Experimental and Theoretical Studies of Autogyro Fight Dynamics
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Montgomerie-Bensen B8MR, G-BXDC
Montgomerie-Bensen B8MR, G-BXDC AAIB Bulletin No: 1/2001 Ref: EW/C2000/04/03 - Category: 2.3 Aircraft Type and Registration: Montgomerie-Bensen B8MR, G-BXDC No & Type of Engines: 1 Rotax 582 piston engine Year of Manufacture: 1999 Date & Time (UTC): 16 April 2000 at 1411 hrs Location: Carlisle Airport, Cumbria Type of Flight: Private Persons on Board: Crew - 1 - Passengers - None Injuries: Crew - 1 - Passengers - N/A Nature of Damage: Aircraft destroyed Commander's Licence: Private Pilot's Licence (gyroplanes) Commander's Age: 51 years Commander's Flying Experience: 67 hours (of which 30 were on type) Last 90 days - 44 hours Last 28 days - 43 hours Information Source: AAIB Field Investigation Background information The pilot first showed an active interest in autogyros when in March 1999 he visited Carlisle Airport for a trial lesson. He had not flown before and enjoyed the experience so much that he flew again the same day and agreed to embark on a formal training programme with an instructor who was authorised by the CAA to conduct dual and single seat autogyro training as well as flight examinations. The instructor reported that his student approached all matters to do with his flying 'with a great deal of enthusiasm and a fair degree of ability'. From the start of his course until January 2000 the pilot undertook dual instruction, mainly at weekends, on a two seater VPM M16 autogyro. By March 2000 he was sufficiently experienced to transfer to the 'open frame' single-seat Benson autogyro. He flew this for approximately 20 hours, carrying out mainly short 'hops' along the length of the runway and practising balancing on the main wheels before progressing to flying the aircraft in the visual circuit and carrying out general handling exercises. -
Book Reviews the SYCAMORE SEEDS
Afterburner Book Reviews THE SYCAMORE SEEDS Early British Helicopter only to be smashed the following night in a gale. The book then covers the Cierva story in some detail, the Development chapter including, out of context, two paragraphs on By C E MacKay the Brennan propeller-driven rotor driven helicopter [helicogyro] fl own in 1924 at Farnborough but Distributed by A MacKay, 87 Knightscliffe Avenue, aborted by the Air Ministry the next year, stating that Netherton, Glasgow G13 2RX, UK (E charlese87@ there was no future for the helicopter and backing btinternet.com). 2014. 218pp. Illustrated. £12.95. Cierva’s autogyro programme contracting Avro to build ISBN 978-0-9573443-3-4. the fi rst British machines. Good coverage is given to the range of Cierva autogyros culminating in the Avro Given the paucity of coverage of British helicopter C30 Rota and its service use by the RAF. development I approached this slim (218 A5 pp) The heart of the book begins with a quotation: publication with interest. While autogyros have been “Morris, I want you to make me blades, helicopter well documented, Charnov and Ord-Hume giving blades,” with which William Weir, the fi rst Air Minister, exhaustive and well documented treatments of the founder of the RAF and supporter of Cierva, brought helicopter’s predecessor, the transition to the directly furniture maker H Morris & Co into the history of driven rotor of the helicopter is somewhat lacking. rotorcraft pulling in designers Bennett, Watson, Unfortunately MacKay’s book only contributes a Nisbet and Pullin with test pilots Marsh and Brie fi nal and short chapter to the ‘British Helicopter’ to form his team. -
Over Thirty Years After the Wright Brothers
ver thirty years after the Wright Brothers absolutely right in terms of a so-called “pure” helicop- attained powered, heavier-than-air, fixed-wing ter. However, the quest for speed in rotary-wing flight Oflight in the United States, Germany astounded drove designers to consider another option: the com- the world in 1936 with demonstrations of the vertical pound helicopter. flight capabilities of the side-by-side rotor Focke Fw 61, The definition of a “compound helicopter” is open to which eclipsed all previous attempts at controlled verti- debate (see sidebar). Although many contend that aug- cal flight. However, even its overall performance was