A Direct Optimization Based Tool to Determine Orbit-Raising Trajectories to GEO for All-Electric Telecommunication Satellites

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

doi:10.2514/6.2012-4589

Cited by 12 publications

(5 citation statements)

References 18 publications

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“…In other words, the mass b Preliminary investigation for transfers from circular orbits show that the optimal solution obtained by direct optimization approach as in Ref. 23 lies in between the solutions obtain by the methodology used in the paper and that obtained by our implementation of the Q-law. penalty due to longer operation of arcjets increases at a higher rate compared to reduction of transfer time.…”

Section: Ivb Trade-offs Between Fuel Expenditure and Transfer Timementioning

confidence: 92%

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

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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

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Section: Ivb Trade-offs Between Fuel Expenditure and Transfer Timementioning

confidence: 92%

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

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“…We follow a direct optimization approach which is known to be more robust numerically in terms of initial guesses and solution convergence [21]. We extend our developed solver in reference [22] by considering discretizing the energy spectrum of protons encountered during the transfer in order to compute the displacement damage dose associated with the transfer. Furthermore, rather than using lookup tables [13], we incorporate an analytical radiation model [17] within the optimization framework to facilitate the optimization process.…”

Section: Solution Methodologymentioning

confidence: 99%

“…The minimum time solutions are derived by solving a much simpler NLP as described in Ref. [22]. The optimization solver needs an initial guess and we use the following initial guesses to yield converged solution for the numerical examples considered in this paper: radial position r is considered a cubic polynomial of the time-like parameter τ , transverse velocity v = µ/r, thrust is considered to have a component only along e θ direction and final time…”

Section: Nlp Solutionmentioning

confidence: 99%

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

Dutta

Libraro

Kasdin

et al. 2014

2014 American Control Conference

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The capability of a Geostationary satellite to perform electric orbit-raising enables the development of allelectric satellites. Key challenges to the realization of electric deployment of satellites to the Geostationary orbit are the long transfer times, high power requirement of the electric thrusters and the solar array degradation experienced by the satellite during its transit through the Van Allen radiation belts. In this paper, we consider the problem of electric orbit-raising of a telecommunication satellite to the Geostationary orbit. We propose an optimization framework to minimize the fuel expenditure during the transfer subject to upper bounds on the transfer time and the displacement damage dose. Our developed framework considers the discretization of the satellite trajectory as well as the energy spectrum of protons encountered during the transfer, and utilizes analytic models of the geomagnetic field and associated radiation flux. Finally, we illustrate with numerical examples the fuel savings that can be achieved by comparing minimum-time and minimum-fuel solution.

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“…15. Furthermore, note that the solar array degradation can be reduced by allowing for appropriate shielding.…”

Section: Ivc Power Subsystemmentioning

confidence: 97%

Design of Next-Generation All-Electric Telecommunication Satellites

Dutta¹,

Libraro²,

Kasdin³

et al. 2013

31st AIAA International Communications Satellite Systems Conference

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In this paper, we revisit the problem of electric orbit-raising of telecommunication satellites. The paper outlines the mathematical framework we have developed to determine trajectories that minimize the radiation damage during orbit-raising. This framework also allows us to analyze a variety of mission scenarios in order to identify the favourable designs for all-electric satellites. We outline the number and type of thrusters most suitable for the orbit-raising maneuver and the associated design of the power subsystem. We also consider the possible launch options of the satellites and demonstrate the advantages that all-electric satellites have by being stacked together to reduce the launch costs compared to their chemical or hybrid counterparts.

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A Direct Optimization Based Tool to Determine Orbit-Raising Trajectories to GEO for All-Electric Telecommunication Satellites

Cited by 12 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

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

Design of Next-Generation All-Electric Telecommunication Satellites

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