Take-Off and Landing Using Ground-Based Power-Simulation of Critical Landing Load Cases Using Multibody Dynamics

Wu, Po-Han; Voskuijl, Mark; Tooren, M.J.L. Van; Veldhuis, L.L.M.

doi:10.1061/(asce)as.1943-5525.0000520

Cited by 9 publications

(5 citation statements)

References 18 publications

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“…Then, at standstill, the landing gear reached a steady-state compression due to the weight of the aircraft and the absence of aerodynamic lift. Such behavior is comparable to others found in the literature, thereby effectively simulating a mass spring-damper system [27,28].…”

Section: Vertical Dynamicssupporting

confidence: 86%

Model-Based Design of Aircraft Landing Gear System

Delprete,

Dagna,

Brusa

2023

Applied Sciences

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The aerospace industry is one of the leading figures in the development and improvement of techniques for the design of new products. One of the most promising developments of the last decades is the exploitation of digital models that make it possible to evaluate design solutions and simulate the behavior of the individual systems and their interactions. The goal is to be able to predict and analyze all aspects an aircraft much in advance of its industrialization in order to heavily reduce the time and costs of product development and to guarantee flexibility to test a multitude of solutions. The main issue in this context is the complexity of creating models that are capable of accurately sizing and simulating multiple interacting systems, thus considering the constraints imposed by the need for their mutual compatibility. The present contribution introduces two interconnected models regarding an aircraft system, in particular, the landing gear, that make it possible to size its main components and subsystems and to use the found parameters to populate a dynamic model that simulates the behavior of the aircraft during landing. These models provide a preliminary digitalization of the system itself and of the design process as well, thereby making it possible to define a potential configuration and to test it in a dynamic virtual environment, thus taking into account the interaction between the individual subsystems. The model was tested through three use cases, differentiated by class and scope, which made it possible to compare and validate the obtained results with actual values.

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Section: Vertical Dynamicssupporting

confidence: 86%

Model-Based Design of Aircraft Landing Gear System

Delprete,

Dagna,

Brusa

2023

Applied Sciences

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“…Many factors have effect on the impact load of tire. Wu et al (2016) find that the peak impact force between the aircraft tire and ground generated during landing process, increases with the growth of sink rate. So it has important significance to study the variation of impact load under different landing speed for safety assessment.…”

Section: Dynamic Simulations and Analysismentioning

confidence: 84%

“…The certification specifications of European Aviation Safety Agency (EASA) ( 2013) and the Federal Aviation Administration (FAA) ( 2006) state that this max sink rate should not exceed 3.05 m/s for airframe structural strength design and 3.66 m/s for civil aircraft landing gear design (Wu et al, 2016). The vertical landing speed is a key parameter for the safety of aircraft tire during the landing scenario.…”

Section: Dynamic Simulations and Analysismentioning

confidence: 99%

Finite element analysis of aircraft tire for safety assessment with CV and CPM methods

Yao

Zhu

Geng

et al. 2017

MMMS

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Purpose The purpose of this paper is to present a study of radial aircraft tire for safety assessment during various scenarios. Design/methodology/approach A detailed finite element (FE) model of aircraft tire was established based on the actual geometry of the target tire for numerical simulations. As the major component of this tire, rubber material usually presents a complicated mechanical behavior. To obtain the reliable hyperelastic properties of rubber, a series of material tests have been processed. Moreover, in order to validate the proposed model, the simulations results of inflation and static load scenarios were compared with the experimental results. Both of the control volume and corpuscular particle method methods were used in the numerical simulations of aircraft tire. Findings The comparisons of the two methods exhibit close agreement with the experimental results. To assess the safety of aircraft tire during the landing scenario, the dynamic simulations were processed with different landing weights and vertical landing speeds. According to the relevant airworthiness regulations and technical documents, the tire pressure, deflection and load have been chosen as the safety criteria. Subsequently, the analysis, results and comments have been discussed in detail. Originality/value The validated FE model proposed in present study can be effectively used in tire modeling in static and dynamic problems, and also in the design process of aircraft tire.

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“…The developed simulation models [76][77][78] have two major parts. One of them includes (i) the pilot module, (ii) the flight control system, (iii) the aerodynamic model and (iv) the power plant simulation.…”

Section: Concept Validation With Theoretical Methodsmentioning

confidence: 99%

Magnetic levitation assisted aircraft take-off and landing (feasibility study – GABRIEL concept)

Rohács

2016

Progress in Aerospace Sciences

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Take-Off and Landing Using Ground-Based Power-Simulation of Critical Landing Load Cases Using Multibody Dynamics

Cited by 9 publications

References 18 publications

Model-Based Design of Aircraft Landing Gear System

Model-Based Design of Aircraft Landing Gear System

Finite element analysis of aircraft tire for safety assessment with CV and CPM methods

Magnetic levitation assisted aircraft take-off and landing (feasibility study – GABRIEL concept)

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