Interagency Helicopter Pilot Practical Test Standards 2015
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Adventures in Low Disk Loading VTOL Design
NASA/TP—2018–219981 Adventures in Low Disk Loading VTOL Design Mike Scully Ames Research Center Moffett Field, California Click here: Press F1 key (Windows) or Help key (Mac) for help September 2018 This page is required and contains approved text that cannot be changed. NASA STI Program ... in Profile Since its founding, NASA has been dedicated • CONFERENCE PUBLICATION. to the advancement of aeronautics and space Collected papers from scientific and science. The NASA scientific and technical technical conferences, symposia, seminars, information (STI) program plays a key part in or other meetings sponsored or co- helping NASA maintain this important role. sponsored by NASA. The NASA STI program operates under the • SPECIAL PUBLICATION. Scientific, auspices of the Agency Chief Information technical, or historical information from Officer. It collects, organizes, provides for NASA programs, projects, and missions, archiving, and disseminates NASA’s STI. The often concerned with subjects having NASA STI program provides access to the NTRS substantial public interest. Registered and its public interface, the NASA Technical Reports Server, thus providing one of • TECHNICAL TRANSLATION. the largest collections of aeronautical and space English-language translations of foreign science STI in the world. Results are published in scientific and technical material pertinent to both non-NASA channels and by NASA in the NASA’s mission. NASA STI Report Series, which includes the following report types: Specialized services also include organizing and publishing research results, distributing • TECHNICAL PUBLICATION. Reports of specialized research announcements and feeds, completed research or a major significant providing information desk and personal search phase of research that present the results of support, and enabling data exchange services. -
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). -
Helicopter Safety July-August 1991
F L I G H T S A F E T Y F O U N D A T I O N HELICOPTER SAFETY Vol. 17 No. 4 For Everyone Concerned with the Safety of Flight July/August 1991 The Philosophy and Realities of Autorotations Like the power-off glide in a fixed-wing aircraft, the autorotation in a helicopter must be used properly if it is to be a successful safety maneuver. by Michael K. Hynes Aviation Consultant In all helicopter flying, there is no single event that has a In the early years of airplane flight, the fear of engine greater impact on safety than the autorotation maneuver. failure, or that the airplane might have structural prob- The mere mention of the word “autorotation” at any lems during flight, was very strong. If either of these gathering of helicopter pilots, especially flight instruc- events took place, the pilot’s ability to get the airplane tors, will guarantee a long and lively discussion. safely on the ground quickly was important. The time it took to get the airplane on the ground was directly in There are many misconceptions about autorotations and proportion to the altitude at which the airplane was being they contribute to the accident rate when an autorotation flown. It is therefore logical that all early flights were precedes a helicopter landing accident. One approach to flown at low altitudes, often at less than 500 feet above a discussion of autorotations is to look at the subject the ground (agl). from three views: first, the philosophy of the subject; second, the reality of the circumstances that require au- At these low altitudes, the pilot did not always have the torotations; and third, the execution of the maneuver. -
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. -
Development of a Helicopter Vortex Ring State Warning System Through a Moving Map Display Computer
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection 1999-09 Development of a helicopter vortex ring state warning system through a moving map display computer Varnes, David J. Monterey, California. Naval Postgraduate School http://hdl.handle.net/10945/26475 DUDLEY KNOX LIBRARY NAVAL POSTGRADUATE SCHOOL MONTEREY CA 93943-5101 NAVAL POSTGRADUATE SCHOOL Monterey, California THESIS DEVELOPMENT OF A HELICOPTER VORTEX RING STATE WARNING SYSTEM THROUGH A MOVING MAP DISPLAY COMPUTER by David J. Varnes September 1999 Thesis Advisor: Russell W. Duren Approved for public release; distribution is unlimited. Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instruction, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington. VA 22202-4302, and to the Office of Management and Budget. Paperwork Reduction Project (0704-0188) Washington DC 20503. REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED 1. agency use only (Leave blank) September 1999 Master's Thesis 4. TITLE AND SUBTITLE 5. FUNDING NUMBERS DEVELOPMENT OF A HELICOPTER VORTEX RING STATE WARNING SYSTEM THROUGH A MOVING MAP DISPLAY COMPUTER 6. AUTHOR(S) Varnes, David, J. 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) PERFORMING ORGANIZATION Naval Postgraduate School REPORT NUMBER Monterey, CA 93943-5000 10. -
