Relevant bibliographies by topics / Landing gear retraction

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Conference papers

Academic literature on the topic 'Landing gear retraction'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Landing gear retraction"

1

Parat, Camille, Zu-Yun Li, and Jing-Shan Zhao. "Design and stiffness analysis of an overconstrained landing gear retraction mechanism with four side-stays." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 12 (January 13, 2019): 4421–35. http://dx.doi.org/10.1177/0954410018824509.

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It is the first mission for a landing gear retraction system to extend the structure during the phases of take-off and landing of the flight. Besides, the structure should be available to improve the reliability, strength and stability of the system while reducing the influence of the landing gear on the total drag. However, a large number of airplane accidents are due to the malfunctions or failures of the landing gear retraction system. In this paper, a novel design of retraction system is proposed. Instead of having only one side-stay to execute the desired motion, this new design proposed an over-constrained mechanism with four side-stays, which augments the structural strength and stability of the landing gear system with six over constraints. With such configuration, a second actuating motor to retract the landing gear can be inserted regardless of the first actuator to augment the reliability on the execution of the mechanism. Analyses on the properties of the landing gear retraction system with four side-stays show that the landing gear strut has a vertical motion, which decreases the working and storage spaces used for the system. Finally, this paper examines the statics and the stiffness coefficients of the retraction system with respect to its structure parameters. This provides the optimum structure for the landing gear system in terms of strength and reliability.
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Liang, Yong, Kun Zhao, Yingchun Chen, Longjun Zhang, and Gareth J. Bennett. "An Experimental Characterization on the Acoustic Performance of Forward/Rearward Retraction of a Nose Landing Gear." International Journal of Aerospace Engineering 2019 (July 4, 2019): 1–11. http://dx.doi.org/10.1155/2019/4135094.

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The modern undercarriage system of a large aircraft normally requires the landing gear to be retractable. The nose landing gear, installed in the front of the fuselage, is retracted either forward or rearward. In the forward/rearward retraction system, the landing gear is normally installed to the trailing/leading side of the bay. When the incoming flow passes the landing gear as well as the bay, the installation that corresponds to the forward/rearward retraction system has a significant impact on the coupling flow and the associated noise of the landing gear and the bay. In this paper, acoustic performance of the forward/rearward retraction of the nose landing gear was discussed based on experiment. The landing gear bay was simplified as a rectangular cavity, and tests were conducted in an aeroacoustics wind tunnel. The cavity oscillation was first analyzed with different incoming speeds. Then, the landing gear model was installed close to the trailing and the leading side of the cavity, respectively. It was observed that installation close to the leading side can help disturb the shear layer so as to suppress the oscillation, while the trailing one can make the landing gear itself produce lower noise. Accordingly, conclusions on the acoustic performance of the forward/rearward retraction of the nose landing gear are made.
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Ma, Jun Gong, Zhong Zhi Wu, Hao Ran Guo, and Jia Li. "Design and Simulation Study of a Certain Landing Gear Loading Simulation System." Advanced Materials Research 871 (December 2013): 69–76. http://dx.doi.org/10.4028/www.scientific.net/amr.871.69.

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The landing gear ground loading tests is a vital part before flight. As the motion of landing gear is three-dimensional motion,the traditional loading method cannot effectively simulate the pneumatic load on the ground. In order to simulate the load in the process of retraction/extension, a loading simulation system is proposed, including retractile system, position follow-up system and force servo loading system. This paper analyzes retraction/extension mechanism of the landing gear and builds up its mathematical model. A co-simulation model is developed in which the hydraulic system model and control system are built in software AMESim, the mechanical system of test platform model is built in software ADAMS. The results of the simulation confirm that the loading simulation system is feasible and provide the basis for building hardware platform.
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NICOLIN, Ilie, and Bogdan Adrian NICOLIN. "Research on the nose landing gear of a military training aircraft." INCAS BULLETIN 12, no. 4 (December 4, 2020): 249–59. http://dx.doi.org/10.13111/2066-8201.2020.12.4.23.

