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Attitude detection and control system of aircraft

A control system and aircraft technology, applied in the direction of attitude control, etc., can solve the problem of unsuitable accelerometer, achieve high precision and accuracy, and solve the effect of noise interference and optimal attitude estimation

Inactive Publication Date: 2014-05-21
姜韫英
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the accelerometer is not suitable for the measurement of short-term attitude angle

Method used

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  • Attitude detection and control system of aircraft

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Embodiment Construction

[0012] As shown in the figure, the present invention includes an X-axis gyroscope, a Y-axis gyroscope, a three-axis acceleration sensor, a first filter circuit, a second filter circuit, a microcontroller, and a bus interface. The microcontroller is connected to the three-axis acceleration sensor, The first filter circuit, the second filter circuit, and the bus interface are connected, the first filter circuit is connected with the X-axis gyroscope, and the second filter circuit is connected with the Y-axis gyroscope.

[0013] The microcontroller is STM32F103.

[0014] The three-axis acceleration sensor is MMA7260.

[0015] The present invention takes the 32-bit single-chip microcomputer STM32F103 as the core, adopts the gyroscope (ENC-03) and the acceleration sensor (MMA7260) as the attitude angle feedback, and sends the measured accurate attitude angle to the upper computer for display through the RS232 serial bus. The whole system is composed of acceleration sensor,...

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Abstract

Disclosed in the invention is an attitude detection and control system of an aircraft. More specifically, the invention, which belongs to the technical field of the control system, especially relates to an attitude detection and control system of an aircraft, wherein the system has the high precision and accuracy. The attitude detection and control system is composed of an X axis gyroscope, a Y axis gyroscope, a three-shaft acceleration sensor, a first filter circuit, a second filter circuit, a micro controller, and a bus interface; and the key points of the structure are as follows: the micro controller is respectively connected with the three-shaft acceleration sensor, the first filter circuit, the second filter circuit, and the bus interface; the first filter circuit is connected with the X axis gyroscope; and the second filter circuit is connected with the Y axis gyroscope.

Description

technical field [0001] The invention belongs to the technical field of control systems, in particular to an aircraft attitude detection and control system. Background technique [0002] MEMS inertial sensors have the advantages of small size, light weight, low power consumption, fast startup, low cost, and high reliability. Therefore, the miniaturized attitude measurement system based on MEMS sensors has become the first choice for aerial photography of unmanned aerial vehicles. Accurate and real-time acquisition of the attitude angle of the aircraft in the air is the key to determining the control accuracy and system stability. However, in the aerial survey system composed of low-cost MEMS inertial sensors, the micro-mechanical gyroscope is affected by factors such as temperature and mechanical vibration. . There is a large static drift error, and the long-time integration will cause the attitude angle to diverge, so it is not suitable for the determination of the long-ter...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 姜韫英傅乃文
Owner 姜韫英