Journal articles: 'Main landing gear'

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Sartor, P., K. Worden, R. K. Schmidt, and D. A. Bond. "Bayesian sensitivity analysis of flight parameters that affect main landing gear yield locations." Aeronautical Journal 118, no. 1210 (December 2014): 1481–97. http://dx.doi.org/10.1017/s0001924000010150.

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Abstract An aircraft and landing gear loads model was developed to assess the Margin of Safety (MS) in main landing gear components such as the main fitting, sliding tube and shock absorber upper diaphragm tube. Using a technique of Bayesian sensitivity analysis, a number of flight parameters were varied in the aircraft and landing gear loads model to gain an understanding of the sensitivity of the MS of the main landing gear components to the individual flight parameters in symmetric two-point landings. The significant flight parameters to the main fitting MS, sliding tube bending moment MS and shock absorber upper diaphragm tube MS include: longitudinal tyre-runway friction coefficient, aircraft vertical descent velocity, aircraft Euler pitch angle and aircraft mass. It was also shown that shock absorber servicing state and tyre pressure do not contribute significantly to the MS.

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Wandono, Fajar Ari. "Optimization of the Main Landing Gear Structure of LSU-02NGLD." Computational And Experimental Research In Materials And Renewable Energy 4, no. 1 (May 28, 2021): 30. http://dx.doi.org/10.19184/cerimre.v4i1.24965.

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The mass of the landing gear structure becomes an important aspect of the total mass of the UAV (unmanned aerial vehicle). Therefore, many efforts have been made to reduce the mass of the landing gear by performing structural optimization. Reducing the mass of the landing gear structure can be used as a substitute to increase the payload on the UAV. The landing gear structure in this paper is the main landing gear of LSU-02NGLD (LAPAN Surveillance UAV series 02 New Generation Low Drag). LSU-02NGLD is a UAV that has 2.9 m of wingspan with a total mass of 21 kg. This paper aims to optimize the main landing gear structure so that optimization can reduce the mass. The optimization was carried out using the finite element software by modeling the main landing gear structure as a 1D beam element. There were 9 beam elements in the main landing gear structure model. The cross-sectional width (w) and the cross-sectional height (h) for each element were used as design variables. The objective of the optimization was to minimize the mass while maintaining maximum bending stress not greater than 20 MPa, displacement in y-direction not greater than 1 mm, and displacement in z-direction not greater than 0.1 mm. The optimization result showed that the mass reduction of the main landing gear structure was 50%, with all constraints fulfilled.

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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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Hidayat, Dony, Jos Istiyanto, Danardono Agus Sumarsono, and Aryandi Marta. "INVESTIGASI GAYA KONTAK/IMPAK PADA MAIN LANDING GEAR PESAWAT KOMUTER DENGAN PENDEKATAN MULTI-BODY SIMULATION (MBS) RIGID MODELS." Jurnal Teknologi Dirgantara 15, no. 1 (December 14, 2017): 1. http://dx.doi.org/10.30536/j.jtd.2017.v15.a2529.

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Landing Gear Drop Test (LGDT) which aims to determine the characteristic of contact/impact force that occurs in the time of the touchdown landing has been conducted. Experimental tests using the apparatus requires a substantial time and cost. Virtual Landing Gear Drop Test (vLGDT) using MSC ADAMS software is one of the solutions for initial stage to testing landing gear. Stiffness values and damping coefficient obtained from vLGDT are 5.0e5 N/m and 1600 N.sec/m. Contact/impact force that occurs on vLGDT is 75996 N, while from experimental is 73612 N. The difference between vLGDT and experimental result is 3.14%.Abstrak:Pengujian landing gear yang bertujuan untuk mengetahui karakteristik gaya kontak/impak yang terjadi saat touchdown landing telah dilakukan. Pengujian eksperimental menggunakan apparatus membutuhkan waktu yang lama dan biaya yang besar. Vitual Landing Gear Drop Test (vLGDT) menggunakan perangkat lunak MSC ADAMS merupakan salah satu alternatif untuk pengujian tahap awal landing gear. Dari simulasi menggunakan vLGDT diperoleh nilai k = 5.0e5 N/m dan cmax = 1600 N.detik/m. Gaya kontak/impak yang terjadi pada simulasi menggunakan vLGDT sebesar 75996 N, sedangkan dari eksperimental sebesar 73612 N. Hasil vLGDT lebih besar 3.14% dibandingkan eksperimental.

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Krason, W., and J. Malachowski. "Multibody rigid models and 3D FE models in numerical analysis of transport aircraft main landing gear." Bulletin of the Polish Academy of Sciences Technical Sciences 63, no. 3 (September 1, 2015): 745–57. http://dx.doi.org/10.1515/bpasts-2015-0086.

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Abstract Dynamic analyses of a transport aircraft landing gear are conducted to determine the effort of such a complex system and provide capabilities to predict their behaviour under hazardous conditions. This kind of investigation with the use of numerical methods implementation is much easier and less expensive than stand tests. Various 3D models of the landing gear part are defined for the multistage static FE analysis. A complete system of the main landing gear was mapped as a deformable 3D numerical model for dynamic analysis with the use of LS-Dyna code. In this 3D deformable FE model, developed in a drop test simulation, the following matters were taken into consideration: contact problems between collaborating elements, the phenomena of energy absorption by a gas-liquid damper placed in the landing gear and the response of the landing gear during the touchdown of a flexible wheel with the ground. The results of numerical analyses for the selected drop tests and the results from the experiments carried out on a real landing gear were used for verification of FE models and a methodology of the landing gear dynamics analysis. The results obtained from the various simulations of the touchdown have proved the effectiveness of the 3D numerical model and how many problems can be solved in the course of only one numerical run, e.g. geometric and material nonlinearities, a question of contact between the mating components, investigation of the landing gear kinematics, investigation of the energy dissipation problem in the whole system and the stresses influence on the structure behaviour, which can appear in some elements due to overload.