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This paper presents the analysis of the landing gear configurations and the proposal of a solution for a military training aircraft. The paper presents both landing gears: nose and main because they are inextricably linked. The nose landing gear of military aircraft is a complex system composed of structural elements, electric and hydraulic components, energy absorption components, aircraft tire wheels etc., which is dimensioned according to the weight of the aircraft. Additional components attached to the nose landing gear include a landing gear extension and retraction mechanism and a steering system. The landing gear must withstand the weight of the aircraft in all phases of take-off (maximum weight: fuel, armament, ammunition, other equipment, flight crew etc.) and landing (impact from landing and a lower weight after completing the mission due to fuel consumption and ammunition use).
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Shams, Taimur Ali, Syed Irtiza Ali Shah, Muhammad Ayaz Ahmad, Kashif Mehmood, Waseem Ahmad, and Syed Tauqeer ul Islam Rizvi. "Selection Methodology of an Electric Actuator for Nose Landing Gear of a Light Weight Aircraft." Applied Sciences 10, no. 23 (December 6, 2020): 8730. http://dx.doi.org/10.3390/app10238730.

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Landing gear system of an aircraft enables it to take off and land with safety and comfort. Because of the horizontal and vertical velocity of aircraft, upon landing, the complete aircraft undergoes different forcing functions in the form of the impact force that is absorbed by landing gears, shock absorbers, and actuators. In this research, a selection methodology has been proposed for an electrical actuator to be installed in the retraction mechanism of nose landing gear of an aircraft having 1600 kg gross takeoff weight. Nose landing gear and its associated components, like strut and shock absorbers, were modeled in CAD software. Analytical expressions were then developed in order to calculate the actuator stroke, translational velocity, force, and power for complete cycle of retraction, and some were subsequently compared with the computational results that were obtained using MSC ADAMS®. Air in the oleo-pneumatic shock absorber of nose landing gear was modeled as a nonlinear spring with equivalent spring constant, whereas hydraulic oil was modeled as a nonlinear damper with equivalent damping constant. The nose landing gear system was modeled as a mass-spring-damper system for which a solution for sinusoidal forcing functions is proposed. Finally, an electrical actuator has been selected, which can retract and extend nose landing gear, meeting all of the constraints of aircraft, like fuselage space, aircraft ground clearance, locking loads, power consumption, retraction and extension time, and dynamic response of aircraft. It was found that the selection of an electrical actuator is based upon the quantification of forces transmitted to electrical actuator during one point load at gross takeoff weight. The ability of retraction and extension time, as dictated by Federal Aviation Regulation, has also been given due consideration in the proposed methodology as significant criteria. The proposed system is now in the process of ground testing, followed by flight testing in the near future.
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Zhang, Li, Hong Nie, and Xiaohui Wei. "Tolerance Design and Robust Study for The Joint Clearances of Landing Gear Retraction Mechanisms." Applied Sciences 10, no. 14 (July 15, 2020): 4856. http://dx.doi.org/10.3390/app10144856.

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Joint clearances inevitably affect the kinematic accuracy and robustness of landing gear retraction mechanisms. However, the complexity and uncertainty of the clearances lead to difficulty in establishing mathematic models and analyzing effects. In the interest of assessing the clearance effects on the kinematic accuracy of landing gears, an integrated tolerance theory is proposed in this paper. In the theory proposed, Jacobian–Torsor model is combined with robust analysis to establish the kinematic accuracy model and predict the influences of clearances. The overall steps to apply the theory presented in practice are given. A typical landing gear retraction mechanism is chosen for the case study and the results show that the tendencies of clearances can be observed. Through the process of tolerance design, robust study, and tolerance redesign, the kinematic accuracy is significantly improved. The integrated tolerance theory proposed and the study conducted will provide designers new insights for the clearance analysis of landing gear mechanisms.
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Zhou, Changcong, Mengyao Ji, Yishang Zhang, Fuchao Liu, and Haodong Zhao. "Mechanism reliability and sensitivity analysis of landing gear under multiple failure modes." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 39, no. 1 (February 2021): 46–54. http://dx.doi.org/10.1051/jnwpu/20213910046.

