Design of Remote Virtual Testing System for Aircraft Attitude

Abstract

An integrative remote testing system of gyro was designed and implemented, subject to requirements such as fine real-time performance, high precision, high reliability, etc. The system is developed for physical simulation of remote wireless data acquisition for altitude information in aircraft navigation a control system and engineering application. In the testing system, rotary table was used to provide standard rate, FOG was testing criteria, and MEMS gyro was tested gyro. Butter worth low-pass filter combined with moving-average filter was also designed to smooth the output of these gyros. Testing and computing methods of main technical parameters such as scale factor, nonlinearity, max input rate, etc were analyzed and system modeling of gyro was carried out by identification method to enhance the accuracy of data acquisition. Within GSM mobile communication network, GPRS wireless terminal was used to acquire data of gyro testing remotely via Internet. Moreover, Virtual instrument techniques were used to testing functions such as data acquisition a processing of two gyros, data awaveform display, data printing a storage, etc. Besides, a buttery power supply system was designed. Experiment result shows that the testing system is able to acquire data remotely and tested parameters a gyro model can represent the actual state of tested gyro. Its accuracy a real-time performance as well as the power super subsystem meet the design requirements.