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Skorupka, Zbigniew. "Dynamic Fatigue Tests Of Landing Gears." Fatigue of Aircraft Structures 2020, no. 12 (December 1, 2020): 69–77. http://dx.doi.org/10.2478/fas-2020-0007.

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Abstract Landing gears are one of the main components of an aircraft. The landing gear is used not only during take-off and landing but also, in most cases, during ground manoeuvres. Due to its function, the landing gear is also one of the key safety components of the aircraft due to dissipating landing loads acting on the aircraft. The mentioned loads come from both the vertical and horizontal speeds during touchdown and by the aircraft’s losing the speed by braking. The landing gear is then loaded with constantly changing forces acting in various directions during every landing, with the only difference coming from their magnitude. The repeatable loading conditions cause significant wear of the landing gear. This wear can be divided into two categories, one is the wear of consumable parts such as the brake linings and the other is the fatigue wear of the structural components. The latter type of wear is much more dangerous due to its slow, and in many cases, unnoticeable progression. Fatigue wear can be estimated by numerical analyses – this method works with a great degree of probability on single components but due to the complexity of the landing gear as a whole it is not precise enough to be applied to the full structure. In order to evaluate the fatigue of the whole landing gear the best method accepted by regulations is the laboratory testing method. It involves a series of various drop tests resembling the real landing condition distribution. The aim of the tests is to check the fatigue wear of the landing gear and to prove its reliability for certification and/or operational purposes. In this paper the author describes the basics of the landing gear fatigue wear, possibilities of its evaluation and presents laboratory dynamic method used for extensive tests in life-like operation conditions.

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NICOLIN, Ilie, and Bogdan Adrian NICOLIN. "Preliminary calculation of the landing gear of a military training aircraft." INCAS BULLETIN 12, no. 4 (December 4, 2020): 241–47. http://dx.doi.org/10.13111/2066-8201.2020.12.4.22.

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The paper presents a preliminary calculation method, which is easy to apply for pre-dimensioning the landing gear. Preliminary calculation of the landing gear includes estimating the loads on landing and determining the position of the nose landing gear and the main landing gear of a military training aircraft. Another purpose of the preliminary calculation is to ensure the stability of a military training aircraft on landing and take-off, as well as to ensure the lateral stability of the aircraft during ground operations such as taxiing, landing or take-off.

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Chuban, Vitalii Dmitrievich. "SHIMMY ANALYSIS OF LIGHT AIRPLANE MAIN LANDING GEAR." TsAGI Science Journal 48, no. 7 (2017): 665–72. http://dx.doi.org/10.1615/tsagiscij.2018026284.

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9

Mu, Yongfei, Jie Li, Wutao Lei, and Daxiong Liao. "The effect of doors and cavity on the aerodynamic noise of fuselage nose landing gear." International Journal of Aeroacoustics 20, no. 3-4 (March 15, 2021): 345–60. http://dx.doi.org/10.1177/1475472x211003297.

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The aerodynamic noise of landing gears have been widely studied as an important component of the airframe noise. During take-off and landing, there are doors, cavity and fuselage around the landing gear. The noise caused by these aircraft components will interfere with aerodynamic noise generated by the landing gear itself. Hence, paper proposes an Improved Delayed Detached Eddy Simulation (IDDES) method for the investigation of the flow field around a single fuselage nose landing gear (NLG) model and a fuselage nose landing gear model with doors, cavity and fuselage nose (NLG-DCN) respectively. The difference between the two flow fields were analyzed in detail to better understand the influence of these components around the aircraft’s landing gear, and it was found that there is a serious mixing phenomenon among the separated flow from the front doors, the unstable shear layer falling off the leading edge of the cavity and the wake of the main strut which directly leads to the enhancement of the noise levels. Furthermore, after the noise sound waves are reflected by the doors several times, an interference phenomenon is generated between the doors. This interference may be a reason why the tone excited in the cavity is suppressed.

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10

Chen, Pu Woei, Shu Han Chang, and Chan Ming Chen. "Impact Loading Analysis of Light Sport Aircraft Landing Gear." Applied Mechanics and Materials 518 (February 2014): 252–57. http://dx.doi.org/10.4028/www.scientific.net/amm.518.252.

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This paper examined the critical loading condition of a light sport aircrafts main landing gear during the impact loading condition. The new category airplane was established by the FAA in 2004. The light sport aircraft has great market demand for personnel entertainment purpose and regional transportation. The main object of this research was to establish a static and dynamic loading simulation model for the aluminum alloy landing gear of a light sport aircraft. This work also examined the critical loading parameters of the main landing gear, including the maximum take-off weight and maximum stall speed. The analysis was performed using ANSYS and LS-DYNA to establish the finite element model after simplifying the geometric characteristics and verifying the results by energy conservation, hourglass energy, and sliding energy. The study tested aluminum plates with a thickness from 15~25 mm. The results showed all the samples could sustain the required loading condition, except for the thickness of 15mm that failed under impact loading. The simulation model provides a cost-saving process compared to a real crashworthiness drop test to test the main landing gears compliance with regulations.

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Luong, Quoc Viet, Dae-Sung Jang, and Jai-Hyuk Hwang. "Semi-Active Control for a Helicopter with Multiple Landing Gears Equipped with Magnetorheological Dampers." Applied Sciences 11, no. 8 (April 19, 2021): 3667. http://dx.doi.org/10.3390/app11083667.

