Relevant bibliographies by topics / Landing Gear Strut Dynamics

Contents

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

Academic literature on the topic 'Landing Gear Strut Dynamics'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Landing Gear Strut Dynamics"

1

Jia, Zhong Hu, Wei Han, Xiao Hong Zheng, and Yang Tao. "Analysis of the Arresting Dynamic Loads of Aircraft’s Landing Gear." Applied Mechanics and Materials 105-107 (September 2011): 470–73. http://dx.doi.org/10.4028/www.scientific.net/amm.105-107.470.

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The arresting landing of carrier aircraft is especial dynamic problem. During this process,the gear would bear the very big dynamic load,which does the biggest harm to gear .In this paper,it analyzed the landing gear shock strut in carrier aircraft arresting landing,and aiming at the runout of shock strut and the flexibility of the landing gear by using the Lagrange equation.Then it concluded the chaging of landing gear shock strut with symmetrical and straight arresting,3m of off-center distance arresting and 2°of rolling angle arresting after simulating.The conclusion showed that the landing gear shock strut would be stable after a short time concussion;rolling and unsymmetrical affected the shock strutmore severe than off-center and symmetrical arresting,and the qualities of concussion also being more acute.
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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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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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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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Giridharan, V., and S. Sivakumar. "Shimmy analysis of light weight aircraft nose wheel landing gear." Vibroengineering PROCEDIA 47 (December 12, 2022): 8–15. http://dx.doi.org/10.21595/vp.2022.22988.

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This paper presents mathematical modeling and analysis of shimmy oscillations for a light weight airplane single wheel nose landing gear. Shimmy is a self-excited oscillation which occurs usually on the nose wheel landing gear assembly during ground maneuvers which is governed by the dynamic characteristics of the landing gear and tires. Shimmy oscillation may lead to reduce the fatigue life of the landing gear and fuselage structure. So, the study of dynamic response and stability boundaries of landing gear plays crucial role while designing of airplanes. In earlier studies of vehicle shimmy only 3 degrees of freedom (DOF) considered such as torsional mode, lateral bending mode and tire lateral deformation. In this work along with above mentioned DOF, two more additional DOF introduced such as axial vibration of strut and tire in order to include the effect of vertical dynamics on shimmy model. Gyroscopic coupling effect also included in the model to study its influence on shimmy. Analysis carried out to determine critical velocity region for occurrence of shimmy and to investigate the effectiveness of ground unevenness on the landing gear system for two different runway conditions such as flat runway and random roughness runway. The results are more helpful to study significant interaction between the different parameters of landing gear and to represent stability boundaries.
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Chen, Hu, Xingbo Fang, and Hong Nie. "Analysis of Carrier-Based Aircraft Catapult Launching Based on Variable Topology Dynamics." Applied Sciences 11, no. 19 (September 28, 2021): 9037. http://dx.doi.org/10.3390/app11199037.

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The catapult process of a carrier-based aircraft includes multiple links such as catapult tensioning, separation of the holding rod, dragging and running, separation of the catapult and drag shuttle, and free running. The connection relationships between the front landing gear of the carrier-based aircraft and other related components in each link are different, therefore, it is necessary to adjust the topological relationships of the dynamic model in real time, when solving the catapult dynamics of a carrier-based aircraft. In this paper, a dynamic model of the multibody system of the catapult take-off is established, and a variable topology solution is carried out for the dynamic model by adjusting dynamic augmentation equations; in addition, a dynamic analysis of a carrier-based aircraft catapult and take-off process is carried out. A catapult dynamics model and variable topology solution method were established, which solved the changes at the moment of the restraining rod separation, catapult rod separation, and catapult tackle during the aircraft catapult take-off. After the restraining rod was separated from the front landing gear, the catapult force was transmitted to the rear strut, which instantly increased the load of the rear strut by 238.5 kN. In addition, after the carrier-based aircraft reached the end of the catapult’s stroke, the catapult rod was separated from the catapult tow shuttle then unloaded, and the load of the rear strut was reduced from 486.2 kN to −20.3 kN. Under the protruding effect of the nose gear, the pitch angle of the carrier-based aircraft increased rapidly from −0.93° and reached 0.54° when the carrier-based aircraft rushed out of the deck.
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Zhu, Xin Yu, and Jun Wen Lu. "Stress and Buckling Analysis of a Certain Type of All-Composite Landing Gear." Advanced Materials Research 663 (February 2013): 692–97. http://dx.doi.org/10.4028/www.scientific.net/amr.663.692.

