Landing Gear Concept and Dynamic Landing Loads of the Unmanned Space Re-entry Vehicle USV3

Paletta, Nicola; Dmytriv, A.; Belardo, Marika; Cristillo, D.; Pecora, M.

doi:10.1016/j.proeng.2015.08.030

Cited by 5 publications

(4 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…However, it absorbs the forces produced during the retardation phase, the main landing gear bears the largest dynamic load during take-off. Both static and dynamic loads must be taken into account in order to correctly assess the overall loads on the landing gears (Chaudhary, 2021;Jiang et al, 2023;Paletta et al, 2015).…”

Section: Loading Conditions (Dynamic)mentioning

confidence: 99%

Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Yadav,

Sudhakar

2023

Orchid Acad. Siraha

View full text Add to dashboard Cite

Landing gear failures are a major cause of aircraft failures because they are an integral part of the aircraft's development. According to the Federal Aviation Administration (FAA), 50% of all aircraft failures occur during take-offs and landing. The landing gear of a short take-offs and landing (STOL) aircraft has had its static and dynamic forces analyzed analytically and numerically. SOLIWORKS is used to model the landing gear, and ANSYS is used to perform the numerical simulation results. Following it, the model is examined for stress and deformation with the boundary conditions and computed loads into account. This study uses structural finite element analysis (FEA) to analyze the nose gear's stress behavior and displacement during landing, as well as to assess the effect of the runway gradient. Utilizing a comprehensive numerical simulation, the landing gear of a real material Twin-Otter STOL aircraft has been demonstrated to be subjected to a dynamic force of 3653.26N, a pneumatic pressure of 1.59MPa, a bead pressure of 7.97MPa, and a vertical force of 1672.31lbs on level runways, or runways with no gradient. These findings will increase the level of confidence of aircraft manufacturers to make necessary appropriate design of STOL aircraft’s landing gear. It may can decrease the aircraft accidents and increase human life safety ultimately saving valuable time and resources too.

show abstract

Section: Loading Conditions (Dynamic)mentioning

confidence: 99%

Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Yadav,

Sudhakar

2023

Orchid Acad. Siraha

View full text Add to dashboard Cite

show abstract

“…In some studies, cases where the orifice diameters were changed by mattering pin according to the strut length were examined. This provides better absorption during impact as a passive control (Paletta et al , 2015). Oleo shock absorbers have a pneumatic spring.…”

Section: Introductionmentioning

confidence: 99%

“…Pecora (2021) simulated the drop test of the oleo-pneumatic suspension numerically. Paletta et al (2015) made a concept oleo-pneumatic design for an unmanned space vehicle.…”

Section: Introductionmentioning

confidence: 99%

Fuzzy control of a landing gear system with oleo-pneumatic shock absorber to reduce aircraft vibrations by landing impacts

Arık

Bilgiç

2022

AEAT

View full text Add to dashboard Cite

Purpose The purpose of this paper is to control a landing gear system with an oleo-pneumatic shock absorber with the fuzzy controller. Design/methodology/approach The landing gear system with an oleo-pneumatic shock absorber is modeled mathematically. A fuzzy controller is designed for reducing aircraft vibrations. Stroke velocity and main mass velocity parameters were used to decide variable gas pressure with the fuzzy controller. Findings The fuzzy controller, designed according to stroke velocity and main mass velocity, reduces aircraft vibrations by the landing impacts. The controller can provide strong robustness because it shows similar good performance for different descent speeds. Research limitations/implications This study was carried out through simulations in a computer environment and has not been experimentally tested in a real environment. In addition, signal and measurement delays are not taken into account. In future models, the effects of these signal delays can be added, and the controller can be tested on a real model. Originality/value In this study, to the best of the authors’ knowledge, for the first time, the gas pressure for the landing gear system using an oleo-pneumatic shock absorber was controlled by a fuzzy controller that adjusts the stroke velocity and the main mass velocity. Although the oleo-pneumatic shock absorber model contains high nonlinearities, the designed fuzzy controller gave successful results as robust.

show abstract

“…In previous studies, the main focus on the drop dynamic response of landing gear is the structural parameters, air spring force, friction force and structural force, rather than the discharge coefficient [4][5][6][7]. It is common that the discharge coefficient is estimated empirically as a constant in the landing gear dynamic analysis.…”

Section: Introductionmentioning

confidence: 99%

Discharge coefficient calculation method of landing gear shock absorber and its influence on drop dynamics

Ding¹,

Wei²,

Nie³

et al. 2018

J. vibroeng.

View full text Add to dashboard Cite

Oleo-damping performance is a key factor affecting the landing gear buffer performance, while the flow discharge coefficient determines buffer damping force. For improving the calculation precision of discharge coefficient estimation method in aircraft design manual, a model for discharge coefficient is established based on pipeline fluid mechanics and damping orifice structure, and a numerical calculation is performed. Computational fluid dynamics (CFD) analysis is also conducted for damping orifice structure using the commercial software FLUNET. The simulation result of damping orifice discharge coefficient correlates well with the theoretical result. On this basis, landing gear drop dynamic response are calculated with the numerical analysis method using obtained discharge coefficient and compared with experimental results. Furthermore, the influences of current discharge coefficient estimation method and simulation method are analyzed and compared on the hydraulic force and the ground reaction force. The study demonstrates that the poor precision of discharge coefficient estimation method in aircraft design manual leads to more than 30 % differences between the drop dynamic estimation results and the experimental results. The method of CFD simulation or theoretical analysis can improve the calculation precision of discharge coefficient by about 17 %.Yong-Ping Li received the B.S. degree in aircraft design from Nanchang Hangkong University, Nanchang, China, in 2015. Now he is studying for a Master degree with aircraft design,

show abstract

Landing Gear Concept and Dynamic Landing Loads of the Unmanned Space Re-entry Vehicle USV3

Cited by 5 publications

References 10 publications

Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study

Fuzzy control of a landing gear system with oleo-pneumatic shock absorber to reduce aircraft vibrations by landing impacts

Discharge coefficient calculation method of landing gear shock absorber and its influence on drop dynamics

Contact Info

Product

Resources

About