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A method of using micromachined gyroscope (mems) in deep space exploration

A micro-machined gyroscope, deep space exploration technology, applied in the direction of speed measurement, gyroscope/steering sensing device, measuring device, etc.

Active Publication Date: 2016-05-04
上海航天控制工程研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, micromechanical gyroscopes have not been used in deep space exploration. Therefore, it is necessary to propose a method for using micromechanical gyroscopes in deep space exploration.

Method used

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  • A method of using micromachined gyroscope (mems) in deep space exploration
  • A method of using micromachined gyroscope (mems) in deep space exploration
  • A method of using micromachined gyroscope (mems) in deep space exploration

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Embodiment Construction

[0013] Such as figure 1 Shown is a block diagram of the zero calibration test of the present invention. To use micromechanical gyroscopes in deep space exploration, it is first necessary to carry out a high and low temperature calibration test of the gyroscope zero position, connect the calibration test equipment, install the gyroscope on the tooling and put it in a temperature control box with a turntable, so that the gyroscope sensitive axis is Placed in east-west orientation. When the temperature control box reaches each set temperature point and keeps warm for 3 hours, measure and save a set of signal output and thermistor output for no less than 5 minutes. 6 temperature points are a cycle, and the whole test has 4 cycles. Temperature stability of temperature control turntable: ±3°C, the rate of temperature change is not less than 1°C / min. Take 6 temperature points within the working temperature range for testing, keep warm for 2 hours at each temperature point, and tak...

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Abstract

The invention discloses a method for using a micromechanical gyroscope (MEMS) (Micro-electromechanical System) in deep space exploration. Aiming at the characteristics that the zero position of the micromechanical gyroscope is changed along with temperature (temperature drift) and is changed along with time (year drift), the method comprises the following steps of firstly fitting a gyroscope zero position coefficient in a ground calibration test and secondly providing an on-track compensation algorithm. Compared with the prior art, the method provides a novel sensor for deep space exploration, has great advantages in weight, size, power consumption and the like, and has strong practical popularization values.

Description

technical field [0001] The invention relates to a method of using a micromechanical gyroscope (MEMS) in deep space exploration. In order to meet the requirements of deep space detectors for the weight, volume and power consumption of a stand-alone attitude control system, quartz microcomputers are used for the first time in domestic deep space exploration. A mechanical gyroscope is used as an angular velocity measurement device. The zero position of the micromechanical gyro changes with temperature (temperature drift) and with time (annual drift). A related on-orbit compensation algorithm has been developed to meet the requirements of the attitude control system of deep space probes. Background technique [0002] Domestically developed Mars probes need to perform rate damping, capture the sun, and establish initial attitude when performing Mars exploration missions. The Mars probe has strict requirements on the quality of the entire star, and it is necessary to optimize the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C19/00G01C25/00
Inventor 尹海宁袁彦红聂章海蔡陈生李芳华沈怡颹刘振刚
Owner 上海航天控制工程研究所