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FEA method was conducted to investigate static stress and buckling analysis of a certain all-composite landing gear strut. The critical buckling load and bucking mode shapes of the landing gear is obtained using ANSYS finite element analysis code. The first six buckling mode shapes and static stress distribution are given. According to the analysis results, the dynamic characteristics of the landing gear are discussed. The analysis method and results in this paper can be used for further study on making maintenance plan and safety verification for the landing gear.
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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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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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Zhang, Songyang, Qiaozhi Yin, Xiaohui Wei, Jiayi Song, and Hong Nie. "Study of Brake Disc Friction Characteristics Effect on Low Frequency Brake Induced Vibration of Aircraft Landing Gear." Aerospace 9, no. 12 (December 9, 2022): 809. http://dx.doi.org/10.3390/aerospace9120809.

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During aircraft braking, the change of ground adhesion forces can cause forward and backward vibration of the landing gear, and the performance of the brake disc may exacerbate this vibration. In order to solve this problem, a rigid–flexible coupling dynamic model of a two-wheel strut landing gear considering the friction characters of brake discs with different materials and a hydraulic brake system model is established in this paper. The brake disc friction characteristics effect on the low-frequency brake-induced vibration of the landing gear given different brake disc materials and ambient temperatures is studied. It is shown that the C/SiC brake disc has a “negative slope” phenomenon between the friction coefficient of the brake disc and the wheel speed, and this variable friction characteristic has a great effect on the low-frequency braking-induced vibration of the landing gear. In addition, the variable friction characteristics of the C/SiC brake disc are easily affected by ambient temperature, while the friction coefficient of the C/C brake disc changes stably.
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Dissertations / Theses on the topic "Landing Gear Strut Dynamics"

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Kewley, Sarah Elizabeth. "Parametric study into the shimmy dynamics of a nose landing gear-fuselage model." Thesis, University of Bristol, 2015. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.702149.

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This thesis investigates the influence of different parameters on the shimmy dynamics of a nose landing gear. This is achieved by considering a sequence of increasingly complex models. Due to the nature of landing gear dynamics, numerical continuation is used to analyse the system's shimmy characteristics. A nose landing gear model consisting of a strut, caster and single wheel is presented. It has torsional and lateral bending vibrational modes and is completed with an elastic tyre. The critical forward velocity of the aircraft shimmy onset can be determined as the equilibrium solution loses stability via a Hopf bifurcation. The bifurcating steady-state periodic solution gives the maximum amplitude of the self-sustained shimmy oscillation, which are dominated by one of the vibrational modes of the gear. The Hopf bifurcation points can be continued in two parameters where they form stability boundaries for the gear's equilibrium solution over gear vertical loading and ground speed. The nose landing gear model is then coupled to a two degree of freedom model, consisting of two mass spring damper systems acting at the nose landing gear-fuselage attachment point in the lateral and vertical directions. These represent any local displacement resulting from flexible deformation of the fuselage. Shimmy onset is found to be sensitive to the lateral, but not the vertical, motion of the fuselage. However, the amplitude and frequency of shimmy oscillations are influenced by the vertical mode. The latter part of the thesis presents an extended nose landing gear-fuselage model. Here the fuselage model includes a rigid body lateral fuselage mode that represents lateral motion of the fuselage at the nose landing gear-fuselage attachment point due to fuselage yaw; it also comprises roll and pitch rotations which present themselves as rotations in the nose landing gear. The gear model also includes axial compression of the strut, has a dual wheel configuration and includes their gyroscopic effects. The shimmy dynamics of the gear are found to be virtually unaffected by the presence of the rigid body fuselage model, whilst the two wheels and their gyroscopic effects are found to strongly influence the shimmy onset point. The gear's design and tyre parameters are investigated next. The increase in separation distance merges the two shimmy oscillations into one displaying large amplitudes in both modes. It is also found that a decreased rake angle and increased caster length stabilises the gear considerably. The gear's tyre relaxation length and contact patch length are found to stabilise the gear when increased and decreased, respectively. This effect, along with that of the flexible fuselage, however, is dwarfed by the influence of the rake angle and caster length. Moreover, the gear was found to be very sensitive to the change in magnitude of the self-aligning moment. Thus, it is concluded that the fuselage dynamics play little part in the onset of shimmy, and that when considering shimmy onset particular attention should be paid to the rake angle, caster length and self-aligning moment which appear to be highly influential in triggering shimmy.
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Zanini, Marcelo Augusto Xavier. "Comparison of different identification techniques of vertical structural dynamics of twin-wheeled telescopic landing gear." Instituto Tecnológico de Aeronáutica, 2009. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=898.