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For a certain type of aircraft landing gear retraction-extension mechanism, a multi-body dynamic simulation model is established, and the time-dependent curves of force and angle are obtained. Considering the random uncertainty of friction coefficient, assembly error, and the change of hinge wear under different retraction times, the reliability model is built including three failure modes of landing gear, i.e. blocking failure, positioning failure and accuracy failure. Based on the adaptive Kriging model, the reliability and sensitivity of retraction-extension system under the condition of single failure mode and multiple failure modes in series are analyzed, and the rule of reliability and sensitivity changing with the number of operations is given. The results show that the system failure probability of landing gear mechanism tends to decrease first and then increase when considering the given information of random factors, and the influences of random factors on the failure probability vary with the number of operations. This work provides a viable tool for the reliability analysis and design of landing gear mechanisms.
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De Stefano, Giuliano, Nunzio Natale, Giovanni Paolo Reina, and Antonio Piccolo. "Computational Evaluation of Aerodynamic Loading on Retractable Landing-Gears." Aerospace 7, no. 6 (May 29, 2020): 68. http://dx.doi.org/10.3390/aerospace7060068.

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Computational fluid dynamics is employed to evaluate the mean aerodynamic loading on the retractable landing-gears of a regional transport commercial aircraft. The mean turbulent flow around simplified landing-gear systems including doors is simulated by using the Reynolds-averaged Navier–Stokes approach, where the governing equations are solved with a finite volume-based numerical method. Using a dynamic meshing method, the computational grid is automatically and continuously adapted to the time-changing geometry, while following the extension/retraction of the landing-gear systems. The temporal evolution of the aerodynamic forces on both the nose and the main landing-gears, along with the hinge moments of the doors, is numerically predicted. The proposed computational modeling approach is verified to have good practical potential when compared with reference experimental data provided by the Leonardo Aircraft structural loads group.
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Liu, Ji Hong, Ying Zhong Pang, and Yu Ming Zhu. "Multi-Domain Unified Modeling and Simulation for Aircraft Landing Gear Using Modelica." Advanced Materials Research 311-313 (August 2011): 2457–60. http://dx.doi.org/10.4028/www.scientific.net/amr.311-313.2457.

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Modern products become more and more complex, the modeling and simulation of them are carried out with different software on heterogeneous platforms, which always caused the heterogeneous data, separated disciplines and cannot obtain the result of unified model correctly. Therefore, a Modelica-based modeling and simulation method for aircraft landing gear is proposed. The landing gear library based on Modelica was established. The unified physical model of landing gear which is composed of structural, thermodynamics and hydromechanics disciplines is constructed. The aircraft landing process, the track of retraction mechanism and the impact work amount of the shock absorber are obtained through multi-domain unified simulation, which provides references for deisgners.
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Yin, Yin, Nie Hong, Ni Huajin, and Zhang Ming. "Reliability Analysis of Landing Gear Retraction System Influenced by Multifactors." Journal of Aircraft 53, no. 3 (May 2016): 713–24. http://dx.doi.org/10.2514/1.c033333.

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Dissertations / Theses on the topic "Landing gear retraction"

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Yang, Yang. "Aircraft landing gear extension and retraction control system diagnostics, prognostics and health management." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7266.

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This thesis contains the Group Design Project (GDP) work and Individual Research Project (IRP) work. The target of this GDP was to design a long range flying wing passenger aircraft to meet the increasing global aircraft demand. The name of this flying wing aircraft is FW-11. This is a project cooperated between Aviation Industry Corporation of China (AVIC) and Cranfield University. The writer was involved in the conceptual design stage of this project. The author was in charge of the engine market, engine selection, engine sizing and performance. The target of the IRP is to build a set of health management methods including system real-time monitoring, accurate fault diagnosis and prognosis of major components which are suitable for the aircraft landing gear extension and retraction control system. These technologies have the capability to improve mission reliability of the aircraft and the maintenance costs could be reduced. Simultaneously, aircraft landing gear extension and retraction control system, as one of the most important aircraft systems on-board, could directly affect the flight safety. Consequently, diagnostic, prognostic and health management (DPHM) technology is necessary for the system. Based on the FHA, FMEA and FTA of the aircraft landing gear extension and retraction control system, each of the catastrophic events, all the root causes and their effects were identified. Synchronously, all the components which are related to the catastrophic events were found. The rule-based expert system diagnostic technology was chosen from the available approaches and it was successfully applied on the system. Appropriate prognosis approach was recommended for each component of the system according to the features of components of the system. Finally, the DPHM architecture of the landing gear extension and retraction control system was built.
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Novák, Josef. "Návrh podvozku VUT200 TwinCobra." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232017.

