Research And Implementation Of Attitude Measurement Of Aircraft System Based On Mini-AHRS Sensors

Electronic mechanical system tends to miniaturization in the rapid development of microelectronic change rapidly, because of its small volume, low power consumption, high performance and strong anti interference is widely used in the field of measurement and control. This paper aims to design a device based on micro AHRS (Mini-AHRS) spacecraft attitude measurement system, inertial measurement unit output data for vehicle navigation information, realize the measurement and control of spacecraft attitude can be real-time acquisition of the raw data.This paper first introduces the basic theory of the inertial system and the basic working principle, including the transformation between the coordinate system definition and inertial coordinate system, and the basic principle of gyro and accelerometer is introduced.Based on the three kinds of sensors in the inertial measurement unit (gyroscope, accelerometer and magnetometer) analysis of the working principle and performance index, the error sources of data measurement, and according to the system accuracy, measuring range and cost factors, choice of the Mini-AHRS devices as the inertial measurement unit. This paper describes in detail the implementation scheme of hardware and software of the system. The system hardware is composed of inertial measurement unit, a microprocessor (DSP),RS-485serial communication interface and some peripheral auxiliary equipment. The software takes PC as the carrier, through the LabVIEW NI based on a graphical programming language, using its powerful software function superior, realize the collection, processing, calculation, conversion and display for the Mini-AHRS measurement information.