Performance testing of a main rotor system for a utility helicopter at 1/4 scale by John D. Berry

Cover of: Performance testing of a main rotor system for a utility helicopter at 1/4 scale | John D. Berry

Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, National Technical Information Service, distributor in Washington, D.C, [Springfield, Va .

Written in English

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Subjects:

  • Rotors (Helicopters) -- Aerodynamics.,
  • Wind tunnels -- Ground simulators.,
  • Helicopters -- Flight testing.

Edition Notes

Book details

StatementJohn D. Berry.
SeriesNASA technical memorandum -- 83274., AVRADCOM technical report -- 82-B-3.
ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., Army Research and Technology Laboratories (U.S.). Structures Laboratory.
The Physical Object
Paginationiii, 45 p. :
Number of Pages45
ID Numbers
Open LibraryOL17799133M

Download Performance testing of a main rotor system for a utility helicopter at 1/4 scale

Format: Book, Government Document, EBook; LOC call number: TLT4 A3 no ; Published: Washington, D.C.: National Aeronautics and Space Administration. Performance testing of a main rotor system for a utility helicopter at 1/4 scale.

Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.: National Technical Information Service, distributor, ]. Aerodynamic and Performance Analysis of a Morphing Helicopter Rotor System.

The purpose of this study was to investigate the effect of rotor morphing, specifically variable rotor speed and variable blade twist, on various parameters such as the distribution of angle of attack, lift, power, thrust and/or other metrics describing the performance ofAuthor: Vinay Gopal Krishnan.

Performance testing of a main rotor system for a utility helicopter at 1/4 scale / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.: National Technical Information Service, distributor, ]), by John D. Berry, Army Research and Technology Laboratories (U.S.

high advance ratios. Furthermore, the XV-1 rotor is complex and is thus less desirable for correlation as part of this study. The data from the NASA Langley test was reported in Ref.

The teetering rotor was tested in the 30×60 tunnel (Langley Full Scale Tun-nel) at advance ratios ranging from to The variables measuredFile Size: KB. A helicopter main rotor or rotor system is the combination of several rotary wings (rotor blades) and a control system that generates the aerodynamic lift force that supports the weight of the helicopter, and the thrust that counteracts aerodynamic drag in forward flight.

Each main rotor is mounted on a vertical mast over the top of the helicopter, as opposed to a helicopter tail rotor, which. a rotor performance investigation in the Langley by Foot Subsonic Thnnel using a scale model of the AH Apache attack helicopter rotor and fuse­ lage.

Two sets of rotor blades were utilized and in­ cluded baseline blades modeled after the current op­ erational rotor and a set of alternate blades withFile Size: 8MB. The rotor system, or more simply rotor, is the rotating part of a helicopter that generates lift.A rotor system may be mounted horizontally, as main rotors are, providing lift vertically, or it may be mounted vertically, such as a tail rotor, to provide horizontal thrust to counteract torque from the main rotors.

INTRODUCTION TO HELICOPTER AERODYNAMICS WORKBOOK AERODYNAMICS TRANSITION HELICOPTER LETTER 0 – 0 iii -ix 0 (blank) 0 x (blank) 0 0 Since DA affects helicopter rotor and engine performance, it is a necessary consideration forFile Size: 2MB.

An isolated full-scale XV rotor was tested in helicopter mode in the NASA Ames 80 by Foot Wind Tunnel. Extensive acoustic data were obtained to define the rotor operating condition for. The rotor properties are shown in Table 1. The rotor’s simplicity makes it a good test article for correlation with analysis.

The CAMRAD II model was set up to match the wind tunnel test conditions as closely as possible. Distributed properties for the rotor are not available, so it was modeled using rigid blades.

The shaft angle was fixed. related to a joint Boeing/MIT effort to develop a system for actively twisting helicopter blades using interdigitated electrode piezoelectric fiber composite plies.

They report achieving levels of twist up to degrees in a bench test of a 1/16 Froude scaled model rotor blade. The vibration reduction potential of a proposed 1/6 Mach scaledCited by: Home › Scale › ️Aircraft › Scale Heli › Scale Helicopter Main Discussion › ULSRS (Ultra Low-Speed Rotor System) Project PM 12 years ago Topic Vote 0 Post 1.

for its impact on the performance improvement and vibration reduction in the present study. Numerical simulations are based on the UHA Blackhawk helicopter with an active Gurney flap spanning from 70%Rto 80%Rof the main rotor.