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The goal of following master thesis is to design variety of configuration and retraction options of VUT200 TwinCobra landing gear. For each option are a wheel base and a gauge set up by possibility of main landing gear retraction. Next, CS 23 demands and stress analysis are followed. There is a view of twin engine aircraft landing gear disclosed as well.
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Bartoněk, Jaroslav. "Návrh zatahovacího podvozku pro letoun NG4." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2011. http://www.nusl.cz/ntk/nusl-229467.

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This diploma thesis describes the design of retractable landing gear for the NG-4 ultralight aircraft. Its main part consists of general principle of gear retraction, kinematics analysis, load calculation and structural analysis, material selection and means of controlling by pilot. The thesis contents marginally the typology of aircraft landing gears and their evolution.
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Hsin, Chien-Chou, and 辛建周. "On the motion of a spatial 6R retracting and twisting mechanism for landing gears." Thesis, 1995. http://ndltd.ncl.edu.tw/handle/11627014269902616192.

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碩士
國立成功大學
機械工程研究所
83
Landing gear is one of the necessary systems of an airplane. The major object of this research is to investigate the application of Lee-Yan type II spatial 6R linkage for landing gears. First, existing landing gear mechanisms are surveyed and classified based on the characteristics of retraction, twisting ,and contraction. Then, Lee-Yan type II spatial 6R linkage is adopted as the retracting and twisting mechanism for the landing gear. Kinematic analysis of this mechanism is carried out according to matrix-loop approach and some constraints. The concept of "moving plane" is purposed and a systematic design procedure is presented for the kinematic design of the landing gear. The concept of moving plane, with only simple graph concept, can synthesize the landing gear easily without involving complicated algebraic and numerical calculations. Furthermore, engineers can change design parameters based on various spatial constraints and reguirements to obtain the same retracting and twisting motions and to avoid the problem of unique solution. Furthermore, since Lee-Yan type II mechanism is a compact mechanism in any position, the problem of interference can be checked by the concept of planar 4-bar linkages. Finally, an example is presented to illustrate the feasibility of the proposed approach.
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Books on the topic "Landing gear retraction"

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Schmidt, Robert Kyle. The Design of Aircraft Landing Gear. SAE International, 2021. http://dx.doi.org/10.4271/9780768099430.

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The aircraft landing gear and its associated systems represent a compelling design challenge: simultaneously a system, a structure, and a machine, it supports the aircraft on the ground, absorbs landing and braking energy, permits maneuvering, and retracts to minimize aircraft drag. Yet, as it is not required during flight, it also represents dead weight and significant effort must be made to minimize its total mass. The Design of Aircraft Landing Gear, written by R. Kyle Schmidt, PE (B.A.Sc. - Mechanical Engineering, M.Sc. - Safety and Aircraft Accident Investigation, Chairman of the SAE A-5 Committee on Aircraft Landing Gear), is designed to guide the reader through the key principles of landing system design and to provide additional references when available. Many problems which must be confronted have already been addressed by others in the past, but the information is not known or shared, leading to the observation that there are few new problems, but many new people. The Design of Aircraft Landing Gear is intended to share much of the existing information and provide avenues for further exploration. The design of an aircraft and its associated systems, including the landing system, involves iterative loops as the impact of each modification to a system or component is evaluated against the whole. It is rare to find that the lightest possible landing gear represents the best solution for the aircraft: the lightest landing gear may require attachment structures which don't exist and which would require significant weight and compromise on the part of the airframe structure design. With those requirements and compromises in mind,The Design of Aircraft Landing Gear starts with the study of airfield compatibility, aircraft stability on the ground, the correct choice of tires, followed by discussion of brakes, wheels, and brake control systems. Various landing gear architectures are investigated together with the details of shock absorber designs. Retraction, kinematics, and mechanisms are studied as well as possible actuation approaches. Detailed information on the various hydraulic and electric services commonly found on aircraft, and system elements such as dressings, lighting, and steering are also reviewed. Detail design points, the process of analysis, and a review of the relevant requirements and regulations round out the book content. The Design of Aircraft Landing Gear is a landmark work in the industry, and a must-read for any engineer interested in updating specific skills and students preparing for an exciting career.
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Conference papers on the topic "Landing gear retraction"

