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 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 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 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.

Multidisciplinary Assessment of the Control of the Propellers of a Pusher Geared Open Rotor—Part II: Impact on Fuel Consumption, Engine Weight, Certification Noise, and NOx Emissions

2016 ◽  
Vol 138 (7) ◽  
Author(s):  
Pablo Bellocq ◽  
Inaki Garmendia ◽  
Vishal Sethi ◽  
Alexis Patin ◽  
Stefano Capodanno ◽  
...  
Keyword(s):  
Fuel Consumption ◽  
Full Range ◽  
Low Pressure ◽  
Performance Model ◽  
Preliminary Design ◽  
Fuel Saving ◽  
Low Thrust ◽  
Regulatory Constraints ◽  
Open Rotor ◽  
The Impact

Due to their high propulsive efficiency, counter-rotating open rotors (CRORs) have the potential to significantly reduce fuel consumption and emissions relative to conventional high bypass ratio turbofans. However, this novel engine architecture presents many design and operational challenges both at engine and aircraft level. The assessment of the impact of the main low-pressure preliminary design and control parameters of CRORs on mission fuel burn, certification noise, and emissions is necessary at preliminary design stages in order to identify optimum design regions. These assessments may also aid the development process when compromises need to be performed as a consequence of design, operational, or regulatory constraints. Part I of this two-part publication presents a novel 0D performance model for counter-rotating propellers (CRPs) allowing an independent definition of the design and operation of each of the propellers. In Part II, the novel CRP model is used to create an engine performance model of a geared open rotor (GOR). This engine model is integrated in a multidisciplinary simulation platform which was used to assess the impact of the control of the propellers, on specific fuel consumption (SFC), engine weight, certification noise, and NOx emission, for a GOR with a 10% clipped rear propeller designed for a 160 PAX and 5700 NM aircraft. The main conclusions of the study are: (1) Minimum SFC control schedules were identified for climb, cruise, and descent (high-rotational speeds for high thrust and low-rotational speeds for low thrust), (2) SFC reductions up to 2% in cruise and 23% in descent can be achieved by using the minimum SFC control. However, the relatively high SFC reductions in descent SFC result in ∼3.5% fuel saving for a 500 NM and ∼0.7% fuel saving for a full range mission, (3) at least 2–3 dB noise reductions for both sideline and flyover can be achieved by reducing the rotational speeds of the propellers at a cost of ∼6% increase of landing and takeoff cycle (LTO) NOx and 10 K increase in turbine entry temperature, (4) approach noise can be reduced by at least 2 dB by reducing CRP rotational speeds with an associated reduction of ∼0.6% in LTO NOx, and (5) the control of the CRP at takeoff has a large impact on differential planetary gearbox (DPGB) weight, but it is almost identical in magnitude and opposite to the change in low-pressure turbine (LPT) and CRP weight. Consequently, the control of the CRP at takeoff has a negligible impact in overall engine weight.

scholarly journals On the choice of a parking orbit for a service spacecraft

2020 ◽  
Vol 2020 (3) ◽  
pp. 30-38
Author(s):  
Yu.M. Holdshtein ◽  
Keyword(s):  
Mathematical Model ◽  
Operational Reliability ◽  
Analytical Determination ◽  
Transfer Program ◽  
Low Thrust ◽  
Transfer Energy ◽  
Orbital Transfer ◽  
Energy Expenditures ◽  
Parking Orbit ◽  
Orbital Transfers

At present, the requirements for increasing spacecraft active life and operational reliability and reducing spacecraft operation costs become more and more stringent. Because of this, on-orbit servicing becomes more and more attractive. One of the most promising ways to increase the efficiency of transport operations in space is to carry out on-orbit servicing using reusable spacecraft with low-thrust solar electrojet engines. The aim of this paper is to develop a mathematical model for the choice of an optimal low near-Earth parking orbit for a reusable service spacecraft. The case of noncoplanar near-circular orbits of spacecraft and a shuttle scenario of their servicing is considered. The solution of the problem of choosing an optimal parking orbit for a reusable service spacecraft involves repeated solutions of the problem of determining the delta-velocity of the service spacecraft’s orbital transfers between its parking orbit and the orbits of the serviced spacecraft. In this connection, using the averaging method, a mathematical model is developed for the analytical determination of orbital transfer program controls and trajectories and assessing orbital transfer energy expenditures. With its use, a mathematical model is developed for the choice of a service spacecraft’s optimal parking orbit. The objective function is the total delta-velocity of the service spacecraft’s orbital transfers from its parking orbit to the orbits of the serviced spacecraft and vice versa with the inclusion of the orbital transfer frequency. The optimizable parameters are the service spacecraft parking orbit parameters. The use of the proposed models is illustrated by an example of service spacecraft parking orbit optimization. What is new is the mathematical models developed. The results obtained may be used in the preliminary planning of on-orbit servicing operations.

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.

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