中国科学院机构知识库网格系统: 检索

Inclination prediction of a giant open caisson during the sinking process using various machine learning algorithms 期刊论文 OAI收割
OCEAN ENGINEERING, 2023, 卷号: 269
作者: Dong, Xuechao; Guo, Mingwei; Wang, Shuilin

|

收藏 | 浏览/下载：15/0 | 提交时间：2023/08/02

Open caisson Inclination prediction Machine learning Sinking safety Parameter influence Parameter optimization

Influence of the Choice of Reference Planes on the Determination of 2D and 3D Joint Roughness Parameters 期刊论文 OAI收割
ROCK MECHANICS AND ROCK ENGINEERING, 2021, 页码: 14
作者: Wong, Louis Ngai Yuen; Meng, Fanzhen; Zhou, Hui; Yu, Jin; Cheng, Guangtan

|

收藏 | 浏览/下载：32/0 | 提交时间：2021/06/18

Roughness parameter Reference plane Best fit plane Anisotropy Influence factor

A New Set of Parameters of High-Mass X-ray Binaries Found with their Cyclotron Lines 期刊论文 OAI收割
arXiv e-prints, 2018
作者: Zhang, Chengmin; Taani, Ali; Chaty, Sylvain; Karino, Shigeyuki; Song, Liming

|

收藏 | 浏览/下载：76/0 | 提交时间：2019/07/12

Astrophysics - High Energy Astrophysical Phenomena Abstract: We have derived new physical quantities for several High-Mass X-ray Binaries (HMXBs) with supergiant (SG) companions through their cyclotron lines. The parameters are: the terminal velocity of the wind, the mass loss rate of the donor, the effective temperature and the magnetic fields. These parameters influence significantly the improvement of the model of accretion. In spite of the variety of their observational properties, the corresponding magnetic field is around B ~ 10^12 G. This result can be constrained by the effects on stellar evolution. In addition, we have performed a segmentation in the parameter space of donors intended for several SG-HMXB listed in our sample set. The parameter space can be categorized into five regimes depending on the possibility of disk formation associated with accretion from the stellar wind. This can give a quantitative clarification of the observed variability and the properties of these objects. We show that, when these systems come into the direct accretion region, systems with corresponding parameters can emit X-rays.

Aircraft flight simulation with landing gear based on multi-domain modeling technology (EI CONFERENCE) 会议论文 OAI收割
2012 2nd International Conference on Computer Application and System Modeling, ICCASM 2012, July 27, 2012 - July 29, 2012, Shenyang, China
作者: Li M.

收藏 | 浏览/下载：16/0 | 提交时间：2013/03/25

This paper create a full aircraft flight simulation model for accurately analyzing the performance and influence of landing gear system. The use of multi-domain modeling technology enables detailed modeling of the flight dynamic and landing gear dynamic. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is actual in the physical process. The parameter design space is easily searched by considering a number of different landing scenarios to optimize the design. the authors.

Establishment of airplane flight model and simulation analysis of landing behavior (EI CONFERENCE) 会议论文 OAI收割
2nd Annual Conference on Electrical and Control Engineering, ICECE 2011, September 16, 2011 - September 18, 2011, Yichang, China
作者: Li L.; Li M.

收藏 | 浏览/下载：25/0 | 提交时间：2013/03/25

This paper create a high fidelity plant model of an aircraft landing gear to inclusion into a full aircraft flight simulation for accurately analyzing the performance and influence of landing gear system. The use of domain specific modeling software enables detailed modeling of the physics and facilitates accurate computational simulation of the flight dynamic aerodynamic landing gear dynamic and mechanical loads that occur when the landing gear are deployed and retracted during landing and take-off operations. The parameter design space is easily searched by considering a number of different landing scenarios including touching down on one wheel first to optimize the design. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is actual in the physical process. 2011 IEEE.

Study of the neural network constitutive models for turfy soil with different decomposition degree (EI CONFERENCE) 会议论文 OAI收割
2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China
作者: Nie L.

收藏 | 浏览/下载：19/0 | 提交时间：2013/03/25

The turfy soil is of a special humus soil. The decomposition degree is the main factor on the physical and mechanical properties of turfy soil. To build the turfy soil constitutive model there are a few shortages such as the calculation cumbersome and low accuracy for parameter value with the method of traditional models. Furthermore those methods did not reflect the influence of strength that effected by decomposition degree of the turfy soil. In this paper the relationship of stress-strain with different decomposition degrees of turfy soil was carried out through indoor tests. Based on above experimental results an improved method which divided into different zones according to different decomposition degrees of turfy soil and calculated combining with neural network constitutive model is put forward. The result shows that the neural network of turfy soil has good fitting precision and good generalization ability. It can fully describe the influence of the turfy soil. 2011 IEEE.

