ratio is decreased, but substantial capability remains for vehicle lift-to-drag ratios lower than the Apollo entry vehicle. Accuracy degrades in both downrange and crossrange with steeper entry interface flight-path angles. However, higher lift-to-drag ratios partially mitigate these effects, allowing greater freedom in selection of entry interface flight-path angles. The ability to perform long-range entries and accurate landings over the range of design lift-to-drag ratios currently under consideration may provide significant benefits in operational complexity and cost to the Orion program. However, these benefits must be balanced with increased mass and entry system complexity.
UR - http://www.scopus.com/inward/record.url?scp=49349108591&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=49349108591&partnerID=8YFLogxK
U2 - 10.1109/AERO.2008.4526287
DO - 10.1109/AERO.2008.4526287
M3 - Conference contribution
AN - SCOPUS:49349108591
SN - 1424414881
SN - 9781424414888
T3 - IEEE Aerospace Conference Proceedings
BT - 2008 IEEE Aerospace Conference, AC
ER -