Determination of Takeoff and Landing Distances Using an Ipad Performance Application for the Diamond DA40
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China's Aircraft Carrier Ambitions
CHINA’S AIRCRAFT CARRIER AMBITIONS An Update Nan Li and Christopher Weuve his article will address two major analytical questions. First, what are the T necessary and suffi cient conditions for China to acquire aircraft carriers? Second, what are the major implications if China does acquire aircraft carriers? Existing analyses on China’s aircraft carrier ambitions are quite insightful but also somewhat inadequate and must therefore be updated. Some, for instance, argue that with the advent of the Taiwan issue as China’s top threat priority by late 1996 and the retirement of Liu Huaqing as vice chair of China’s Central Military Commission (CMC) in 1997, aircraft carriers are no longer considered vital.1 In that view, China does not require aircraft carriers to capture sea and air superiority in a war over Taiwan, and China’s most powerful carrier proponent (Liu) can no longer infl uence relevant decision making. Other scholars suggest that China may well acquire small-deck aviation platforms, such as helicopter carriers, to fulfi ll secondary security missions. These missions include naval di- plomacy, humanitarian assistance, disaster relief, and antisubmarine warfare.2 The present authors conclude, however, that China’s aircraft carrier ambitions may be larger than the current literature has predicted. Moreover, the major implications of China’s acquiring aircraft carriers may need to be explored more carefully in order to inform appropriate reactions on the part of the United States and other Asia-Pacifi c naval powers. This article updates major changes in the four major conditions that are necessary and would be largely suffi cient for China to acquire aircraft carriers: leadership endorsement, fi nancial affordability, a relatively concise naval strat- egy that defi nes the missions of carrier operations, and availability of requisite 14 NAVAL WAR COLLEGE REVIEW technologies. -
The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
Constraints for STOL Operations in South Florida Conurbation Cedric Y
Constraints for STOL Operations in South Florida Conurbation Cedric Y. Justin June 2021 Based on research previously published: Development of a Methodology for Parametric Analysis of STOL Airpark Geo-Density, Robinson et al. AIAA AVIATION 2018 Door-to-Door Travel Time Comparative Assessment for Conventional Transportation Methods and Short Takeoff and Landing On Demand Mobility Concepts, Wei et al. AIAA AVIATION 2018 Wind and Obstacles Impact on Airpark Placement for STOL-based Sub-Urban Air Mobility, Somers et al., AIAA AVIATION 2019 Optimal Siting of Sub-Urban Air Mobility (sUAM) Ground Architectures using Network Flow Formulation, Venkatesh et al, AIAA AVIATION 2020 Comparative Assessment of STOL-based Sub-Urban Air Mobility Operations in Massachusetts and South Florida, Justin et al. AIAA AVIATION 2020 Current Market Segmentation ? VTOL CTOL CTOL CTOL CTOL Capacity ? 200-400+ pax Twin Aisle Are there 120-210 pax scenarios where Single Aisle an intermediate solution using 50-90 pax STOL vehicles and Regional Aircraft sitting in- Design range below 300 nm Commuters between UAM 9-50 pax Flight time below 1.5 hours Thin-Haul and thin-haul 9 to 50 seat capacity operations exists? 4-9 pax Sub-Urban Missions 50-150 nm Air Mobility 4 to 9 revenue-seats Missions below 50 nm Urban Air Mobility 1-4 pax 1 to 4 revenue-seats 50 nm 300 nm 500 nm 3000 nm 6000+ nm Artwork Credit Uber Design Range 2 Introduction • Population, urbanization, and congestion Atlanta, GA Miami, FL Dallas, TX Los Angeles, CA have increased steadily over the past several decades • Increasing delays damage the environment and substantially impact the economy Driving time: 8 min. -
Off Airport Ops Guide
Off Airport Ops Guide TECHNIQUES FOR OFF AIRPORT OPERATIONS weight and balance limitations for your aircraft. Always file a flight plan detailing the specific locations you intend Note: This document suggests techniques and proce- to explore. Make at least 3 recon passes at different levels dures to improve the safety of off-airport operations. before attempting a landing and don’t land unless you’re It assumes that pilots have received training on those sure you have enough room to take off. techniques and procedures and is not meant to replace instruction from a qualified and experienced flight instruc- High Level: Circle the area from different directions to de- tor. termine the best possible landing site in the vicinity. Check the wind direction and speed using pools of water, drift General Considerations: Off-airport operations can be of the plane, branches, grass, dust, etc. Observe the land- extremely rewarding; transporting people and gear to lo- ing approach and departure zone for obstructions such as cations that would be difficult or impossible to reach in trees or high terrain. any other way. Operating off-airport requires high perfor- mance from pilot and aircraft and acquiring the knowledge Intermediate: Level: Make a pass in both directions along and experience to conduct these operations safely takes either side of the runway to check for obstructions and time. Learning and practicing off-airport techniques under runway length. Check for rock size. Note the location of the supervision of an experienced flight instructor will not the touchdown area and roll-out area. Associate land- only make you safer, but also save you time and expense. -
