| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 480326 | European Journal of Operational Research | 2012 | 6 Pages |
Abstract
⺠Propellant mass is minimized for LEO orbital transfer using successive impulses. ⺠Aerodynamic drag loss and deviation between thrust and velocity are modeled. ⺠An analytical optimal average burn time is found to minimize the propellant mass. ⺠Optimal variable burn time sequence is computed using nonlinear programming.
Keywords
Related Topics
Physical Sciences and Engineering
Computer Science
Computer Science (General)
Authors
M. Fakhri Noushabadi, N. Assadian,