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Due to their extensive use in various applications, helicopters need to be able to land in a variety of conditions. Typically, a helicopter landing gear system with skids or passive wheel-dampers is designed based on only one critical touchdown condition. Thus, this helicopter landing gear system may not perform well in different landing conditions. A landing gear system with magnetorheological (MR) dampers would be a promising candidate to solve this problem. However, a semi-active controller must be designed to determine the electrical current applied to the MR damper to directly manage the damping force. This paper presents a new skyhook controller, called the skyhook extended controller, for a helicopter with multiple landing gears equipped with MR dampers to reduce the helicopter’s acceleration at the center of gravity in off-normal landing attitude conditions. A 9-DOF simulation model of a helicopter with multiple MR landing gears was built using RECURDYN. To verify the effectiveness of the proposed controller, co-simulations were executed with RECURDYN and MATLAB in different initial pitch and roll angles at touchdown. The main simulation results show that the proposed controller can greatly decrease the peak and rms acceleration of the helicopter’s center of gravity compared to a traditional skyhook controller and passive damper.

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12

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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Chen, Fei, Yong Lv, and Zhi Wei Xing. "The Strength Analysis of Aircraft Landing Gear Strut Based on ANSYS." Advanced Materials Research 490-495 (March 2012): 2686–90. http://dx.doi.org/10.4028/www.scientific.net/amr.490-495.2686.

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Because the landing gear structure is complicated, it is difficult to draw accurate stress and strain distribution through the theoretical calculation. In this paper, based on the modeling and stress analysis of the buffer mechanism of aircraft landing gear, by converting the stress of a dynamic system into a static stress, the force of the landing gear struts are calculated. This paper analyzes the strength of the aircraft main landing gear by using computer simulation technology and finite element analysis, it provides an effective basis for maintenance and the damage prediction

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Rui Pires, Dr, Prof .Dr. S. M.J.Ali, and A. S. A. Al-banaa. "Stress analysis on main landing gear for small aircraft." AL-Rafdain Engineering Journal (AREJ) 22, no. 1 (February 28, 2014): 26–33. http://dx.doi.org/10.33899/rengj.2014.87009.

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Li, Yuan, Jason Zheng Jiang, and Simon Neild. "Inerter-Based Configurations for Main-Landing-Gear Shimmy Suppression." Journal of Aircraft 54, no. 2 (March 2017): 684–93. http://dx.doi.org/10.2514/1.c033964.

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Diltemiz, Seyid Fehmi. "Failure analysis of aircraft main landing gear cylinder support." Engineering Failure Analysis 129 (November 2021): 105711. http://dx.doi.org/10.1016/j.engfailanal.2021.105711.

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Vechtel, Dennis, Ute Marita Meissner, and Klaus-Uwe Hahn. "On the use of a steerable main landing gear for crosswind landing assistance." CEAS Aeronautical Journal 5, no. 3 (March 30, 2014): 293–303. http://dx.doi.org/10.1007/s13272-014-0107-2.

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Zhou, Jin, Jianjiang Zeng, Jichang Chen, and Mingbo Tong. "Analysis of Global Sensitivity of Landing Variables on Landing Loads and Extreme Values of the Loads in Carrier-Based Aircrafts." International Journal of Aerospace Engineering 2018 (2018): 1–14. http://dx.doi.org/10.1155/2018/2105682.

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When a carrier-based aircraft is in arrested landing on deck, the impact loads on landing gears and airframe are closely related to landing states. The distribution and extreme values of the landing loads obtained during life-cycle analysis provide an important basis for buffering parameter design and fatigue design. In this paper, the effect of the multivariate distribution was studied based on military standards and guides. By establishment of a virtual prototype, the extended Fourier amplitude sensitivity test (EFAST) method is applied on sensitivity analysis of landing variables. The results show that sinking speed and rolling angle are the main influencing factors on the landing gear’s course load and vertical load; sinking speed, rolling angle, and yawing angle are the main influencing factors on the landing gear’s lateral load; and sinking speed is the main influencing factor on the barycenter overload. The extreme values of loads show that the typical condition design in the structural strength analysis is safe. The maximum difference value of the vertical load of the main landing gear is 12.0%. This research may provide some reference for structure design of landing gears and compilation of load spectrum for carrier-based aircrafts.

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Wijaya, Yusuf Giri, and Abian Nurrohmad. "DESIGN OF FORCE MEASURING SYSTEM ON MAIN LANDING GEAR WEIGHT DROP TESTING MACHINE FOR THE APPLICATION OF LSU SERIES." Jurnal Teknologi Dirgantara 18, no. 2 (December 27, 2020): 159. http://dx.doi.org/10.30536/j.jtd.2020.v18.a3377.

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In this research, the design of the force measuring system on main landing gear weight drop test for the LSU series that developed by LAPAN was carried out. The principle of this machine is to apply the load according to the weight of the aircraft on the main landing gear and drop it at a certain height assisted by the guiding rail. At the bottom of this machine there is a impact platform where each angle is mounted with a load cell that functions to measure the reaction force due to the impact of the main landing gear. In addition, there is a data acquisition system whose function is to process the output signal from load cell and display measurement data. The data acquisition system used consists of DAQ measurement hardware made by national instruments and LabVIEW software installed on a PC. The design of this testing tools aims to carry out a dynamic impact test on the main landing gear structure of the UAV. In this study, static calibration has also been successfully performed on the impact platform and shows consistent results for various test masses.

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Zhang, Wei, Qian Dong, and Xian Min Zhang. "Study on Mechanical Response Changes of Pavement to Aircraft Loads with Different Landing Gear Configurations." Applied Mechanics and Materials 723 (January 2015): 60–64. http://dx.doi.org/10.4028/www.scientific.net/amm.723.60.

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The finite element model of runway is established based on elastic layered theory and it is used for analyzing the influence on mechanical responses due to changes of main landing gear configurations. The results show that the more the total number of wheels on a main landing gear is, the smaller displacement peak, maximum tensile stress under panel bottom and solid foundation influence depth are in conditions that aircraft loads are equal. When the landing gear spacing is smaller, the displacement curves in the loading area are gentler. The changes of configurations influence little on displacements in regions far away from loading area.