A Conceptual Design of a Short Takeoff and Landing Regional Jet Airliner
A Conceptual Design of a Short Takeoff and Landing Regional Jet Airliner Andrew S. Hahn 1 NASA Langley Research Center, Hampton, VA, 23681 Most jet airliner conceptual designs adhere to conventional takeoff and landing performance. Given this predominance, takeoff and landing performance has not been critical, since it has not been an active constraint in the design. Given that the demand for air travel is projected to increase dramatically, there is interest in operational concepts, such as Metroplex operations that seek to unload the major hub airports by using underutilized surrounding regional airports, as well as using underutilized runways at the major hub airports. Both of these operations require shorter takeoff and landing performance than is currently available for airliners of approximately 100-passenger capacity. This study examines the issues of modeling performance in this now critical flight regime as well as the impact of progressively reducing takeoff and landing field length requirements on the aircraft’s characteristics. Nomenclature CTOL = conventional takeoff and landing FAA = Federal Aviation Administration FAR = Federal Aviation Regulation RJ = regional jet STOL = short takeoff and landing UCD = three-dimensional Weissinger lifting line aerodynamics program I. Introduction EMAND for air travel over the next fifty to D seventy-five years has been projected to be as high as three times that of today. Given that the major airport hubs are already congested, and that the ability to increase capacity at these airports by building more full- size runways is limited, unconventional solutions are being considered to accommodate the projected increased demand. Two possible solutions being considered are: Metroplex operations, and using existing underutilized runways at the major hub airports. -
United States Rocket Research and Development During World War II
United States Rocket Research and Development During World War II Unidentified U.S. Navy LSM(R) (Landing Ship Medium (Rocket)) launching barrage rockets during a drill late in the Second World War. Image courtesy of the U.S. National Archives and Records Administration. and jet-assisted takeoff (JATO) units for piston-pow- Over the course of the Second World War, rockets ered attack fighters and bombers. Wartime American evolved from scientific and technical curiosities into rocket research evolved along a number of similar and practical weapons with specific battlefield applications. overlapping research trajectories. Both the U.S. Navy The Allied and Axis powers both pursued rocket re- and Army (which included the Army Air Forces) devel- search and development programs during the war. Brit- oped rockets for ground bombardment purposes. The ish and American rocket scientists and engineers (and services also fielded aerial rockets for use by attack their Japanese adversaries) mainly focused their efforts aircraft. The Navy worked on rocket-powered bombs on tactical applications using solid-propellant rockets, for antisubmarine warfare, while the Army developed while the Germans pursued a variety of strategic and the handheld bazooka antitank rocket system. Lastly, tactical development programs primarily centered on both the Army and Navy conducted research into JATO liquid-propellant rockets. German Army researchers units for use with bombers and seaplanes. Throughout led by Wernher von Braun spent much of the war de- the war, however, limited coordination between the veloping the A-4 (more popularly known as the V-2), armed services and federal wartime planning bodies a sophisticated long-range, liquid-fueled rocket that hampered American rocket development efforts and led was employed to bombard London and Rotterdam late to duplicated research and competition amongst pro- in the war. -
Advisory Circular 120-62
