Ariane 5-ME and Electric Propulsion: GEO Insertion Options

Abstract

Electric propulsion is now widely used on commercial satellites, and the prospects of allelectric satellites may be considered for future comsats where all propulsive duties are fulfilled by the electric propulsion subsystem, including orbit raising. In such a configuration, the full benefits of using higher specific impulse devices for the satellite onboard propulsion would be realized. These benefits may be expressed in terms of increased payload capability in geostationary orbit, but also in terms of increased satellite operational life or decreased launch costs, depending on market demands. This study examines the best match options between electric propulsion and a launch vehicle with frozen specification, with Ariane 5-ME taken as a reference example. Departure orbit options before the electric orbit raising to GEO are traded in order to realize the full potential of both the launch vehicle performance and electric propulsion. The selection of the best options is discussed, depending on the priority given to fast electric orbit raising and low radiation fluence versus improved dry mass capability to geostationary orbit. Nomenclaturea = semi-major axis length, m g 0 = standard free fall, 9.81 m.s -2 i = orbit inclination, deg. Isp = specific impulse, s V a = apogee velocity, m/s Z a , Z p = apogee (respectively perigee) altitude, m ∆V = velocity increment, m/s α = ratio of satellite solar array power (Beginning of Life) to launch mass, W/kg β = power-specific thrust, N/W η = thrust efficiency µ = standard gravitational parameter for Earth, 3.99×10 14 m 3 /s 2

On the Design of Power and Propulsion Subsystems of All-Electric Telecommunication Satellites

“…These studies can be broadly classified into two types: one set of studies primarily focusses on the determination of optimal orbit-raising trajectories, 5,6,7,8,9,10 while the other set considers the evaluation of the tradeoffs associated with the orbit-raising maneuver. 11,12,13,14,15,16,17 However, these studies have primarily considered the use of a single type of thruster during the orbit-raising maneuver. In this paper, we consider the problem of using two different types of thruster during the orbit-raising maneuver.…”

Minimum-fuel electric orbit-raising of telecommunication satellites subject to time and radiation damage constraints

“…panels during the transfer and are possibly harmful for other electronics too [7], [8], [9]. Several researchers have investigated the different aspects of the problem of electric orbitraising including radiation damage during the maneuver [10], [11], [5], [12]. However, these studies have primarily considered the computation of minimum-time trajectories and analyzed the radiation impact on them.…”

Minimum Time Orbit Raising of Geostationary Spacecraft by Optimizing Feedback Gain of Steering Law

“…In recent years, low-propulsion thrusters, such as ion thruster and hall thrusters, have become hopeful propulsion systems for spacecraft transferring from a low Earth orbit (LEO), a geostationary transfer orbit (GTO), or a supersynchronous orbit (SSTO) to a geostationary orbit (GEO). [1][2][3] Conventionally, a geostationary spacecraft is placed in a GTO by a launcher. However, to complete the orbit transfer, the spacecraft employs an on-board high-chemical propulsion thruster, called the apogee kick motor, at the apogee of the GTO so that the semimajor axis, eccentricity, and inclination of the orbit correspond with those of the GEO.…”