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Attitude dynamic of spin-stabilized satellites with flexible appendages
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Renard, M. L. |
| Copyright Year | 1973 |
| Description | Equations of motion and computer programs have been developed for analyzing the motion of a spin-stabilized spacecraft having long, flexible appendages. Stability charts were derived, or can be redrawn with the desired accuracy for any particular set of design parameters. Simulation graphs of variables of interest are readily obtainable on line using program FLEXAT. Finally, applications to actual satellites, such as UK-4 and IMP-1 have been considered. |
| File Size | 4658681 |
| Page Count | 266 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740007404 |
| Archival Resource Key | ark:/13960/t20c9qn6n |
| Language | English |
| Publisher Date | 1973-09-01 |
| Access Restriction | Open |
| Subject Keyword | Space Vehicles Flexible Bodies Computer Programming Satellite Attitude Control Dynamic Stability Spacecraft Stability Equations of Motion Spin Stabilization Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |