Method for determining wing structure load when transportation aircraft drops goods

A transport aircraft and cargo airdrop technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of impact, large structural flexibility, unfavorable aircraft structural safety and flight safety, etc.

Active Publication Date: 2014-02-12
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

[0003] The disadvantages of the current method for determining the wing structure load during the airdrop of transport aircraft cargo are: first, the determined wing structure load has a large error
Due to the characteristics of large structural flexibility and low frequency of transport aircraft, the excitation load in the process of cargo airdrop, especially heavy cargo airdrop, has a wide frequency band, which will excite more elastic mode vibrations of the aircraft, and this dynamic response It may be made larger by the aeroelastic effect, which will cause an incr

Method used

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  • Method for determining wing structure load when transportation aircraft drops goods
  • Method for determining wing structure load when transportation aircraft drops goods
  • Method for determining wing structure load when transportation aircraft drops goods

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Embodiment

[0074] By adopting the invention, the simulation calculation is carried out to determine the load of the wing structure when a certain type of transport aircraft performs cargo airdrop.

[0075] A certain type of transport aircraft is discretized into a finite element model FEM, so that the aircraft can be simulated as an elastic aircraft; the mass ratio of the cargo to the aircraft is 0.13; the initial loading position of the cargo in the aircraft cargo compartment is the center of mass of the aircraft; moving acceleration a b 2.5m / s 2 ; The flight height H of the aircraft is 30m; the flight speed V of the aircraft is 150m / s; the average aerodynamic chord length c is 4.5m; the first 40 modes of the aircraft are selected; w is 7.6m / s; discrete gust scale L w It is 112.5m. Use the above parameters as initialization parameters.

[0076] Using the commercial software Nastran to conduct modal analysis on the finite element model FEM of the aircraft, the first 40 modal matrix Φ...

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Abstract

The invention belongs to the technical field of aircraft flying load design, and relates to the improvement on a method for determining a wing structure load when a transportation aircraft drops goods. The method for determining the wing structure load is characterized by comprising the step of initializing aircraft air-dropping goods parameters, the step of analyzing aircraft limited element modals, the step of calculating an aircraft non-steady aerodynamic coefficient matrix, the step of calculating an aircraft air-dropping goods dynamic response, the step of calculating a wing structure load dynamic response, and the step of determining the design load of the wing structure in the process of air-dropping. By means of the improved method for determining the wing structure load when the transportation aircraft drops the goods, the determining precision of the wing structure load is improved, and the safety of the wing structure and the flying safety of the aircraft are guaranteed.

Description

technical field [0001] The invention belongs to the technical field of aircraft flight load design, and relates to the improvement of a method for determining the load of a wing structure during airdropping of transport aircraft cargo. Background technique [0002] Airdrop is one of the important working modes of transport aircraft. During airdrop, it is generally necessary to determine the design loads of the aircraft cargo floor, cargo bridge, connectors, wings and other components. The current transport aircraft regards the aircraft as a rigid body when airdropping cargo, and only considers the static aeroelastic correction of the aerodynamic force, and relies on the rigid body flight dynamics equation to solve the problem. For specific techniques, see the literature: "Flight Dynamics Modeling and Simulation of Transport Airdrops" , Yang Miaosheng, Qu Xiangju, "Flight Mechanics", 2010, Vol. 28 (No. 3), P.9-12. [0003] The disadvantages of the current method for determi...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 荆志伟侯宗团
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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