Method for measuring heading attitude of general aviation aircraft and small aircraft

Abstract

The invention discloses a method for measuring the heading attitude of a general aviation aircraft and a small aircraft. A data acquisition unit, a data processing unit and a data calibration unit are included; the data processing unit is composed of a single-chip microcomputer and a peripheral circuit thereof, the data calibration unit is an internal code of the single-chip microcomputer. The method comprises the following steps: S1, data acquisition: a three-axis acceleration sensor respectively acquires data of longitudinal acceleration, vertical acceleration and transverse acceleration; wherein the three-axis gyroscope is used for collecting data of the pitch rate, the rolling rate and the yaw rate. and temperature sensors are fixedly arranged on the side parts of the three-axis acceleration sensor and the three-axis gyroscope; S2, data processing; S3, data calibration compensation: the data calibration unit firstly screens the data after data processing, then performs temperature compensation on measured values of a three-axis acceleration sensor and a three-axis gyroscope, and then performs data calibration compensation, wherein data calibration compensation is divided into sensor calibration, type calibration and specific calibration.

Description

technical field [0001] The invention belongs to the field of aviation flight, and more specifically, the invention relates to a method for measuring the attitude of general aviation aircraft and small aircraft. Background technique [0002] Heading attitude information is an important flight parameter of the aircraft, which is of great significance to the normal operation of the aircraft. The current commonly used navigation and attitude systems mainly include inertial navigation, attitude system, integrated navigation, attitude system and strapdown navigation, attitude system. Among them, inertial navigation, attitude system, integrated navigation, and attitude system are complex and The cost is too high to be applied on a large scale; and the strapdown navigation and attitude system have huge advantages in aircraft applications because they use a digital platform instead of a physical platform. [0003] However, the accuracy of strapdown navigation and heading system is p...

AI Technical Summary

Problems solved by technology

[0003] However, the accuracy of strapdown navigation and heading system is poor due to calculation errors and sensory data are susceptible to environmental interference

At present, the commonly used attitude calculation methods include complementary filter attitude calculation algorithm, attitude calculation algorithm based on gradient descent method, attitude calculation algorithm based on Kalman filter, and particle filter attitude calculation algorithm. These algorithms may have poor accuracy. Or the algorithm is complex and has poor real-time performance, which is difficult to apply on the aircraft

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