Regulation Gazette, No. 7249
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Government of India Office of Director General of Civil Aviation
GOVERNMENT OF INDIA OFFICE OF DIRECTOR GENERAL OF CIVIL AVIATION TECHNICAL CENTRE, OPPOSITE SAFDARJUNG AIRPORT, NEW DELHI CIVIL AVIATION REQUIREMENTS DRAFT SECTION 2 – AIRWORTHINESS SERIES 'O', PART VI F No.11-690/CAR/O-VI/2006/AI (2) ISSUE II DATED __________APRIL 2016 EFFECTIVE: FORTHWITH Subject Manufacture, Registration and Operation of Powered Hang Gliders 1 INTRODUCTION This part of the Civil Airworthiness Requirements specifies requirements relating to, manufacture, registration, maintenance operation and security of powered hang gliders. 1.1 For the purpose of this CAR, a powered hang glider is a vehicle that is used or intended to be used for manual operation in the air by a single occupant/ double 1.1.1 occupant. is used or intended to be used for recreation, sport, or any other purpose approved by 1.1.2 DGCA in writing. 1.1.3 has the maximum AUW less than 275 kgs for a single seater. 1.1.4 has the maximum AUW less than 375 kgs for a double seater. 1.1.5 is not capable of more than 70 knots calibrated air speed at full power in level flight, and 1.1.6 has a power-off stall speed which does not exceed 30 knots calibrated air speed. 2 DEFINITION 2.1 "Acrobatic flight" means manoeuvres intentionally performed by an aircraft involving an abrupt change in its attitude, an abnormal attitude or abnormal variation in speed. 2.2 "Air Traffic Control Clearance" means authorisation by an Air Traffic Control unit for an aircraft to proceed within controlled airspace under specified conditions. 2.3 "Controlled Airport” means an airport at which an Air Traffic Control unit is provided. -
HELICOPTERS (Air-Cushion Vehicles B60V)
CPC - B64C - 2020.02 B64C AEROPLANES; HELICOPTERS (air-cushion vehicles B60V) Special rules of classification The use of the available Indexing Codes under B64C 1/00- B64C 2230/00 is mandatory for classifying additional information. B64C 1/00 Fuselages; Constructional features common to fuselages, wings, stabilising surfaces and the like (aerodynamical features common to fuselages, wings, stabilising surfaces, and the like B64C 23/00; flight-deck installations B64D) Definition statement This place covers: • Overall fuselage shapes and concepts (only documents relating thereto are attributed the symbol B64C 1/00, when the emphasis is on aerodynamic aspects the symbol B64C 1/0009 is attributed). • Structural features (including frames, stringers, longerons, bulkheads, skin panels and interior liners). • Windows and doors (including hatch covers, access panels, drain masts, canopies and windscreens). • Fuselage structures adapted for mounting power plants, floors, integral loading means (such as steps). • Attachment of wing or tail units or stabilising surfaces to the fuselage; • Relatively movable fuselage parts (for improving pilot's view or for reducing size for storage). • Severable/jettisonable parts for facilitating emergency escape. • Inflatable fuselage components. • Fuselage adaptations for receiving aerials or radomes. • Passive cooling of fuselage structures and sound/heat insulation (including isolation mats, and clips for mounting such mats and components such as pipes or cables). References Limiting references This place does not cover: Structural features and concepts are attributed the relevant symbol(s) in B64C 1/06 - B64C 1/12 Aerodynamical features common to fuselages, wings, stabilising B64C 23/00 surfaces, and the like Flight-deck installations B64D Special rules of classification Structures and components for helicopters falling within this main group and/or appended subgroups are additionally attributed the symbol B64C 27/04. -
FAA Regulations of Ultralight Vehicles Sudie Thompson
Journal of Air Law and Commerce Volume 49 | Issue 3 Article 4 1984 FAA Regulations of Ultralight Vehicles Sudie Thompson Follow this and additional works at: https://scholar.smu.edu/jalc Recommended Citation Sudie Thompson, FAA Regulations of Ultralight Vehicles, 49 J. Air L. & Com. 591 (1984) https://scholar.smu.edu/jalc/vol49/iss3/4 This Comment is brought to you for free and open access by the Law Journals at SMU Scholar. It has been accepted for inclusion in Journal of Air Law and Commerce by an authorized administrator of SMU Scholar. For more information, please visit http://digitalrepository.smu.edu. Comments FAA REGULATION OF ULTRALIGHT VEHICLES SUDIE THOMPSON A RELATIVELY NEW form of sport and recreational avi- ation has swept the aviation industry - ultralights. Ul- tralights are the first airplanes to have been developed and marketed as "air recreational vehicle[s]." ' Powered ul- tralights are featherweight planes which cost between $2,800 and $7,000.2 Unpowered ultralights are most frequently called hang gliders.' It is estimated that the worldwide total of powered and unpowered ultralights of all types is 25,000,' and one source predicts that the world total of 20,000, pow- ered ultralights will soon double.5 An October, 1981, article places the Federal Aviation Administration's (FAA) estimate of the number of powered ultralights flying in the United States alone at about 2,500.6 Less than one year later the Experimental Aircraft Association (EAA) and the FAA in- creased their estimates of the number of operational powered and unpowered ultralights (excluding true hang gliders) to 7 10,000. -
Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment
University of Tennessee, Knoxville TRACE: Tennessee Research and Creative Exchange Masters Theses Graduate School 5-2006 Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment Scott Bennett Trail University of Tennessee - Knoxville Follow this and additional works at: https://trace.tennessee.edu/utk_gradthes Part of the Aerospace Engineering Commons Recommended Citation Trail, Scott Bennett, "Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment. " Master's Thesis, University of Tennessee, 2006. https://trace.tennessee.edu/utk_gradthes/1816 This Thesis is brought to you for free and open access by the Graduate School at TRACE: Tennessee Research and Creative Exchange. It has been accepted for inclusion in Masters Theses by an authorized administrator of TRACE: Tennessee Research and Creative Exchange. For more information, please contact [email protected]. To the Graduate Council: I am submitting herewith a thesis written by Scott Bennett Trail entitled "Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment." I have examined the final electronic copy of this thesis for form and content and recommend that it be accepted in partial fulfillment of the equirr ements for the degree of Master of Science, with a major in Aviation Systems. Robert B. Richards, Major Professor We have read this thesis and recommend its acceptance: Rodney Allison, Frank Collins Accepted for the Council: Carolyn R. Hodges Vice Provost and Dean of the Graduate School (Original signatures are on file with official studentecor r ds.) To the Graduate Council: I am submitting herewith a thesis written by Scott Bennett Trail entitled “Evaluation of V-22 Tiltrotor Handling Qualities in the Instrument Meteorological Environment”. -
2012 Alumni Fellow Teaching Award, Penn I Am Also Delighted to Announce That David and Nancy Pauling Have En- State’S Highest Teaching Award
A P U B L I C A T I O N O F A E R O S P A C E E N G I N E E R I N G · F A L L 2 0 1 2 Message from the Department Head ur faculty, students, and staff continue to Susan Stewart, Sven Schmitz, and Dennis McLaughlin continue to lead advance aerospace technology and sys- our efforts to develop new courses related to wind energy. At present, O tems, contributing to national defense, three courses are being developed for online offering, with initial rollout commercial flight, earth observation, exploration, imminent. Elaine Gustus joined our department as instructional designer and new sources of energy. And as the aerospace to assist our faculty content experts in making these courses a reality. The enterprise gears up to address significant work- courses will comprise a graduate certificate program, and will provide a force challenges in the coming decade, our major degree option for a proposed online master’s degree program in Renewa- continues to be in high demand. Our undergradu- ble Energy and Sustainability Systems. ate and graduate programs are ranked 10th and We are pleased to acknowledge Peter and Barbara Papadakos for their 13th by U.S. News & World Report and Penn gifts of a restored AGM-78 missile and a MK-44 torpedo. These have State Engineering was ranked 11th in the annual already found places in our undergraduate structures laboratory, where Academic Ranking of World Universities! students are gaining invaluable experience by performing structural vibra- Our faculty members continue to garner well-deserved recognition. -
Mathematical Modelling of Gimballed Tilt-Rotors for Real-Time Flight Simulation
aerospace Article Mathematical Modelling of Gimballed Tilt-Rotors for Real-Time Flight Simulation Anna Abà 1, Federico Barra 2,*,† , Pierluigi Capone 1 and Giorgio Guglieri 2 1 ZAV Centre for Aviation, ZHAW Zurich University of Applied Sciences, CH-8401 Winterthur, Switzerland; [email protected] (A.A.); [email protected] (P.C.) 2 Department of Mechanical and Aerospace Engineering, Politecnico di Torino, 10129 Torino, Italy; [email protected] * Correspondence: [email protected] † Current address: Technikumstrasse 9, P.O. Box 8401 Winterthur, Switzerland. Received: 29 July 2020; Accepted: 26 August 2020; Published: 28 August 2020 Abstract: This paper introduces a novel gimballed rotor mathematical model for real-time flight simulation of tilt-rotor aircraft and other vertical take-off and landing (VTOL) concepts, which