A method for predicting aerodynamic characteristics of real gas environment in Martian atmosphere

A technology of aerodynamic characteristics and real gas, applied in design optimization/simulation, special data processing applications, instruments, etc., it can solve the problems that the gas effect cannot be completely simulated, and the equivalent value of specific heat ratio is not the same, so as to improve the value Accuracy, reduce time and cost, and improve the effect of calculation accuracy

Active Publication Date: 2020-07-14
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

The equivalent values ​​of the specific heat ratio obtained by the above methods are not the same, and they cannot fully simulate the real gas effect of the Mars probe in the Martian atmosphere. The calculation of the calculated aerodynamic and chemical non-equilibrium models of the Mars probe There is some difference between the results

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  • A method for predicting aerodynamic characteristics of real gas environment in Martian atmosphere
  • A method for predicting aerodynamic characteristics of real gas environment in Martian atmosphere
  • A method for predicting aerodynamic characteristics of real gas environment in Martian atmosphere

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Embodiment

[0050] Taking a Mars probe as an example, the typical hypersonic state of the Mars probe is assumed to be Ma=25.3. First, the chemical non-equilibrium model is used to predict the aerodynamic characteristics of the probe in the real gas environment of the Martian atmosphere, and the detection The flow field parameters of the vehicle at zero angle of attack and zero sideslip angle.

[0051] Figure 2(a) is the flow field diagram of the flow around the Mars rover under the conditions of hypersonic velocity, zero angle of attack, and zero sideslip angle calculated by using the chemical non-equilibrium model; Figure 2(b) is the flow field around the Mars rover Density changes before and after a normal shock in the field.

[0052] Figure 3(a) and Figure 3(b) show the gas temperature near the position of the normal shock wave on the symmetry axis of the detector, and the ratio of the local flow field density to the incoming flow density ρ / ρ ∞ Distribution. As shown in the figure, p...

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Abstract

The invention provides a prediction method for aerodynamic characteristics of actual gaseous environment of Mars atmosphere. The method is characterized by calculating a flow field under hypersonic velocity and zero-incidence of a Mars probe by using a chemical non-equilibrium model, extracting temperature at the position of normal shock waves and the mass percents of gas components from the flow field, and obtaining the equivalent specific heat ratio gamma eff value of mixed gas through thermodynamic relations and weighted averaging of the mass percents; inputting the equivalent specific heat ratio gamma eff value into a perfect gas model as a known parameter and simulating the aerodynamic characteristics of the Mars probe in actual gaseous environment of Mars by using a CFD numerical simulation method. The accuracy and reliability of the method are provided by typical example of the American Phoenix Mars lander. The method can rapidly predict the aerodynamic force performance under real gas effect of Mars atmosphere with accuracy and efficiency.

Description

technical field [0001] The invention relates to a method for predicting the aerodynamic characteristics of the real gas environment in the Martian atmosphere, which can accurately and efficiently perform rapid prediction of the aerodynamic performance under the effect of the real gas in the Martian atmosphere. Background technique [0002] The Mars probe enters the Martian atmosphere at ultra-high speed, and the accurate prediction of the aerodynamic force during the entry stage is the prerequisite for the design of the probe's aerodynamic layout. The main characteristics of the hypersonic flow of the Mars rover are: 2 Gas is the main medium, showing the characteristics of low Reynolds number and high Mach number, and the flow is often accompanied by real gas effects. Only by fully understanding the particularity of the hypersonic flow in the Martian atmospheric environment and establishing a suitable aerodynamic prediction method can the aerodynamic characteristics of the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F119/14
CPCG06F30/20G06F2119/06
Inventor 詹慧玲周伟江刘周龚安龙纪楚群
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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