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Duarte, Rafael, Manuela Azevedo, and Manuel Afonso-Dias. "Segmentation and fishery characteristics of the mixed-species multi-gear Portuguese fleet." ICES Journal of Marine Science 66, no. 3 (February 19, 2009): 594–606. http://dx.doi.org/10.1093/icesjms/fsp019.

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Abstract Duarte, R., Azevedo, M., and Afonso-Dias, M. 2009. Segmentation and fishery characteristics of the mixed-species multi-gear Portuguese fleet. – ICES Journal of Marine Science, 66: 594–606. Fleet segmentation and knowledge of fishing fleet dynamics are essential to move from single species to fishery/fleet-based advice. The coastal mixed-species multi-gear Portuguese fleet comprises medium-sized (>12 m) vessels, using a diversity of passive gears, and is economically important. For hake (under a recovery plan) and monkfish (overexploited), it contributes >50% to their total annual landings. Commercial daily landings in 2005 from 271 vessels were analysed by region using non-hierarchical cluster analysis and multivariate regression trees. The cluster analysis allowed the identification of regional fleet segments with a low mixture of species throughout the year. The multivariate regression trees were applied to clusters of vessels with a high mixture of species, to explain weekly landing profiles (species) by vessel technical characteristics, fishing license, and main landing port. The results showed a link between exploited species and geographic location, and in the north between vessel size and depth and an inshore/offshore range. Finally, from the analysis and for the most important species exploited by the Portuguese multi-gear fleet, it was possible to define two or three vessel groups that accounted for at least 50% of the landed value.

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Zhang, Li, and Cai Jun Xue. "A Landing Gear Drop Dynamic Simulation Based on the LMS. Virtual. Lab." Applied Mechanics and Materials 55-57 (May 2011): 684–87. http://dx.doi.org/10.4028/www.scientific.net/amm.55-57.684.

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In order to evaluate the dynamic behavior of the buffer of the Seagull 300 aircraft’s main landing gear, a drop model is built to simulate the drop dynamics using the software of LMS Virtual Lab Motion. The fluid damping force of the buffer, the air spring force of the buffer, the tire force of the landing gear and the weight of the fuselage are considered in the model. The simulation results are compared with the results of the Seagull 300 landing gears drop test, which proves the accuracy of the simulation model. Then the buffer performance and its influence factors are computationally discussed. This method gives a new way to study and improve the performance of the buffer system of an aircraft.

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Yadav, D., and R. P. Ramamoorthy. "Nonlinear Landing Gear Behavior at Touchdown." Journal of Dynamic Systems, Measurement, and Control 113, no. 4 (December 1, 1991): 677–83. http://dx.doi.org/10.1115/1.2896474.

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Landing gear dynamics for an aircraft has been analyzed with a heave-pitch model having telescopic main gear and articulated nose gear using oleopneumatic shock absorber. System equations have been presented incorporating the effects of linkage dynamics, frictional forces, and nonlinearities in the tyre, air spring, and oleo damping forces. Sensitivity of the system response to variations in some shock strut parameters has been investigated for the landing touchdown impact phase to bring about improvement in the performance.

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Chondrou, I. T., G. Mavrantonakis, N. Tsagarakis, E. Vergis, D. Pangalos, and T. G. Chondros. "Design evaluation of the fractured main landing gear of a BAE Jetstream SX-SKY aircraft." International Journal of Structural Integrity 6, no. 4 (August 10, 2015): 468–92. http://dx.doi.org/10.1108/ijsi-08-2014-0039.

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Purpose – The purpose of this paper is to study the main landing gear (MLG) mechanism configuration. Design/methodology/approach – Mechanism kinematics and dynamics, stress analysis and sizing of the MLG structural members, and fatigue issues related with the mechanism operation. Spreadsheet solutions were incorporated to this survey to analyze the most conceivable loading situations, and important factors of the mechanism design for an initial evaluation of safety implications. Findings – MLG design approach along with conservative fatigue design factors lies in the area of accepted limits in commercial aircraft industry. Research limitations/implications – MLG loading associated with landing as well as those associated with ground maneuvers (steering, braking and taxiing) contribute significantly to fatigue damage, along with the stresses induced by manufacturing processes and assembly. The application of FEA methods for the design of the landing gear does not always guarantee a successful approach to the problem solution, if precise analytical solutions are not available in advance. Practical implications – From the investigation of this incident of fractured struts of the MLG it is confirmed that the reduction in Pintle Housing diameter on the upper part has contributed to the avoidance of damaging the fuel tank above the MLG that would lead to a catastrophic event. On the other hand, the airframe of the SKY-Jet was proved efficient for a belly landing with minor damages to the passengers and heavier damages for the aircraft. Social implications – On-line vibration monitoring sensors hooked up to the landing gear strut and Pintle House would greatly enhance safety, without relying in optical surveys in hard to access and inspect areas of the landing gears mechanisms housings. Originality/value – Analytic methods were adopted and spreadsheet solutions were developed for the MLG main loading situations, along with design issues concerning mechanism kinematics and dynamics, stress analysis and sizing of the MLG structural members, as well as fatigue issues related with the mechanism operation. Spreadsheet solutions were incorporated to this survey to analyze the most conceivable loading situations, and important factors of the mechanism design for an initial evaluation of safety implications.

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Wang, Hong Feng, W. W. Song, J. L. Wang, Dun Wen Zuo, and X. L. Duan. "Effect of the Impact Load on the Main Welding Outer Cylinder of Large Aircraft Landing Gear." Key Engineering Materials 567 (July 2013): 169–73. http://dx.doi.org/10.4028/www.scientific.net/kem.567.169.

