Flight attitude determining method based on polarized light sensor

A measurement method and polarized light technology, applied in instruments, measuring devices, navigation through speed/acceleration measurement, etc., can solve problems such as increased heading error, easy to lose stars, and failure to provide heading angles

Active Publication Date: 2015-02-25
DALIAN UNIV OF TECH
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Problems solved by technology

However, the above two methods of measurement have their own shortcomings: the magnetometer of the first combination is easily affected by the surrounding magnetic field and other airborne electronic equipment, resulting in an increase in heading error; It cannot provide heading angle, and it is easy to lose stars during high maneuvering, which will also lead to an increase in heading error

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  • Flight attitude determining method based on polarized light sensor
  • Flight attitude determining method based on polarized light sensor
  • Flight attitude determining method based on polarized light sensor

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Embodiment Construction

[0031] The specific embodiments of the present invention will be further elaborated below in conjunction with the accompanying drawings and specific technical solutions.

[0032] Such as figure 1 As shown, the coordinate systems involved in the present invention include: horizon coordinate system, navigation coordinate system, body coordinate system, and polarized light sensor coordinate system. The navigation coordinate system is the northeast sky coordinate system, and in order to reduce the conversion between coordinate systems, the horizon coordinate system is selected to coincide with the navigation coordinate system, which is the northeast sky coordinate system, and the polarization sensor coordinate system coincides with the body coordinate system. Let the Y axis of the polarized light sensor coordinate system be its body axis, then the polarization azimuth angle ψ measured by the polarized light sensor pl is the angle between the projection of the maximum polarization...

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Abstract

The invention discloses a flight attitude determining method based on a polarized light sensor. According to the invention, adopted equipment comprises a three-axis gyroscope, a three-axis accelerometer, the polarized light sensor, a GPS and a flight control computer. A complementary filter algorithm is used to fuse sensor data; pitch angle and rolling angle errors of the angular speed of the gyroscope are revised through measured data of the accelerometer; and an course angle error of the angular speed of the gyroscope is revised through measured data of the polarized light sensor, so that the attitude measurement precision of an aircraft is improved. Compared with a traditional flight attitude reference system, the flight attitude determining method has the advantages that the flight attitude determining method is not interfered by electromagnetism, the measurement precision of static and dynamic environments is high and the like.

Description

technical field [0001] The invention belongs to the technical field of aircraft attitude measurement and estimation, and relates to a method for measuring attitude of an aircraft based on a polarized light sensor. Background technique [0002] Attitude Heading Reference System (AHRS) can provide heading angle, roll angle and pitch angle information for the aircraft. It is generally composed of multiple axial sensors. At present, there are two main combinations: one is composed of a three-axis gyroscope, a three-axis accelerometer and a three-axis magnetometer, and the other is composed of a three-axis gyroscope and a three-axis accelerometer. And GPS composition. However, the above two methods of measurement have their own shortcomings: the magnetometer of the first combination is easily affected by the surrounding magnetic field and other airborne electronic equipment, resulting in an increase in heading error; It cannot provide the heading angle, and it is easy to lose t...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/12G01C25/00
CPCG01C21/12G01C25/005
Inventor 金仁成华宗治芮杨陈文褚金奎孙会生
Owner DALIAN UNIV OF TECH
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