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A two-axis integrated gyro accelerometer and servo control method

An accelerometer and servo control technology, applied in the direction of using gyroscope for acceleration measurement, electric speed/acceleration control, etc., can solve the problems of gyro accelerometer measurement error, affecting the accuracy of instrument use, etc. Small volume, the effect of overcoming measurement errors

Active Publication Date: 2020-11-10
BEIJING INST OF AEROSPACE CONTROL DEVICES
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  • Claims
  • Application Information

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Problems solved by technology

And the disturbance torque M x , input acceleration a y and base angular velocity It will cause the measurement error of the gyro accelerometer, which will affect the accuracy of the instrument.

Method used

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  • A two-axis integrated gyro accelerometer and servo control method
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  • A two-axis integrated gyro accelerometer and servo control method

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Embodiment Construction

[0052] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0053] Such as figure 1 As shown, the present invention discloses a two-axis integrated gyro accelerometer and a servo control method. The two-axis integrated gyro accelerometer is composed of a meter head part, a servo loop part, an output part and a casing. The head part includes the gyro rotor with eccentric mass, table body, table shaft, frame and frame shaft, one end of the table body shaft is equipped with an angle sensor, the other end is equipped with a torque motor, one end of the frame shaft is equipped with an angle sensor, and the other end is Equipped with a torque motor. The servo loop part includes a loop in which the axis angle of the platform acts on the frame torque motor through the amplifier, and another loop in which the frame axis angle sensor acts on the torque motor in the platform through the amplifier. The output p...

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Abstract

The invention discloses a two-axis integrated gyroscope accelerometer and a servo control method. The gyroscope accelerometer comprises a header part, a servo loop part, an output part and a housing body. The header part comprises a gyro-rotor with eccentric mass, a bench body, a bench body shaft, a framework and a framework shaft. An angle sensor is installed on one end of the bench body shaft and a torque motor is installed on the other end. An angle sensor is installed on one end of the framework shaft and a torque motor is installed on the other end. The servo loop part comprises one loopwhere bench body shaft angle amplifier acts on the framework torque motor through the amplifier, and another loop where the framework angle sensor acts on the bench body torque motor through the amplifier. The output part comprises a current value acts on the two motors. The current values are acquired and output to an on-missile computer. According to the invention, it is achieved that accelerated speed in two directions is measured by one accelerometer.

Description

technical field [0001] The invention relates to a two-axis gyro accelerometer and a servo control method, in particular to an accelerometer for an inertial stable platform, which belongs to the field of aviation and aerospace for high-precision apparent acceleration measurement. Background technique [0002] In high-precision inertial stabilization platforms, quartz flexible accelerometers and pendulum integrating gyro accelerometers are mainly used at present, both of which are single-degree-of-freedom accelerometers, and each accelerometer is sensitive to apparent acceleration in one direction. [0003] Taking the Pendulum Integral Gyro Accelerometer (PIGA) as an example, it is a pendulum accelerometer that uses gyro torque for feedback. Its working principle is shown in the figure below. In the figure, OX 1 Y 1 Z 1 is the coordinate system fixed to the frame, OX 1 is the input axis; Oxyz is the Ley difference coordinate system, and the Oz axis coincides with the rotor...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01P15/14G05D13/62
CPCG01P15/14G05D13/62
Inventor 魏宗康周姣
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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