Simulation of microsatellite attitude using Kalman filtering in orbit results

Mohammed, A. M. Si; Benyettou, M.; Boudjemai, A.; Hashida, Y.; Sweeting, Martin

doi:10.1016/j.simpat.2007.11.009

Cited by 8 publications

(6 citation statements)

References 9 publications

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“…The extended Kalman filter is the nonlinear version of the Kalman filter which makes use of the nominal nonlinear system dynamics to predict the evolution of the state while it uses updated local linearisations of the nonlinear system at the currect estimated state to estimate the covariance of the state vector [24]. Many authors have also used the EKF approach to reconstruct the spacecraft attitude parameters [25], [26]. Here, the state estimatesẑ k are updated according to the nonlinear equation…”

Section: B State Estimationmentioning

confidence: 99%

Sloshing-aware attitude control of impulsively actuated spacecraft

Sopasakis

Bernardini

Strauch

et al. 2015

2015 European Control Conference (ECC)

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Abstract-Upper stages of launchers sometimes drift, with the main engine switched-off, for a longer period of time until re-ignition and subsequent payload release. During this period a large amount of propellant is still in the tank and the motion of the fluid (sloshing) has an impact on the attitude of the stage. For the flight phase the classical spring/damper or pendulum models cannot be applied. A more elaborate sloshing-aware model is describe in the paper involving a time-varying inertia tensor.Using principles of hybrid systems theory we model the minimum impulse bit (MIB) effect, that is, the minimum torque that can be exerted by the thrusters. We design a hybrid model predictive control scheme for the attitude control of a launcher during its long coasting period, aiming at minimising the actuation count of the thrusters.

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Section: B State Estimationmentioning

confidence: 99%

Sloshing-aware attitude control of impulsively actuated spacecraft

Sopasakis

Bernardini

Strauch

et al. 2015

2015 European Control Conference (ECC)

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“…As result, the LEO satellite dynamic model is expressed as 3 ( ) r μ γ = + r = -r + f r w (7) where w = [w x w y w z ] T is the process noise.…”

Section: Orbit Dynamic Modellingmentioning

confidence: 99%

“…Since the appearance of the (LEO) satellite, the EMF has been applied to determine satellite orbit and attitude in LEO satellites. The use of the magnetometers measurements for hybrid navigation has attracted much attention in research community and has been the subject of many publications [1][2][3][4][5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

An autonomous hybrid navigation filter using earth magnetic field measurements for low earth orbit satellite

Bellar

Mohammed

2015

2015 3rd International Conference on Control, Engineering &Amp; Information Technology (CEIT)

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The primary focus of this paper is the design of an hybrid navigation filter algorithm based on Extended Kalman Filter (EKF), which autonomously and simultaneously estimates three axis attitude, rate and orbit using only Earth Magnetic Field (EMF) measurements. The presented hybrid navigation filter algorithm is based on the laws of orbital mechanics, attitude dynamic and the EMF measurements. According to our simulations study, the developed hybrid navigation filter shows the capability of estimating the attitude with accuracy less than 1.5 deg and rate order is 1.5 milli-deg/sec. In orbit estimation, the filter is able of estimating the position with accuracy of 15.5 km and velocity 0.013 km/s. Based upon results, the orbit and attitude accuracy is sufficient for Low Earth Orbit (LEO) satellite with coarse accuracy mission requirements and it can be used as a backup system to provide redundancy.

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“…Previous study of the three-axis attitude determination for LEO satellite using only magnetometer measurement is successfully presented in [14], [15] which estimated small attitude and rate angle and produce acceptable attitude and rate error. A similar approach was performed for LEO EgyptSat-2 using only magnetometer measurement at big attitude angle (in detumbling mode) was presented in [16] and showed that estimated attitude produced quite big attitude error.…”

Section: Figure 1 Innosatmentioning

confidence: 99%

“…Time update is used to predict next estimate value and measurement update is used to correct the error. Attitude estimation using EKF is initiated by describing non-linear differential equation of a dynamic system [6], [15], [27]. The general nonlinear differential equation is defined as,…”

Section: Extended Kalman Filter (Ekf)mentioning

confidence: 99%

Deterministic and Recursive Approach in Attitude Determination for InnoSAT

et al. 2011

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AbstrakSistem penentuan atituda (ADS) Kata kunci: Perhitungan sikap, InnoSAT, EKF, QUEST Abstract Attitude determination system (ADS) was indispensable in attitude control of satellite. Especially for InnoSAT due to the limitation of budget, weight, and power, the attitude was determined using onboard position sensors. Previous research has successfully implemented the attitude determination using onlyEarth's magnetic field sensors for small attitude angle, but the approach produced quite big error for large attitude angle. This paper presents attitude determination for InnoSAT using combination of sun sensors and earth's magnetic field for large attitude angle. The attitude was determined using a deterministic (QUEST) and recursive (EKF) approach. A problem arises when using the sun sensors while the satellite experiencing eclipse. Consequently, the accuracy of both approaches was analyzed at eclipse and no eclipse conditions. The result shows that deterministic approach produced better accuracy at no eclipse but recursive approach produced better accuracy at eclipse. The strategy to apply the both approaches and eclipse conditions also discussed in this paper.

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Simulation of microsatellite attitude using Kalman filtering in orbit results

Cited by 8 publications

References 9 publications

Sloshing-aware attitude control of impulsively actuated spacecraft

Sloshing-aware attitude control of impulsively actuated spacecraft

An autonomous hybrid navigation filter using earth magnetic field measurements for low earth orbit satellite

Deterministic and Recursive Approach in Attitude Determination for InnoSAT

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