Attitude Determination and Control Subsystem Hardware in the Loop Test on Air Bearing Trolley

2006 ◽  
Author(s):  
Warren Soh ◽  
Norhizam Hamzah ◽  
Willem Steyn
Keyword(s):  
Attitude Determination ◽  
Air Bearing ◽  
Hardware In The Loop ◽  
Control Subsystem ◽  
And Control

scholarly journals Three-axis air-bearing based platform for small satellite attitude determination and control simulation

2005 ◽  
Vol 3 (03) ◽  
Author(s):  
J. Prado ◽  
G. Bisiacchi ◽  
L. Reyes ◽  
E. Vicente ◽  
F. Contreras ◽  
...  
Keyword(s):  
Attitude Control ◽  
Attitude Determination ◽  
Center Of Mass ◽  
Measurement Unit ◽  
Simulation Platform ◽  
Air Bearing ◽  
Small Satellites ◽  
Main Components ◽  
Free Environment ◽  
And Control

A frictionless environment simulation platform, utilized for accomplishing three-axis attitude control tests in small satellites, is introduced. It is employed to develop, improve, and carry out objective tests of sensors, actuators, and algorithms in the experimental framework. Different sensors (i.e. sun, earth, magnetometer, and an inertial measurement unit) are utilized to assess three-axis deviations. A set of three inertial wheels is used as primary actuators for attitude control, together with three mutually perpendicular magnetic coils intended for desaturation purposes, and as a backup control system. Accurate balancing, through the platform’s center of mass relocation into the geometrical center of the spherical air-bearing, significatively reduces gravitational torques, generating a virtually torque-free environment. A very practical balancing procedure was developed for equilibrating the table in the local horizontal plane, with a reduced final residual torque. A wireless monitoring system was developed for on-line and post-processing analysis; attitude data are displayed and stored, allowing properly evaluate the sensors, actuators, and algorithms. A specifically designed onboard computer and a set of microcontrollers are used to carry out attitude determination and control tasks in a distributed control scheme. The main components and subsystems of the simulation platform are described in detail.

Closed Loop Dynamic Testing of The Intelsat V Attitude Determination and Control Subsystem Hardware

1979 ◽  
Vol 12 (4) ◽  
pp. 383-404
Author(s):  
H. Bittner ◽  
E. Brüderle ◽  
Α. Brauch ◽  
H. Pfefferl ◽  
A. Scheit ◽  
...  
Keyword(s):  
Closed Loop ◽  
Attitude Determination ◽  
Dynamic Testing ◽  
Control Subsystem ◽  
And Control

CLOSED LOOP DYNAMIC TESTING OF THE INTELSAT V ATTITUDE DETERMINATION AND CONTROL SUBSYSTEM HARDWARE

1980 ◽  
pp. 383-404 ◽  
Author(s):  
H. Bittner ◽  
E. Brüderle ◽  
A. Brauch ◽  
H. Pfefferl ◽  
A. Scheit ◽  
...  
Keyword(s):  
Closed Loop ◽  
Attitude Determination ◽  
Dynamic Testing ◽  
Control Subsystem ◽  
And Control

scholarly journals Microsatellite Attitude Determination and Control Subsystem Design and Implementation: Software-in-the-Loop Approach

2014 ◽  
Vol 2014 ◽  
pp. 1-12 ◽  
Author(s):  
Ho-Nien Shou
Keyword(s):  
Angular Velocity ◽  
Normal Mode ◽  
Attitude Control ◽  
Attitude Determination ◽  
Control Method ◽  
Measurement Data ◽  
Low Earth Orbit ◽  
Control Subsystem ◽  
Institute Of Technology ◽  
And Control

The paper describes the development of a microsatellite attitude determination and control subsystem (ADCS) and verification of its functionality by software-in-the-loop (SIL) method. The role of ADCS is to provide attitude control functions, including the de-tumbling and stabilizing the satellite angular velocity, and as well as estimating the orbit and attitude information during the satellite operation. In Taiwan, Air Force Institute of Technology (AFIT), dedicating for students to design experimental low earth orbit micro-satellite, called AFITsat. For AFITsat, the operation of the ADCS consists of three modes which are initialization mode, detumbling mode, and normal mode, respectively. During the initialization mode, ADCS collects the early orbit measurement data from various sensors so that the data can be downlinked to the ground station for further analysis. As particularly emphasized in this paper, during the detumbling mode, ADCS implements the thrusters in plus-wide modulation control method to decrease the satellite angular velocity. ADCS provides the attitude determination function for the estimation of the satellite state, during normal mode. The three modes of microsatellite adopted Kalman filter algorithm estimate microsatellite attitude. This paper will discuss using the SIL validation ADCS function and verify its feasibility.

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