| Popis: |
The most important way to improve the satellite is to create more precise, easy, reliable and durable satellite attitude determination and control systems (ADCS). This is provided by a sustained progress, currently, observed in the area of the sensors and executive bodies. Thus, improving the reliability and quality of the newly created satellite ADCS, requires repeated debugging and testing work. To provide this work it is necessary to create laboratory benches and complexes using HIL (hardware-in-the-loop) simulation methods. The basic principle of such laboratory benches and systems is to simulate the input action on ADCS sensor in accordance with the calculated values, similar to the angular motion of the satellite. Thus, an efficiency of using such stands and complexes, while testing the satellite ADCS, depends directly on the environmental fidelity of its functioning, which, in turn, requires high fidelity of environment action on the ADCS sensing elements in accordance with the calculated values, similar to the angular motion of the real satellite. To date, to conduct ground tests of the satellite ADCS there is a complex modeling stand in JSC "ISS". It comprises a variety of test equipment, including a stand to simulate the angular motion of the satellite, i.e. a three-axis simulator of motion, built on the three-gimbal suspension with integrating rotary drives.The article consists of two sections. The first section presents in detail the requirements for control of a three-axis motion simulator to carry out dynamic tests of the satellite ADCS on the complex modeling stand. The second one gives quite detailed description of the synthesis strategy of a positional control of the tri-axial motion simulator based on the system invariance as related to the reference variable. The article shows main advantages of the proposed algorithm of control.In conclusion, the article shows that, when using a control algorithm of developed tri-axial motion simulator based on the invariance, the total error of the simulating limit performance of the satellite ADCS reference variable does not exceed the requirements-specified error. The feature of the given algorithm is that it is easy implemented, as well as is capable to vary the control parameters both gain and discreteness on time, without disturbing the invariance conditions. |
