Abstract
Minimum-fuel rendezvous of two power-limited spacecraft is investigated. Both vehicles are active and provide thrust to complete the rendezvous. Total propellant consumption is minimized. Spacecraft propellant constraints are included. Two gravitational field models are investigated: the Hill-Clohessy- Wiltshire linearized field and the inverse-square field. Analytical solutions are obtained for the linearized gravity field. A direct method using direct collocation with nonlinear programming is used for the nonlinear gravity field.
| Original language | English (US) |
|---|---|
| Pages | 246-255 |
| Number of pages | 10 |
| State | Published - Jan 1 1992 |
| Externally published | Yes |
| Event | Astrodynamics Conference, 1992 - Hilton Head Island, United States Duration: Aug 10 1992 → Aug 12 1992 |
Other
| Other | Astrodynamics Conference, 1992 |
|---|---|
| Country | United States |
| City | Hilton Head Island |
| Period | 8/10/92 → 8/12/92 |
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ASJC Scopus subject areas
- Astronomy and Astrophysics
Cite this
Optimal cooperative power-limited rendezvous with propellant constraints. / Coverstone, Victoria; Prussing, J. E.
1992. 246-255 Paper presented at Astrodynamics Conference, 1992, Hilton Head Island, United States.Research output: Contribution to conference › Paper
}
TY - CONF
T1 - Optimal cooperative power-limited rendezvous with propellant constraints
AU - Coverstone, Victoria
AU - Prussing, J. E.
PY - 1992/1/1
Y1 - 1992/1/1
N2 - Minimum-fuel rendezvous of two power-limited spacecraft is investigated. Both vehicles are active and provide thrust to complete the rendezvous. Total propellant consumption is minimized. Spacecraft propellant constraints are included. Two gravitational field models are investigated: the Hill-Clohessy- Wiltshire linearized field and the inverse-square field. Analytical solutions are obtained for the linearized gravity field. A direct method using direct collocation with nonlinear programming is used for the nonlinear gravity field.
AB - Minimum-fuel rendezvous of two power-limited spacecraft is investigated. Both vehicles are active and provide thrust to complete the rendezvous. Total propellant consumption is minimized. Spacecraft propellant constraints are included. Two gravitational field models are investigated: the Hill-Clohessy- Wiltshire linearized field and the inverse-square field. Analytical solutions are obtained for the linearized gravity field. A direct method using direct collocation with nonlinear programming is used for the nonlinear gravity field.
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UR - http://www.scopus.com/inward/citedby.url?scp=85007153097&partnerID=8YFLogxK
M3 - Paper
AN - SCOPUS:85007153097
SP - 246
EP - 255
ER -