mented forward propulsion is all that is necessary to modest, particularly with regards to forward speed. Even place a helicopter in the “compound” category, others after Igor Sikorsky perfected the now-classic configura- insist that it need only possess some form of augment- tion of a large single main rotor and a smaller anti- ed lift, or that it must have both. Focusing on what torque tail rotor a few years later, speed was still limited could be called “propulsive compounds,” the following in comparison to that of the helicopter’s fixed-wing pages provide a broad overview of the different helicop- brethren. Although Sikorsky’s basic design withstood ters that have been flown over the years with some sort the test of time and became the dominant helicopter of auxiliary propulsion unit: one or more propellers or configuration worldwide (approximately 95% today), jet engines. This survey also gives a brief look at the all helicopters currently in service suffer from one pri- ways in which different manufacturers have chosen to mary limitation: the inability to achieve forward speeds approach the problem of increased forward speed while much greater than 200 kt (230 mph). -
DYNAMIC MODELING of AUTOROTATION for SIMULTANEOUS LIFT and WIND ENERGY EXTRACTION by SADAF MACKERTICH B.S. Rochester Institute O
DYNAMIC MODELING OF AUTOROTATION FOR SIMULTANEOUS LIFT AND WIND ENERGY EXTRACTION by SADAF MACKERTICH B.S. Rochester Institute of Technology, 2012 A thesis submitted in partial fulfilment of the requirements for the degree of Master of Science in the Department of Mechanical and Aerospace Engineering in the College of Engineering and Computer Science at the University of Central Florida Orlando, Florida Spring Term 2016 Major Professor: Tuhin Das c 2016 Sadaf Mackertich ii ABSTRACT The goal of this thesis is to develop a multi-body dynamics model of autorotation with the objective of studying its application in energy harvesting. A rotor undergoing autorotation is termed an Autogyro. In the autorotation mode, the rotor is unpowered and its interaction with the wind causes an upward thrust force. The theory of an autorotating rotorcraft was originally studied for achieving safe flight at low speeds and later used for safe descent of helicopters under engine failure. The concept can potentially be used as a means to collect high-altitude wind energy. Autorotation is inherently a dynamic process and requires detailed models for characterization. Existing models of autorotation assume steady operating conditions with constant angu- lar velocity of the rotor. The models provide spatially averaged aerodynamic forces and torques. While these steady-autorotation models are used to create a basis for the dynamic model developed in this thesis, the latter uses a Lagrangian formulation to determine the equations of motion. The aerodynamic effects on the blades that produce thrust forces, in- plane torques, and out-of-plane torques, are modeled as non-conservative forces within the Lagrangian framework. -
Aviation Safety Letter Produce a Flurry of Re-Circulating Snow, Reducing Local Visibility and Causing Whiteout Conditions
Transport Transports Canada Canada Transport Transports aviation safety in history Canada Canada TP 185E A Issue 1/2008 viation Safety in History 1907—The Helicopter’s Chaotic Beginnings by Guy Houdin, Chief, Aviation Terminology Standardization, Policy and Regulatory Services, Civil Aviation, Transport Canada In those days, the safety of humans and machines was a concept that was buried in the subconscious. What mattered most was rising up, flying in the air, and landing without damaging the machine, or “beating up” the pilot. But first, the sky had to be iation Safety in History conquered and mastered. Av On July 14, 2007, I was watching the military parade, ones to witness this first successful flight, and although celebrating France’s National Day in Paris, on television. others before him—such as Léger in Monaco, Bréguet Approximately one hundred aircraft had been invited to and Vollumard in Douai, France—had some good, but less Snow Landing and Take-off Techniques for Helicopters the event. The airplanes started the procession down the convincing, attempts, historians retained November 13, 1907, Champs-Élysées, followed by the troops on foot and in as the birth date of free flight by a rotary wing aircraft. Throughout the course of winter operations, helicopters face a significant hazard associated with takeoffs, vehicles, and then about 30 helicopters brought up the landings and hovering when the ground is covered with fresh or light snow. The rotor down wash can rear. When you could barely see them, high above the La aviation safety letter produce a flurry of re-circulating snow, reducing local visibility and causing whiteout conditions. -
