A Hierarchical Optimization Method for Overall Configuration of Aircraft Based on Multi-Performance Index System
A technology of index system and optimization method, applied in instrument, geometric CAD, electrical and digital data processing, etc., can solve the problem of difficult to achieve reliable optimization of the overall configuration of high-speed aircraft, and achieve the effect of improving reliability and optimization efficiency
Active Publication Date: 2020-05-12
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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Therefore, there are great uncertainties in the final "trial and error" results obtained through the existing "trial and error method", and it is difficult to achieve reliable optimization of the overall configuration of high-speed aircraft
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[0043] In order to make the objectives, technical solutions and advantages of the present invention clearer, the following will further describe the public implementation of the present invention in detail with reference to the accompanying drawings.
[0044] Reference figure 1 , Shows a step flow chart of a method for hierarchical optimization of the overall configuration of an aircraft based on a multi-performance index system in an embodiment of the present invention. In this embodiment, the method for grading and optimizing the overall configuration of the aircraft based on the multiple performance index system includes:
[0045] Step 101: Establish an overall configuration multiple performance index system.
[0046] In this embodiment, the lift-to-drag ratio, lift coefficient, longitudinal stability, yaw stability and roll stability are selected as the overall configuration multi-performance index system according to the aerodynamic characteristics of the aircraft's overall des...
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The invention discloses an aircraft overall configuration hierarchical optimization method based on a multi-performance index system, which comprises a step that establishing an overall configuration multi-performance index system; wherein the index system comprises the following indexes: lift-drag ration, lift coefficient, longitudinal stability, yaw stability and rolling stability. The aircraft overall configuration optimization model is built according to the multi-performance index system; wherein the optimization model comprises an expected value of the index performance of each index in the index system. The aircraft overall configuration is hierarchically optimized of the multi-performance index, according to the optimization model, until the index performance of all indexes is capable of satisfying the expected value corresponding to each index. Through the aircraft overall configuration hierarchical optimization method, the high-speed aircraft overall configuration is optimized under the condition of strong coupling of multi-performance indicators, and the reliability of the optimization and optimization efficiency are improved.
Description
Technical field [0001] The invention belongs to the technical field of high-speed aircraft overall configuration optimization design, and in particular relates to a multi-performance index system-based classification optimization method for the overall configuration of the aircraft. Background technique [0002] The overall aerodynamic configuration design is the "pioneer" in the design of all types of aircraft systems. The speed and quality of its design directly affect the design process and design quality of the entire system of the aircraft. For this reason, the development of a fast, effective, and engineering-oriented high-speed The optimization design method of the overall configuration of the aircraft is of great significance. [0003] Different from aviation two-dimensional airfoil optimization, in high-speed aircraft (especially Mach number Ma> 5.0 aircraft) in the overall configuration optimization, especially for engineering applications, it is necessary to directly ...
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IPC IPC(8): G06F30/15G06F119/14
CPCG06F30/13G06F30/15Y02T90/00
Inventor 王官宇闵昌万朱广生汪雷王美利徐春铃薛鹏飞吴小华苗萌
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST