Add to ORKGAttitude estimation of earth orbiting satellites (including Large Space Telescope) subjected to environmental disturbances and noises was investigated. Modern control and estimation theory is used as a tool to design an efficient estimator for attitude estimation. Decomposed linear recursive filters for both continuous-time systems and discrete-time systems are derived. By using this accurate estimation of the attitude of spacecrafts, state variable feedback controller may be designed to achieve (or satisfy) high requirements of system performance
Attitude determination has been considered as a permanent topic of active research and perhaps remai...
Partial differential equations used to correct values of orbital elements for satellites in near ear...
Computer program for determining attitude of orbiting vehicle using Kalman filte
Computer simulation results of attitude estimation of Earth-orbiting satellites (including Space Tel...
An adaptive Kalman filter design that utilizes recursive maximum likelihood parameter identification...
In this paper, a comprehensive comparison of two robust estimation techniques namely, compensated cl...
A weighted least-squares recursive estimator program is reported for simulating spacecraft orbital p...
Methods of determining satellite orbit and attitude parameters are considered. The Goddard Trajector...
Prediction Algorithms for the Attitude Estimator The attitude estimator is an extended Kalman filte...
Precision attitude determination for recent and planned space missions typically includes quaternion...
For spacecraft conducting on-orbit operations, changes to the structure of the spacecraft are not un...
Attitude determination is a major element of the operation and maintenance of a spacecraft. There ar...
Satellite attitude determination by simulation program using Monte Carlo sampling and Kalman-Schmidt...
This paper mainly focuses on the maneuver of the satellite in orbit. A non-linear multi-inputs multi...
Given a valid system model and adequate observability, a Kalman filter will converge toward the true...
Attitude determination has been considered as a permanent topic of active research and perhaps remai...
Partial differential equations used to correct values of orbital elements for satellites in near ear...
Computer program for determining attitude of orbiting vehicle using Kalman filte
Computer simulation results of attitude estimation of Earth-orbiting satellites (including Space Tel...
An adaptive Kalman filter design that utilizes recursive maximum likelihood parameter identification...
In this paper, a comprehensive comparison of two robust estimation techniques namely, compensated cl...
A weighted least-squares recursive estimator program is reported for simulating spacecraft orbital p...
Methods of determining satellite orbit and attitude parameters are considered. The Goddard Trajector...
Prediction Algorithms for the Attitude Estimator The attitude estimator is an extended Kalman filte...
Precision attitude determination for recent and planned space missions typically includes quaternion...
For spacecraft conducting on-orbit operations, changes to the structure of the spacecraft are not un...
Attitude determination is a major element of the operation and maintenance of a spacecraft. There ar...
Satellite attitude determination by simulation program using Monte Carlo sampling and Kalman-Schmidt...
This paper mainly focuses on the maneuver of the satellite in orbit. A non-linear multi-inputs multi...
Given a valid system model and adequate observability, a Kalman filter will converge toward the true...
Attitude determination has been considered as a permanent topic of active research and perhaps remai...
Partial differential equations used to correct values of orbital elements for satellites in near ear...
Computer program for determining attitude of orbiting vehicle using Kalman filte