improves the previous version of a multi-purpose rotor mathematical model developed by ZHAW and Politecnico di Torino as part of a comprehensive flight simulation model of a tilt-rotor aircraft currently implemented in the Research and Didactics Simulator of ZHAW and used for research activities such as handling qualities studies and flight control systems development. In the novel model, a new formulation of the flapping dynamics is indroduced to account for the gimballed rotor and better suit current tilt-rotor designs (XV-15, V-22, AW-609). This paper describes the mathematical model and provides a generic formulation as well as a specific one for 3-blades proprotors. The method expresses the gimbal attitude but also considers the variation of each blade’s flapping due to the elasticity of the blades, so that the rotor coning angle can be represented. -
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3rd International Conference on Mechanical Engineering and Intelligent Systems (ICMEIS 2015) A Fast Method of Aerodynamic Computation for Compound Gyroplane MA Tielin1, a, HAO Shuai2, XUE Pu2, LI Gen2,GAN Wenbiao1 1Research Institute of Unmanned Aerial Vehicle, Beijing University of Aeronautics and Astronautics, Beijing 100191,China 2School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China aemail:[email protected] Keywords: Compound gyroplane; Engineering estimation method; Blade element momentum theory; Fast method; CFD Abstract. A fast method of aerodynamic computation (FMAC) is put forward for compound gyroplane. It combines advantages of the blade element momentum theory and the engineering estimation method. To fast obtain aerodynamic characteristics of the compound gyroplane, the FMAC simplifies the interface between rotor and wing, and uses the estimation method to analyze wing and the blade element momentum theory integration method for rotor. Based on the FMAC, aerodynamic characteristics of a certain compound gyroplane are researched, and compares with the sliding mesh CFD method. The comparison confirmed the effectiveness and rapidness of this method. It is shown that the FMAC can be used for rapid aerodynamic analysis and design optimization of compound gyroplane. Introduction The compound gyroplane is a combination of gyroplane and fixed-wing aircraft. It has advantages of the both flight vehicles, and uses autorotation rotor and fixed wing as lifting surface. The flight performance of the aircraft is similar with gyroplane at low speed. When it is flying at high speed, collective pitch of rotor is reduced, so the rotor is unloaded to avoid disadvantages such as wingtip stalling. -
Vehicle Registration Application Form
Vehicle Registration Application Form NAME_______________________________________________________________________________________________________ last first middle ADDRESS__________________________________________________________________________________________________ CITY ________________________________________________________ STATE ________ ZIP Phone (______) ______________ Date of Birth ____/____/_____ USUA Member # (REQUIRED FOR REGISTRATION) A _______________ This is a ❏new address ❏ new phone number. Please update my records. Instructions for Vehicle Registration 1. Complete and sign the application. Except for signatures, all data should be typewritten or printed legibly. 2. Send completed application and processing fee to USUA. I AM APPLYING FOR: Vehicle Make & Model To Be Registered ❏ New Vehicle Registration ___________________________________________ (Valid only with current USUA membership) Vehicle Manufacturer Name ❏ Custom Numbers (Available only with New Vehicle Registration) ___________________________________________ Vehicle Model Name ❏ Transfer Of Existing Registration (Valid only with current USUA membership) _______________________ _________________ Engine Make/Model Airframe Serial # (if any) Vehicle Description Vehicle Registration Transfer * If Applicable Check items below as applicable: TO NEW OWNER Registration may be transferred to a new owner when the following statement from the previous owner is completed indicating ❏ SINGLE PLACE forfeiture of the registration number. The new owner may then apply ❏ TWO -
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. -
What Is a Tiltrotor? a Fundamental Reexamination of the Tiltrotor Aircraft Design Space
