Propeller aircraft longitudinal aerodynamic force balancing method considering gravity center influence

An aerodynamic and propeller technology, which is applied in the field of longitudinal aerodynamic trimming of propeller aircraft, can solve the problems of long time consumption, low efficiency, and heavy workload of trimming, and achieve the effect of shortening time consumption and improving calculation efficiency

Pending Publication Date: 2022-07-01
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method requires a lot of repeated superposition work in the trimming process. For aircraft with complex configurations, due to the variety of trimming configurations, the trimming workload is large, time-consuming and inefficient.

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  • Propeller aircraft longitudinal aerodynamic force balancing method considering gravity center influence
  • Propeller aircraft longitudinal aerodynamic force balancing method considering gravity center influence
  • Propeller aircraft longitudinal aerodynamic force balancing method considering gravity center influence

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Embodiment Construction

[0047] In order to make the objectives, technical solutions and advantages of the implementation of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. Throughout the drawings, the same or similar reference numbers refer to the same or similar elements or elements having the same or similar functions. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to be used to explain the present application, but should not be construed as a limitation to the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present...

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Abstract

The invention belongs to the field of aerodynamic balancing of aviation aircrafts, and discloses a propeller-driven aircraft aerodynamic longitudinal balancing method considering gravity center influence. The method comprises the following steps: according to longitudinal reference aerodynamic data of an airplane, a propeller slip flow influence increment, elevator control surface efficiency and an airplane balancing gravity center offset, obtaining non-balancing aerodynamic data considering the gravity center offset influence quantity; and solving the longitudinal trim aerodynamic force of the aircraft under the given configuration by adopting a difference method interpolation. The method is suitable for longitudinal aerodynamic force balancing in propeller aircraft design and development, the aerodynamic force balancing efficiency of the propeller aircraft is improved, and a basis is provided for aerodynamic force balancing use of the propeller aircraft in different states in engineering development.

Description

technical field [0001] The present application belongs to the field of aerodynamic trim of aeronautical aircraft, and in particular relates to a longitudinal aerodynamic trim method of a propeller aircraft considering the influence of the center of gravity. Background technique [0002] In the process of aircraft design and development, the aerodynamic data obtained by CFD simulation calculation or wind tunnel test needs to be trimmed before it can be used for calculation and analysis by downstream professionals. Therefore, aerodynamic trim is an important technology for aircraft aerodynamic data processing. Due to the influence of the propeller slip flow, the aerodynamic force of the propeller aircraft is much more complicated than that of the general turbofan aircraft, and the aerodynamic force obtained from the wind tunnel test is also more complicated. How to fully consider the influence of the propeller slip flow to obtain accurate aerodynamic trim results, directly Pro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/28G06F113/08G06F119/14
CPCG06F30/15G06F30/28G06F2113/08G06F2119/14
Inventor 张超明亚丽谭蓉蓉徐声明商立英张泰安
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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