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厦门大学 [1]
长春光学精密机械与物... [1]
武汉大学 [1]
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会议论文 [2]
期刊论文 [1]
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2014 [1]
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厦门大学2013国际太阳能十项全能竞赛风环境模拟
期刊论文
2014
郑婷婷
;
王波
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浏览/下载:5/0
  |  
提交时间:2016/05/17
PHONICS
风环境模拟
太阳能十项全能竞赛
室内通风
PHONICS
the wind environment simulation
Solar Decathlon
indoor air ventilation
Renewal Strategy of the Traditional Streets Based on Wind Environment Simulation
会议论文
作者:
Wang Yansong
;
Liu Xi
;
Li Yunwu
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浏览/下载:5/0
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提交时间:2019/12/05
comfort
wind environment
the traditional street in Lichuan
numerical simulation
renewal strategy
Modular aircraft simulation platform based on simulink (EI CONFERENCE)
会议论文
2010 IEEE International Conference on Mechatronics and Automation, ICMA 2010, August 4, 2010 - August 7, 2010, Xi'an, China
Chen C.-Q.
;
Ji Y.
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浏览/下载:20/0
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提交时间:2013/03/25
Aircraft simulation platform is the most important supporting technology in the aircraft development process. This simulation platform can be used for validating the design of subsystem and also it provides the necessary data for the Aircraft design. Wind has great impact on the flight parameter. In order to accurately simulate the wind model and calculate the flight parameters
a simulation modeling method for flight parameter simulation platform under wind field environment is established. Firstly
the various sub-systems which affecting flight parameters are analyzed
some mathematical models of the flight parameter simulation platform is established. Secondly
the atmospheric wind field is studied to analyze the impact on its trajectory. Then the model is built in the Simulink toolbox in the Matlab which is based on the principles of hierarchy and modularity
using C MEX S-function for the complex kinetic equations. Finally
when the models have been established
encapsulating models for several subsystem and assembling them for the Aircraft simulation platform based on the unified interface. The simulation tests (including the performance test of a certain gliding Aircraft
the wind influence test of a certain uncontrolled aircraft) prove the simulation capability of the platform
and its calculating step can reach 1 ms. Comparing simulation with field test data of a certain uncontrolled aircraft
it shows that the relative deviation of range is 0.47%
the relative deviation of maximal altitude is 2.1%. Taking relevant standards as a reference standard
it is demonstrated the platform is reliable
meets the engineering accuracy requirements. 2010 IEEE.
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