Increasing of Reliability of Spacecraft Control System on Base of Robust Diagnostic Models and Division Principle in Parity Space

2020 ◽  
Vol 21 (4) ◽  
pp. 249-256
Author(s):  
A. I. Zavedeev
Keyword(s):  
Control System ◽  
Attitude Control ◽  
High Reliability ◽  
System Model ◽  
Diagnostic Systems ◽  
Attitude Control System ◽  
Spacecraft Control ◽  
Mathematical System ◽  
Diagnostic Models ◽  
Parity Space

Different directions of creation high reliability integrate spacecraft control system are discussed on base of robust diagnostic models and division principle in parity space. Problems of synthesis spacecraft control system algorithms are examined with incomplete apriory and distorted current information, action of uncontrolled and random factors, information losses and equipment failures. The structure of onboard attitude control system is synthesized and control algorithms are chosen, which guarantee robust stability and failure stability in presence indignant factors and obstacles. An instrumental structure and operational modes of spacecraft attitude control system are described. Methods of dynamic research, computer technology and modeling particularities are indicated. Diagnostic and reconfiguration algorithms for onboard complex of connection, navigation, geodesy satellites and earth inspectoral satellite in prolonged space flight utilization are proposed. Testing procedure is contains two stage: discovering and eliminating faults. Given mathematical system model is researched by means of difference signals, which forms with arise at fault emergence. The failure character is established by deciding rules on base difference signals and measures to it eliminating are took. Questions of onboard spacecraft control system failure stable improving are discussed on base principle reconfiguration with apply to adaptive logic in testing and diagnostic algorithms. The mathematical system model is researching with implementation of analytic reserving. Difference signals are formed, which arise at fault appearance. The adaptive approach to development testing and diagnostic systems provide for realization of flexible logic of control system function to take into account factual onboard equipment state. Special attention is devote to problem influence liquid fuel reactive engine agility on spacecraft control attitude system dynamic characteristics and precision. The effectiveness of prepositional approaches and algorithms is confirmed by mathematical modeling results for several actual technical systems. Recommendations to their practical applications are given. 

Construction of Highfailurestable Spacecraft Control System with Apply to Adaptive Logic in Diagnostic and Testing Algorithms

2018 ◽  
Vol 19 (10) ◽  
pp. 664-672 ◽  
Author(s):  
A. I. Zavedeev
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Control Algorithms ◽  
Signal Loss ◽  
Diagnostic Systems ◽  
Adaptive Logic ◽  
Attitude Control System ◽  
Spacecraft Control ◽  
Practical Applications ◽  
Testing Algorithms

Different approaches to problem of improving onboard spacecraft control system failurestable on base principles of analytical excess, optimization and reconfiguration with using probability index and adaptive logic in diagnostic and testing algorithms are considered. One of problem is synthesis of spacecraft control system algorithms with incomplete apriory and distorted current information, action of uncontrolled and random factors, equipment failures and signal loss in information channel. Ways of failure diagnostic are examinated, in particular, problem excluding of failures sensors and power drives. Onboard attitude control system is synthesized and control algorithms are chosen, which guarantee robust stability and failure stability in presence indignant factors. Questions of onboard spacecraft control system failurestable improving are discussed on base reconfiguration with apply to adaptive logic in diagnostic and testing algorithms. The features of simulation are described on instrumental structure and operational modes of the attitude control system, the methods of dynamic research and computer simulation utilized during designing are indicated. Onboard complex control algorithms, diagnostic and reconfiguration are proposed for navigation, communication, geodesy satellites and earth inspectoral vehicles with prolonged utilization (more 10 years) in space flight conditions. Testing system have to decide two problem: discovering and eliminating faults. The mathematical system model is researching with implementation of analytic reserving. Difference signals are formed, which arise at fault appearance. The failure character is established by deciding rules on base difference signals and measures to it eliminating are took. The adaptive approach to development testing and diagnostic systems provide for realization of flexible logic of control system function to take into account factual onboard equipment state. The effectiveness of prepositional approaches and algorithms is confirmed by mathematical modeling results for several actual technical systems. Recommendations to their practical applications are gave.

