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Landing gear

About: Landing gear is a research topic. Over the lifetime, 3403 publications have been published within this topic receiving 25370 citations. The topic is also known as: landing gear & gear.


Papers
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01 May 2014
TL;DR: In this paper, a flexible wing modeling and physical mass estimation system for early aircraft design stages is developed, where the core of the interdisciplinary tool chain is a central model generator that automatically generates all analysis models from the DLR aircraft data format CPACS (Common Parametric Aircraft Configuration Scheme).
Abstract: State-of-the-art models in preliminary wing design apply physics-based methods for primary structures while using empirical correlations for secondary structures. Using those methods, a detailed optimization such as e.g. rear spar positions or flap size is only possible within a limited design space. Novel structural concepts such as multi-spar flap layouts or the introduction of composite materials cannot be analyzed using statistical methods and require extended higher level structural modeling. Therefore, a flexible wing modeling and physical mass estimation system for early aircraft design stages is developed – the WINGmass system. The core of the interdisciplinary tool chain is a central model generator that automatically generates all analysis models from the DLR aircraft data format CPACS (Common Parametric Aircraft Configuration Scheme). For the automatic model generation, a large amount of engineering rules are implemented in the model generator, to reduce the amount of required input parameters and therefore to relieve the aircraft designer. Besides the multi-model generator, the tool chain consist of a structural finite element model (incl. wing primary structures, flaps, flap tracks, ailerons, engine pylon and landing gear), a structural sizing algorithm and loads models for aerodynamic, fuel, landing gear and engine loads. The wing mass estimation system is calibrated against real mass values of the wing primary structures and the trailing edge devices of the Airbus A320 and A340-200. The results of the calibrated tool chain are compared to the masses of the primary structures of the B747-100 and the aluminum baseline version of the MD-90-40X. The calibration factors for composite primary structures are derived from the composite version of the MD-90-40X. Finally, the benefits of the extended physics-based modeling and the application of the WINGmass system in an interdisciplinary aircraft design environment are shown in an aircraft design study. The objective of this study is to compute the optimal wing shape in terms of mission fuel as a function of the take-off field length. Therefore, a parameter variation of the wing and flap geometry is performed, the engine scaled correspondingly and the mission fuel evaluated.

13 citations

Journal ArticleDOI
TL;DR: In this article, an algorithm is developed to study the transient response of concrete airport pavements resting on viscoelastic foundations and subjected to moving aircraft, and a computer program is developed on the basis of the proposed algorithm that can be used to predict dynamic deflections and stresses of concrete Airport pavements induced by the general moving mass and the simplified moving force and static loads.

13 citations

Patent
08 Dec 1944
TL;DR: In this article, the authors proposed a means for indicating to the pilot of an aircraft equipped with a retractable landing gear that the landing gear has been replaced by a fixed landing gear.
Abstract: This invention relates to aircraft, more particularly to landing gear therefor, and has for an object to provide improved apparatus of this character. Another object of the invention is to provide, in aircraft equipped with retractable landing gear, means for indicating to the pilot of the...

13 citations

Patent
19 Mar 1942
TL;DR: In this paper, a landing gear capable of being extended below, and retracted into (a) a motor nacelle located in the aircraft wing (b) a wing, or (c) a fuselage.
Abstract: The present invention relates generally to retractable landing gear arrangements for aircraft, and more particularly landing gear capable of being extended below, and retracted into (a) a motor nacelle located in the aircraft wing (b) a wing, or (c) a fuselage. The invention has for its primary...

13 citations

16 Sep 2007
TL;DR: The discussion, vision and the conclusions all aim at presenting the gathered requirements and the establishments for system design at a general level, hence the information about specific sensors and data requirements should be regarded as illustrative, realistic examples, not as an actual design specification.
Abstract: Report Abstract: This case study aims at analysing the requirements for the integration of RFID and sensors in the integrated system health management process of aircraft landing gears. The study is based on a number of interviews and site visits at Messier-Dowty and Messier Services as well as on previous research conducted at the Cambridge Auto-ID Lab. The discussion, vision and the conclusions all aim at presenting the gathered requirements and the establishments for system design at a general level, hence the information about specific sensors and data requirements should be regarded as illustrative, realistic examples, not as an actual design specification.

13 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202353
2022135
2021101
2020116
2019199
2018190