Session a – Tuesday Morning, May 5 – 8:00 A.M. – 12 Noon Aerodynamics I Aircraft Design I Crash Safety I Dynamics I Paper # 1 – 8:00 – 8:30 A.M
Session A – Tuesday Morning, May 5 – 8:00 a.m. – 12 noon Aerodynamics I Aircraft Design I Crash Safety I Dynamics I Paper # 1 – 8:00 – 8:30 a.m. Paper # 1 – 8:00 – 8:30 a.m. Paper # 1 – 8:00 – 8:30 a.m. Paper # 1 – 8:00 – 8:30 a.m. Navier-Stokes Assessment of Systematic Analysis of Rotor Evaluation of the Second Investigation of Whirl Flutter Test Facility Effects on Hover Blade Effective Twist Due to Transport Rotorcraft Airframe Stabilization using Active Performance (48) Planform Variation (76) Crash Testbed (TRACT 2) Full Trailing Edge Flaps (62) Neal Chaderjian and Jasim Fu-Shang (John) Wei, Central Scale Crash Test (73) Tobias Richter, Tobias Rath and Ahmad, NASA Ames Research Connecticut State U. and David Martin Annett, NASA Langley Walter Fichter, University of Center A. Peters, Washington Research Center Stuttgart; Oliver Oberinger, Paper # 2– 8:30 – 9:00 a.m. University, St Louis Paper # 2– 8:30 – 9:00 a.m. Technical University of Munich Comparing Numerical and Paper # 2– 8:30 – 9:00 a.m. Rotocraft Troop Seat with Paper # 2– 8:30 – 9:00 a.m. Experimental Results for Drag Development of Rotor Selectable Energy Absorber Effects of 2/rev Trailing Edge Reduction by Active Flow Structural Design Optimization System – Design & Test (145) Flap Input on Helicopter Control Applied to a Generic Framework for Compound Stanley Desjardins and Leda Vibrations for Modular Multi- Rotorcraft Fuselage (59) Rotorcraft with a Lift Offset (53) Belden, Safe Inc.; Lance Labun, Objective Active Rotor Control Caroline Lienard and Arnaud Le SangJoon Shin and YooJin Kang, Labun, LLC; Jin Woodhouse, US (56) Pape, ONERA; Norman W. -
Aerodynamic Concept of the Uav in the Gyrodyne Configuration
TRANSACTIONS OF THE INSTITUTE OF AVIATION 1 (250) 2018, pp. 49–66 DOI: 10.2478/tar-2018-0005 © Copyright by Wydawnictwa Naukowe Instytutu Lotnictwa AERODYNAMIC CONCEPT OF THE UAV IN THE GYRODYNE CONFIGURATION Jan Muchowski*, Marek Szumski*, Andrzej Krzysiak** *Department of Fluid Mechanics and Aerodynamics, Mechanical Engineering and Aeronautics, Rzeszow University of Technology, al. Powstańców Warszawy 8, 35-959 Rzeszow **Aerodynamics Department, Institute of Aviation, Al. Krakowska 110/114, 02-256 Warsaw [email protected], [email protected], [email protected], Abstract The article presents an aerodynamic concept of UAV in the gyrodyne configuration, as a more efficient one than the currently used UAV airframe configuration applied for monitoring tasks of pow- er lines and railway infrastructure. A sample task which is realised by conceptual gyrodyne based on monitoring aerial power lines was characterised and described . The assumed idea of UAV was shown in comparison to the currently used aircraft configuration presented in the introduction. Referring to momentum theory, hover efficiency of the multicopter and the helicopter was evaluated. In relation to the helicopter, an initial draft of the airframe conception accompanied by a description of advan- tages of the gyrodyne configuration was exposed. Problems related to the gyrodyne configuration were emphasised in the summary. Keywords: aerodynamic concept, UAV, VTOL, gyrodyne, airframe configuration 1. INTRODUCTION In recent years a dynamic growth of the UAV (Unmanned Aerial Vehicle) usage in civil and mili- tary missions can be observed . Economic aspects are the main reasons of that increase, i.e. the purchas- ing cost of the UAS (Unmanned Aircraft System) varies from 40% up to 80% of the manned system cost. -
Performance Analysis of the Slowed-Rotor Compound Helicopter Configuration