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Analysis about the cause of the main failure and the forces of the main welding outer cylinder of the recent large aircraft landing gear were given. The impact load for main welding outer cylinder in the process of the taking off and landing was calculated of 580MPa. Finite element model of the main welding outer cylinder was then established and the influence of the impact loading to the main welding outer cylinder was analyzed. The results showed that crack was most likely take place on the top of the outer cylinder, and then on the two welds. The crack expanded in an S shape. This study could provide an important basis for the safety of the aircraft landing gear inspection and service life prediction.

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Chen, Pu Woei, Shu Han Chang, and Tsung Hsign Yu. "Analysis of the Dynamic and Static Load of Light Sport Aircraft Composites Landing Gear." Advanced Materials Research 476-478 (February 2012): 406–12. http://dx.doi.org/10.4028/www.scientific.net/amr.476-478.406.

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Composites have become extensively used in aircraft, including the latest Airbus A380 and Boeing 787 models. Due to their high specific strength ratio, the composites can help to reduce fuel consumption. For this reason, small business jets and light aircraft have begun to use composites in their fuselage designs. The main purpose of this study is to analyze the reaction of the composite landing gear of a light sport aircraft (LSA), under loading. Finite element analysis software was used to analyze and compare the static and dynamic loads on the LSA landing gear. Takeoff weight and sink speed, defined by FAR and ASTM, were used as parameters. This work investigated three different types of landing gear materials: aluminum alloy, glass fiber reinforced composite and carbon fiber reinforced composite. The maximum stress, maximum strain and displacement of landing gear of different shapes (leaf, column and tube shapes) was also measured. Of all the samples tested, tube-shaped glass fiber reinforced composite landing gear exhibited the lowest maximum stress under a static load; it also exhibited the smallest maximum strain and y-axis displacement. The results for dynamic load show taht column-shaped landing gear exhibits the smallest maxiumum stress. The results also show that landing gear made with glass fiber reinforced composite exhibits the lowest maximum strain under a dynamic load, while landing gear made with carbon fiber reinforced composite exhibits the largest displacement of the three materials.

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Suresh, PS, Niranjan K. Sura, and K. Shankar. "Investigation of nonlinear landing gear behavior and dynamic responses on high performance aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 15 (July 1, 2019): 5674–88. http://dx.doi.org/10.1177/0954410019854628.

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The dynamic responses simulation of aircraft as rigid body considering heave, pitch, and roll motions, coupled onto a tricycle landing gear arrangement is presented. Equation of motion for each landing gear consists of un-sprung mass vertical and longitudinal motions considering strut nonlinear stiffness and damping combined with strut bending flexibility. Initially, the nonlinear dynamic response model is subjected to an input of riding over staggered bump and the responses are compared with linear landing gear model. It is observed that aircraft dynamics and important landing gear events such as vertical, spin-up and spring-back are truly represented with nonlinear stiffness and damping model considering strut bending flexibility. Later, landing response analysis is performed, with the input from nonlinear flight mechanics model for several vertical descent rate cases. The aircraft and landing gear dynamic responses such as displacement, velocity, acceleration, and reaction forces are obtained. The vertical and longitudinal drag forces from the nonlinear dynamic response model is compared with “Book-case method” outlined in landing gear design technical specifications. From the reaction force ratio calculation, it is shown that for lower vertical descent rate case the predicted loads are lesser using nonlinear dynamic response model. The same model for higher vertical descent rate cases predicts higher ratios on vertical reaction for main landing gear and longitudinal reaction for nose landing gear, respectively. The scope for increase in fatigue life for low vertical descent rate landing covering major design spectrum and the concern for static strength and structural integrity consideration for higher vertical descent rate cases are discussed in the context of event monitoring on aircraft in services.

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Pecora, Rosario. "A Rational Numerical Method for Simulation of Drop-Impact Dynamics of Oleo-Pneumatic Landing Gear." Applied Sciences 11, no. 9 (April 30, 2021): 4136. http://dx.doi.org/10.3390/app11094136.

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Oleo-pneumatic landing gear is a complex mechanical system conceived to efficiently absorb and dissipate an aircraft’s kinetic energy at touchdown, thus reducing the impact load and acceleration transmitted to the airframe. Due to its significant influence on ground loads, this system is generally designed in parallel with the main structural components of the aircraft, such as the fuselage and wings. Robust numerical models for simulating landing gear impact dynamics are essential from the preliminary design stage in order to properly assess aircraft configuration and structural arrangements. Finite element (FE) analysis is a viable solution for supporting the design. However, regarding the oleo-pneumatic struts, FE-based simulation may become unpractical, since detailed models are required to obtain reliable results. Moreover, FE models could not be very versatile for accommodating the many design updates that usually occur at the beginning of the landing gear project or during the layout optimization process. In this work, a numerical method for simulating oleo-pneumatic landing gear drop dynamics is presented. To effectively support both the preliminary and advanced design of landing gear units, the proposed simulation approach rationally balances the level of sophistication of the adopted model with the need for accurate results. Although based on a formulation assuming only four state variables for the description of landing gear dynamics, the approach successfully accounts for all the relevant forces that arise during the drop and their influence on landing gear motion. A set of intercommunicating routines was implemented in MATLAB® environment to integrate the dynamic impact equations, starting from user-defined initial conditions and general parameters related to the geometric and structural configuration of the landing gear. The tool was then used to simulate a drop test of a reference landing gear, and the obtained results were successfully validated against available experimental data.

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Yin, Qiaozhi, Jason Zheng Jiang, Simon A. Neild, and Hong Nie. "Investigation of gear walk suppression while maintaining braking performance in a main landing gear." Aerospace Science and Technology 91 (August 2019): 122–35. http://dx.doi.org/10.1016/j.ast.2019.05.026.

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Caputo, F., A. De Luca, A. Greco, A. Marro, A. Apicella, R. Sepe, and E. Armentani. "Established Numerical Techniques for the Structural Analysis of a Regional Aircraft Landing Gear." Advances in Materials Science and Engineering 2018 (October 17, 2018): 1–21. http://dx.doi.org/10.1155/2018/8536581.

