scholarly journals DEVELOPMENT OF PROTOTYPE ELECTRO-HYDROSTATIC ACTUATOR FOR LANDING GEAR EXTENSION AND RETRACTION SYSTEM

2008 ◽  
Vol 2008 (7-1) ◽  
pp. 165-168 ◽  
Author(s):  
Norio TAKAHASHI ◽  
Taku KONDO ◽  
Masayuki TAKADA ◽  
Kazuhiro MASUTANI ◽  
Shingo OKANO ◽  
...  
Keyword(s):  
Landing Gear

Metrological aspects of pre-flight anti-icing procedures for civil aircraft

2019 ◽  
pp. 22-26
Author(s):  
А. Богоявленский ◽  
A. Bogoyavlenskiy
Keyword(s):  
Negative Impact ◽  
Landing Gear ◽  
Flight Performance ◽  
Spray Nozzle ◽  
Subsequent Formation ◽  
Inlet Guide Vanes ◽  
Civil Aircraft ◽  
Engine Compressor ◽  
Temperature And Pressure ◽  
Instrumental Control

Snow-ice deposits formed on the outer surfaces of aircrafts on the ground during parking can have a negative impact during take-off due to the deterioration of aerodynamic and flight performance, a significant and even critical decrease in lift, increased drag, blocking controls, difficulty or blocking of landing gear retraction, damage to the blades of inlet guide vanes and/or the blades of an engine compressor. To exclude the influence of snow and ice deposits, anti-icing treatment is performed, including their removal and/or protection from subsequent formation. For this purpose, special anti-icing machines (deicers), equipped with such means of instrumental control as counters of anti-icing fluid pumps, measuring scales of anti-icing fluid tanks, thermometers and pressure gauges for temperature and pressure measuring at the outlet of a spray nozzle, are used. The article deals with the metrological aspects of civil aircrafts anti-icing prior to flight.

Development of the C-17 Nose Landing Gear Container, CNU-691/E

2007 ◽  
Author(s):  
Joel A. Sullivan ◽  
Susan J. Evans
Keyword(s):  
Landing Gear

scholarly journals A Rational Numerical Method for Simulation of Drop-Impact Dynamics of Oleo-Pneumatic Landing Gear

2021 ◽  
Vol 11 (9) ◽  
pp. 4136
Author(s):  
Rosario Pecora
Keyword(s):  
Numerical Method ◽  
Initial Conditions ◽  
Impact Load ◽  
Numerical Models ◽  
Landing Gear ◽  
Design Stage ◽  
Impact Dynamics ◽  
State Variables ◽  
Adopted Model ◽  
The Impact

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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