A Qualitative Introduction to the Vortex-Ring-State, Autorotation, and Optimal Autorotation
36th European Rotorcraft Forum, Paris, France, September 7-9, 2010 Paper Identification Number 089 A Qualitative Introduction to the Vortex-Ring-State, Autorotation, and Optimal Autorotation Skander Taamallah ∗† ∗ Avionics Systems Department, National Aerospace Laboratory (NLR) 1059 CM Amsterdam, The Netherlands ([email protected]). † Delft Center for Systems and Control (DCSC) Faculty of Mechanical, Maritime and Materials Engineering Delft University of Technology, 2628 CD Delft, The Netherlands. Keywords: Vortex-Ring-State (VRS); autorotation; Height-Velocity diagram; optimal control; optimal autorotation Abstract: The main objective of this pa- 1 Introduction per is to provide the reader with some qualita- tive insight into the areas of Vortex-Ring-State This paper summarizes the results of a brief (VRS), autorotation, and optimal autorota- literature survey, of relevant work in the open tion. First this paper summarizes the results literature, covering the areas of the VRS, of a brief VRS literature survey, where the em- autorotation, and optimal autorotation. Due phasis has been placed on a qualitative descrip- to time and space constraints, only published tion of the following items: conditions leading accounts relative to standard helicopter to VRS flight, the VRS region, avoiding the configurations will be covered, omitting thus VRS, the early symptoms, recovery from VRS, other types such as tilt-rotor, side-by-side, experimental investigations, and VRS model- tandem, and co-axial. Presenting a complete ing. The focus of the paper is subsequently survey of a field as diverse as helicopter VRS, moved towards the autorotation phenomenon, autorotation, and optimal trajectories in where a review of the following items is given: autorotation is a daunting task. -
The Pennsylvania State University
The Pennsylvania State University The Graduate School Department of Aerospace Engineering REAL-TIME PATH PLANNING AND AUTONOMOUS CONTROL FOR HELICOPTER AUTOROTATION A Dissertation in Aerospace Engineering by Thanan Yomchinda 2013 Thanan Yomchinda Submitted in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy May 2013 The dissertation of Thanan Yomchinda was reviewed and approved* by the following: Joseph F. Horn Associate Professor of Aerospace Engineering Dissertation Co-Advisor Co-Chair of Committee Jacob W. Langelaan Associate Professor of Aerospace Engineering Dissertation Co-Advisor Co-Chair of Committee Edward C. Smith Professor of Aerospace Engineering Christopher D. Rahn Professor of Mechanical Engineering George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering *Signatures are on file in the Graduate School iii ABSTRACT Autorotation is a descending maneuver that can be used to recover helicopters in the event of total loss of engine power; however it is an extremely difficult and complex maneuver. The objective of this work is to develop a real-time system which provides full autonomous control for autorotation landing of helicopters. The work includes the development of an autorotation path planning method and integration of the path planner with a primary flight control system. The trajectory is divided into three parts: entry, descent and flare. Three different optimization algorithms are used to generate trajectories for each of these segments. The primary flight control is designed using a linear dynamic inversion control scheme, and a path following control law is developed to track the autorotation trajectories. Details of the path planning algorithm, trajectory following control law, and autonomous autorotation system implementation are presented. -
OAS-69B Helicopter Pilot Evaluation Qualification Check.Xlsx