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Usually during the design of landing gear, simplified Finite Element (FE) models, based on one-dimensional finite elements (stick model), are used to investigate the in-service reaction forces involving each subcomponent. After that, the design of such subcomponent is carried out through detailed Global/Local FE analyses where, once at time, each component, modelled with three-dimensional finite elements, is assembled into a one-dimensional finite elements based FE model, representing the whole landing gear under the investigated loading conditions. Moreover, the landing gears are usually investigated also under a kinematic point of view, through the multibody (MB) methods, which allow achieving the reaction forces involving each subcomponent in a very short time. However, simplified stick (FE) and MB models introduce several approximations, providing results far from the real behaviour of the landing gear. Therefore, the first goal of this paper consists of assessing the effectiveness of such approaches against a 3D full-FE model. Three numerical models of the main landing gear of a regional airliner have been developed, according to MB, “stick,” and 3D full-FE methods, respectively. The former has been developed by means of ADAMS® software, the other two by means of NASTRAN® software. Once this assessment phase has been carried out, also the Global/Local technique has verified with regard to the results achieved by the 3D full-FE model. Finally, the dynamic behaviour of the landing gear has been investigated both numerically and experimentally. In particular, Magnaghi Aeronautica S.p.A. Company performed the experimental test, consisting of a drop test according to EASA CS 25 regulations. Concerning the 3D full-FE investigation, the analysis has been simulated by means of Ls-Dyna® software. A good level of accuracy has been achieved by all the developed numerical methods.

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Rośkowicz, Marek, and Piotr Leszczyński. "The Selected Problems of Studies of Aircraft Landing Gear." Research Works of Air Force Institute of Technology 39, no. 1 (December 1, 2016): 91–102. http://dx.doi.org/10.1515/afit-2016-0020.

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Abstract The article portrays the results of experimental studies conducted in the field of static strength test of main landing gear of lightweight aircraft as well as in the area of establishing the pneumatic tyre characteristics of main landing gear. The studies were carried out in compliance with methodologies of performing studies for the purposes of solutions implemented in aviation structures. It was stated that static strength tests of landing gear should not be done with the use of shock absorbers, due to the fact that this element, distinguished by high viscoelastic properties, by being statically loaded, is subject to displacements that do not occur during normal operation of the aircraft. Excessive displacements of shock absorber result in the load distribution in other landing gear elements being incompatible with project assumptions, which in turn leads to this strength test being interrupted, bearing in mind significantly lower loads than anticipated. It was also concluded that in order to determine pneumatic tyre characteristics it is not necessary to carry out tests on the whole landing gear strut, because the results obtained in the compression test of the wheel itself with pneumatic tyre are identical as the results acquired during tests conducted in accordance with methodology. Test preparation process with the use of the wheel itself and its realization is less time-consuming, less expensive and does not entail the necessity to build complex test stands.

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Yin, Yin, Simon A. Neild, Jason Zheng Jiang, James A. C. Knowles, and Hong Nie. "Optimization of a Main Landing Gear Locking Mechanism Using Bifurcation Analysis." Journal of Aircraft 54, no. 6 (November 2017): 2126–39. http://dx.doi.org/10.2514/1.c034228.

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Knowles, James A. C., Bernd Krauskopf, Mark H. Lowenberg, Simon A. Neild, and P. Thota. "Numerical Continuation Analysis of a Dual-Sidestay Main Landing Gear Mechanism." Journal of Aircraft 51, no. 1 (January 2014): 129–43. http://dx.doi.org/10.2514/1.c032130.

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Li, Yuan, Jason Zheng Jiang, and Simon Neild. "Optimisation of shimmy suppression device in an aircraft main landing gear." Journal of Physics: Conference Series 744 (September 2016): 012066. http://dx.doi.org/10.1088/1742-6596/744/1/012066.

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Hyun, Young-O., Jae-Up Hwang, Jae-Hyuk Hwang, Jae-Sung Bae, Kyoung-Ho Lim, Doo-Man Kim, Tae-Wook Kim, and Myung-Ho Park. "Force Control of Main Landing Gear using Hybrid Magneto-Rheological Damper." Journal of the Korean Society for Aeronautical Space Science 38, no. 4 (April 1, 2010): 315–20. http://dx.doi.org/10.5139/jksas.2010.38.4.315.

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36

Bagnoli, F., and M. Bernabei. "Fatigue analysis of a P180 aircraft main landing gear wheel flange." Engineering Failure Analysis 15, no. 6 (September 2008): 654–65. http://dx.doi.org/10.1016/j.engfailanal.2007.10.003.

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Barter, S. A. "Investigation of a Boeing 747 wing main landing gear trunnion failure." Engineering Failure Analysis 35 (December 2013): 387–96. http://dx.doi.org/10.1016/j.engfailanal.2013.03.026.

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C V, Chandrashekara, Arjun Srivathsa, S. S. Adarsha, M. V. Bharath Narayana, and K. S. Sridhar. "The Dynamic Characteristics of a non-linear main landing gear system of an aircraft during landing." Vibroengineering PROCEDIA 30 (April 2, 2020): 97–102. http://dx.doi.org/10.21595/vp.2020.21393.

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Ma, Wu Yuan, Hui Sun, Bo Liu, and Hong Guang Jia. "Analysis of UAV Main Landing Gear Loads during Wheel Spin-Up Process." Advanced Materials Research 753-755 (August 2013): 1595–98. http://dx.doi.org/10.4028/www.scientific.net/amr.753-755.1595.

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To understand the wheel spin-up process of UAV main landing gear, this paper constructs the simplified mechanical model. The bilinearity model is used to simulate the relation between tire-runway adhesion coefficient and slip ratio. Some factor influenced the resultant load is analyzed. The axle and flange are analyzed with ABAQUS.

