Aircraft standing point temperature calculation method based on two-dimensional search

A stagnation point temperature and two-dimensional search technology, applied in calculation, instrumentation, special data processing applications, etc., can solve problems such as discontinuous calculation and inaccurate stagnation point temperature of aircraft, so as to increase calculation accuracy, reduce error, and improve accuracy sexual effect

Active Publication Date: 2018-01-09
XIDIAN UNIV
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Problems solved by technology

[0011] The object of the present invention is to provide a kind of aircraft stagnation point temperature calculation method based on two-dimensional search, increase calculation accuracy under the condition of only increasing a search operation, and obtain the stagnation point temperature under the continuous altitude and speed range, solve the problem Problems of inaccurate and discontinuous calculation of stagnation point temperature of aircraft in prior art

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  • Aircraft standing point temperature calculation method based on two-dimensional search
  • Aircraft standing point temperature calculation method based on two-dimensional search
  • Aircraft standing point temperature calculation method based on two-dimensional search

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Embodiment Construction

[0046] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0047] refer to figure 1 , a method for calculating the stagnation point temperature of an aircraft based on two-dimensional search, which is carried out according to the following steps:

[0048] Step 1, according to the flight altitude and flight speed of the aircraft, establish an initial blank lookup tableγ M×N ; Each line of the lookup table corresponds to a flight altitude of the aircraft, the altitude H ranges from 20-70km, stepping 2km, the number of ...

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Abstract

The invention discloses an aircraft standing point temperature calculation method based on two-dimensional search. A look-up table is established; a gamma-T curve is fitted out; the gamma-T curve is converted into the look-up table, and the temperature value T is used as a searching condition, and a corresponding air specific heat capacity ratio gammaT can be found out; the standing point temperature value when V=5Ma is calculated, according to the temperature value, a gamma value is selected, the standing point temperature is repeatedly calculated, and the gamma initial value is determined; the air specific heat capacity ratios gammai and gammaj are calculated; the flight speed V and the height H are used as conditions, the air specific heat capacity ratio gamma is searched in the two-dimensional look-up table, the aircraft standing point temperature T at the corresponding speed and height is calculated, and finally, when the height is within 20-70 km and the speed is within 5-22 Ma,the aircraft standing point temperature can be obtained. The problems that in the prior art, the aircraft standing point temperature is not accurate and calculation is discontinuous are solved.

Description

technical field [0001] The invention belongs to the technical field of aerodynamic thermal effects, and in particular relates to a two-dimensional search-based aircraft stagnation point temperature calculation method suitable for academic research and practical engineering applications. Background technique [0002] Hypersonic vehicles in near space have a unique military strategic position, and various scientific researches have been carried out one after another based on this background. Compared with traditional aircraft, in addition to the significant increase in speed of hypersonic aircraft, the plasma sheath derived from the aerothermal effect in the hypersonic flight environment will cause electromagnetic interference to radar detection signals, resulting in signal strength attenuation, phase distortion, and frequency of radar echoes. Dispersion and other issues will affect the precision and accuracy of radar detection. [0003] In order to analyze the influence of t...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
Inventor 刘彦明牛戈钊张晰
Owner XIDIAN UNIV
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