Optimum design of the carbon fiber thin-walled baffle for the space-based camera (EI CONFERENCE) 会议论文 OAI收割
International Symposium on Photoelectronic Detection and Imaging 2011: Space Exploration Technologies and Applications, May 24, 2011 - May 26, 2011, Beijing, China
Yan Y.; Gu S.; An Y.; Jin G.

收藏 | 浏览/下载：14/0 | 提交时间：2013/03/25

The thin-walled baffle design of the space-based camera is an important job in the lightweight space camera research task for its stringent quality requirement and harsh mechanical environment especially for the thin-walled baffle of the carbon fiber design. In the paper an especially thin-walled baffle of the carbon fiber design process was described and it is sound significant during the other thin-walled baffle design of the space camera. The designer obtained the design margin of the thin-walled baffle that structural stiffness and strength can tolerated belong to its development requirements through the appropriate use of the finite element analysis of the walled parameters influence sensitivity to its structural stiffness and strength. And the designer can determine the better optimization criterion of thin-walled baffle during the geometric parameter optimization process in such guiding principle. It sounds significant during the optimum design of the thin-walled baffle of the space camera. For structural stiffness and strength of the carbon fibers structure which can been designed the effect of the optimization will be more remarkable though the optional design of the parameters chose. Combination of manufacture process and design requirements the paper completed the thin-walled baffle structure scheme selection and optimized the specific carbon fiber fabrication technology though the FEM optimization and the processing cost and process cycle are retrenchment/saved effectively in the method. Meanwhile the weight of the thin-walled baffle reduced significantly in meet the design requirements under the premise of the structure. The engineering prediction had been adopted and the related result shows that the thin-walled baffle satisfied the space-based camera engineering practical needs very well its quality reduced about 20% the final assessment index of the thin-walled baffle were superior to the overall design requirements significantly. The design method is reasonable and efficient to the other thin-walled baffle that mass and work environment requirement is requirement harsh. 2011 SPIE.

Aircraft landing gear simulation using multidomain modeling technology (EI CONFERENCE) 会议论文 OAI收割
2011 International Conference on Information Technology, Computer Engineering and Management Sciences, ICM 2011, September 24, 2011 - September 25, 2011, Nanjing, Jiangsu, China
作者: Li M.

收藏 | 浏览/下载：40/0 | 提交时间：2013/03/25

In order to accurately analyze the performance and influence of landing gear system this paper presents a high fidelity plant model of an aircraft landing gear to inclusion into a full aircraft flight simulation. The use of domain specific modeling software enables detailed modeling of the physics and facilitates accurate computational simulation of the flight dynamic aerodynamic landing gear dynamic and mechanical loads that occur when the landing gear are deployed and retracted during landing and take-off operations. The parameter design space is easily searched by considering a number of different landing scenarios including touching down on one wheel first to optimize the design. The simulation results show that the aircraft landing gear system mathematical model established appropriately reflects the change of force and moment in the process of taking off and landing and it is improve the precision of flight simulation. 2011 IEEE.

Modular aircraft simulation platform based on simulink (EI CONFERENCE) 会议论文 OAI收割
2010 IEEE International Conference on Mechatronics and Automation, ICMA 2010, August 4, 2010 - August 7, 2010, Xi'an, China
Chen C.-Q.; Ji Y.

收藏 | 浏览/下载：28/0 | 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.

Dynamic closed-loop test for real-time drift angle adjustment of space camera on the Earth (EI CONFERENCE) 会议论文 OAI收割
5th International Symposium on Advanced Optical Manufacturing and Testing Technologies: Optical Test and Measurement Technology and Equipment, April 26, 2010 - April 29, 2010, Dalian, China
作者: Xu S.; Wang D.

收藏 | 浏览/下载：36/0 | 提交时间：2013/03/25

In order to eliminate the influence of aircraft attitude angle to the image quality of space camera and assure that the drift angle of space camera could be accurately adjusted at the orbit a novel closed-loop test method is provided for real-time drift angle adjustment of space camera on the Earth. A long focal length dynamic aim generator is applied to simulate the image motion and the variety drift angle and to detect the precision of the image motion compensation machinery and the capability of the drift angle control system. The computer system is used to control the dynamic aim generator accomplish the data processing transmit and receive the data information. The seamless connection and the data transmission between the aim generator and the aircraft simulation devices are constituted. The command parameter and drift angle data transmitted by the simulation devices are received by the space camera at the real time then the photos are taken and the draft angle is adjusted simultaneously. It is shown that the drift angle can be accurately tracked by the space camera at the real time and the detective method satisfies the test requirement. 2010 Copyright SPIE - The International Society for Optical Engineering.