Subsonic cruise voyage optimization design method for fixed-wing aircraft

A technology of optimized design and cruising range, applied in the field of flight mechanics, can solve the problems of high selectivity and substandard indicators, and achieve the effect of fast and simple calculation and meeting the accuracy requirements

Active Publication Date: 2021-03-19
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0005] However, in the actual selection of aircraft lift-to-drag ratio and cruising speed, due to different methods and methods, various design and res

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  • Subsonic cruise voyage optimization design method for fixed-wing aircraft
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  • Subsonic cruise voyage optimization design method for fixed-wing aircraft

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[0051] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the field of flight mechanics, and particularly relates to a subsonic cruise voyage optimization design method for a fixed-wing aircraft. The method comprises the steps: obtaining 1, flight parameters of the fixed-wing aircraft, wherein the flight parameters comprise the maximum lift-drag ratio Kmax, the cruise lift coefficient Cy and the cruise Mach number M; 2, determining the engine thrust oil consumption rate Ce0 of a cruise entry point and the engine thrust oil consumption rate Ce1 of a cruise end point according to the flight parameters; 3, calculating the average oil consumption rate according to the engine thrust oil consumption rate Ce0 at the cruise entry point and the engine thrust oil consumption rate Ce1 at the cruise end point, and taking the averageoil consumption rate as the voyage calculation oil consumption rate Ce; and 4, calculating the variable-height cruise voyage L of the fixed-wing aircraft according to the voyage calculation oil consumption rate Ce. According to the optimization design method for the subsonic cruise voyage of the fixed-wing aircraft, a large amount of original data used by professional performance software or simulation software is not needed, calculation is rapid and simple, and the model argumentation precision requirement is met.

Description

technical field [0001] The application belongs to the field of flight mechanics, and in particular relates to an optimal design method for subsonic cruising range of a fixed-wing aircraft. Background technique [0002] Range is one of the important tactical and technical indicators of an aircraft. In the context of competitive procurement, the maximum range often plays a decisive role. [0003] Due to the lack of complete and detailed calculation and analysis data at the beginning of the design, for fixed-wing aircraft, the following classic formula is usually used to determine the flight range: [0004] [0005] However, in the actual selection of aircraft lift-to-drag ratio and cruising speed, various design and research units often have high selectivity due to different methods and methods, resulting in the phenomenon that the indicators in the aircraft finalization assessment are not up to standard. [0006] Therefore, it is desirable to have a technical solution to ...

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Application Information

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IPC IPC(8): G06F30/15G06F30/20B64F5/00G06F119/14
CPCG06F30/15G06F30/20B64F5/00G06F2119/14Y02T90/00
Inventor 王宝冬
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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