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Simple computations for near-optimum ascent and abort maneuver targets and deorbit ignition time
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | McHenry, R. L. |
| Copyright Year | 1980 |
| Description | Closed-form solutions are presented for a two-burn orbit insertion, AOA, and ATO maneuver targets, and for time of ignition of a one-burn deorbit. Based on the assumption that the orbits involved deviate only to the first order about a reference circular orbit, these solutions are nearly fuel-minimum. They are expressed in terms of linear terminal velocity constraint shuttle guidance targets and, thus, are readily applicable to both ground and onboard software use. In addition to potential application to real-time targeting, the equations may be used as a mission design aid in preliminary definition of target loads and definition of abort mode boundaries. |
| File Size | 631469 |
| Page Count | 24 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800006926 |
| Archival Resource Key | ark:/13960/t5n922c34 |
| Language | English |
| Publisher Date | 1980-01-01 |
| Access Restriction | Open |
| Subject Keyword | Astronautics (general) Orbitals Terminal Velocity Space Shuttles Transfer Orbits Optimal Control Ignition Mission Planning Space Flight Abort Trajectories Orbital Maneuvers Orbit Perturbation Ascent Trajectories Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
