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Accelerometer uncertainty analysis method based on arbitrary chaotic polynomial

A chaotic polynomial and uncertainty technology, applied in the field of inertial navigation, can solve problems such as large dispersion, achieve the effects of uncertainty optimization, improve pass rate, and wide application range

Active Publication Date: 2019-08-27
XIAN FLIGHT SELF CONTROL INST OF AVIC +1
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AI Technical Summary

Problems solved by technology

[0004] In the actual assembly process of the accelerometer, there are multi-source uncertain factors such as inconsistent adhesive bonding area and the number of air bubbles in the adhesive, resulting in a relatively large dispersion of the accelerometer bias output. Follow-on applications such as inertial guidance pose challenges

Method used

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  • Accelerometer uncertainty analysis method based on arbitrary chaotic polynomial
  • Accelerometer uncertainty analysis method based on arbitrary chaotic polynomial
  • Accelerometer uncertainty analysis method based on arbitrary chaotic polynomial

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Embodiment Construction

[0071] figure 1 The flowchart of the method for analyzing the uncertainty of the accelerometer based on arbitrary chaotic polynomials according to the present invention is shown.

[0072] Such as figure 1 As shown, a kind of accelerometer uncertainty analysis method based on arbitrary chaotic polynomial provided by the present invention comprises the following steps:

[0073] Step 1. Analysis figure 2 Uncertainty factors in the assembly process of the shown accelerometer;

[0074] Combined with the actual assembly process and the experience of engineers, analyze and obtain the uncertain factors in the accelerometer assembly process, such as image 3 As shown, they are: the equivalent modulus of the adhesive, the bonding angle between the aluminum material and the copper material, the bonding angle between the aluminum material and the silicon material, the bonding angle between the tungsten material and the copper material, the bonding angle between the tungsten material a...

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Abstract

The invention belongs to the technical field of inertial navigation, and discloses an accelerometer uncertainty analysis method based on an arbitrary chaotic polynomial. The method comprises the stepsof analyzing the uncertain factors existing in the accelerometer assembling process, establishing an accelerometer uncertainty analysis model, obtaining the statistical moment information of the uncertain parameters through statistical analysis according to the existing experimental data and the engineering experience, and solving the output mean value, variance, kurtosis and skewness of the biasvalue of the accelerometer based on an arbitrary chaotic polynomial method, and fitting the probability distribution outputted by the bias value of the accelerometer by adopting a maximum entropy principle. According to the method, the influence of the uncertain factors during the accelerometer assembling process on the offset output of the accelerometer is quantitatively evaluated, and the theoretical guidance is provided for the subsequent optimization of the accelerometer assembling process and structure so as to improve the accelerometer percent of pass.

Description

technical field [0001] The invention relates to the technical field of inertial navigation, in particular to an accelerometer uncertainty analysis method based on arbitrary chaotic polynomials. Background technique [0002] Inertial navigation is a precision navigation technology with strong autonomy, high precision, safety and reliability. It has been widely used in many important fields such as aviation, aerospace, navigation, and high-speed rail. [0003] As the core component of inertial navigation and guidance systems, accelerometers are used to measure the linear motion of sensitive carriers in space in real time, so as to provide position and speed information for carrier navigation and guidance. Accelerometer performance is the most direct and important factor to determine the accuracy of inertial navigation and guidance systems. Therefore, modern high-precision inertial navigation and guidance systems have higher requirements for accelerometer performance (bias valu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 滕霖姜潮陈亮姚中洋叶坤
Owner XIAN FLIGHT SELF CONTROL INST OF AVIC
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