Modeling SMAP Spacecraft Attitude Control Estimation Error Using Signal Generation Model

2016 ◽  
Author(s):  
Farheen Rizvi
Keyword(s):  
Attitude Control ◽  
Estimation Error ◽  
Signal Generation ◽  
Spacecraft Attitude ◽  
Generation Model ◽  
Spacecraft Attitude Control

scholarly journals Deep Generative Models-Based Anomaly Detection for Spacecraft Control Systems

Sensors ◽  
2020 ◽  
Vol 20 (7) ◽  
pp. 1991
Author(s):  
Hyojung Ahn ◽  
Dawoon Jung ◽  
Han-Lim Choi
Keyword(s):  
Neural Network ◽  
Control System ◽  
Control Systems ◽  
Attitude Control ◽  
Bayesian Optimization ◽  
Series Data ◽  
Spacecraft Attitude ◽  
Generation Model ◽  
Spacecraft Attitude Control ◽  
Attitude Control System

A spacecraft attitude control system provides mechanical and electrical control to achieve the required functions under various mission scenarios. Although generally designed to be highly reliable, mission failure can occur if anomalies occur and the attitude control system fails to properly orient and stabilize the spacecraft. Because accessing spacecraft to directly repair such problems is usually infeasible, developing a continuous condition monitoring model is necessary to detect anomalies and respond accordingly. In this study, a method for detecting anomalies and characterizing failures for spacecraft attitude control systems is proposed. Herein, features are extracted from multidimensional time-series data of a simulation of the attitude control system. Then, the artificial neural network learning algorithms based on two types of generation models are applied. A Bayesian optimization algorithm with a Gaussian process is used to optimize the hyperparameters for the neural network to improve the performance. The performance is evaluated based on the reconstruction error through the algorithm using the newly generated data not used for learning as input data. Results show that the detection performance depends on the operating characteristics of each submode in the operation scenarios and type of generation model. The diagnostic results are monitored to detect anomalies in operation modes and scenarios.

Retrospective cost adaptive spacecraft attitude control using control moment gyros

2014 ◽  
Author(s):  
Marc Camblor ◽  
Gerardo Cruz ◽  
Sergio Esteban ◽  
Fred A. Leve ◽  
Dennis S. Bernstein
Keyword(s):  
Attitude Control ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment

Spacecraft attitude control with mutating orbital rate and actuator fading under Markovian jump framework

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Chengxi Zhang ◽  
Hui-Jie Sun ◽  
Jin Wu ◽  
Zhongyang Fei ◽  
Yu Jiang ◽  
...  
Keyword(s):  
Control Problem ◽  
Attitude Control ◽  
Algorithm Design ◽  
Control Policy ◽  
Spacecraft Attitude ◽  
Actuator Faults ◽  
Spacecraft Attitude Control ◽  
Dynamics Model ◽  
Markovian Jump ◽  
Content Type

Purpose This paper aims to study the attitude control problem with mutating orbital rate and actuator fading. Design/methodology/approach To avoid malicious physical attacks and hide itself, the spacecraft may irregularly switch its orbit altitude within a specific range, which will bring about variations in orbital rate, thereby causing mutations in the attitude dynamics model. The actuator faults will also cause changes in system dynamics. Both factors affect the control performance. First, this paper determines the potential switching orbits. Then under different conditions, design controllers that can accommodate actuator faults according to the statistical law of actuator fading. Findings This paper, to the best of the authors’ knowledge, for the first time, introduces the Markovian jump framework to model the possible unexpected mutating of orbital rate and actuator fading of spacecraft and then designs a novel control policy to solve the attitude control problem. Practical implications This paper also provides the algorithm design processes in detail. A comparative numerical simulation is given to verify the effectiveness of the proposed algorithm. Originality/value This is an early solution for spacecraft attitude control with dynamics model mutations.

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