Performance Analysis of the Slowed-Rotor Compound Helicopter Configuration Matthew W. Floros Wayne Johnson Raytheon ITSS Army/NASA Rotorcraft Division Moffett Field, California NASA Ames Research Center Moffett Field, California The calculated performance of a slowed-rotor compound aircraft, particularly at high flight speeds, is exam- ined. Correlation of calculated and measured performance is presented for a NASA Langley high advance ratio test and the McDonnell XV-1 demonstrator to establish the capability to model rotors in such flight conditions. The predicted performance of a slowed-rotor vehicle model based on the CarterCopter Technology Demonstra- tor is examined in detail. An isolated rotor model and a model of a rotor and wing are considered. Three tip speeds and a range of collective pitch settings are investigated. A tip Mach number of 0.2 and zero collective pitch are found to be the optimum condition to minimize rotor drag. Performance is examined for both sea level and cruise altitude conditions. Nomenclature Much work has been focused on tilt rotor aircraft; both military and civilian tilt rotors are currently in development. But other configurations may provide comparable benefits to CT thrust coefficient tilt rotors in terms of range and speed. Two such configura- CQ torque coefficient tions are the compound helicopter and the autogyro. These CH longitudinal inplane force coefficient configurations provide STOL or VTOL capability, but are ca- D drag pable of higher speeds than a conventional helicopter because L lift the rotor does not provide the propulsive force or at high MTIP tip Mach number speed, the vehicle lift. The drawback is that redundant lift VT tip speed and/or propulsion add weight and drag which must be com- q dynamic pressure pensated for in some other way. -
Pilot Operating Handbook Pilot Operating Handbook for Gyroplane Cavalon
Pilot Operating Handbook Pilot Operating Handbook for Gyroplane Cavalon AutoGyro_POH_Cavalon Revision 3.1 – Issue Date 20.10.2018 Pre-pages 1 All rights reserved. Under the copyright laws, this manual may not be copied, in whole or in part, without the written consent of AutoGyro GmbH. AutoGyro reserves the right to change or improve its products and to make changes in the content of this manual without obligation to notify any person or organisation of such changes or improvements. Notifications to the Civil Aviation Authorities or other organisations based on legal regulations are unaffected. MTOsport, Calidus, Cavalon, the AutoGyro logo and word picture mark are trademarks or registered trademarks of AutoGyro AG, registered in Germany and other countries. Other company and product names mentioned herein may be trademarks of their respective companies. Mention of third- party products is for informational purposes only and constitutes neither an endorsement nor a recommendation. AutoGyro assumes no responsibility with regard to the performance or use of these products. All understandings, agreements, or warranties, if any, take place directly between the vendors and the prospective users. U.S. and foreign patents of AutoGyro AG are used in the Calidus and Cavalon gyroplanes - (US.Pat.No. 8,690,100; US.Pat.No. D699,153) Every effort has been made to ensure that the information in this manual is accurate. AutoGyro GmbH is not responsible for printing or clerical errors. AutoGyro_POH_Cavalon Revision 3.1 – Issue Date 20.10.2018 Pre-pages -
Measurements of Aerodynamic Interference of a Hybrid
sensors Article Measurements of Aerodynamic Interference of a y Hybrid Aircraft with Multirotor Propulsion Zbigniew Czy˙z 1,* and Mirosław Wendeker 2 1 Aeronautics Faculty, Military University of Aviation, 35 Dywizjonu 303 St., 08-521 D˛eblin,Poland 2 Department of Thermodynamics, Fluid Mechanics and Aviation Propulsion Systems, Faculty of Mechanical Engineering, Lublin University of Technology, 36 Nadbystrzycka St., 20-618 Lublin, Poland; [email protected] * Correspondence: [email protected] This paper is an extended version of our paper published in Zbigniew Czy˙z,Ksenia Siadkowska. y Measurement of Air Flow Velocity around the Unmanned Rotorcraft. In Proceedings of the 2020 IEEE International Workshop on Metrology for AeroSpace, Pisa, Italy, 22–24 June 2020. Received: 10 May 2020; Accepted: 11 June 2020; Published: 13 June 2020 Abstract: This article deals with the phenomenon of aerodynamic