An Electrical Vortex Ergograph (EVE) is a popular experimental rig for vehicle performance test. The control and monitoring of the EVE device is of fundamental importance for safety concerns and economic reasons. The ...
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ISBN:
(纸本)7121002159
An Electrical Vortex Ergograph (EVE) is a popular experimental rig for vehicle performance test. The control and monitoring of the EVE device is of fundamental importance for safety concerns and economic reasons. The control of an EVE is often hampered by an effect that results from an interaction of the eddy current and the electromagnet, which often causes signal noising. For smooth controller action, a filtering of the recorded signals is therefore required. The on-line identification of related filters, however, is a time-critical issue. This paper introduces a computationally efficient filtering method to reduce the impact of the excessive measurement and process noise. The proposed filtering technique forms part of a hardware in loop simulation (HILS) and is applied to a laboratory scale experiment and then in the real system.
This work describes the strategy of a hybrid simulation program to be used in order to assess the performance of a satellite launcher system. The hybrid simulation starts with two simulation programs, one that simulat...
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This work describes the strategy of a hybrid simulation program to be used in order to assess the performance of a satellite launcher control system. The hybrid simulation starts with two simulation programs, one that...
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This work describes the strategy of a hybrid simulation program to be used in order to assess the performance of a satellite launcher control system. The hybrid simulation starts with two simulation programs, one that simulates the on board computer with control laws and the other that simulates the rest of the system. After validation of these two programs the hardware interfaces are then included. After a new validation, the real actuators are included in the system, and finally the real sensors are included. So in the final phase only the vehicle dynamics is simulated digitally, and as this is the most real condition possible before the real flight, it represents the best condition to assess the flight control system performance and to detect possible problems not clear at the design phase. The work describes mainly the method used in order to obtain a very reliable hybrid simulation program for a satellite launcher control system.
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