Ephemeris of a highly eccentric orbit: Explorer 28 | Zendy

B. E. Lowrey | Zendy

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Ephemeris of a highly eccentric orbit: Explorer 28

Author(s) -

B. E. Lowrey

Publication year - 1972

Publication title -

celestial mechanics

Language(s) - English

Resource type - Journals

eISSN - 2214-7284

pISSN - 0008-8714

DOI - 10.1007/bf01229516

Subject(s) - ephemeris , orbit (dynamics) , geodesy , orbit determination , orbital eccentricity , numerical integration , physics , orbital elements , eccentric , computer science , mathematics , astronomy , planet , mathematical analysis , geology , aerospace engineering , satellite , engineering , quantum mechanics

An ephemeris has been obtained for Explorer 28 (IMP 3) which agrees well with 2 years of radio observations and with SAO observations a year later. This ephemeris is generated over the 3 year lifetime by a numerical integration method utilizing a set of initial conditions, at launch and without requiring further differential correction. Because highly eccentric orbits are difficult to compute with acceptable accuracy and because a long continuous arc has been obtained which compares with actual data to a known precision, this ephemeris may be used as a standard for computing highly eccentric orbits in the Earth-Moon system.

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