Optimum trajectories to circular synchronous equatorial orbit for smaller-than-optimum apogee motors

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086 0 ‡aNAS 1.14:D-5998
100 1 ‡aSpurlock, Omer F.
245 1 0 ‡aOptimum trajectories to circular synchronous equatorial orbit for smaller-than-optimum apogee motors / ‡cOmer F. Spurlock and Fred Teren.
246 0 ‡aNASA TN D-5998
260 ‡aWashington, D.C. : ‡bNational Aeronautics and Space Administration: ‡b[For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], ‡c1970.
300 ‡a28 p. : ‡bill.; ‡c27 cm.
490 0 ‡aNASA technical note. ‡vD-5998
520 ‡aAnalysis, procedure, and results are presented for maximizing payload capability for trajectories to circular synchronous equatorial orbit where thea pogee motor total impulse is much smaller than optimum. The trajectories begin at launch and are numerically integrated to insertion into the final orbit. Constraints on parking orbit perigee radius and duration are included. These trajectories, unlike conventional synchronous orbit trajectories, were found to require noncircular parking orbits and large amounts of inclination reduction before the apogee burn. The analysis and procedure were also applied to the conventional circular synchronous equatorial orbit problem where the burn and coast durations are optimum. Results are presented for the Applications Technology Satellite (ATS)-E missiod, which is an example of a problem where the apogee motor is small, and for the conventional case where the apogee motor is of optimum size.
538 ‡aMode of access: Internet.
650 0 ‡aTrajectory.
650 0 ‡aSynchronous orbit.
650 0 ‡aCalculus of variations.
650 0 ‡aOptimum trajectories.
700 1 ‡aTeren, Fred.
710 2 ‡aLewis Research Center.
710 1 ‡aUnited States. ‡bNational Aeronautics and Space Administration.
CID ‡a011444055
DAT 0 ‡a20101109154906.0 ‡b20141009010000.0
DAT 1 ‡a20141112165512.0 ‡b2023-03-14T18:25:50Z
DAT 2 ‡a2023-03-14T17:30:02Z ‡b2019-10-29T20:00:02Z
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