Determining satellite orbit from two velocity vectors

Details Determining satellite orbit from two velocity vectors Determining satellite orbit from two velocity vectors

Jan 1986

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1986rpspr......102o&link_type=abstract

In its USSR Report: Space (JPRS-USP-86-001) p 102-103 (SEE N86-20178 10-88) Transl. into ENGLISH from Izvestiya Vysshikh Uche

Mathematics

Angular Velocity, Artificial Satellites, Kepler Laws, Orbital Position Estimation, Satellite Orbits, Vectors (Mathematics), Algorithms, Orbital Elements

Scientific paper

A method is proposed for determining the Keplerian orbit of an artificial satellite of the Earth or of a planet according to two velocity vectors given at known moments of time. The method relies on a Newtonian orbit-parameter iteration procedure. A numerical example is presented for an Earth satellite with the following orbital elements: a = 6700 km, e = 0.01, i = 1 rad, Omega = 0 deg, omega = 0 deg, and M(0) = 0 deg. It is concluded that the proposed algorithm is sufficiently simple and that the convergence speed of the iterative procedure is high.

Affiliated with

Also associated with

No associations

Rating

Determining satellite orbit from two velocity vectors does not yet have a rating. At this time, there are no reviews or comments for this scientific paper.

If you have personal experience with Determining satellite orbit from two velocity vectors, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Determining satellite orbit from two velocity vectors will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFWR-SCP-O-1847831