fw 3 Advisory U.S.Department of Transportation Federal Aviation Circular ’ AdminisWation Qlbject: TAKEOFF SAFETY TRAINING AID bte: g/Q/g4 AC No. 120-6.2 Announcement Of Availability Initiatedby: AFS-210 Change; 1 PURPOSE. This advisory circular (AC) announces the availability of a joint industry/Federal Aviation Administration (FAA) Takeoff Safety Training Aid to help air carriers and pilots increase safety during the takeoff phase of flight. a. The FAA recommends early consideration of the information contained in the aid and use of the material, as appropriate, for training aircrews. This AC also highlights certain key items, concepts, and definitions that each air carrier or operator should address in their respective operational procedures and crew qualification programs. b This circular applies to Federal Aviation Regulations (FAR) Part 121 operators. However, many of the principles, concepts, and procedures described apply to operations under FAR Parts 918 129, and 135 for certain aircraft, and are recommended for use by those operators when applicable. 2 BACKGROUND. Takeoff accidents resulting from improper rejected takeoff (RTO) decisions and procedures are significant contributors to worldwide commercial aviation accident statistics. For those takeoffs that are rejected, and for takeoffs made under certain environmental conditions and with certain system failures, risks could be reduced by a higher level of flightcrew knowledge and by the use of improved procedures. Due to the risks and the accident statistics associated with takeoffs, a joint FAA/industry team studied what actions might be taken to increase takeoff safety. These studies included simulation trials and in-depth analysis of takeoff accidents and incidents. -
Draft Environmental Assessment for Issuing an Experimental Permit to Spacex for Operation of the Grasshopper Vehicle at the Mcgregor Test Site, Texas September 2011
Federal Aviation Administration Draft Environmental Assessment for Issuing an Experimental Permit to SpaceX for Operation of the Grasshopper Vehicle at the McGregor Test Site, Texas September 2011 HQ-111451 Draft EA for Issuing an Experimental Permit to SpaceX for Operation of the Grasshopper Vehicle at the McGregor Test Site, Texas TABLE OF CONTENTS Section Page ACRONYMS AND ABBREVIATIONS ...................................................................................... iv 1. INTRODUCTION ....................................................................................................................1 1.1 Background .....................................................................................................................1 1.2 Purpose and Need for Agency Action .............................................................................2 1.3 Request for Comments on the Draft EA .........................................................................2 2. DESCRIPTION OF THE PROPOSED ACTION AND NO ACTION ALTERNATIVE ......3 2.1 Proposed Action ..............................................................................................................3 2.1.1 Grasshopper RLV ..............................................................................................5 2.1.1.1 Description ......................................................................................... 5 2.1.1.2 Pre-flight and Post-flight Activities ................................................... 5 2.1.1.3 Flight Profile (Takeoff, Flight, -
A SEMI-EMPIRICAL METHODOLOGY for BALANCED FIELD LENGTH ESTIMATION of JET- ENGINED AIRCRAFT in EARLY DESIGN PHASES Tulio Angeiras Embraer S.A
A SEMI-EMPIRICAL METHODOLOGY FOR BALANCED FIELD LENGTH ESTIMATION OF JET- ENGINED AIRCRAFT IN EARLY DESIGN PHASES Tulio Angeiras Embraer S.A. and Aeronautical Technology Institute – ITA Product Development Engineer and Graduate Student Sao Jose dos Campos, SP, 12227-901, Brazil [email protected] Adson de Paula (ITA), Bento Mattos (ITA), Tarik Orra (Embraer) ABSTRACT Current levels of competitiveness displayed in business and commercial aviation market led to increasingly stringent performance and economy requirements. One of the key elements of these requirements is field performance, a factor that has great influence on the viability of certain route or operation for the aircraft in question, and that might shift the balance in a purchase decision. During early design phases, aerodynamic data about the aircraft being developed is often inaccurate and subject to changes during its evolution, which, alongside with difficulties do validate the results, renders numerical simulation methods unpractical for estimating field performance. These factors stimulated the development of a number of semi-empirical methodologies to estimate takeoff field lengths, of which some, by taking advantage of the available historical trend, produce very reasonable results and are widespread adopted on the aviation industry. Aiming to enable leaner aircraft designs, this paper presents an overview of several established methods, analyzing structure and comparing results obtained by their application to a databank of existing aircrafts. Finally, it -
Appendix a Description of Declared Distances
