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Optimization method of double-wing layout time-limited carrying airdrop aircraft

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, improve maneuverability, and improve longitudinal stability Effect

Active Publication Date: 2020-04-10
ZHENGZHOU UNIVERSITY OF AERONAUTICS
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  • Description
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  • Application Information

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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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  • Optimization method of double-wing layout time-limited carrying airdrop aircraft
  • Optimization method of double-wing layout time-limited carrying airdrop aircraft
  • Optimization method of double-wing layout time-limited carrying airdrop aircraft

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Embodiment Construction

[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 of a double-wing layout time-limited carrying airdrop aircraft. The optimization method comprises the following steps: S1, calculating wing related dataaccording to power, weight and lift coefficients; S2, determining the span length and the pneumatic chord length of the upper and lower wings; S3, determining selection of the relative positions of the wings and conducting CFD numerical calculation verification; S4, verifying whether a result conforms or not; if yes, continuing the next step, and if not, returning to the third step; S5, comparinga pressure distribution curve with lift-drag characteristics; S6, performing CFD numerical calculation on a full-aircraft model; and S7, optimizing wing design. The use requirements are met, the problem that the wings bear too large torque is solved, and the longitudinal stability of the aircraft is improved.

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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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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