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Fan, Qifeng, Kai Guo, Yan Wang, and Shu Li. "Dynamic simulation of retraction mechanism of the landing gear." In International Conference on Simulation and Modeling Methodologies, Technologies and Applications. Southampton, UK: WIT Press, 2014. http://dx.doi.org/10.2495/smta140551.

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Singh, Krishna Lok, and Vanam Upendranath. "Dynamic Simulation of a Landing Gear System for Retraction and Deployment." In 2013 International Conference on Machine Intelligence and Research Advancement (ICMIRA). IEEE, 2013. http://dx.doi.org/10.1109/icmira.2013.111.

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Jacazio, Giovanni, and Gualtiero Balossini. "A Mechatronic Active Force Control System for Real Time Test Loading of an Aircraft Landing Gear." In ASME 2009 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/detc2009-86148.

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This paper describes an electronically controlled active force control system that was recently developed to provide real time loading for the tests of a landing gear. As the landing gear moves during the test, a force is generated on the landing gear in order to ensure that its dynamics is identical to that that would occur during its operation in an actual flight. Since landing gear deployment and retraction can occur at different environmental and flight conditions, the load profile that must be developed by the force control system depends on the simulated flight condition and is determined by an appropriate landing gear model. To attain accurate force control, a system was setup comprised of a servovalve controlled hydraulic actuator, force and position sensors, and a high rate digital controller implementing a complex adaptive control law. An excellent accuracy of the load control was eventually achieved for all load profiles occurring on the landing gear.
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Zhang, Linhai, Yeming Yao, and Lilin Xu. "Research on control strategy for ground extension and retraction test of landing gear." In 2020 5th International Conference on Automation, Control and Robotics Engineering (CACRE). IEEE, 2020. http://dx.doi.org/10.1109/cacre50138.2020.9230073.

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Krishnan, A., V. Thejus, and B. M. Arjun. "Numerical investigation of structural design of torsion links in a landing gear retraction mechanism." In 2017 2nd International Conference for Convergence in Technology (I2CT). IEEE, 2017. http://dx.doi.org/10.1109/i2ct.2017.8226156.

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Wang Kuan and Huang Xiping. "Research on Simulation of Aircraft's Landing Gear Retraction System Considering Multi-Discipline Coupled Factor." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2018). Institution of Engineering and Technology, 2018. http://dx.doi.org/10.1049/cp.2018.0226.

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Chuang, L., X. Yubing, and W. Hao. "Civil aircraft landing gear retraction/extension system architecture design decision based on safety analysis." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2020). Institution of Engineering and Technology, 2021. http://dx.doi.org/10.1049/icp.2021.0146.

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Green, Bradford E., and Ryan Czerwiec. "CFD Analysis of the F/A-18E Super Hornet during Extension and Retraction of the Landing Gear." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-1106.

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Yang, Beilei, Xiaohua Wu, Weilin Li, Xiyang Zhao, Jiuan Gao, and Yang Yang. "FMI based multi-domain modeling and simulation for extraction and retraction of EHA nose landing gear in Dymola." In 2016 International Conference on Electrical Systems for Aircraft, Railway, Ship Propulsion and Road Vehicles & International Transportation Electrification Conference (ESARS-ITEC). IEEE, 2016. http://dx.doi.org/10.1109/esars-itec.2016.7841376.

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Liu, Kuijian, Yunwen Feng, and Xiaofeng Xue. "Fault Diagnosis and Health Assessment of Landing Gear Hydraulic Retraction System Based on Multi-source Information Feature Fusion." In 2017 International Conference on Sensing, Diagnostics, Prognostics and Control (SDPC). IEEE, 2017. http://dx.doi.org/10.1109/sdpc.2017.68.

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