Aircraft posture control system

An attitude control and aircraft technology, applied in attitude control and other directions, can solve problems such as the inapplicability of accelerometers, achieve high precision and accuracy, and solve the effects of noise interference and optimal attitude estimation problems

Inactive Publication Date: 2015-05-27
惠铁军
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

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

Method used

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  • Aircraft posture control system

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Embodiment Construction

[0010] As shown in the figure, the present invention includes a sensor, a memory, a delay determination module, a calibration module, a filter circuit, an oscillator, a trigger, a timer and a power supply, and is characterized in that: a sensor and a filter, a memory, a delay determination module, The calibration module, the filter circuit, the oscillator and the trigger are connected in sequence; the filter circuit is connected with the oscillator and the trigger, the oscillator is connected with the power supply, and the trigger is connected with the timer.

[0011] As a preferred solution, the processor of the present invention is a STM32F103 single-chip microcomputer.

[0012] 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 bu...

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Abstract

The invention discloses an aircraft posture control system, belongs to the field of control systems, in particular relates to improvement of an aircraft posture control system, and provides an aircraft posture control system which is small in error, low in noise and precise in control. The aircraft posture control system comprises a sensor, a memory, a time-delay judgment module, a calibration module, a filter circuit, an oscillator, a trigger, a timer and a power supply. The aircraft posture control system is characterized in that the sensor is connected with a filter, the memory, the time-delay judgment module, the calibration module, the filter circuit, the oscillator and the trigger in sequence; the filter circuit is connected with the oscillator and the trigger; the oscillator is connected with the power supply; the trigger is connected with the timer.

Description

technical field [0001] The invention belongs to the field of control systems, and in particular relates to an improvement of an aircraft attitude 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, due to the influence of temperature, mechanical vibration and other factors . There is a large static drift error, and long-time integration will cause the divergence of the attitude angle, so it is not suitable for the determination of the long-term attitude angle...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 惠铁军
Owner 惠铁军
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