A Global Fast Integral Operator Terminal Adaptive Sliding-Mode Controller

2012 ◽  
Vol 190-191 ◽  
pp. 880-885
Author(s):  
Lu Cao ◽  
Xiao Qian Chen ◽  
Yong Zhao
Keyword(s):  
Control System ◽  
Integral Operator ◽  
Attitude Control ◽  
High Performance ◽  
Sliding Mode ◽  
High Reliability ◽  
Sliding Mode Controller ◽  
Limited Time ◽  
Attitude Control System ◽  
Adaptive Sliding Mode Controller

Attitude Control System(ACS); Terminal; Adaptive; Integral operator Abstract: Attitude Control System (ACS) with high performance, high precision, and high reliability is the kernel technology of the research of spacecraft, which directly affects the whole performance of spacecraft. Hence, a global fast integral operator Terminal adaptive sliding-mode controller is proposed to come true the high performance control. The theory of this controller is to introduce the limited time mechanics—Terminal mode to the sliding-mode control and introduce the integral operator to the sliding-mode plane, which can realize the convergence of spacecraft attitude in “limited time” in the condition of serious disturbance , in order to enhance the performance of fast response. At last, the simulation results demonstrate the high reliability and advantages of the control approach.

scholarly journals ENSURING THE SURVIVABILITY OF SPACECRAFT CONTROL SYSTEM AT CRITICAL FAILURES OF REACTION WHEELS

2021 ◽  
Vol 23 (2) ◽  
pp. 66-74
Author(s):  
S.Ye. Somov ◽  
◽  
T.Ye. Somova ◽  
◽  
Keyword(s):  
Computer Simulation ◽  
Control System ◽  
Attitude Control ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
General Electric ◽  
Attitude Control System ◽  
Spacecraft Control ◽  
The Earth ◽  
Magnetic Drive

A method for ensuring the survivability of the spacecraft attitude control system with a minimally redundant cluster of flywheels by General Electric scheme and a magnetic drive in the event of the flywheels' failures is presented. The results of computer simulation were obtained and it was found that in case of failure of any two flywheels, the Earth survey satellite retains the ability to scanning observation given targets.

Double Fail-Safe Attitude Control System for Artificial Meteor Microsatellite ALE-1

2021 ◽  
Vol 19 (1) ◽  
pp. 9-16
Author(s):  
Shinya FUJITA ◽  
Yuji SATO ◽  
Toshinori KUWAHARA ◽  
Yuji SAKAMOTO ◽  
Yoshihiko SHIBUYA ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System ◽  
Fail Safe

Flight performance of the LES-8/9 three-axis attitude control system

1980 ◽  
Author(s):  
F. FLOYD ◽  
C. MUCH ◽  
N. SMITH ◽  
J. VERNAU ◽  
J. WOODS
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Flight Performance ◽  
Attitude Control System

Design of attitude control system for ASRTU microsatellite

2020 ◽  
Vol 28 (10) ◽  
pp. 2192-2202
Author(s):  
Feng WANG ◽  
◽  
Shi-bo NIU ◽  
Cheng-fei YUE ◽  
Fan WU ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Attitude Control System

scholarly journals Design, Ground Testing and On-Orbit Performance of a Sun Sensor Based on COTS Photodiodes for the UPMSat-2 Satellite

Sensors ◽  
2021 ◽  
Vol 21 (14) ◽  
pp. 4905
Author(s):  
Angel Porras-Hermoso ◽  
Daniel Alfonso-Corcuera ◽  
Javier Piqueras ◽  
Elena Roibás-Millán ◽  
Javier Cubas ◽  
...  
Keyword(s):  
Control System ◽  
Attitude Control ◽  
Response Curve ◽  
The Sun ◽  
Space Systems ◽  
Attitude Control System ◽  
Ground Testing ◽  
Sun Sensor ◽  
Early Results ◽  
Red Leds

This paper presents the development of the UPMSat-2 sun sensor, from the design to on-orbit operation. It also includes the testing of the instrument, one of the most important tasks that needs to be performed to operate a sensor with precision. The UPMSat-2 solar sensor has been designed, tested, and manufactured at the Universidad Politécnica de Madrid (UPM) using 3D printing and COTS (photodiodes). The work described in this paper was carried out by students and teachers of the Master in Space Systems (Máster Universitario en Sistemas Espaciales—MUSE). The solar sensor is composed of six photodiodes that are divided into two sets; each set is held and oriented on the satellite by its corresponding support printed in Delrin. The paper describes the choice of components, the electrical diagram, and the manufacture of the supports. The methodology followed to obtain the response curve of each photodiode is simple and inexpensive, as it requires a limited number of instruments and tools. The selected irradiance source was a set of red LEDs and halogen instead of an AM0 spectrum irradiance simulator. Some early results from the UPMSat-2 mission have been analyzed in the present paper. Data from magnetometers and the attitude control system have been used to validate the data obtained from the sun sensor. The results indicate a good performance of the sensors during flight, in accordance with the data from the ground tests.

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