Earth science satellite missions currently require orbit determination solutions with position accuracies to within a centimeter. The estimation of empirical accelerations has become commonplace in precise orbit determination (POD) for Earth-orbiting satellites. Dynamic model compensation (DMC) utilizes an exponentially time-correlated system noise process, known as a first-order GaussMarkov pr...

When working with space systems the keyword is resources. For a satellite in orbit all resources are sparse and the most critical resource of all is power. It is therefore crucial to have detailed knowledge on how much power is available for an energy harvesting satellite in orbit at every time – especially when in eclipse, where it draws its power from onboard batteries. This paper addresses t...

Compared with Geostationary Orbit (GEO) satellite systems and Medium Earth Orbit (MEO) satellite systems, Low Earth Orbit (LEO) satellite systems provide lower propagation delay as well as higher throughput. Because of these reasons, LEO satellite systems can play a pivotal role in providing services to areas where there is no substantial terrestrial infrastructure. In this paper, a novel kind ...

The halo orbits around the Earth-Moon L2 libration point provide a great candidate orbit for a lunar communication satellite, where the satellite remains above the horizon on the far side of the Moon being visible from the Earth at all times. Such orbits are generally unstable, and station-keeping strategies are required to control the satellite to remain close to the reference orbit. A recentl...

A novel load balancing routing scheme is proposed for Polar-orbit Low Earth Orbit satellite networks. This scheme employs mobile agents to gather related routing information by migrating autonomously. And, stationary agents estimate Inter-satellite Link (ISL) cost, routing path cost and update routing items on satellites. In the proposed scheme, ISL queueing delay is estimated using M/M/1 queue...

From the last few decades, the space science community has shown considerable interest in missions which take place in the vicinity of the Lagrangian points in the restricted three-body problem (RTBP) of the Sun-Earth and the Earth-Moon systems [1]. Designing trajectories for these missions is a challenging task due to inadequacy of the conic approximations. The RTBP deals the situation where o...