State Vector Determination By A Single Tracking Satellite

TL;DR

This paper presents a theoretical algorithm that enables the determination of an orbit and current state vector of an object using only range measurements from a single tracking satellite, even in unknown Keplerian orbits.

Contribution

The paper introduces a novel algorithm for orbit and state vector calculation using minimal data from a single satellite, advancing tracking capabilities.

Findings

Algorithm successfully computes orbit from range data

Applicable to unknown Keplerian orbits

Requires only a single tracking satellite

Abstract

Using only a single tracking satellite capable of only range measurements to an orbiting object in an unknown Keplerian orbit, it is theoretically possible to calculate the orbit and a current state vector. In this paper we derive an algorithm that can perform this calculation.