OAS-69B(12/12) Helicopter Pilot Evaluation/Qualification Check Section I - Pilot Information (to be filled out by pilot seeking approval ) 1. Name: (Last, First, Middle Initial) 2. Employed By: 3. Type of Evaluation: Initial Recurrent Compliance Postaccident 4. Aircraft: (make, model, series) 5. Aircraft N Number: 6. Flight Time: 7. Location of Flight Evaluation: SECTION II - Statement of Retention of Aircraft Pilot-in-Command Authority 1. Authority Statement: I will remain responsible as the sole Pilot-in-Command of the aircraft during this evaluation flight and I will refuse to attempt any maneuver which, in my opinion, may be hazardous, unsafe, or result in any contractual, company, or FAA violation. 2. Pilot's Signature (sign prior to flight) 3. Date SECTION III - Pilot Evaluation Summary D-Demonstrated Ability K-Knowledgeable U-Unsatisfactory 1. Prerequisites 7. Special Use Operations 1 a. MH1 Basic Fire Behavior and Tactics (attach copy) Expires: a. Low Level (Recon. & Surv.) 1 b. MH2 Organization, Communication, and Airspace (attach copy) Expires: b. Helitack/Passenger Transport 1 c. MH3 Fire Helicopter Operations (attach copy) Expires: (1) Crew/Passenger Brief 1 d. A-110 Aviation Transport of Hazardous Materials (attach copy) Expires: (2) Manifest 2 e. Grand Canyon SFAR (attach copy) Expires: c. External Load (belly hook) Note Recurrence: 1 3 year 2 1 year d. Water/Retardant Delivery 2. General Knowledge e. Longline VTR (150 ft) a. Interagency Operations and Safety Procedure Guide (Fire Only) f. Snorkel b. Pilot Authority and Responsibility (1) VTR c. Power Assurance Check (2) Mirror d. Flight Time and Duty Day Limitations g. -
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. -
A Qualitative Introduction to the Vortex-Ring-State, Autorotation, and Optimal Autorotation
UNCLASSIFIED Nationaal Lucht- en Ruimtevaartlaboratorium National Aerospace Laboratory NLR Executive summary A Qualitative Introduction to the Vortex-Ring-State, Autorotation, and Optimal Autorotation Problem area survey relative to single-engine The main objective of this paper is helicopter optimal autorotation, and Report no. to provide the reader with some its associated problem formulation NLR-TP-2010-282 qualitative insight into the areas of as a nonlinear, constrained, optimal Vortex-Ring-State (VRS), control problem. Author(s) autorotation, and optimal S. Taamallah autorotation. Results and conclusions Presenting a complete survey of a Report classification Description of work field as diverse as helicopter VRS, UNCLASSIFIED First this paper summarizes the autorotation, and optimal Date results of a brief VRS literature trajectories in autorotation is a May 2011 survey, where the emphasis has daunting task. Hence the review been placed on a qualitative is from a common qualitative Knowledge area(s) description of the following items: approach, with emphasis on Helikoptertechnologie conditions leading to VRS flight, concepts rather than on details. the VRS region, avoiding the VRS, Descriptor(s) the early symptoms, recovery from Applicability Vortex-Ring-State (VRS) VRS, experimental investigations, This survey was essentially tailored Autorotation and VRS modeling. The focus of for researchers interested in Height-Velocity diagram the paper is subsequently moved designing control systems, for Optimal control towards the autorotation helicopter flight in the VRS and Optimal autorotation phenomenon, where a review of the autorotation, such as automatic following items is given: the VRS avoidance, automatic recovery maneuver, the height-velocity from VRS flight, and automatic zones, and factors affecting autorotation. -
Motivations and Preliminary Design for Mid-Air Deployment of a Science Rotorcraft on Mars
Motivations and Preliminary Design for Mid-Air Deployment of a Science Rotorcraft on Mars Jeff Delaune∗ Jacob Izraelevitz† Evgeniy Sklyanskiy‡ Aaron Schutte§ Abigail Fraeman¶ Valerie Scott‖ Carl Leake∗∗ Erik Ballesteros†† Kim Aaron‡‡ Jet Propulsion Laboratory, California Institute of Technology, Pasadena, CA, 91109 Larry A. Young§§ Wayne Johnson¶¶ Shannah Withrow-Maser∗∗∗ Haley Cummings††† Raghav Bhagwat‡‡‡ NASA Ames Research Center, Moffett Field, CA, 94035 Marcel Veismann§§§ Skylar Wei¶¶¶ Regina Lee17 Luis Pabon Madrid18 Morteza Gharib19 Joel Burdick20 Center for Autonomous Systems and Technologies (CAST), California Institute of Technology, Pasadena, CA, 91125 William Rapin21 CNRS, Toulouse, 31400, France Mid-Air Deployment (MAD) of a rotorcraft during Entry, Descent and Landing (EDL) on Mars eliminates the need to carry a propulsion or airbag landing system. This reduces the total mass inside the aeroshell by more than 100 kg and simplifies the aeroshell architecture. MAD’s lighter and simpler design is likely to bring the risk and cost associated with the mission down. Moreover, the lighter entry mass enables landing in the Martian highlands, at elevations inaccessible to current EDL technologies. This paper proposes a novel MAD concept for a Mars helicopter. We suggest a minimum science payload package to perform relevant science in the highlands. A variant of the Ingenuity helicopter is proposed to provide increased deceleration during MAD, and enough lift to fly the science payload in the highlands. We show in simulation that the lighter aeroshell results in a lower terminal velocity (30 m/s) at the end of the parachute phase of the EDL, and at higher altitudes than other approaches.