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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.


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Journal ArticleDOI
TL;DR: In this article, a simplified landing gear assembly model was created to complement with an accurate slave link subassembly, generated based of drawings supplied from the industrial partner, Safran Landing Systems.
Abstract: Aircraft landing gear assemblies comprise of various subsystems working in unison to enable functionalities such as taxiing, take-off and landing. As development cycles and prototyping iterations begin to shorten, it is important to develop and improve practical methodologies to meet certain design metrics. This paper presents an efficient methodology that applies high-fidelity multi-disciplinary design optimization techniques to commercial landing gear assemblies, for weight, cost, and structural performance by considering both structural and dynamic behaviours. First, a simplified landing gear assembly model was created to complement with an accurate slave link subassembly, generated based of drawings supplied from the industrial partner, Safran Landing Systems. Second, a Multi-Body Dynamic (MBD) analysis was performed using realistic input motion signals to replicate the dynamic behaviour of the physical system. The third stage involved performing topology optimization with results from the MBD analysis; this can be achieved through the utilization of the Equivalent Static Load Method (ESLM). Lastly, topology results were generated and design interpretation was performed to generate two designs of different approaches. The first design involved trying to closely match the topology results and resulted in a design with an overall weight savings of 67%, peak stress increase of 74%, and no apparent cost savings due to complex features. The second design focused on manufacturability and achieved overall weight saving of 36%, peak stress increase of 6%, and an estimated 60% in cost savings.

46 citations

Patent
04 May 1973
TL;DR: A landing gear device for an aircraft including a landing gear having a landing wheel rotatively mounted thereon and a variable speed motor for selectively engaging the wheel and rotating the same, at a selectable speed in the forward direction during the flight of an aircraft preparatory to the landing of the aircraft.
Abstract: A landing gear device for an aircraft including a landing gear having a landing wheel rotatively mounted thereon and a variable speed motor for selectively engaging the wheel and rotating the same, at a selectable speed in the forward direction during the flight of the aircraft preparatory to the landing of the aircraft, reciprocal drive element, operably interconnecting the motor to the landing wheel adapted to engage the wheel and rotate the wheel when power is applied to the electrical motor, and adapted to disengage from the wheel to permit free rotation thereof when the motor is deenergized, and speed control element, connected to the motor for substantially synchronizing the rotational speed of the landing wheel to that of the landing speed of the aircraft.

44 citations

Journal ArticleDOI
TL;DR: In this article, the problem of allocation of fuel consumption and carbon-dioxide emissions from transport aircraft is presented, where an accurate comprehensive program for transport aircraft has been developed, including a geometry deck with 12 subsystems, a separate engine input deck with basic parameters, a database of engine performance from independent simulation, an aerodynamics model for all flight conditions, and an operational deck.
Abstract: The problem of allocation of fuel consumption and carbon-dioxide emissions from transport aircraft is presented. An accurate comprehensive program for transport aircraft has been developed. The model includes a geometry deck with 12 subsystems, a separate engine input deck with basic parameters, a database of engine performance from independent simulation, an aerodynamics model for all flight conditions, and an operational deck. Validation of the model is discussed from the point of view of aerodynamics and payload-range performance. The aircraft considered are the Boeing B-737-500, B-747-400, and B-777-300, and the Airbus A340-300. Parametric studies are shown in terms of flight distance, passenger load, baggage allowance, operation with an en route stop, and direct flight. Calculations of best flight range and average passenger load have been considered. Data are presented in matrix form to be used for allocation of carbon dioxide in carbon trading schemes and for the critical evaluation of emissions from civil and commercial operations. It is shown that emissions per passenger per nautical mile range from 0.5 to 1.5 times the reference conditions, which is taken from the design range at full passenger load. It is also shown that fuel and emission savings can be achieved from optimal flight distance.

43 citations

Patent
22 May 2000
TL;DR: In this article, an onboard system for use in measuring, computing and displaying the weight and center-of-gravity for aircraft, while keeping aircraft movement to a minimum, is presented.
Abstract: An onboard system for use in measuring, computing and displaying the weight and center-of-gravity for aircraft, while keeping aircraft movement to a minimum. Pressure sensors are mounted in relation to each of the landing gear struts. An onboard pump and reservoirs are attached to each of the landing gear struts and are activated by a computer/controller, while landing gear strut pressures are monitored in the determination of strut stiction. The computer/controller calculates the stiction of each landing gear strut and compensates for the pressure distortions caused by landing gear strut stiction. Additional features include reducing strut stiction, measuring landing gear strut fluid levels, monitoring landing gear strut health, weight adjustments for external ice and de-icing fluids, weight adjustments for wind, monitoring aircraft landing gear strut movement.

43 citations

Patent
16 Nov 2006
TL;DR: An onboard system and method for determining the instantaneous weight and balance of an aircraft simply, reliably, accurately, and requiring a minimum amount of calibration includes a memory for storing previously determined breakout friction data of the aircraft's landing gear shock struts and sensors for sensing the pressures in the struts, the vertical loads exerted by the landing gear on the aircraft, and the attitude of aircraft relative to the horizontal during loading or unloading thereof.
Abstract: An onboard system and method for determining the instantaneous weight and balance of an aircraft simply, reliably, accurately, and requiring a minimum amount of calibration includes a memory for storing previously determined breakout friction data of the aircraft's landing gear shock struts, sensors for sensing the pressures in the struts, the vertical loads exerted by the landing gear on the aircraft, and the attitude of the aircraft relative to the horizontal during loading or unloading thereof, and a computer for computing the vertical load in each of the landing gears from the stored calibration breakout friction data and the shock strut pressures, landing gear vertical loads and aircraft attitude sensed during the loading or unloading. The computer then computes the gross weight of the aircraft and the location of its center of gravity (CG) using the computed vertical loads in the landing gears.

43 citations


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