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The main purpose of this work is to model dynamically the latero-torsional response of the structure of a landing gear using identification techniques. The emphasis is placed on identifying this motion on aircraft twin-wheeled telescopic main landing gears. Between the many possible model structures, a linear polynomial ARX and ARMAX model structures and a state space model structure were adopted, all of them discrete models. Structures of the Output-Error (OE) e Box-Jenkins (BJ) type were also analysed but were discarted. The coefficients of the ARX model are obtained through least square techniques and the ones for the ARMAX by using the extended least square estimator. The ones for the state space model are obtained through subspace projection techniques for obtaining the states e also by least square for obtaining the dynamic matrices. The system dynamical equations are developed for a better understanding of the physical problem. The landing gear lateral and torsional structural deflections, wheels rotations and tire angular slip are considered as degrees of freedom of the model. The problem physics and correlation analysis was used for obtaining the polynomial model and state space model order and input delay respectively. For the ARX and ARMAX models, it is proposed an order reduction and obtention of a second order model. Using the transfer function obtained from this model it is possible to find the frequency and damping of the landing gear modes. For the state space model, through the obtention of the dynamical matrix and its eigenvalues it is possible to find the frequency and damping of the landing gear modes. The results obtained through these techniques are compared.
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Tran, Tuan H. "Landing-Gear Impact Response: A Non-linear Finite Element Approach." UNF Digital Commons, 2019. https://digitalcommons.unf.edu/etd/896.

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The primary objective of this research is to formulate a methodology of assessing the maximum impact loading condition that will incur onto an aircraft’s landing gear system via Finite Element Analysis (FEA) and appropriately determining its corresponding structural and impact responses to minimize potential design failures during hard landing (abnormal impact) and shock absorption testing. Both static and dynamic loading condition were closely analyzed, compared, and derived through the Federal Aviation Administration’s (FAA) airworthiness regulations and empirical testing data. In this research, a nonlinear transient dynamic analysis is developed and established via NASTRAN advanced nonlinear finite element model (FEM) to simulate the worst-case loading condition. Under the appropriate loading analysis, the eye-bar and contact patch region theory were then utilized to simulate the tire and nose wheel interface more accurately. The open geometry of the nose landing gear was also optimized to minimize the effect of stress concentration. The result of this research is conformed to the FAA’s regulations and bound to have an impact on the design and development of small and large aircraft’s landing gear for both near and distant future.
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Pauliny, Jozef. "Návrh podvozku čtyřmístného jednomotorového letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2014. http://www.nusl.cz/ntk/nusl-231654.

