In the process of aircraft development, the assessment of handling quality is particularly step for verifying the cockpit control units design whether meets the design requirements or not. If the assess results are not met the design requirements, the design must to be optimized or even redesigned. At present, most of research is mainly related to the design of cockpit control units and simulating and assessment of their maneuverability based on the dynamic model in the normal mode, however, the research on handling quality of cockpit control units in the failure operating mode is seldom. Moreover, override rod linkage form as a new kind of cockpit control units brings plenty of profits such as the weight saved and maintainability improved, however, it causes the failure mode becomes diverse and complicated. Therefore it will increase the difficulty of assessing this kind of cockpit control units. The object of this paper is to do a research on working principle and physical characteristics of cockpit control units of override rod linkage form, through modeling and simulation on its normal operating mode and failure mode, and finally gives an analysis and evaluation for the column force quality of each failure mode. The simulation results reveal the column force quality of each failure mode is acceptable.
| Published in | American Journal of Aerospace Engineering (Volume 6, Issue 1) |
| DOI | 10.11648/j.ajae.20190601.13 |
| Page(s) | 17-23 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2019. Published by Science Publishing Group |
Fly-By-Wire Civil Aircraft, Cockpit Control Units, Override Rod, Failure Mode, Flight Quality Evaluation
| [1] | Song Xianggui, Zhang Guoxin. Fly-by-Wire Flight Control System [M]. Beijing, National Defence Industrial Press, 2003: 7-9. |
| [2] | Shen Yongkui, Wu Mei, Chen Lan, An Jinwen. Modeling and Simulation of Vehicle Control System [J]. Fire Control and Command Control, 2005, 30 (3): 98-104. |
| [3] | Li Hao, Wang Haiyan. The New Development of Fly-by-Wire Control System in Civil aircraft [J]. Journal of Civil Aviation University of China, 2000 (6): 8-11. |
| [4] | Zheng Shutao, Liao Feng, Wang Liwen. Experimental Study of Control Loading System of the Flight Simulator [J]. Journal of System Simulation, 2008, 20 (4): 965-969. |
| [5] | Zhang Chong, Xue Ying, Guo Jianwei. Simulation Research on Disengagement Force of Column Mechanism of Civil aircraft [J]. Science and Technology Innovation Herald, 2013, 26 (3): 23-24. |
| [6] | Yu Liming, Wang Zhanlin, Qiu Lihua. Simulation Research on Flight Control System Modeling and Order Reduction [J]. Computer Simulation, 2000, 17 (3): 15-18. |
| [7] | Tian Jinqiang, Xue Ying, Guo Jianwei. The Kinetics Simulation of Fly-by-Wire Aircraft Control Column System [J]. Civil Aircraft Design and Research Institute, 2012, 25 (3): 53-56. |
| [8] | Zhang Yusong. Study on Control Loading System in Flight Simulator Base on the Electro-Motive [D]. Tianjin: Civil Aviation University of China, 2009. |
| [9] | Sun Guoqing, Lv Ming. Analysis of Fly-by-Wire Control System [J]. Mechanical and Electronic, 2008, (18): 444. |
| [10] | Wang Junlong. Research on Mechanism Structure and Control Scheme of Active Side-stick in Aeroplane [D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2008 |
| [11] | Wang Ting, Zou Quan Liu Yan. Flight Test Method Study on Civil Aircraft Primary Flight Control Surfaces Jamming [J]. Xi’an: Advances in Aeronautical Science and Engineering, 2014. |
| [12] | Zhang Fang, The Operating Components in Cockpit of Fly-by-Wire Flight Control System Research [J]. Beijing: China Aeronautical academy, 2014. |
| [13] | Lin Fengjun. Design and analysis of CRJ200 aircraft flight control system [J]. Shanghai: Design and research of civil aircraft, 2001, 4, 32-39. |
| [14] | Ding Zuoquan. Active Side-stick Control System for Aeroplane [D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2011. |
| [15] | Gao Jinyuan, Li Luyu, Feng Yachang. Aircraft Handing Qualities [M]. Beijing: National Defence Industry Press, 2003: 31-47. |
| [16] | Tom Berger and Mark B. Handling Qualities Flight Test Assessment of a Business Jet NzU P-β Fly-By-Wire Control System [J]. American Institute of Aeronautics and Astronautics, 2017. |
| [17] | Berger, T., Tischler, M. B., Hagerott, S. G., Cotting, M. C., Gresham, J. L., George, J. E., Krogh, K. J., D’Argenio, A., and Howland, J. D., “Development and Validation of a Flight Identified Business Jet Simulation Model Using a Stitching Architecture,” AIAA Modeling and Simulation Technologies Conference, Grapevine, TX, January 2017. |
