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

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.

2020 ◽  
Vol 21 (4) ◽  
pp. 249-256
Author(s):  
A. I. Zavedeev

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. 


2008 ◽  
Vol 15 (3-4) ◽  
pp. 395-402 ◽  
Author(s):  
G.T. Conti ◽  
L.C.G. Souza

Future space missions will involve satellites with great autonomy and stringent pointing precision, requiring of the Attitude Control Systems (ACS) with better performance than before, which is function of the control algorithms implemented on board computers. The difficulties for developing experimental ACS test is to obtain zero gravity and torque free conditions similar to the SCA operate in space. However, prototypes for control algorithms experimental verification are fundamental for space mission success. This paper presents the parameters estimation such as inertia matrix and position of mass centre of a Satellite Attitude Control System Simulator (SACSS), using algorithms based on least square regression and least square recursive methods. Simulations have shown that both methods have estimated the system parameters with small error. However, the least square recursive methods have performance more adequate for the SACSS objectives. The SACSS platform model will be used to do experimental verification of fundamental aspects of the satellite attitude dynamics and design of different attitude control algorithm.


Author(s):  
S.Ye. Somov ◽  
◽  
T.Ye. Somova ◽  
◽  

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.


2020 ◽  
Vol 2020 ◽  
pp. 1-17
Author(s):  
Janusz Narkiewicz ◽  
Mateusz Sochacki ◽  
Bartłomiej Zakrzewski

A generic model of a nanosatellite attitude control and stabilization system was developed on the basis of magnetorquers and reaction wheels, which are controlled by PID controllers with selectable gains. This approach allows using the same architectures of control algorithms (and software) for several satellites and adjusting them to a particular mission by parameter variation. The approach is illustrated by controlling a satellite attitude in three modes of operation: detumbling after separation from the launcher, nominal operation when the satellite attitude is subjected to small or moderate disturbances, and momentum unloading after any reaction wheel saturation. The generic control algorithms adjusted to each mode of operation were implemented in a complete attitude control system. The control system model was embedded into a comprehensive simulation model of satellite flight. The simulation results proved the efficiency of the proposed approach.


Author(s):  
Shinya FUJITA ◽  
Yuji SATO ◽  
Toshinori KUWAHARA ◽  
Yuji SAKAMOTO ◽  
Yoshihiko SHIBUYA ◽  
...  

1974 ◽  
Author(s):  
J. NOTTI ◽  
A. CORMACK, III ◽  
W. KLEIN

1980 ◽  
Author(s):  
F. FLOYD ◽  
C. MUCH ◽  
N. SMITH ◽  
J. VERNAU ◽  
J. WOODS

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

Sign in / Sign up

Export Citation Format

Share Document