Results 1 to 10 of about 874 (99)

Determination of the Tail Unit Parameters of Ultralight Manned and Unmanned Helicopters at the Preliminary Design Stage

Aerospace
The 1–2 seat helicopters have developed considerably in recent years. They have a maximum take-off weight of 250 to 750 kg. Most of these helicopters have been converted into unmanned versions.
Vitaly Dudnik
exaly   +4 more sources

Determination of loads in the ultralight helicopter blades

Aviation, 2023
The article describes research that was carried out on coaxial a single-seat ultralight helicopter Rotorschmiede VA-115 which is manufactured by German firm RS Helikopter GmbH.
Vitaly Dudnik
doaj   +2 more sources

Ultralight and Very Light Helicopter Rotor Data

Transactions of the Institute of Aviation, 2023
Abstract In recent years, a significant number of one- and two-seat lightweight helicopters have come into existence, and this makes it possible to analyse parameters and determine dependencies for this class of helicopters. the knowledge of such dependencies is necessary at the preliminary design stage.
Vitaly Dudnik
exaly   +2 more sources

Reduction of torque pulsation in ultralight helicopter transmission

Acta Polytechnica
Usually, 1–2 seats helicopters use piston engines. One of their disadvantages is a significant torque pulsation on the engine shaft. The main reason for such fluctuations is the change in parameters during the engine’s operating cycle.
Vitaly Dudnik
doaj   +2 more sources

Determination of Ultralight Helicopter Test Loads

Repüléstudományi Közlemények, 2023
In recent times, more and more development activities have been taking place in our country, mainly on own resources. Some promising designs, such as the HC02.2 helicopter, are slowly reaching the milestone of type certification. This article deals with the design considerations for the related strength tests through a particular example.
exaly   +3 more sources

SIMULATION AND OPTIMIZATION OF ULTRALIGHT HELICOPTER AERODYNAMIC CHARACTERISTICS

Advanced Engineering Research, 2012
The simulation and optimization of the ultralight helicopter aerodynamic characteristics at the design stages and phases which permit to determine optimal values of the engine power and speed are performed.
Viktor P. Zharov, Sergey P. Lisin
doaj   +2 more sources

DETERMINATION OF OPTIMAL AZIMUTH FOR MOUNTING ULTRALIGHT COAXIAL HELICOPTER BLADES

Advanced Engineering Research, 2011
The possibility of reducing vibration of the ultralight coaxial helicopter blades on the through harmonic wave by mounting blades on the optimal azimuth is shown.
Vitaly V. Dudnik, Vladimir A. Kolot
doaj   +2 more sources

LIFETIME DETERMINATION OF ULTRALIGHT HELICOPTER BLADES

Transport Problems
Determining the guaranteed operational time of helicopter blades is one of the important tasks necessary for successful vehicle use. Flight tests on different modes and special fatigue benches are used to solve such problems. The loads recorded during the flight are applied to ground tests on a bench.
exaly   +2 more sources

Toward Smart Air Mobility: Control System Design and Experimental Validation for an Unmanned Light Helicopter

Drones, 2023
Light helicopters are used for a variety of applications, attracting users from private and public market segments because of their agility and convenient storage capabilities.
Emanuele Luigi de Angelis, Fabrizio Giulietti, Gianluca Rossetti, Matteo Turci, Chiara Albertazzi   +4 more
doaj   +1 more source

Fuel Weight Determination of Ultralight and Very Light Helicopters at the Preliminary Design Stage

Transactions on Aerospace Research, 2022
Abstract In recent years, a large number of one- to two-seat-type helicopters have appeared, raising the possibility to determine the dependencies inherent in these classes. Such dependencies are extremely necessary at the preliminary design stage, in particular, for determining the fuel mass.
Vitaly Dudnik, Victor Karabut
openaire   +1 more source