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Mars high-rise atmosphere wind field and density inversion method based on entry sphere

A sphere and mars technology, applied in instrumentation, electrical digital data processing, computer-aided design, etc., can solve problems such as inversion of few wind field parameters

Active Publication Date: 2021-02-05
BEIHANG UNIV
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  • Application Information

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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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  • Mars high-rise atmosphere wind field and density inversion method based on entry sphere
  • Mars high-rise atmosphere wind field and density inversion method based on entry sphere
  • Mars high-rise atmosphere wind field and density inversion method based on entry sphere

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Experimental program
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Embodiment Construction

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

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

[0119] The measurement deviation is corrected by using the initial estimated value of the accelerometer scale factor, and a more accurate atmospheric drag acceleration is obtained in the spherical body system.

[0120]

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

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

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

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

[0125]

[0126] Among them, g(r e ) is calculated by the Martian gravitational field model, a e Measured by the accelerometer, e represents the fixed coordinate system o...

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Abstract

The invention provides a high-precision Mars high-rise atmospheric wind field and density inversion method. The specific implementation method comprises the following steps: constructing a relationship between atmospheric resistance acceleration entering a ball and parameters such as atmospheric wind speed and density, determining trajectory attitude parameters entering the ball by using inertialcomponents such as an accelerometer and a gyroscope, realizing atmospheric wind field parameter inversion based on an atmospheric resistance direction measured by the accelerometer, and performing modeling based on the atmospheric resistance modulus value and the atmospheric resistance coefficient to realize atmospheric density inversion. The method has the advantages of high precision and low cost; the effective load only comprises one three-axis accelerometer and one gyroscope, a high-precision result can be obtained based on high-precision data given by a precision instrument; the method can be realized based on a micro-nano satellite platform, a micro-nano satellite detection satellite group is established on the basis, and the full-coverage detection of the Mars high-rise atmosphere can be realized.

Description

technical field [0001] The present invention provides a high-precision Mars high-level atmospheric wind field and density inversion method, which involves the use of inertial components such as accelerometers and gyroscopes that enter the ball to determine its trajectory attitude parameters, and atmospheric resistance measured based on the accelerometer A series of methods for inversion of atmospheric wind field parameters and atmospheric density inversion based on atmospheric drag modulus 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 models of Mars orbiters, landers and future Mars aircraft, and are the basic input parameters for the Mars entry vehicle. The error directly affects the aerodynamic layout a...

Claims

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Application Information

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Patent Type & Authority Applications(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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