Aircraft designing and manufacturing method based on aerodynamic force mathematical model and aircraft thereof

A technology of mathematical models and manufacturing methods, applied in design optimization/simulation, special data processing applications, geometric CAD, etc., can solve the problems of workload, lack of flexibility in data accuracy, and shorten the design cycle and save costs. , the effect of getting rid of the constraints of the control strategy

Active Publication Date: 2021-10-15
SHANGHAI INST OF ELECTROMECHANICAL ENG
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  • Abstract
  • Description
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Problems solved by technology

[0007] In view of the above prior art, the inventor believes that the above method is limited by the control strategy, and the existing linear mathematical model and nonlinear mathematical model are insufficient in terms of workload, data accuracy and flexibility of use

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  • Aircraft designing and manufacturing method based on aerodynamic force mathematical model and aircraft thereof
  • Aircraft designing and manufacturing method based on aerodynamic force mathematical model and aircraft thereof
  • Aircraft designing and manufacturing method based on aerodynamic force mathematical model and aircraft thereof

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Embodiment Construction

[0041] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0042] The embodiment of the present invention discloses an axisymmetric aircraft design and manufacturing method based on an aerodynamic mathematical model and the aircraft, which is suitable for an axisymmetric aircraft with any number of rudder surfaces and the rudder surfaces are uniformly distributed in the circumferential direction of the aircraft or with protrusions. Approximate axisymmetric aircraft.

[0043] It includes the following steps: Step 1: Establishing an aerodynamic mathematical model...

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Abstract

The invention provides an axial symmetry aircraft manufacturing method based on an aerodynamic force mathematical model, which is characterized by comprising the following steps: 1, establishing an aerodynamic force mathematical model; and 2, performing construction simulation on flight mechanics, a control system, a structural system and an electrical system of the aircraft according to the aerodynamic force mathematical model, and manufacturing the aircraft according to a construction simulation result. The method is suitable for an axisymmetric aircraft or an approximately axisymmetric aircraft with any number of control surfaces, the aerodynamic mathematical model starts from rudder deflection of each control surface instead of controlling rudder deflection channel combination, the model expression is simplified, the limitation of a control strategy is got rid of, the defects of an existing linear mathematical model and an existing nonlinear mathematical model in the aspects of workload, data accuracy, use flexibility and the like are overcome, the advantages of the linear mathematical model and the advantages of the nonlinear mathematical model are considered, and efficiency is improved.

Description

technical field [0001] The present invention relates to the technical field of axisymmetric aircraft, in particular, to an aircraft design and manufacturing method based on an aerodynamic mathematical model and the aircraft, in particular to an aerodynamic mathematical model modeling method for an axisymmetric aircraft that is independent of control strategies . Background technique [0002] In the process of aircraft design, it is necessary to obtain aircraft power and aerodynamic moment. Under modern technical conditions, the means of obtaining aerodynamic force usually include numerical calculation and wind tunnel test. The obtained data are discrete points, which cannot be compared with flight mechanics and control systems Considering the cost of manpower, material resources and time, the numerical calculation and wind tunnel test cannot be carried out according to the state points required by flight mechanics and control systems. Therefore, it is necessary to establish...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/28
CPCG06F30/15G06F30/28Y02T90/00
Inventor 梁伟扬帆徐胜利侯振乾韦亚利李欣吴王浩周小川李晓冬史松伟
Owner SHANGHAI INST OF ELECTROMECHANICAL ENG
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