Attitude Kinematics and Dynamics

Markley, F. Landis

doi:10.1007/978-1-4939-0802-8_3

Cited by 7 publications

(5 citation statements)

References 15 publications

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“…Measurements are assumed to be the quaternion with noise. More details of the MEKF can be found in [ 34 ].…”

Section: Simulation Resultsmentioning

confidence: 99%

Adaptive Lag Smoother for State Estimation

Poddar

2022

Sensors

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Fixed-lag smoothing has been used across different disciplines for offline analysis in many applications. With rising computational power and parallel processing architectures, fixed-lag smoothers are increasingly integrated into online processing system with small delays. This delay is directly related to the lag-length used in system design, which needs to be chosen appropriately. In this work, an adaptive approach is devised to choose an appropriate lag-length that provides a good trade-off between accuracy and computational requirements. The analysis shown in this paper for the error dynamics of the fixed-lag smoother over the lags helps in understanding its saturation over increasing lags. In order to provide the empirical results, simulations are carried out over a second-order Newtonian system, single-axis attitude estimation, Van der Pol’s oscillator, and three-axis attitude estimation. The simulation results demonstrate the performance achieved with an adaptive-lag smoother as compared to a fixed-lag smoother with very high lag-length.

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“…Measurements are assumed to be the quaternion with noise. More details of the MEKF can be found in [ 34 ].…”

Section: Simulation Resultsmentioning

confidence: 99%

Adaptive Lag Smoother for State Estimation

Poddar

2022

Sensors

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“…The attitude determination and control subsystem (ADCS) is in charge of the satellite stabilization and keeps it pointed in the appropriate direction throughout the mission [12]. ADCS will be ASAT-20 Journal of Physics: Conference Series 2616 (2023) 012026 highlighted in this section, which consists of many blocks, as presented in figure 1.…”

Section: Attitude Determination and Control Subsystem (Adcs)mentioning

confidence: 99%

“…The station-keeping maneuver is performed by adding or subtracting delta velocity from the satellite's velocity. Equation (12,13) provides the required delta velocity to achieve the maneuver [17].…”

Section: Rct Configurationmentioning

confidence: 99%

Modeling and analysis for reaction control thruster used for station-keeping maneuvers of a GEO satellite

Ashraf,

Hendy,

Sallam

et al. 2023

J. Phys.: Conf. Ser.

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This paper introduces a theoretical description, force, and torque analysis of a Reaction Control Thruster (RCT) used as an actuator in Attitude Determination and Control Subsystem (ADCS). Mathematical formalization, realization, and implementation are offered to implement the RCT model using Matlab-Simulink. Furthermore, this paper proposes an accurate RCT Simulink model to control the orientation and stabilizes the Geostationary Earth Orbit (GEO) satellite within its orbit. Finally, a comparative analysis is carried out with an existing satellite platform (Eurostar-3000) based on the Root Mean Square Error (RMSE) for the delta velocity (delta-𝒱) parameter. The outcomes of the model simulation validated the effectiveness of the proposed approach.

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“…In this section, the kinematics of the attitude are discussed. We represent the attitude of the satellite by a quaternion, which leads to the following representation for the attitude kinematics (Markley, & Crassidis, 2014)…”

Section: Attitude Kinematicsmentioning

confidence: 99%

“…The attitude kinematics can be expressed by an attitude matrix, quaternion products and the angular velocity vector. See for further information (Markley, & Crassidis, 2014).…”

Section: Attitude Kinematicsmentioning

confidence: 99%

Control Allocation of a GEO Satellite for Station-Keeping and Momentum Management by Using Thrusters and Reaction Wheels

Emri¹,

Cihan²

2021

European Journal of Science and Technology

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This paper presents a control allocation method for simultaneous station-keeping and momentum management maneuvers. The considered satellite model is equipped with internal and external actuators to control the satellite's orbit and attitude and, concurrently, unload the angular momentum stored in the reaction wheels. Our method allocates the external and internal actuators to achieve the control objectives. Internal actuators such as reaction wheels generate torque based on the conservation of the momentum. In this study, two different controllers are utilized to control satellite attitude and reaction wheel speeds. To manage the satellite attitude in three axes, at least three reaction wheels are needed. In this study, four reaction wheels are used to ensure control in case of failure of a reaction wheel. In addition, with six chemical thrusters, east-west and north-south orbit correction maneuvers are performed. For the satellite to serve throughout its service life, fuel optimization of the satellite is required. The proposed control allocation method will enforce constraints that maintain orbital accuracy and the satellite in a nadir pointing attitude configuration while minimizing the use of thrusters, significantly reducing fuel consumption. The method combines the two generally separated objectives of orbital and attitude control through constraints determined by the propulsion system. Numerical simulations are performed to validate the proposed method. The simulations show that using the proposed control allocation method can significantly increase the service life of geostationary satellites.

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Attitude Kinematics and Dynamics

Cited by 7 publications

References 15 publications

Adaptive Lag Smoother for State Estimation

Adaptive Lag Smoother for State Estimation

Modeling and analysis for reaction control thruster used for station-keeping maneuvers of a GEO satellite

Control Allocation of a GEO Satellite for Station-Keeping and Momentum Management by Using Thrusters and Reaction Wheels

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