interference occurring in the innovative hybrid system of multirotor aircraft propulsion. The approach to aerodynamics requires a determination of the impact of active sources of lift and thrust upon the aircraft aerodynamic characteristics. The hybrid propulsion unit, composed of a conventional multirotor source of thrust as well as lift in the form of the main rotor and a pusher, was equipped with an additional propeller drive unit. The tests were conducted in a continuous-flow low speed wind tunnel with an open measuring space, 1.5 m in diameter and 2.0 m long. Force testing made it possible to develop aerodynamic characteristics as well as defining aerodynamic characteristics and defining the field of speed for the considered design configurations. Our investigations enabled us to analyze the results in terms of a mutual impact of particular components of the research object and the area of impact of active elements present in a common flow. -
NASA Design and Analysis of Rotorcraft User Training
https://ntrs.nasa.gov/search.jsp?R=20180008700 2019-08-31T17:42:25+00:00Z NDARC NASA Design and Analysis of Rotorcraft User Training March 2014 NDARC User Training March 2014 1 PREPARED BY Christopher Silva Jeffrey Sinsay U.S. Army Aviation Development Directorate (AFDD) Aviation & Missile Research, Development & Engineering Center Research, Development and Engineering Command Wayne Johnson National Aeronautics and Space Administration Ames Research Center, Moffett Field, California 94035 NDARC User Training March 2014 2 Training Objectives Purpose: • Provide overview of how NDARC conducts design and analysis tasks • Introduce NDARC input/output construct and syntax • Explain steps necessary to accomplish common design / analysis tasks • Illuminate common pitfalls and methods for debugging input Assumptions: • Familiar with the preliminary design process • Understand classic helicopter and fixed wing theory that underpins NDARC analysis (see Theory manual for details) • Familiar with FORTRAN namelist input Outcomes: • User can execute and parse input/output of NDARC examples • User can create a new design by modifying an example • User can use Theory manual and Input manual to set up more complex cases NDARC User Training March 2014 3 Outline Introduction Documentation Overview • Tasks • Aircraft NDARC Job • Input • Organization • Output Solution Procedures • Debugging Input Manual • Aircraft • Tasks Tutorial NDARC User Training March 2014 4 Rotorcraft System Design and Analysis Rotorcraft design work in government laboratory supports -
Autogyro C-30 Fuselage Finite Element Model Analysis
BACHELOR'S THESIS Degree in Aerospace Engineering Autogyro C-30 Fuselage Finite Element Model Analysis Enrique Labiano Laserna Supervisor Jos´e D´ıaz Alvarez´ February 2019 Abstract The main objective of this paper is to design and analyze the autogyro C-30 fuse- lage structure. The autogyro, considered as a hybrid between an airplane and a helicopter, is one the most important milestone in aircraft aviation. It was invented by Juan De la Cierva and became the first rotary wing aircraft that achieved suc- cess. In fact, this kind of rotorcraft will have a lot of influence on how the helicopter operates nowadays. The project will be divided into several parts. Firstly, all the information and draw- ings of the fuselage structure will be gathered and analyzed. After that, the fuselage structure will be modeled in a finite element software, called Abaqus. Secondly, all parts that composed the autogyro will be determined and their weights will be esti- mated taking into account the MTOW of the aircraft. According to the regulations established in the British Civil Airworthiness Requirements (BCAR), loads will be introduced in the model simulating a symmetric pull-up maneuver. The scope of the study will involve a stress analysis and finally, a modal analysis in order to determine the natural frequencies of the structure. Finally, a socio-economic impact of designing an autogyro will be presented together with a rough budget of manufacturing the fuselage structure of the autogyro C-30. Keywords: Autogyro C-30, fuselage structure, FEM analysis, modal analysis iii Acknowledgements First of all, I would like to thank my parents and my brothers who have helped me from the beginning.