Design of Next-Generation All-Electric Telecommunication Satellites

Dutta, Atri; Libraro, Paola; Kasdin, N. Jeremy; Choueiri, Edgar Y.; Fracken, Philippe

doi:10.2514/6.2013-5625

Cited by 8 publications

(2 citation statements)

References 18 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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.…”

Section: Introductionmentioning

confidence: 99%

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

Dutta

Sreesawet

Vijayan

et al. 2014

32nd AIAA International Communications Satellite Systems Conference

Self Cite

View full text Add to dashboard Cite

High power budget of telecommunication spacecraft can potentially allow the operation of multiple electric thrusters simultaneously during an orbital transfer to the Geostationary Earth orbit. In this paper, we consider the problem of electric orbit-raising during which the spacecraft uses more than one thruster type during the transfer. We develop a methodology to determine trajectories from arbitrary starting orbits to the GEO for the case when two different thruster types are used during the maneuver. We also develop a framework to analyze the solar array degradation caused by protons in the Van Allen radiation belts during orbit-raising. We demonstrate our methodology with the help of numerical examples that evaluate the trade-offs associated with using arcjets during the initial part of the transfer. We consider different cases of switching from arcjets to Hall thrusters during the maneuver and evaluate the requirements on shielding thickness in order to limit the radiation exposure for representative orbit-raising trajectories. Nomenclature x, y, z components of the position vector of a spacecraft r P periapsis of the instantaneous orbit of a spacecraft u radial velocity of the satellite v transverse velocity of the satellite w out-of-plane velocity component of the satellite m mass of the satellite T thrust magnitude α, β direction of the thrust vector of the satellite D d displacement damage dose t ffinal time for the orbit-raising maneuver µ gravitational parameter for the Earth R E radius of the Earth ∆P deg solar array degradation Ψ P flux of protons at a location in space Φ P fluence of protons of energy-level E along a trajectory E energy levels of incident protons E energy levels of transmitted protons T max maximum thrust provides by the electric thruster n i number of thrusters of type i T i thrust provided by a specific thruster of type i Subscripts:i Index number of thruster type

show abstract

Section: Introductionmentioning

confidence: 99%

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

Dutta

Sreesawet

Vijayan

et al. 2014

32nd AIAA International Communications Satellite Systems Conference

Self Cite

View full text Add to dashboard Cite

show abstract

“…T HE micro-thrust (mN or μN class) of electrical propulsion (EP) devices work over long period of time to accelerate spacecraft for interplanetary navigation and orbit maneuver [1], so the measurement of accumulating momentum is crucial to evaluate performance of EP devices. The micro-thrust measurements for EP devices often have been made by measuring deflection of the mechanism to which the thruster is mounted and converting that deflection to thrust through some suitable calibration.…”

Section: Introductionmentioning

confidence: 99%

Effect of Temperature on Rotation Loss in a Superconducting Device for Microthrust Measurement of Electric Propulsion System

Yang

Wang

et al. 2015

IEEE Trans. Appl. Supercond.

View full text Add to dashboard Cite

Accurate measurement for long-term accumulating momentum of electrical propulsion (EP) requires the microthrust stand with high performance. A microthrust-measuring device using high-temperature superconductor magnetic levitation (HTSML) is designed to remove connecting interferences for better evaluation of EP thrusters. Levitating rotation loss is the main factor that affects measuring accuracy of the HTSML device. In this paper, we propose a new method to measure the accumulating momentum. A vacuum experimental setup that can control the temperature of YBCO bulk was built up to investigate the rotation loss at low speed. Effects of temperature and field cooling (FC) height on the coefficient of friction μ are analyzed. By analyzing the basic phenomenon of the rotation friction in the low speed range less than 30 Hz, the low speed rotation can be divided into three different phases. When the rotation frequency is closed to the natural frequency of the HTSML device, oscillation happens and leads to serious rotation loss. The friction loss after the oscillation is very steady and can be used in the measurement of accumulating momentum. The large FC height and temperature can diminish the rotation loss, and increasing FC height could diminish rotation loss dependence of temperature. Although the experimental measurements show good repeatability, large rotation loss (10 -4 ∼10 -3 ) in the experimental setup means that this setup should be further improved.

show abstract

Orbital Dynamics and Guidance

Mazzini

2015

Flexible Spacecraft Dynamics, Control and Guidance

View full text Add to dashboard Cite

Design of Next-Generation All-Electric Telecommunication Satellites

Cited by 8 publications

References 18 publications

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

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

Effect of Temperature on Rotation Loss in a Superconducting Device for Microthrust Measurement of Electric Propulsion System

Orbital Dynamics and Guidance

Contact Info

Product

Resources

About