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Son, Lovely, Mulyadi Bur, and Meifal Rusli. "A new concept for UAV landing gear shock vibration control using pre-straining spring momentum exchange impact damper." Journal of Vibration and Control 24, no. 8 (July 26, 2016): 1455–68. http://dx.doi.org/10.1177/1077546316661470.

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This study proposes a new method for reducing the shock vibration response of an Unmanned Aerial Vehicle (UAV) during the landing process by means of the momentum exchange principle (MEID). The performance of the impact damper is improved by adding a pre-straining spring to the damper system. This research discusses the theoretical application of the damper to the UAV landing gear system. The UAV dynamics is first modeled as a simple lumped mass translational vibration system. Then we analyze a more complex two-dimensional model of UAV dynamics. This model consists of the main wheel, nose wheel and main body. Three cases of UAV landing gear mechanisms: without damper, with passive MEID (PMEID) and with pre-straining spring MEID (PSMEID) are simulated. The damper performance is evaluated from the maximum acceleration and force transmission to the main body. The energy balance calculation is conducted to investigate the performance of PSMEID. The simulation results show that the proposed PSMEID method is the most effective method for reducing the maximum acceleration and force transmission of UAV during impact landing.

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Cerreta, Pietro, Paola Iaccarino, Massimo Viscardi, and Maurizio Arena. "Design challenge of a new monolithic concept for the main landing gear bay of a large passenger aircraft." MATEC Web of Conferences 233 (2018): 00011. http://dx.doi.org/10.1051/matecconf/201823300011.

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In this paper, ITEMB team in the contest of the Clean Sky 2 framework, with the scope of a new architecture for the Main Landing Gear of a single isle aircraft type, presents its development in designing the two major item of the Main Landing Gear Bay that are the “roof” and the “rear pressure bulkhead” using pre-preg CFRP material. Typically, a lot of parts (metallic and also composite made) are involved in the two items manufacturing: the research effort has targeted the design of one piece structures consisting in a monolithic “roof” and “monolithic “rear pressure bulkhead”. The assembly of these ones takes advantages from a hole-tohole assembly supported by statistical analysis. The main expected advantages are the reduction of: both non-recurring and recurring cost, the overall flow time and weight saving. The ITEMB (InTEgrated Main landing gear Box) team has worked adapting a bag-to-bag technology to the geometrical and strength capability requirements of the component and outcome of the research (not yet concluded at time of issuing this paper) includes: A design principle supported by stress analysis for strength, stability and local main load introduction; A manufacturing trials campaign to reach the possess of a robust process; A limited coupons test campaign to demonstrate that no specific critical items exists in the design approach. Finally, participants have acquired a new design and manufacturing technique, applicable also to other Aircraft components upgrading their capabilities and European strength in composite structures manufacturing.

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Hidayat, Dony. "Effect Of Rubber Damper Stiffness And Tire Pressure To Reduce Ground Reaction Load Factor On Main Landing Gear Using Multi-Body Simulation (MBS) Rigid Model." Jurnal Teknologi Dirgantara 17, no. 2 (December 20, 2019): 123. http://dx.doi.org/10.30536/j.jtd.2019.v17.a3131.

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Landing Gear Drop Test (LGDT) utilizes the apparatus requiring a substantial time and cost. Virtual LGDT (vLGDT) using MSC ADAMS software is one of the solutions for initial stage to testing landing gear. From simulation with vsink 1.7 m/s and load 22000 N obtained contact/impact force that ensue in MSC ADAMS was 73650 N, while from experimental was 73612 N. The difference between vLGDT and LGDT result is 0.05 %. To obtain ground reaction load factor below 3 in vsink = 3.05 m/s, the rubber damper should have stiffness in the range of 1900 - 2100 N/mm and for the tire pressure of 60 - 65 psi.

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Howcroft, C., M. Lowenberg, S. Neild, and B. Krauskopf. "Effects of Freeplay on Dynamic Stability of an Aircraft Main Landing Gear." Journal of Aircraft 50, no. 6 (November 2013): 1908–22. http://dx.doi.org/10.2514/1.c032316.

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Knowles, J. A. C., B. Krauskopf, and M. Lowenberg. "Numerical continuation analysis of a three-dimensional aircraft main landing gear mechanism." Nonlinear Dynamics 71, no. 1-2 (November 13, 2012): 331–52. http://dx.doi.org/10.1007/s11071-012-0664-z.

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Huang, Mingyang, Hong Nie, and Ming Zhang. "Analysis of ground handling characteristic of aircraft with electric taxi system." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 233, no. 6 (April 11, 2018): 1546–61. http://dx.doi.org/10.1177/0954407018764163.

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Electric landing gear drive equipped with traction motors can provide taxi capability without the use of main engines or tractor. The ground handling characteristic of aircraft with electric taxi system is analyzed. The new mathematic model of aircraft ground maneuver is established, considering the 6-degree-freedom aircraft body and the flexible main strut and the powered wheel. Quasi-steady method is applied to calculate tire side forces and moments, to determine side slip. The simulation for the ground steering response of aircraft with electric taxi system is done by employing ADAMS and Simulink co-simulation platform. The dynamic responses of aircraft ground steering and landing gear spin-up and spring back are simulated. Different taxi conditions including powered nose wheel mode and powered main wheel mode are compared. Four conclusions are obtained: electric taxi system helps the aircraft turn on the spot and the turning radius is smaller than the aircraft using engines; differential powered main wheel mode has the minimum turning radius while turning-circle with uniform velocity, and it has smaller difference between two vertical loads of main landing gear than powered nose wheel mode; in the case of the same steering angle, the extreme velocity of differential powered main wheel mode before side slip is larger than powered nose wheel mode; and pre-rotation of powered main wheel decreases the spin-up drag load and spring back drag load.

