Attitude measurement method and system based on dual-ultrasonic platform

A technology of dynamic measurement and attitude, which is applied in the direction of navigation and navigation calculation tools through velocity/acceleration measurement, which can solve the problem that the satellite attitude measurement method does not consider the kinematic characteristics of the measured object, and achieve the effect of high-precision attitude measurement

Active Publication Date: 2020-10-09
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

[0005] The traditional satellite attitude measurement method does not consider the kinematic characteristics of the measured object, and its measurement accuracy is determined by the measurement sensor and the joint attitude determination algorithm

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  • Attitude measurement method and system based on dual-ultrasonic platform
  • Attitude measurement method and system based on dual-ultrasonic platform
  • Attitude measurement method and system based on dual-ultrasonic platform

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Embodiment Construction

[0032] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0033] Such as figure 1 As shown, a kind of high-precision attitude measurement method based on double super-platform provided by the present invention is characterized in that, comprising:

[0034] Correction steps of star sensor equivalent noise angle:

[0035] The equivalent noise angle of the star sensor is corrected by using the gyro measurement data of the double super platform and the satellite orbit data.

[0036] Step 1: Collect the original measurement data of the star sensor, and obtain the...

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Abstract

The invention provides an attitude measurement method and system based on a double-super platform. The method comprises the steps: introducing kinematic characteristics into an attitude measurement model, carrying out the quasi-static attitude measurement through the double-super platform, and obtaining the measurement data of a star sensor; based on kinematic characteristics of a measured object,performing dynamic measurement error correction on measurement data of the star sensor by adopting a smooth filtering method; and combining the dynamic characteristics of the double-super platform, carrying out expansion solving on the measurement data of the star sensor according to a Taylor formula, carrying out inversion of an attitude change curve after smooth filtering, and carrying out segmented polynomial interpolation to obtain a high-precision measurement result in full space-time. The method is suitable for a high-precision and high-stability double-super platform, does not depend on a high-performance gyroscope, and can realize high-precision attitude measurement only by virtue of the star sensor.

Description

technical field [0001] The invention relates to the field of attitude kinematics, in particular to a high-precision attitude measurement method and system based on a double-super-platform. Background technique [0002] With the continuous development of the satellite field, the current satellite field has gradually changed from qualitative functional requirements to high-precision quantitative applications. Attitude measurement accuracy is one of the important indicators representing the comprehensive performance of satellites, which directly determines the quantitative application level of satellites. In order to meet the increasing technical requirements of space science in various fields such as measurement, meteorology, and national defense, it is necessary to carry out research on satellite high-precision attitude measurement methods. [0003] The attitude measurement accuracy of the satellite is mainly determined by the attitude sensor and high-precision attitude dete...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/18G01C21/20
Inventor 张伟周世宏宋效正郑京良王田野
Owner SHANGHAI SATELLITE ENG INST
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