ERROR ANALYSIS OF KEPLERIAN TRAJECTORIES,
Abstract
When designing a satellite vehicle it is usually necessary to be able to predict the behavior of the vehicle in the face of minor deviations in the dynamic and kinematic parameters. The prime reasons for this are: (a) to determine whether or not the possible changes in the course of the vehicle will hamper its usefulness for the intended mission, and (b) to determine which are the most critical parameters and thereby endeavor to design the vehicle system so that its dependency upon these parameters is reduced. For the sake of completeness, and also to avoid misinterpretations, some space has been allotted in this report to the outline of some of the fundamental equations describing satellite orbits. Since only the vehicle's characteristics from the end of its powered flight to the point where it begins to trace its undisturbed orbit are considered, the method of launching is immaterial to the discussion. In all cases, the results presented herein apply only to a twodimensional trajectory. Hence, a great deal of care should be exercised in extrapolating these results to the threedimensional case. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 15, 1959
- Accession Number
- AD0606822
Entities
People
- E. C. Levy
Organizations
- TRW Inc.