Accession Number : AD0281757

Title :   DETERMINATION OF A SATELLITE ORBIT ABOUT THE OBLATE EARTH FROM TWO POSITIONS,

Corporate Author : NAVAL WEAPONS LAB DAHLGREN VA

Personal Author(s) : Oesterwinter,Claus

Report Date : 31 MAY 1962

Pagination or Media Count : 41

Abstract : A discrete set of possible orbits for an artificial earth satellite can be computed when only its absolute positions in space are known at two times. The approach employed in the present method is to scan systematically all possible values of the number of revolutions and of the semi-latus rectum and eventually to compare the observed time interval of the above two times with computed values for this time difference; a possible solution is obtained when these two quantities become identical. With the aid of additional observational material it is then a simple matter to search for the true orbit among the set of possible solutions. The calculations take into account first-order secular perturbations due to the oblateness of the earth. In its present form, the method demands the use of a high-speed digital computer. (Author)

Descriptors :   *ORBITS, DIFFERENTIAL EQUATIONS, DIGITAL COMPUTERS, INTEGRAL EQUATIONS, PARTIAL DIFFERENTIAL EQUATIONS, PROGRAMMING (COMPUTERS), SATELLITES (ARTIFICIAL)

Distribution Statement : APPROVED FOR PUBLIC RELEASE