scholarly journals Low-Thrust Out-of-Plane Orbital Station-Keeping Maneuvers for Satellites

2012 ◽  
Vol 2012 ◽  
pp. 1-14 ◽  
Author(s):  
Vivian M. Gomes ◽  
Antonio F. B. A. Prado
Keyword(s):  
Main Idea ◽  
Low Thrust ◽  
Station Keeping ◽  
Control Approach ◽  
Orbital Maneuvers ◽  
Hybrid Optimal Control ◽  
The Earth ◽  
Out Of Plane ◽  
Orbital Correction ◽  
Optimal Control Approach

This paper considers the problem of out of plane orbital maneuvers for station keeping of satellites. The main idea is to consider that a satellite is in an orbit around the Earth and that it has its orbit is disturbed by one or more forces. Then, it is necessary to perform a small amplitude orbital correction to return the satellite to its original orbit, to keep it performing its mission. A low thrust propulsion is used to complete this task. It is important to search for solutions that minimize the fuel consumption to increase the lifetime of the satellite. To solve this problem a hybrid optimal control approach is used. The accuracy of the satisfaction of the constraints is considered, in order to try to decrease the fuel expenditure by taking advantage of this freedom. This type of problem presents numerical difficulties and it is necessary to adjust parameters, as well as details of the algorithm, to get convergence. In this versions of the algorithm that works well for planar maneuvers are usually not adequate for the out of plane orbital corrections. In order to illustrate the method, some numerical results are presented.

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.

Earth Orbital Mission Requirements for Secondary Propulsion Systems and Their Impact on Colloid Systems

1970 ◽  
Vol 92 (3) ◽  
pp. 621-627 ◽  
Author(s):  
Ralph A. Benson
Keyword(s):  
Vector Control ◽  
Attitude Control ◽  
Low Thrust ◽  
Station Keeping ◽  
Propulsion Systems ◽  
Thrust Vector Control ◽  
The Earth ◽  
Thrust Vector ◽  
Colloid Systems ◽  
Orbital Mission

This paper develops the earth synchronous orbital mission requirements for secondary propulsion subsystems (SPS) involving positioning of satellites in orbit and station keeping when in position. It also discusses the orbital requirements associated with attitude control and touches on the requirements for SPS pulsing, thrust vector alignment, and thrust vector control. After developing the earth-orbital mission requirements for SPS, the implications of using low-thrust colloid SPS are discussed. Conclusions are then presented regarding use of colloid, SPS for synchronous earth-orbital operations.

Rendez vous with Saturn's rings

1984 ◽  
Vol 75 ◽  
pp. 743-759 ◽  
Author(s):  
Kerry T. Nock
Keyword(s):  
Solar Energy ◽  
Electric Propulsion ◽  
Power Source ◽  
Propulsion System ◽  
Low Thrust ◽  
Ring Plane ◽  
The Earth ◽  
Total Impulse ◽  
Saturn's Rings

ABSTRACTA mission to rendezvous with the rings of Saturn is studied with regard to science rationale and instrumentation and engineering feasibility and design. Future detailedin situexploration of the rings of Saturn will require spacecraft systems with enormous propulsive capability. NASA is currently studying the critical technologies for just such a system, called Nuclear Electric Propulsion (NEP). Electric propulsion is the only technology which can effectively provide the required total impulse for this demanding mission. Furthermore, the power source must be nuclear because the solar energy reaching Saturn is only 1% of that at the Earth. An important aspect of this mission is the ability of the low thrust propulsion system to continuously boost the spacecraft above the ring plane as it spirals in toward Saturn, thus enabling scientific measurements of ring particles from only a few kilometers.

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