APA Style
Jingru Wang, Sen Liang. (2019). Modelling and Analysis About a Fault State of a New Cockpit Control Mechanism. American Journal of Aerospace Engineering, 6(1), 17-23. https://doi.org/10.11648/j.ajae.20190601.13
ACS Style
Jingru Wang; Sen Liang. Modelling and Analysis About a Fault State of a New Cockpit Control Mechanism. Am. J. Aerosp. Eng. 2019, 6(1), 17-23. doi: 10.11648/j.ajae.20190601.13
AMA Style
Jingru Wang, Sen Liang. Modelling and Analysis About a Fault State of a New Cockpit Control Mechanism. Am J Aerosp Eng. 2019;6(1):17-23. doi: 10.11648/j.ajae.20190601.13
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Download@article{10.11648/j.ajae.20190601.13,
author = {Jingru Wang and Sen Liang},
title = {Modelling and Analysis About a Fault State of a New Cockpit Control Mechanism},
journal = {American Journal of Aerospace Engineering},
volume = {6},
number = {1},
pages = {17-23},
doi = {10.11648/j.ajae.20190601.13},
url = {https://doi.org/10.11648/j.ajae.20190601.13},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.20190601.13},
abstract = {In the process of aircraft development, the assessment of handling quality is particularly step for verifying the cockpit control units design whether meets the design requirements or not. If the assess results are not met the design requirements, the design must to be optimized or even redesigned. At present, most of research is mainly related to the design of cockpit control units and simulating and assessment of their maneuverability based on the dynamic model in the normal mode, however, the research on handling quality of cockpit control units in the failure operating mode is seldom. Moreover, override rod linkage form as a new kind of cockpit control units brings plenty of profits such as the weight saved and maintainability improved, however, it causes the failure mode becomes diverse and complicated. Therefore it will increase the difficulty of assessing this kind of cockpit control units. The object of this paper is to do a research on working principle and physical characteristics of cockpit control units of override rod linkage form, through modeling and simulation on its normal operating mode and failure mode, and finally gives an analysis and evaluation for the column force quality of each failure mode. The simulation results reveal the column force quality of each failure mode is acceptable.},
year = {2019}
}
TY - JOUR T1 - Modelling and Analysis About a Fault State of a New Cockpit Control Mechanism AU - Jingru Wang AU - Sen Liang Y1 - 2019/09/04 PY - 2019 N1 - https://doi.org/10.11648/j.ajae.20190601.13 DO - 10.11648/j.ajae.20190601.13 T2 - American Journal of Aerospace Engineering JF - American Journal of Aerospace Engineering JO - American Journal of Aerospace Engineering SP - 17 EP - 23 PB - Science Publishing Group SN - 2376-4821 UR - https://doi.org/10.11648/j.ajae.20190601.13 AB - In the process of aircraft development, the assessment of handling quality is particularly step for verifying the cockpit control units design whether meets the design requirements or not. If the assess results are not met the design requirements, the design must to be optimized or even redesigned. At present, most of research is mainly related to the design of cockpit control units and simulating and assessment of their maneuverability based on the dynamic model in the normal mode, however, the research on handling quality of cockpit control units in the failure operating mode is seldom. Moreover, override rod linkage form as a new kind of cockpit control units brings plenty of profits such as the weight saved and maintainability improved, however, it causes the failure mode becomes diverse and complicated. Therefore it will increase the difficulty of assessing this kind of cockpit control units. The object of this paper is to do a research on working principle and physical characteristics of cockpit control units of override rod linkage form, through modeling and simulation on its normal operating mode and failure mode, and finally gives an analysis and evaluation for the column force quality of each failure mode. The simulation results reveal the column force quality of each failure mode is acceptable. VL - 6 IS - 1 ER -
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