中国科学院机构知识库网格系统: 检索

A Three-State Space Modeling Method for Aircraft System Reliability Design 期刊论文 OAI收割
MACHINES, 2024, 卷号: 12, 期号: 1
作者: Wang, Yao; Wang, Fengtao; Feng, Yue; Cao, Shancheng

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收藏 | 浏览/下载：16/0 | 提交时间：2024/03/04

aircraft system optimization design function architecture reliability model failure mode

Design, modeling, and control of morphing aircraft: A review 期刊论文 OAI收割
Chinese Journal of Aeronautics, 2022, 页码: 1-27
作者: Chu LL(禇玲玲); Li Q(李琦); Gu F(谷丰); Du XT(杜心田); He YQ(何玉庆)

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收藏 | 浏览/下载：40/0 | 提交时间：2021/12/31

Aircraft design Dynamic modeling Fault tolerance Flight control Intelligent material Morphing aircraft Unmanned Aerial Vehicles (UAV)

Simulation of Short Take-Off and Vertical Landing (STOVL) Aircraft in 5G OGCE 会议论文 OAI收割
2nd International Conference on Robotics and Automation Engineering (ICRAE), Shanghai, CHINA, December 29-31, 2017
作者: Wang ZF(王忠锋); Lu, Yi; Lu, Zhi; lvzhi@tute.edu.cn; Yuan MZ(苑明哲)

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收藏 | 浏览/下载：32/0 | 提交时间：2018/04/01

5G open grid computing environment (5G OGCE) short take-off and vertical landing (STOVL) hand type vertical jet nozzle robot balance tail robot aircraft design robotics turbofan and robots MPP simulation in 5G OGCE distributed artificial intelligence (distributed AI) software architecture and engineering

A conceptual design of next generation hypersonic air-breathing airplanes with dual waveriders forebody 会议论文 OAI收割
20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015, Glasgow, United kingdom, July 6, 2015 - July 9, 2015
作者: Cui K(崔凯); Hu SC(胡守超); Li GL; Xiao Y(肖尧); Situ M

收藏 | 浏览/下载：31/0 | 提交时间：2017/05/05

Aero dynamic performance Aerodynamic performance predictions Design Methodology Flight altitudes Numerical results Propulsion system Turbulent models Wing body aircraft

Longitudinal control law design and simulation of fixed-wing UAV (EI CONFERENCE) 会议论文 OAI收割
2012 International Conference on Measurement, Instrumentation and Automation, ICMIA 2012, September 15, 2012 - September 16, 2012, Guangzhou, China
作者: Duan Z.

收藏 | 浏览/下载：27/0 | 提交时间：2013/03/25

Taken some fixed-wing UAV as the study object the aircraft movement was broken down into the longitudinal movement and lateral movement according to the linearized small perturbation principle the longitudinal control law design method was discussed using root locus which belonged to classical control theory. The six degrees of freedom nonlinear model simulation result shows that: the control parameters designed are reasonable the simulation profile is fully consistent with the setting profile the control effect of pitch angle loop and altitude loop meets with the indices requirements the method is mature and reliable easy to realize in engineering. (2013) Trans Tech Publications Switzerland.

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.

The aircraft autopilot design of parameters changing in a wide range (EI CONFERENCE) 会议论文 OAI收割
2011 International Conference on Electric Information and Control Engineering, ICEICE 2011, April 15, 2011 - April 17, 2011, Wuhan, China
Zhen D.; Yue Z.

收藏 | 浏览/下载：28/0 | 提交时间：2013/03/25

Autopilot is an important part of aircraft Under the action of the disturbance torque for the flight parameters of aircraft Changing in a wide range the range was about 16km on the basic of analyzing the typical trajectory the max height was about 5100m the trajectory of feature points were selected the deviation of lateral was about 12m taking pitch control loop for example the maximum angle of attack was about 3.6 a sub- PID autopilot was designed using classical control theory the maximum elevator deflection was less than 5 using single-mode Transient suppression method the maximum aileron deflection was less than 2 the overload due to control surface transition deflection was avoided when control parameters changing the maximum roll was less than 5 the verification was done by non-linear simulation. The result showed that: the phase margin of autopilot was greater than 30 the response of overload can accurately track the given overload instruction. An autopilot design method of aircraft of parameter changes in a wide range was provided. 2011 IEEE. the bandwidth was more than 14rad / s the settling time was less than 0.7s the maximum overshoot was 23.3%

Evaluation of the operating range for ground-based infrared imaging tracking system (EI CONFERENCE) 会议论文 OAI收割
International Symposium on Photoelectronic Detection and Imaging 2011: Advances in Infrared Imaging and Applications, May 24, 2011 - May 24, 2011, Beijing, China
作者: Zhang Z.-D.

收藏 | 浏览/下载：48/0 | 提交时间：2013/03/25

Ground-based infrared imaging tracking system (GIITS) is of great importance for aerial target warning and guard. The operating range is one of the key performance specifications on the other which should be calculated calculate the radiation power received on the detector in order to analysis whether the output signal meets the detection requirements or not analyzed and studied during the whole GIITS design process. The operating range is mostly influenced by a few factors without considering the effect of the background radiation. By improving of the traditional method including atmospheric attenuation a new operating range calculation model of the GIITS was established based on two requirements. One is that the image size of observed target should meet the requirement of the processor signal extraction. The number of the pixel occupied by target image should be more than 9. The other is that the signal noise ratio (SNR) of the GIITS should not be less than 5 to meet the requirements of the target detection probability and spatial frequency. The SNR calculation equation in form of energy is deduced and the radiation characteristic of the observed target and background are analyzed. When evaluate the operating range of the GIITS using the new method the performance of GIITS and feature of target and background. This paper firstly makes analysis and summarization on the definite localizations of the traditional operating range equation of the GIITS. The localizations are mainly in two aspects. On one hand we should successively calculate two operating range values according to two requirements mentioned above and choose the minimum value as the analytic result. In the end the dispersion of the image and the effect of image dispersion are not considered in the traditional method an evaluation of operating range for fighter aircraft is accomplished as an example. The influence factors in every aspect on operating range were explored by the calculated result. The new operating range calculation model provides the theoretical basis for the design and applications as well as the comprehensive evaluation of a GIITS. 2011 Copyright Society of Photo-Optical Instrumentation Engineers (SPIE).

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.

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.