Appendix A Description of Declared Distances Declared distances at airports are a mechanism by which specific lengths of runway pavement are identified for use in aircraft operations. Declared distances are incorporated into the Operations Specifications of commercial aircraft operators that are part of the air carrier certificates and operations certificates issued by FAA under 14 CFR Part 119, as well as into the internal operations manuals of those operators. Pilots of commercial aircraft are required to comply with such specifications and manuals. The specified distance available for a particular operation such as landing may be different in each direction on the same runway pavement. The FAA defines four declared distances: • Takeoff Run Available (TORA) – the runway length declared available and suitable for satisfying takeoff run requirements. The TORA is measured from the start of takeoff to a point 200 feet from the beginning of the departure Runway Protection Zone. • Takeoff Distance Available (TODA) – this distance comprises the TORA plus the length of any remaining runway or clearway beyond the far end of the TORA. • Accelerate-Stop Distance Available (ASDA) – the runway plus stopway length declared available and suitable for the acceleration and deceleration of an aircraft that must abort its takeoff. A stopway is an area beyond the takeoff runway able to support the airplane during an aborted takeoff, without causing structural damage to the airplane. • Landing Distance Available (LDA) – the runway length that is declared available and suitable for satisfying aircraft landing distance requirements. The figure below illustrates how declared distances allow a runway pavement length of 11,600 feet to provide a usable runway length of 10,000 feet for landing and 10,600 feet for takeoffs in both directions while still providing the FAA-required runway safety area dimensions of 600 feet prior to the landing threshold and 1,000 feet beyond the runway end. -
(VL for Attrid
ECCAIRS Aviation 1.3.0.12 Data Definition Standard English Attribute Values ECCAIRS Aviation 1.3.0.12 VL for AttrID: 391 - Event Phases Powered Fixed-wing aircraft. (Powered Fixed-wing aircraft) 10000 This section covers flight phases specifically adopted for the operation of a powered fixed-wing aircraft. Standing. (Standing) 10100 The phase of flight prior to pushback or taxi, or after arrival, at the gate, ramp, or parking area, while the aircraft is stationary. Standing : Engine(s) Not Operating. (Standing : Engine(s) Not Operating) 10101 The phase of flight, while the aircraft is standing and during which no aircraft engine is running. Standing : Engine(s) Start-up. (Standing : Engine(s) Start-up) 10102 The phase of flight, while the aircraft is parked during which the first engine is started. Standing : Engine(s) Run-up. (Standing : Engine(s) Run-up) 990899 The phase of flight after start-up, during which power is applied to engines, for a pre-flight engine performance test. Standing : Engine(s) Operating. (Standing : Engine(s) Operating) 10103 The phase of flight following engine start-up, or after post-flight arrival at the destination. Standing : Engine(s) Shut Down. (Standing : Engine(s) Shut Down) 10104 Engine shutdown is from the start of the shutdown sequence until the engine(s) cease rotation. Standing : Other. (Standing : Other) 10198 An event involving any standing phase of flight other than one of the above. Taxi. (Taxi) 10200 The phase of flight in which movement of an aircraft on the surface of an aerodrome under its own power occurs, excluding take- off and landing. -
An Investigation of Ctol Dual-Mode Pave Concepts
AN INVESTIGATION OF CTOL DUAL-MODE PAVE CONCEPTS by James F. Marchman, III, Nanyaporn Interatep, Eugene Skelton, and William H. Mason Aerospace and Ocean Engineering Department Virginia Tech, Blacksburg, VA A REPORT TO NASA - LANGLEY RESEARCH CENTER PERSONAL AIR VEHICLE EVALUATION PROJECT NASA GRANT NAG-1-01100 Virginia Tech AOE Report 276 January 2002 1 TABLE OF CONTENTS EXECUTIVE SUMMARY 3 INTRODUCTION 5 A Primary Roadability Consideration: 3 or 4 Wheels 9 SENSITIVITY AND CONSTRAINT ANALYSIS 10 PAVE Mission Requirements 10 Sensitivity Study 12 PAVE DESIGN RECOMMENDATION 13 Initial Weight Estimation for Redesigned Pegasus 14 Wing Design 14 Inboard Box-Wing/Winglet Concept 15 Outboard Wing Stowage Design 16 Outboard Wing Concepts 16 Lift Coefficient Calculation for the New Wing Concept 20 Power Selection 21 Pusher Propeller 22 Predicted Noise Calculation 24 Component Weight Analysis 25 Performance Estimates 26 ROADABILITY 27 CONCLUSIONS AND RECOMMENDATIONS 27 REFERENCES 29 FIGURES 30 - 38 APPENDIX A: Comparator Aircraft Performance and Sizing Data 39 APPENDIX B: Analysis of Comparator Aircraft 46 APPENDIX C: Roadability Evaluation from Reference 2 65 2 AN INVESTIGATION OF CTOL DUAL-MODE PAVE CONCEPTS by James F. Marchman, III, Nanyaporn Interatep, Eugene Skelton, and William H. Mason Aerospace and Ocean Engineering Department Virginia Tech, Blacksburg, VA EXECUTIVE SUMMARY A study was conducted to assess the feasibility of the dual-mode concept for a personal air vehicle, to determine how constraints differ between the dual-mode concept and a CTOL general aviation aircraft, to recommend a dual-mode vehicle concept, and to recommend areas where further research can contribute to the successful development of a viable PAVE vehicle design.