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Space external heat flux calculation method for carrier rocket

A calculation method and launch vehicle technology, applied in calculations, special data processing applications, instruments, etc., can solve problems such as the complexity of the simulation calculation process

Active Publication Date: 2015-03-11
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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Problems solved by technology

Solar radiation heat flow accounts for the largest proportion among the three kinds of external heat flow, and it is a main factor affecting the temperature of instruments and equipment. At the same time, its simulation calculation process is also relatively complicated.

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  • Space external heat flux calculation method for carrier rocket
  • Space external heat flux calculation method for carrier rocket
  • Space external heat flux calculation method for carrier rocket

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Embodiment Construction

[0047] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0048] Such as figure 1 As shown, the present invention provides a method for calculating heat flow outside the space of a launch vehicle, the steps are as follows:

[0049] (1) Transform the coordinate system at the initial moment to obtain the initial transformation matrix, specifically:

[0050] (1.1) Establish a geocentric equatorial coordinate system: take the center of the earth as the origin, the direction of the vernal equinox is the x-axis, the direction from the center of the earth to the North Pole is the z-axis, and the y-axis conforms to the right-hand rule;

[0051] (1.2) Establish the rocket velocity coordinate system: take the theoretical cusp of the rocket as the origin, the rocket velocity direction is the x-axis, the positive normal direction of the orbital plane where the rocket is located is the z-axis, and the y-...

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Abstract

The invention provides a space external heat flux calculation method for a carrier rocket. The method comprises the following steps that: (1) initial moment coordinate system conversion is carried out to obtain an initial conversion matrix; (2) instantaneous coordinate system conversion is carried out to obtain an instantaneous conversion matrix; (3) the included angle cosine of a sunlight vector, an earth infrared radiation vector, an earth light sun radiation vector and an instantaneous rocket body coordinate system is determined; and (4) an environment virtual mapping surface is built, and the rocket body surface space external heat flux is determined. The method has the advantages that the orbital dynamics and the thermodynamics are combined; the Monte Carlo method radiation heat flux calculation is used as the basis; the space external heat flux on the complicated surface of a rocket body can be finely determined; the problems of shielding and multiple times of reflection among the surfaces are effectively solved; and the coordinate conversion and mathematical calculation flow processes are simplified.

Description

technical field [0001] The invention relates to a method for calculating heat flow outside the space of a carrier rocket, which belongs to the analysis and design of the thermal environment of the carrier rocket. Background technique [0002] During the second-stage flight of the rocket, the outer space heat flow includes: solar radiation heat flow, earth infrared radiation heat flow and earth reflection solar radiation heat flow. Solar radiation heat flow accounts for the largest proportion among the three kinds of external heat flow, and it is a main factor affecting the temperature of instruments and equipment. At the same time, its simulation calculation process is also relatively complicated. During the analysis of the thermal environment, accurate calculation of the radiation heat flow received by the outer surface of the rocket is an important guarantee for the accuracy and reliability of the entire thermal analysis calculation results. [0003] To calculate the oute...

Claims

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Application Information

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IPC IPC(8): G06F19/00
Inventor 苏虹马小亮杨虎军徐珊姝沈丹吴彦森何巍李凰立杜涛
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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