The determination and analysis of the orbit of NIMBUS 1 ROCKET, 1964-52B Part 2: Variations in orbital eccentricity

Details The determination and analysis of the orbit of NIMBUS 1 ROCKET, 1964-52B Part 2: Variations in orbital eccentricity The determination and analysis of the orbit of NIMBUS 1 ROCKET, 1964-52B Part 2: Variations in orbital eccentricity

Jun 1985

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1985p%26ss...33..735b&link_type=abstract

Planetary and Space Science, Volume 33, Issue 6, p. 735-756.

Mathematics

9

Scientific paper

The influence of aerodynamic drag and the geopotential on the motion of the satellite 1964-52B is considered. A model of the atmosphere is adopted that allows for oblateness, and in which the density behaviour approximates to the observed diurnal variation. A differential equation governing the variation of the eccentricity, e, combining the effects of air drag with those of the Earth's gravitational field is given. This is solved numerically using as initial conditions 310 computed orbits of 1964-52B.
The observed values of eccentricity are modified by the removal of perturbations due to luni-solar attraction, solid Earth and ocean tides, solar radiation pressure and low-order long-periodic tesseral harmonic perturbations. The method of removal of these effects is given in some detail. The behaviour of the orbital eccentricity predicted by the numerical solution is compared with the modified observed eccentricity to obtain values of atmospheric parameters at heights between 310 and 430 km. The daytime maximum of air density is found to be at 14.5 hours local time. Analysis of the eccentricity near 15th order resonance with the geopotential yielded values of four lumped geopotential harmonics of order 15, namely: 109 C1,015 = -78.8 +/- 7.0, 109 S1,015 = -69.4 +/- 5.3, 109 C-1,215 = -41.6 +/- 3.5 109 S-1,215 = -26.1 +/- 8.9, at inclination 98.68°.
Permanent address: Department of Mathematics, Coventry (Lanchester) Polytechnic, Priory Street, Coventry CV1 5FB, U.K.

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