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Cílem této práce je návrh pevného tříkolového podvozku pro jednomotorový čtyřmístný celokompozitní letoun s dodržováním certifikačních specifikací CS-23. To zahrnuje návrh kompozitních pružinových hlavních podvozkových vzpěr v kombinaci s hydropneumatickým tlumičem příďového podvozku. Proces návrhu se dělí do pěti specifických fází; požadavky na konstrukci, předběžný návrh, detailní návrh, příprava výroby a zkoušení prototypu. Zatížení podvozku pro jednotlivé případy a konfigurace letounu je definován v předběžné fázi návrhu. Detailní návrh zahrnuje pevnostní analýzu jednotlivých komponentů. Fáze zkoušení prototypu definuje způsob ověření únosnosti zkouškou. Závěr obsahuje podrobnou technickou dokumentaci.
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Kumar, V. V. Nagendra. "An Anti-Skid Brake Controller For A Fighter Aircraft With An Elastic Strut." Thesis, 2007. https://etd.iisc.ac.in/handle/2005/473.

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This thesis deals with the design of an anti-skid brake controller for a generic fighter aircraft. Antiskid brake controllers prevent wheel locking and maximize the coefficient of friction between the tyre and the ground, resulting in lower stopping distance and time. The frictional force is maximized by regulating the slip. A model for the landing gear is first developed, which consists of the translational and rotational motions of the wheel, the equation for the slip and the elastic landing gear strut dynamics. The elastic behaviour of the landing gear is characterized through its modal frequencies, obtained from a Finite element analysis. As the governing equations are nonlinear, with linear elastic deformations of the strut, feedback linearization is used to design the anti-skid controller. The brake controller is found to work well. Its stability is verified through numerical simulations. Both the plant parameters and the sensor measurements are perturbed up to 10% from their nominal values. It is seen that the feedback linearization tolerates these variations quite well. The system is exceptionally tolerant to sensor noises. The torsional stiffness of the strut is found to be more critical than the longitudinal stiffness. Limits on the torsional stiffness that can be tolerated by the controller are found. This determines the limits on the stiffness of the landing gear beyond which gear walk may appear. The thesis concludes with suggestions for future work in this exciting field.
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Kumar, V. V. Nagendra. "An Anti-Skid Brake Controller For A Fighter Aircraft With An Elastic Strut." Thesis, 2007. http://hdl.handle.net/2005/473.

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This thesis deals with the design of an anti-skid brake controller for a generic fighter aircraft. Antiskid brake controllers prevent wheel locking and maximize the coefficient of friction between the tyre and the ground, resulting in lower stopping distance and time. The frictional force is maximized by regulating the slip. A model for the landing gear is first developed, which consists of the translational and rotational motions of the wheel, the equation for the slip and the elastic landing gear strut dynamics. The elastic behaviour of the landing gear is characterized through its modal frequencies, obtained from a Finite element analysis. As the governing equations are nonlinear, with linear elastic deformations of the strut, feedback linearization is used to design the anti-skid controller. The brake controller is found to work well. Its stability is verified through numerical simulations. Both the plant parameters and the sensor measurements are perturbed up to 10% from their nominal values. It is seen that the feedback linearization tolerates these variations quite well. The system is exceptionally tolerant to sensor noises. The torsional stiffness of the strut is found to be more critical than the longitudinal stiffness. Limits on the torsional stiffness that can be tolerated by the controller are found. This determines the limits on the stiffness of the landing gear beyond which gear walk may appear. The thesis concludes with suggestions for future work in this exciting field.
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Kuo, Shiung-shan, and 郭雄山. "Computer Aided Design and Simulation of the Aircraft Landing Gear Shock Strut." Thesis, 2007. http://ndltd.ncl.edu.tw/handle/87581692030461938286.

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碩士
逢甲大學
航太與系統工程所
95
After this text is supposed by a plane of weight, Consult the plane undercarriage design specification , by static load , calculates the quiet pressing and biggest compressing amount of air, after and then changing into the general elastic intensity by the pressure unit. One appears fictitiously to possess, the sport organization of true undercarriage shock attenuation pillar efficiency. Group''s function of the simulation mould that this project moves with COSMOS Motion, Carry out the undercarriage shock attenuation system to the plane structure interface, assault and test hard landing shock attenuation . This Shock Strut assaults the test and includes vertically again hard landing, the posture of angle of hard landing, the side wind deflection dangerously landing. In COSMOS Motion in the structure stress moves the simulated test is analysed, Find the sporadic alone hard landing, von Mises stress produced on the structure belongs to the safe range . When the posture of angle of attack Hard landing, finding the structure assaulted, the stress produced - cycle curve is comparatively unusual, and cycle curve more other tests of the stress are one more more time.
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Khapane, Prashant. "Simulation of landing gear dynamics and brake-gear interaction /." 2008. http://www.gbv.de/dms/bs/toc/571847129.pdf.