For obtaining the aeroelastic response of the rotor blade, finite element method was used to represent elastic blade. performedusingNDARC(NASADesignandAnalysis of Rotorcraft). The aircraft chosen for the study are the UHA single main-rotor and tail-rotor helicopter, the CHD tandem helicopter, the.

The helicopter does lazy stall turns, very nice “gun runs” and is capable of typical scale manuevers. Presence in the air is outstanding. My flying buddies love it. Me too. A 90 size engine would really make this helicopter perform, but a 70 does the job adequately and scale-like flight was the goal.

FAA-SB, Flight Instructor - Rotorcraft (Helicopter and Gyroplane) Practical Test Standards, will be effective December 1, File Size: KB.

Overview: This tutorial provides instruction which could be considered formulaic for modeling a basic helicopter via box modeling. Though primarily directed towards users of Wings 3D, the same concepts can be applied to any modeling program that employs box modeling and Catmull Clark subdivision as a construction method.

Han and Barakos studied the variable-speed in the tail rotor by setting three different tail rotor speed schedules, which achieved a % reduction in total helicopter power in cruise flight when. In this paper, the thickness noise of a rotor with 5 blades is calculated according to equation (2) for even and uneven configuration.

The calculation rotor model is like the rotor of UH-1, which is a 1/4 scale two-bladed untwisted model rotor with a rectangular platform and NACA airfoil section.

Numerical model of single main rotor helicopter dynamics normal to it and pointed lateral and towards the tail of the helicopter. Customarily, the force component along the chosen axis is called the tow force, the force component pointed towards the tail is the H force, and the force component pointed lateral called the Y force.

If the force. GT's HEADSPEED CALCULATOR Enter values and then press Calculate Headspeed to determine RPM of Main Rotor. MOTOR RPM (Value in kV) LIPO CELLS (Number of cells in series) 2S 3S 4S 5S 6S 7S 8S 9S 10S LIPO CELL VOLTAGE (Value of a single cell) MOTOR EFFICIENCY (Value in percent).

Rotor Report Newsletter. This e-newsletter is focused specifically on model helicopter and multirotor enthusiasts and features content from Model Aviation magazine, as well as AMA’s other media outlets. Model Aviation Rotor Report: 1/4/ Model Aviation Rotor.

Aerodynamic performance of the helicopter rotor is determined by the compressibility, flow separation, blade tip vortex and blade-vortex interaction. In this research, aerodynamic analysis and wake simulation of the helicopter rotor were performed using the time-domain panel method and free wake.

2 Numerical Method Governing Equation. This implies that if the hp going to the tail-rotor were sent to a second main-rotor, which was aerodynamically remote from the first main-rotor, the craft would be able to increase its payload by up to a theoretical hp * lb/hp = 4, lbs.

The Empty Weight is 13, lb., which gives a Maximum Payload is 8, lbs. Search. Helicopter pdf. The Mi-8 helicopter class and its modifications also use such a system [].Electric tail rotor. Eurocopter Deutschland GmbH (now Airbus Helicopters) invented a special type of an electrically driven tail rotor or better say fenestron for helicopters [].There is a housing around the tail rotor and at least one, or preferably two, permanent magnet energised synchronous engines are used for by: 3.

1 4 µ 2a o − 1 8 a 1 − 3 16 µ 2a 1 − 1 16 µ 2b 1 − 1 8 b 1 + 1 3 µa o b 1 + 1 4 λµB 1 − 1 8 a 1 B 1 + 1 16 µ2a 1 B 1 − 1 6 µa o A 1 + 1 8 b 1 A 1 + 1 16 µ2b 1 A 1 +,-(6) model for a generic helicopter, which tail rotor Where: Blade chord.

Air density., Main rotor and tail rotor disk ratio or blade length. Flapping blade File Size: KB. The HZ-1 Aerocycle, also known as the YHO-2 and by the manufacturer's designation DH-4 Heli-Vector, was an American one-man "personal helicopter" developed by de Lackner Helicopters in the mids.

