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Method for extracting atmospheric density based on SWARM-C satellite

An atmospheric density and satellite technology, which is applied in satellite radio beacon positioning systems, measuring devices, instruments, etc., can solve problems such as insufficient dynamics, and achieve the effect of superior dynamics and improved accuracy

Active Publication Date: 2019-05-17
UNIV OF ELECTRONIC SCI & TECH OF CHINA
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

However, the dynamics of this method are insufficient, and the atmospheric density obtained is the average atmospheric density of the satellite in a certain period of time

Method used

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  • Method for extracting atmospheric density based on SWARM-C satellite
  • Method for extracting atmospheric density based on SWARM-C satellite
  • Method for extracting atmospheric density based on SWARM-C satellite

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Embodiment

[0049] The purpose of the present invention is to measure the non-conservative acceleration of the satellite in orbit by using the on-board accelerometer of the satellite, and then calculate the atmospheric drag acceleration through the non-conservative acceleration to obtain the atmospheric density. Under the conditions that can be realized, the acceleration data correction is as accurate as possible, and the illumination radiation pressure model modeling is as perfect as possible, so that the calculated satellite atmospheric density will be more accurate. Therefore, the present invention provides a relatively accurate accelerometer calibration method, which adds the estimation of force and temperature parameters to the generalized least square method, removes the accelerometer error caused by temperature, and improves the accuracy of calibration results.

[0050] Below we combine figure 1 , a kind of atmospheric density extracting method based on SWARM-C satellite of the pre...

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Abstract

The invention discloses a method for extracting atmospheric density based on a SWARM-C satellite. Accelerometer data and GPS orbit data of the SAWRM-C satellite are obtained and then subjected to resampling and coordinate conversion; then a peak signal and a step signal in the accelerometer data are then removed; the accelerometer data are calibrated after data check is finished, deviation coefficient, proportional coefficient, and temperature coefficient in a calibration formula are estimated by a generalized least square method to obtain calibrated accelerometer data; then illuminating radiation pressure of a satellite received on an operating orbit of the satellite is subjected to modeling, and the acceleration caused by the illuminating radiation pressure is calculated, and the calibrated accelerometer data subtracts acceleration caused by the illuminating radiation pressure to obtain atmospheric drag acceleration; and in the end a product of damping coefficient of satellite operating in the orbit of the satellite and the effective area is calculated, and atmospheric density near the satellite orbit is calculated based on the atmospheric drag acceleration and the product of thedamping coefficient and the effective area.

Description

technical field [0001] The invention belongs to the technical field of aerospace and space climate, and more specifically relates to a method for extracting atmospheric density based on the SWARM-C satellite. Background technique [0002] The study of atmospheric density is of great significance, and it can be applied to precise orbit determination of different types of spacecraft or trajectory modeling of other flying objects in the universe. The precise orbit determination of a spacecraft needs to obtain the conservative force and non-conservative force it receives in space. The non-conservative force is mainly composed of atmospheric drag force and light radiation pressure, and the magnitude of atmospheric drag force is related to atmospheric density. Precise orbit determination and orbit prediction of satellites using atmospheric density can help low-orbit spacecraft extend their lifespan, help them return to orbit, analyze potential risks and send maneuver signals to sa...

Claims

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Application Information

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IPC IPC(8): G01N9/00G01S19/14G01S19/37
Inventor 杨波葛丽君闫新童刘珊曾庆川刘婷婷郑文锋
Owner UNIV OF ELECTRONIC SCI & TECH OF CHINA
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