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Khapane, Prashant [Verfasser]. "Simulation of landing gear dynamics and brake-gear interaction / von Prashant Khapane." 2008. http://d-nb.info/989875059/34.

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Books on the topic "Landing Gear Strut Dynamics"

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Clark, Archie B. An investigation of classical dynamic scaling techniques applied to an oleo-pneumatic landing gear strut. Wright-Patterson Air Force Base, Ohio: Flight Dynamics, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1987.

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Walker, Richard William Reid. Implementation of an aircraft shock strut and steering system model in real time. [Downsview, Ont.]: Dept. of Aerospace Science and Engineering, 1986.

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Center, Langley Research, ed. An overview of landing gear dynamics. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

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Davis, Pamela A. Langley Aircraft Landing Dynamics Facility. Washington, D.C: National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987.

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L, Martin James, Hardy Gordon H, and Ames Research Center, eds. Flight investigation of the use of a nose gear jump strut to reduce takeoff ground roll distance of STOL aircraft. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Davis, Pamela A. Quasi-static and dynamic response characteristics of F-4 bias-ply and radial-belted main gear tires. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Book chapters on the topic "Landing Gear Strut Dynamics"

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Kadam, Mahesh, S. Sathish, Aditya Bujurke, Keertivardhan Joshi, and Balamurugan Gopalsamy. "Dynamics of Articulated Landing Gear in Tail-Down Landing Condition." In Lecture Notes in Mechanical Engineering, 195–206. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-8597-0_17.

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Collins, Trevor, and Kevin Kochersberger. "Constrained Layer Damping Test Results for Aircraft Landing Gear." In Structural Dynamics, Volume 3, 303–14. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-9834-7_28.

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"Cracking in an Aircraft Nose Landing Gear Strut." In Handbook of Case Histories in Failure Analysis, 11–14. ASM International, 1993. http://dx.doi.org/10.31399/asm.fach.v02.c9001292.

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"Cracking in an Aircraft Main Landing Gear Sliding Strut." In Handbook of Case Histories in Failure Analysis, 7–10. ASM International, 1993. http://dx.doi.org/10.31399/asm.fach.v02.c9001291.

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Conference papers on the topic "Landing Gear Strut Dynamics"

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Li, S., L. Li, H. Wang, and D. Xie. "Research on landing gear strut damping orifice design based on nurbs for optimizing aircraft ground dynamics." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2022). Institution of Engineering and Technology, 2022. http://dx.doi.org/10.1049/icp.2022.1774.

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Farhang, Kambiz, and Karthik Balasubramanian. "Dynamics of a Reduced Scale Landing Gear System Considering the Effect of the Viscoelastic Interaction of the Brake Pads and Rotors." In World Tribology Congress III. ASMEDC, 2005. http://dx.doi.org/10.1115/wtc2005-64319.

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Gear walk is a dynamic instability condition that can pose serious harm to an aircraft and its passengers. The instability is believed to be borne as a result of braking, in which vibration of the landing gear can be induced generating motion reminiscent of a walking movement. This paper focuses on the theoretical account of a Reduced Scale Landing Gear (RSLG) apparatus and studies gear walk phenomenon. The mathematical approach involves lumped-parameter model representation of the RSLG that accounts for the landing gear’s struts, the wheels and the caliper-disc brake dynamics. The theoretical treatment of the RSLG apparatus entails consideration of the structure of the device that includes the account of dynamic response of the assembly consisting of a fuselage, two struts and two wheels. Various physical and geometrical parameters are determined and included in the mathematical model of the apparatus. It is demonstrated that the occurrence of gear walk vibration is greatly influenced by the structural stiffness of the system. Both synchronous and 180° out of phase motion of the struts are generated in a parametric study in which structural stiffness is varied.
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Zia, Benazir, and Hafiz Sana Ullah Butt. "Dynamic Response of a Composite Strut of Landing Gear of an Aircraft against Impact Velocity." In 2019 16th International Bhurban Conference on Applied Sciences and Technology (IBCAST - 2019). IEEE, 2019. http://dx.doi.org/10.1109/ibcast.2019.8667223.

