scholarly journals Minimum Fuel Low-Thrust Transfers for Satellites Using a Permanent Magnet Hall Thruster

2013 ◽  
Vol 2013 ◽  
pp. 1-12 ◽  
Author(s):  
Thais Carneiro Oliveira ◽  
Evandro Marconi Rocco ◽  
José Leonardo Ferreira ◽  
Antonio F. B. A. Prado
Keyword(s):  
Permanent Magnet ◽  
Fuel Consumption ◽  
Hall Thruster ◽  
Optimal Trajectories ◽  
Space Vehicles ◽  
Low Thrust ◽  
Orbital Maneuvers ◽  
Orbital Maneuver ◽  
Different Types ◽  
External Forces

Most of the satellite missions require orbital maneuvers to accomplish its goals. An orbital maneuver is an operation where the orbit of a satellite is changed, usually applying a type of propulsion. The maneuvers may have several purposes, such as the transfer of a satellite to its final orbit, the interception of another spacecraft, or the adjustment of the orbit to compensate the shifts caused by external forces. In this situation it is essential to minimize the fuel consumption to allow a greater number of maneuvers to be performed, and thus the lifetime of the satellite can be extended. There are several papers and studies which aim at the fuel minimization in maneuvers performed by space vehicles. In this context, this paper has two goals: (i) to develop an algorithm capable of finding optimal trajectories with continuous thrust that can fit different types of missions and constraints at the same time and (ii) to study the performance of two propulsion devices for orbital maneuvers under development at the Universidade de Brasilia, including a study of the effects of the errors in magnitude of these new devices.

scholarly journals Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft

2014 ◽  
Vol 2014 ◽  
pp. 1-15 ◽  
Author(s):  
R. C. Domingos ◽  
A. F. B. A. Prado ◽  
V. M. Gomes
Keyword(s):  
Fuel Consumption ◽  
Low Thrust ◽  
Three Body Problem ◽  
Station Keeping ◽  
Third Body ◽  
Orbital Maneuvers ◽  
Orbital Correction ◽  
Averaged Models ◽  
Three Body ◽  
Averaged Methods

The fuel consumption required by the orbital maneuvers when correcting perturbations on the orbit of a spacecraft due to a perturbing body was estimated. The main goals are the measurement of the influence of the eccentricity of the perturbing body on the fuel consumption required by the station keeping maneuvers and the validation of the averaged methods when applied to the problem of predicting orbital maneuvers. To study the evolution of the orbits, the restricted elliptic three-body problem and the single- and double-averaged models are used. Maneuvers are made by using impulsive and low thrust maneuvers. The results indicated that the averaged models are good to make predictions for the orbital maneuvers when the spacecraft is in a high inclined orbit. The eccentricity of the perturbing body plays an important role in increasing the effects of the perturbation and the fuel consumption required for the station keeping maneuvers. It is shown that the use of more frequent maneuvers decreases the annual cost of the station keeping to correct the orbit of a spacecraft. An example of an eccentric planetary system of importance to apply the present study is the dwarf planet Haumea and its moons, one of them in an eccentric orbit.

scholarly journals Orbital Maneuvers Using Low Thrust to Place a Satellite in a Constellation

2007 ◽  
Vol 2007 ◽  
pp. 1-9 ◽  
Author(s):  
Vivian Martins Gomes ◽  
Antonio Fernando Bertachini de Almeida Prado ◽  
Helio Koiti Kuga
Keyword(s):  
Fuel Consumption ◽  
Low Thrust ◽  
Orbital Maneuvers ◽  
Satellite Constellation ◽  
Parking Orbit

This paper considers the problem of low thrust suboptimal maneuvers to insert a satellite in a constellation. It is assumed that a satellite constellation is given with all the Keplerian elements of the satellite members having known values. Then, it is necessary to maneuver a new satellite from a parking orbit to its position in the constellation. The control available to perform this maneuver is the application of a low thrust to the satellite and the objective is to perform this maneuver with minimum fuel consumption.

scholarly journals A Permanent Magnet Hall Thruster for Pulsed Orbit Control of Lunar Polar Satellites

2014 ◽  
Vol 511 ◽  
pp. 012074 ◽  
Author(s):  
Brunno Silva Moraes ◽  
José Leonardo Ferreira ◽  
Ivan Soares Ferreira ◽  
Othon Cabo Winter ◽  
Décio Cardozo Mourão
Keyword(s):  
Permanent Magnet ◽  
Hall Thruster ◽  
Orbit Control

A 200-W permanent magnet Hall thruster discharge with graphite channel wall

2018 ◽  
Vol 382 (42-43) ◽  
pp. 3079-3082 ◽  
Author(s):  
Yongjie Ding ◽  
Hong Li ◽  
Hezhi Sun ◽  
Liqiu Wei ◽  
Boyang Jia ◽  
...  
Keyword(s):  
Permanent Magnet ◽  
Channel Wall ◽  
Hall Thruster

scholarly journals Loosely displaced formation-keeping control for satellite swarm with continuous low-thrust

2020 ◽  
Vol 17 (5) ◽  
pp. 172988142094755
Author(s):  
Lin Zhao ◽  
Kun Zhao ◽  
Hui Li ◽  
Weiquan Huang ◽  
Xinyu Zhang ◽  
...  
Keyword(s):  
Feedback Control ◽  
Fuel Consumption ◽  
Spectral Method ◽  
Control Strategy ◽  
Sliding Mode ◽  
Low Thrust ◽  
Mode Theory ◽  
Pseudo Spectral Method ◽  
Pseudo Spectral ◽  
Formation Keeping

Aiming at a long-term formation-keeping problem for the satellite swarm, the concept of a loosely displaced formation is proposed in this article. On this basis, a continuous low-thrust control strategy for maintaining the loosely displaced formation is designed. The control objective is to reduce more fuel consumption during the formation-keeping. For achieving that, we proposed a forward-feedback control strategy by using pseudo-spectral method and sliding mode theory. To be specific, the control strategy includes two parts: a forward control and a feedback control. For the forward control, a numerical optimization with the Legendre pseudo-spectral method is attempted to convert the optimal control problem into a nonlinear programming problem and fuel consumption is selected as the optimization index. For stability issue, the feedback control via adaptive finite-time sliding mode theory is introduced as an additional control component. Finally, the numerical results demonstrate that propellant mass is effectively saved as well as the formation can be tracked accurately with this control strategy proposed in this article.

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