Intended to be operated by inexperienced pilots with a minimum of 20 minutes of instruction, the HZ-1 was expected to become a standard reconnaissance machine with the United States Army.

Although Designer: Lewis C. McCarty Jr. From Summary: "A method has been proposed for predicting the effect of a rapid blade-pitch increase on the thrust and induced-velocity response of a helicopter rotor.

General equations have been derived for the ensuing motion of the helicopter. These equations yield time histories of thrust, induced velocity, and helicopter vertical velocity for given rates of blade-pitch-angle changes and Cited by: Review of Rotor Reference Axes Dynamics of a Lagging Blade with Hinge Offset Coupled Flap–Lag Motion Introduction to Rotor Trim Chapter Review Questions Bibliography 5 Basic Helicopter Performance Introduction Hovering and Axial Climb Performance Forward Flight File Size: KB.

Helicopter vibrations can exacerbate the effects of high workload environments by increasing pilot fatigue and causing back pain during long missions. Previous work has shown that active rotors equipped with trailing edge flaps are able to significantly reduce helicopter vibrations at the rotor hub and pi lot Size: 2MB.

Main rotor shaft 90° Gyro mounted to the helicopter GY Sensor tape LIMIT GAIN LIMIT GAIN Install the sensor so that the bottom of the gyro is perpendicular to the main rotor shaft axial direction.

Offset of this axis will also re-act in the roll and pitch directions. As shown in. Robinson R44 Big brother to the R22 is the Robinson R44, at 1/4 scale the overall length of the model is 6ft 6in (mm) and has a rotor diameter of m The 9 piece fibreglass fuselage kit comes with 30 scale 3D printed accessories, which include door hinges and handles, windows, undercarriage and woodwork to fit our custom made mechanics.

ness are representative of full-scale helicopter tail Rnr radius of main rotor, ft booms, though without the customary protruding r distance of fuselage station from main rivet heads.

Table I lists 1- and 2-in-high aluminum rotor hub, ft spoilers, attached as shown in figure 2, that were used for some tests. eliminated with this revolutionary sprinkler technology. Proven performance R - LPH Rad. - m 6°, 9°, 12°, 15°, 24° RLP / WF - LPH Rad. - m 25° R33LP / R33 - LPH Rad. - m 25° Performance Pocket Guide 3.

A quad-copter is considered a multi-rotor air-vehicle. Other common multi-rotor configurations include 3, 6 and 8 rotors. Four rotors provides a relatively stable configuration that is symmetric and won't be as expensive as the 6 or 8 rotor configurations. There are two other types of radio-controlled air-vehicles common with hobbyists.

Note: Steam VR is a free download that enables X‑Plane 11 to use VR. Steam VR is compatible with the X‑Plane 11 DVD set, digital download edition, and X‑Plane on Steam.

Note that no Intel GPUs are supported. Room-sized VR is supported, as well as using joysticks and other USB devices. Early Thinking 6 The Hoppers 11 The First Hoverers 17 Not Quite a Helicopter 20 Compressibility Corrections to Rotor Performance Equivalent Blade Chords and Weighted Solidity Principles of Helicopter Aerodynamics, Second Edition J.

Gordon Leishman Frontmatter More information. The Army is currently testing a system that would provide superimposed symbology on NVGs. It will provide simplified flight control information to reduce the pilot's need to monitor cockpit instruments. Download: Download full-size image; Figure Head-up symbology superimposed on the pilot night vision system (PNVS) on the Apache AH Cited by:.

The types of helicopters studied were the Light Observation Helicopter (LOH), the Utility Helicopter (UH), and the Cargo Helicopter (CH). The LOH is 4-place, the UH is place, and the CH is place; all are turbine-powered vehicles.

It was shown in this study that out of accidents were nonsurviv able.Shop by department, purchase cars, fashion apparel, collectibles, sporting goods, cameras, baby items, and everything else on eBay, the world's online marketplace.A helicopter model able to predict the main rotor and tail rotor powers is presented, and the flight test data of the UHA helicopter is used for validation.

The predictions of the main and tail rotor powers are generally in good agreement with flight tests, which justifies the use of the present method in analysing main and tail rotors.

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