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Method for quickly optimizing plane parameters of aircraft wing

An optimization method and wing technology, which is applied in the aviation field, can solve the problems of optimization, long calculation period and insufficient power, and achieve the effect of improving optimization efficiency, shortening optimization period and simplifying calculation model.

Active Publication Date: 2020-05-15
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0002] The traditional optimization of wing plane parameters is carried out by specialization. The aerodynamic performance of the configuration obtained by the aerodynamic professional optimization is the best, and the weight professional optimization is obtained by the weight of the configuration. However, this cannot guarantee the optimal flight performance index of the aircraft.
The calculation of modern aerodynamic force and weight requires the establishment of digital models, and complex numerical calculations require powerful computing resources, and the calculation cycle is long
In the face of a large number of wing configuration samples, traditional optimization methods are unable to do what they want

Method used

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  • Method for quickly optimizing plane parameters of aircraft wing
  • Method for quickly optimizing plane parameters of aircraft wing
  • Method for quickly optimizing plane parameters of aircraft wing

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specific example

[0067] Step 6 optimize the wing configuration, specifically: through two rounds of optimization, take the wing corresponding to the best aircraft configuration as the final optimized configuration, after the first round of optimization screening, 484 aircraft configuration samples meet the optimization constraints There are only 8 configurations remaining, and the two-round optimization model algorithm is adopted for these configurations. The specific examples of the present invention are as follows:

[0068] 1) The optimized target parameter is the range;

[0069] 2) Optimized wing configuration: wing plane parameters: aspect ratio 9.5, leading edge sweep angle 28 degrees, tip-to-root ratio 0.28.

[0070] 3) Aircraft optimization performance data: the maximum flight range is 4917.9km, the take-off weight is 73.49t, and the average lift-to-drag ratio for cruise is 15.6.

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Abstract

The invention discloses a method for quickly optimizing plane parameters of an aircraft wing. The method comprises the following steps: 1, generating a wing configuration sample; 2, setting wing constraint conditions; step 3, screening aircraft configurations; 4, determining an optimization strategy and establishing a configuration optimization calculation model; 5, selecting an optimization target parameter; and 6) optimizing wing configuration. According to the method, a flight performance index serves as the final optimization target, a hierarchical optimization strategy is adopted, the calculation model is simplified, the calculation method is reasonably selected, the optimization efficiency is effectively improved, the optimization period is shortened, and the problems of cross-professional optimization, high optimization resource requirement and low optimization efficiency of a traditional optimization method are solved.

Description

technical field [0001] The invention belongs to the technical field of aviation, and in particular relates to a method for quickly optimizing aircraft wing plane parameters. Background technique [0002] The traditional optimization of wing plane parameters is carried out by specialization. The aerodynamic performance of the configuration obtained by the aerodynamic professional optimization is the best, and the weight of the professional optimization is obtained by the optimal configuration weight. However, this cannot guarantee the optimal flight performance index of the aircraft. The calculation of modern aerodynamic force and weight requires the establishment of digital models, and complex numerical calculations require powerful computing resources, and the calculation cycle is long. In the face of a large number of wing configuration samples, traditional optimization methods are unable to do what they want. Contents of the invention [0003] Purpose of the present in...

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Application Information

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IPC IPC(8): G06F30/15G06F111/10G06F111/06
CPCY02T90/00
Inventor 张声伟
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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