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Li, Long Shuang, Hong Nie, and Xin Xu. "Simulation and Experiment on Landing Gear Component Noise." Applied Mechanics and Materials 170-173 (May 2012): 3454–59. http://dx.doi.org/10.4028/www.scientific.net/amm.170-173.3454.

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Simulation analysis and experiment research are performed on the aeroacoustic noise of a landing gear component in this paper. Detached Eddy Simulation (DES) is used to produce the flow field of the model. The Ffowcs-Williams/Hawkings (FW-H) equation is used to calculate the acoustic field. The sound field radiated from the model is measured in the acoustic wind tunnel. A comparison shows that the simulation results agree well with the experiment results under the acoustic far field condition. The results show that the noise radiated from the model is broadband noise. The directivity of the noise source is like a type of dipole. The location between shock absorber and strut, shock absorber and bogie can induce the interaction noise which is presented by two energy peaks in the spectra. The shock absorber and the bogie is the main contributor while the strut is the least contributor to the total noise.

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Chiariello, Antonio, Salvatore Orlando, Pasquale Vitale, Mauro Linari, Raffaele Longobardi, and Luigi Di Palma. "Development of a Morphing Landing Gear Composite Door for High Speed Compound Rotorcraft." Aerospace 7, no. 7 (June 30, 2020): 88. http://dx.doi.org/10.3390/aerospace7070088.

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In the framework of fast rotorcraft, smoothness and flushness of external aerodynamic surfaces present challenges for high-speed conditions, where aerodynamics is the driver of helicopter performance. For AIRBUS-RACER helicopter the main landing gear trap doors are parts of the lower wing skins (in retracted configuration) affecting helicopter performance by minimizing the drag. Flushness requirements must not be in contrast with the functionally of the Landing gear system that must open and close the doors during the landing gear retraction-extension phases at moderately low velocity. To manage these goals, a novel design logic has been identified to support the trap doors development phase. The identified way to proceed needs of relevant numerical method and tool as well. This method is aimed at identifying the main landing gear composite compartment doors in pre-shaped configuration to match the smoothness and door-stopper engagements over each aerodynamic conditions. The authors propose a detailed non-linear Finite Element method, based on MSC Nastran (MSC Software, Newport Beach, US) SOL-400 solver in which the structure is modelled with deformable contact bodies in a multiple load step sequence, open door condition and pre-shaped, deformed under actuator pre-load, under flight load conditions. The method includes the entire pre-stressed field due to the preload and the actual door stiffness, considering the achieved large displacement to verify the most representative strain field during loads application. The paper defines a robust methodology to predict the deformation and ensure the most appropriate door “pre-bow” and pre-load, in order to achieve the desiderated structural shape that matches aerodynamic requirements. The main result is the identification of a pre-shaped doors configuration for the Airbus RACER Fast Rotorcraft.

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Luong, Quoc Viet, Dae-Sung Jang, and Jai-Hyuk Hwang. "Intelligent Control Based on a Neural Network for Aircraft Landing Gear with a Magnetorheological Damper in Different Landing Scenarios." Applied Sciences 10, no. 17 (August 28, 2020): 5962. http://dx.doi.org/10.3390/app10175962.

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A typical oleo-pneumatic shock-absorbing strut (classic traditional passive damper) in aircraft landing gear has a metering pin extending through the orifice, which can vary the orifice area with the compression and extension of the damper strut. Because the metering pin is designed in a single landing condition, the traditional passive damper cannot adjust its damping force in multiple landing conditions. Magnetorheological (MR) dampers have been receiving significant attention as an alternative to traditional passive dampers. An MR damper, which is a typical semi-active suspension system, can control the damping force created by MR fluid under the magnetic field. Thus, it can be controlled by electric current. This paper adopts a neural network controller trained by two different methods, which are genetic algorithm and policy gradient estimation, for aircraft landing gear with an MR damper that considers different landing scenarios. The controller learns from a large number of trials, and accordingly, the main advantage is that it runs autonomously without requiring system knowledge. Moreover, comparative numerical simulations are executed with a passive damper and adaptive hybrid controller under various aircraft masses and sink speeds for verifying the effectiveness of the proposed controller. The main simulation results show that the proposed controller exhibits comparable performance to the adaptive hybrid controller without any needs for the online estimation of landing conditions.

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Iadicicco, Agostino, Daniele Natale, Pasquale Di Palma, Francesco Spinaci, Antonio Apicella, and Stefania Campopiano. "Strain Monitoring of a Composite Drag Strut in Aircraft Landing Gear by Fiber Bragg Grating Sensors." Sensors 19, no. 10 (May 15, 2019): 2239. http://dx.doi.org/10.3390/s19102239.

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This work reports on the use of Fiber Bragg Grating (FBG) sensors integrated with innovative composite items of aircraft landing gear for strain/stress monitoring. Recently, the introduction of innovative structures in aeronautical applications is appealing with two main goals: (i) to decrease the weight and cost of current items; and (ii) to increase the mechanical resistance, if possible. However, the introduction of novel structures in the aeronautical field demands experimentation and certification regarding their mechanical resistance. In this work, we successfully investigate the possibility to use Fiber Bragg Grating sensors for the structural health monitoring of innovative composite items for the landing gear. Several FBG strain sensors have been integrated in different locations of the composite item including region with high bending radius. To optimize the localization of the FBG sensors, load condition was studied by Finite Element Method (FEM) numerical analysis. Several experimental tests have been done in range 0–70 kN by means of a hydraulic press. Obtained results are in very good agreement with the numerical ones and demonstrate the great potentialities of FBG sensor technology to be employed for remote and real-time load measurements on aircraft landing gears and to act as early warning systems.

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Leodolter, Walter. "Pilot Production of Superplastically Formed/Diffusion Bonded T-38 Main Landing Gear Doors." Journal of Aircraft 22, no. 7 (July 1985): 568–72. http://dx.doi.org/10.2514/3.56762.

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Journal articles on the topic 'Main landing gear'

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