An optimization method for carrying airdrop aircraft in a limited time with biplane layout

An optimization method and carrying technology, applied in aircraft parts, design optimization/simulation, transportation and packaging, etc., can solve problems such as large wing torque, achieve enhanced wing torsion resistance, increase wing angle of attack, and improve control sexual effect

Active Publication Date: 2021-06-08
ZHENGZHOU UNIVERSITY OF AERONAUTICS
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Problems solved by technology

[0005] In view of the above situation, in order to overcome the defects of the prior art, the present invention provides an optimization method for carrying an airdrop aircraft with a biplane layout within a limited time, which effectively solves the problem of excessive torque of the wings in a heavy-duty aircraft

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  • An optimization method for carrying airdrop aircraft in a limited time with biplane layout
  • An optimization method for carrying airdrop aircraft in a limited time with biplane layout
  • An optimization method for carrying airdrop aircraft in a limited time with biplane layout

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[0035] Regarding the aforementioned and other technical contents, features and effects of the present invention, refer to the appended Figure 1 to Figure 7 It will be apparent from the detailed description of the embodiments. The structural contents mentioned in the following embodiments are all based on the accompanying drawings of the description.

[0036] Exemplary embodiments of the present invention will be described below with reference to the accompanying drawings.

[0037] The premise of the present invention is that the time-limited load airdrop requires the weight limit to be changed. The present invention adopts the method of increasing the lift. At present, the methods of increasing the lift mainly include increasing the speed, increasing the lift coefficient, and increasing the wing area. Due to the common problem of the wing not torsion in the limited-time load airdrop aircraft, the wing torque turns at high speed so that the control is ineffective. And under ...

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Abstract

The invention relates to an optimization method for a time-limited carrying and air-dropping aircraft with a double-wing layout, comprising the following steps: step 1, calculating wing-related data according to power, weight and lift coefficient; step 2, determining the span and aerodynamic chord length of the upper and lower wings; step 3 , Determine the selection of the relative position of the wing and the CFD numerical calculation verification; Step 4, verify whether the results are consistent; if the results are consistent, continue to the next step, if the results are not consistent, go back to Step 3; Step 5, pressure distribution curve and lift-drag characteristics Step 6, CFD numerical calculation of the whole aircraft model; Step 7, optimization of the wing design; the present invention meets the usage requirements, solves the problem of excessive torque on the wing, and improves the longitudinal stability of the aircraft.

Description

technical field [0001] The invention relates to the technical field of time-limited airdropping of aircraft, in particular to an optimization method for time-limited airdropping of aircraft with biplane layout. Background technique [0002] At present, aircraft carrying airdrops are widely used in two aviation fields, civil aviation and military aviation. Civil aviation is mainly used to transport living materials to disaster areas or poverty-stricken areas within a specified time; military aviation is mainly used to deliver weapons, ammunition and military supplies to battlefields, national defense borders, and exercise areas within a specified time. With people's requirements for resources and energy, aircraft carrying airdrops has played a more convenient role in our current life. [0003] In today's society, national defense and people's livelihood are particularly important to a country. National defense, as the foundation of a country's people's security, is an indis...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/00B64D1/08G06F30/20G06F30/15G06F111/10G06F119/14
CPCB64D1/08B64F5/00
Inventor 刘双燕黄新俊李洪元张赫天孙瑞明游泽宇
Owner ZHENGZHOU UNIVERSITY OF AERONAUTICS
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