A Martian Upper Atmospheric Wind Field and Density Retrieval Method Based on Entering the Ball

An atmospheric wind field and sphere technology, applied in instrumentation, design optimization/simulation, calculation, etc., can solve problems such as inversion of few wind field parameters, and achieve the effect of high-precision inversion, low cost, and simple resistance characteristics

Active Publication Date: 2022-05-24
BEIHANG UNIV
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Problems solved by technology

[0011] In addition, in the past, most detections of Martian atmospheric parameters were limited to the electron concentration of the Martian ionosphere and the density of the Martian atmosphere, and few studies on the inversion of wind field parameters were involved.

Method used

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  • A Martian Upper Atmospheric Wind Field and Density Retrieval Method Based on Entering the Ball
  • A Martian Upper Atmospheric Wind Field and Density Retrieval Method Based on Entering the Ball
  • A Martian Upper Atmospheric Wind Field and Density Retrieval Method Based on Entering the Ball

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Embodiment Construction

[0117] The following will be combined with the figure 1 and technical solutions, the specific implementation process of the present invention will be further described in detail.

[0118] Step 1: Obtain the atmospheric drag acceleration component of the spherical system

[0119] Using the initial estimated value of the accelerometer scale factor to correct the measurement deviation, the more accurate atmospheric drag acceleration under the spherical system is obtained.

[0120]

[0121] where κ is the scaling factor, b is the bias, and n is the noise.

[0122] This step corresponds to the figure 1 in the middle column of the second box.

[0123] Step 2: Determine the trajectory attitude of the ball

[0124] First give the update equations for position and velocity:

[0125]

[0126] Among them, g(r e ) is calculated by the Mars gravitational field model, a e It is measured by the accelerometer, e represents the Mars fixed coordinate system, and i is the inertial c...

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Abstract

The invention provides a method for retrieving wind field and density of upper atmosphere of Mars with higher precision. The specific implementation method is to construct the relationship between the acceleration of atmospheric resistance entering the sphere and the parameters such as atmospheric wind speed and density, and use inertial components such as accelerometers and gyroscopes to jointly determine the trajectory and attitude parameters of entering the sphere, based on the atmospheric resistance measured by the accelerometer The direction realizes the inversion of atmospheric wind field parameters, and realizes the inversion of atmospheric density based on the modeling of atmospheric resistance modulus and atmospheric resistance coefficient. The present invention has the advantages of high precision and low cost. The payload only includes a three-axis accelerometer and a gyroscope. High-precision results can be obtained based on high-precision data given by precision instruments. It can be realized based on a micro-nano satellite platform. On this basis, a micro-nano-satellite detection constellation can be established to achieve full-coverage detection of the upper atmosphere of Mars.

Description

technical field [0001] The invention provides a high-precision Martian upper atmosphere wind field and a density inversion method, which involves using inertial components such as an accelerometer and a gyroscope to determine its trajectory and attitude parameters, and atmospheric resistance measured based on the accelerometer. A series of methods to achieve atmospheric wind field parameter inversion and atmospheric density inversion based on atmospheric drag model value and drag coefficient modeling. It belongs to the field of aerospace technology. Background technique [0002] The study of the Martian atmosphere is of great significance for future Mars exploration activities. The Martian atmospheric wind field and density are important parameters for establishing the flight dynamics model of the Mars orbiter, lander and future Mars aircraft. They are the basic input parameters of the Mars entry vehicle. The error directly affects the aerodynamic layout and thermal protect...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/28G06F113/08G06F119/14
CPCG06F30/28G06F2113/08G06F2119/14
Inventor 孙秀聪李萧耿铖陈培
Owner BEIHANG UNIV
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