Thermal layer atmospheric density prediction method and system based on distributed sensing units

Abstract

The invention belongs to the technical field of atmospheric density sensing methods and space physics, and particularly relates to a hot layer atmospheric density prediction method based on distributed orbit atmospheric sensing units, which comprises the following steps: obtaining P distributed orbit atmospheric sensing units; in combination with an energy dissipation rate or semi-major axis attenuation, calculating an atmospheric density correction ratio of a track surface thermal layer where each distributed track atmospheric sensing unit is located; periodically and dynamically selecting the multiple space targets are uniformly distributed in the P distributed orbit atmosphere sensing units at different places; in all P distributed track atmosphere sensing units, calculating the atmospheric density of the space point of the space target on the corresponding orbital plane every 2-30 seconds; periodically acquiring a full-space atmospheric density data set {rhoO} within 3-24 hours; calculating a spherical harmonic coefficient, calculating the corrected inflection point temperature and escape layer temperature to form a thermal layer atmospheric density correction model, and obtaining the dynamically corrected thermal layer atmospheric density by using the correction model to predict the atmospheric density of any position in the future space.

Description

technical field [0001] The invention belongs to the field of atmospheric density sensing method and space physics technology, and in particular relates to a thermospheric atmospheric density prediction method and system based on a distributed orbital atmospheric sensing unit. Background technique [0002] High-precision orbital atmospheric prediction has important application value in space activities such as spacecraft orbit determination prediction and return capsule reentry landing point prediction. At present, thermospheric atmospheric models generally have errors of 15-30%, which are even greater during space weather events, which cannot meet the needs of high-precision thermospheric atmospheric prediction. [0003] In aerospace engineering, the method of estimating the drag coefficient to compensate for the error of the atmospheric model can meet the high-precision requirements of the spacecraft with orbit tracking data. Due to the local time, latitude and altitude ch...

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Problems solved by technology

Due to the local time, latitude and altitude characteristics of the thermospheric atmospheric model error, the above method does not have space scalability and cannot be extended to other orbiting spacecraft for application; and the special detection of the thermospheric atm

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