What is a Tiltrotor? A Fundamental Reexamination of the Tiltrotor Aircraft Design Space Larry A. Young NASA Ames Research Center, Moffett Field, CA 94035 Abstract The objective of this work is to fundamentally reexamine the design space of tiltrotor aircraft beyond the very successful conventional vehicle configuration with tractor-type twin proprotors that are nacelle- mounted at the wing tips. This work seeks to define a broad aircraft design space for alternate tiltrotor configurations. It is hoped that this work will not only provide design inspiration for future aircraft developers, but also help realize in the future new applications and missions for both passenger-carrying vehicles and vertical lift UAVs. Introduction After a multi-decade development effort, the first production tiltrotor aircraft, the MV/CV-22 Osprey, has become a key element of U.S. military aviation. After its own long fitful development effort, the AW-609, the first civil tiltrotor aircraft, seems to be finally nearing certification. Design studies continue to show the promise of large civil tiltrotor aircraft for commercial passenger transport – particularly as such aircraft might help enable significant National Airspace System (NAS) throughput increases and delay reduction through their VTOL/runway-independent nature. Tiltrotor aircraft have finally arrived. Meanwhile, though, a recent resurgence of development activity in compound helicopters, notably the X2 and X3 compound helicopters, has narrowed the speed/range advantage of tiltrotor aircraft over such vehicles. In parallel with these advances in manned rotary-wing aircraft, aviation as a whole is poised to see a rapid expansion in uninhabited VTOL UAV’s supporting new civilian/commercial missions/applications. -
Active and Passive Techniques for Tiltrotor Aeroelastic Stability Augmentation
The Pennsylvania State University The Graduate School College of Engineering ACTIVE AND PASSIVE TECHNIQUES FOR TILTROTOR AEROELASTIC STABILITY AUGMENTATION A Thesis in Aerospace Engineering by Eric L. Hathaway c 2005 Eric L. Hathaway Submitted in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy August 2005 The thesis of Eric L. Hathawaywas reviewed and approved* by the following: Farhan Gandhi Associate Professor of Aerospace Engineering Thesis Adviser Chair of Committee Edward C. Smith Professor of Aerospace Engineering Joseph F.Horn Assistant 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. Abstract Tiltrotors are susceptible to whirl flutter, an aeroelastic instability characterized by a coupling of rotor-generated aerodynamic forces and elastic wing modes in high speed airplane-mode flight. The conventional approach to ensuring adequate whirl flutter stability will not scale easily to larger tiltrotor designs. This study constitutes an investigation of sev- eral alternatives for improving tiltrotor aerolastic stability. A whirl flutter stability analysis is developed that does not rely on more complex models to determine the variations in cru- cial input parameters with flight condition. Variation of blade flap and lag frequency, and pitch-flap, pitch-lag, and flap-lag couplings, are calculated from physical parameters, such as blade structural flap and lag stiffness distribution (inboard or outboard of pitch bearing), collective pitch, and precone. The analysis is used to perform a study of the influence of various design parameters on whirl flutter stability. -
Factsheets Factsheet
North Atlantic Treaty Organization www.nato.int/factsheets Factsheet July 2021 Next Generation Rotorcraft Capability (NGRC) Letter of Intent1 signed Memorandum of Understanding2 signed Delivery Participants What is the NGRC? The Next Generation Rotorcraft Capability High Visibility Project3, creates a multinational framework under which its participants can combine efforts to work on design, development and delivery of a medium multi-role helicopter. A significant amount of the medium multi-role assets currently in service by Allies, will reach the end of their life cycle in the 2035-40 period and beyond, The NGRC aims to replace medium multi-role helicopters with the subsequent need for replacements. These existing inventories are all currently in service, like the AW-101. based on designs dating back to the previous century. The aim of the NGRC initiative is to respond to this upcoming requirement, in a timely and cost- effective manner, while concurrently leveraging a broad range of recent advances in technology, production methods, and operational concepts. NATO differentiates between three different classes of vertical lift – or generally known as helicopter – capabilities: light, medium, and heavy. The difference lies in the payload that can be carried. The NGRC concept phase will focus initially on medium multi-role capabilities, taking into account the speed of the technological evolution and participants’ future requirements. Multinational effort Following preliminary discussions about future requirements, Defence Ministers from France, Germany, Greece, Italy, and the United Kingdom, decided to launch the multinational NGRC initiative through the signature of a Letter of Intent in November 2020. Following this agreement, the five Allies have started working on defining a robust Statement of Requirements for informing an envisioned concept phase, and a multi- phase cooperation plan for defining, developing, and fielding of the NGRC capability.