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Chong, Chung-Ook, and Rollin Dix. "Impulse-Momentum in Spacecraft Landing: Analysis and Experiment." In ASME 7th Biennial Conference on Engineering Systems Design and Analysis. ASMEDC, 2004. http://dx.doi.org/10.1115/esda2004-58054.

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Impulse-momentum methods of analysis developed for rigid body impacts are applied in this paper to predict forces acting in a simplified spacecraft model during a touchdown impact. This paper presents both analytic and experimental effort for a complex, multi-body impacting system that include friction and deformable elements. Specifically, we analyze a vertically moving guided mass representing a landing spacecraft to which is attached a telescopic, energy-absorbing leg. The landing gear, which is used in our study, employs crushable material in the leg, strut, and foot plus surface friction to absorb the landing shock. The experimental setup consists of simplified landing system, and accelerometers for the dynamic measurement. Acceleration data collected via data acquisition system is converted to the crushing, normal and tangential velocities. The results showed good agreement between the analysis and experiment for the first phase of motion. The derivation of limiting condition equations for all possible alternatives for the second phase is incomplete. We conclude that the challenges of deriving and testing for all motion phase ending events make the impulse-momentum method inferior to straight-forward dynamic simulation as a design tool.
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Sposito, Alberto, and Ralf D. Pechstedt. "Optical Pressure Sensor for Landing Gear Oleo-Strut Pressure Sensor." In 2018 5th IEEE International Workshop on Metrology for AeroSpace (MetroAeroSpace). IEEE, 2018. http://dx.doi.org/10.1109/metroaerospace.2018.8453517.

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Okolo, Patrick N., Kun Zhao, John Kennedy, and Gareth J. Bennett. "Mesh Screen Application for Noise Reduction of Landing Gear Strut." In 22nd AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-2845.

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Salt, Eric, Marko Arezina, James Lepore, and Samir Ziada. "Experimental Investigation of Landing Light Orientation on Landing Gear Noise." In ASME 2015 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/pvp2015-45137.

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A simplified model of a landing gear is tested in a wind tunnel to investigate the effect of the landing light orientation on the resulting noise generation. Examination of the near-field pressure fluctuations, combined with phase-locked stereoscopic particle imaging velocimetry (SPIV) of the unsteady wake identified two distinct sources of pressure fluctuations. The higher frequency source has a wide frequency band and is situated in the outer regions of the wake near the lights. However, the lower frequency source is found to be stronger, has a narrower frequency band, and is developed further downstream in the wake, closer to the wake centerline. The lower frequency source is observed to be rather robust as it is hardly affected by the orientation of the landing lights, whereas the higher frequency source becomes weaker as the distance between the lights is reduced. The effect of a splitter plate positioned downstream of the strut is also investigated as a means of disrupting the lower frequency pressure fluctuations. Although the lower frequency source is considerably reduced by the splitter plate, substantial enhancement of the higher frequency source is observed.
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Huntington, D., and C. Lyrintzis. "Random vibration in aircraft landing gear." In 37th Structure, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1360.

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Sankar, Balaji. "Effect Of Jump Strut Nose Landing Gear In Preliminary Design Of Aircraft." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4953.

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Ni, Peng. "Strength Analysis of Shock Strut of Aircraft Landing Gear Based on ANSYS." In 2022 IEEE 10th Conference on Systems, Process & Control (ICSPC). IEEE, 2022. http://dx.doi.org/10.1109/icspc55597.2022.10001784.

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