Fuel burn and emissions evaluation for a missed approach procedure performed by a B737-400

2013 ◽  
Author(s):  
Radu Dancila ◽  
Ruxandra M. Botez ◽  
Steven Ford
Keyword(s):  
Fuel Burn

scholarly journals THE FUTURE OF PASSENGER AIR TRANSPORT – VERY LARGE AIRCRAFT AND OUT KEY HUMAN FACTORS AFFECTING THE OPERATION AND SAFETY OF PASSENGER AIR TRANSPORT

2017 ◽  
Vol 12 ◽  
pp. 104
Author(s):  
Petra Skolilova
Keyword(s):  
Human Factors ◽  
Human Error ◽  
Operating Cost ◽  
Aircraft Design ◽  
Air Transport ◽  
Final Decision ◽  
Factors Affecting ◽  
Fuel Burn ◽  
The Future ◽  
The Impact

The article outlines some human factors affecting the operation and safety of passenger air transport given the massive increase in the use of the VLA. Decrease of the impact of the CO2 world emissions is one of the key goals for the new aircraft design. The main wave is going to reduce the burned fuel. Therefore, the eco-efficiency engines combined with reasonable economic operation of the aircraft are very important from an aviation perspective. The prediction for the year 2030 says that about 90% of people, which will use long-haul flights to fly between big cities. So, the A380 was designed exactly for this time period, with a focus on the right capacity, right operating cost and right fuel burn per seat. There is no aircraft today with better fuel burn combined with eco-efficiency per seat, than the A380. The very large aircrafts (VLAs) are the future of the commercial passenger aviation. Operating cost versus safety or CO2 emissions versus increasing automation inside the new generation aircraft. Almost 80% of the world aircraft accidents are caused by human error based on wrong action, reaction or final decision of pilots, the catastrophic failures of aircraft systems, or air traffic control errors are not so frequent. So, we are at the beginning of a new age in passenger aviation and the role of the human factor is more important than ever.

scholarly journals An estimation method for the fuel burn and other performance characteristics of civil transport aircraft during cruise: part 2, determining the aircraft’s characteristic parameters

2020 ◽  
Vol 125 (1284) ◽  
pp. 296-340
Author(s):  
D.I.A. Poll ◽  
U. Schumann
Keyword(s):  
Estimation Method ◽  
Accurate Method ◽  
Characteristic Parameters ◽  
Transport Aircraft ◽  
The Public ◽  
Engine Thrust ◽  
Fuel Burn ◽  
Burn Rate ◽  
Drag Ratio ◽  
Independent Parameters

ABSTRACTA simple yet physically comprehensive and accurate method for the estimation of the cruise fuel burn rate of turbofan powered transport aircraft operating in a general atmosphere was developed in part 1. The method is built on previously published work showing that suitable normalisation reduces the governing relations to a set of near-universal curves. However, to apply the method to a specific aircraft, values must be assigned to six independent parameters and the more accurate these values are the more accurate the estimates will be. Unfortunately, some of these parameters rarely appear in the public domain. Consequently, a scheme for their estimation is developed herein using basic aerodynamic theory and data correlations. In addition, the basic method is extended to provide estimates for cruise lift-to-drag ratio, engine thrust and engine overall efficiency. This step requires the introduction of two more independent parameters, increasing the total number from six to eight. An error estimate and sensitivity analysis indicates that, in the aircraft’s normal operating range and using the present results, estimates of fuel burn rate are expected to be in error by no more than 5% in the majority of cases. Initial estimates of the characteristic parameters have been generated for 53 aircraft types and engine combinations and a table is provided.

CAEP/9-agreed certification requirement for the Aeroplane CO2Emissions Standard: a comment on ICAO Cir 337

2016 ◽  
Vol 120 (1226) ◽  
pp. 693-723 ◽  
Author(s):  
J.E. Green ◽  
J.A. Jupp
Keyword(s):  
Fuel Efficiency ◽  
Scientific Basis ◽  
Civil Aviation ◽  
Aircraft Emissions ◽  
Current Form ◽  
Fuel Burn ◽  
Aircraft Fuel ◽  
Starting Point ◽  
Range Equation ◽  
Main Criticism

ABSTRACTThe International Civil Aviation Organization (ICAO) Circular Cir 337 is the first step towards ICAO establishing an Aeroplane CO2Emissions Standard to form part of Annex 16, Volume III to the Chicago Convention. It describes itself as ‘a work in progress’. This paper reviews Cir 337 against the background of flight physics, the published literature on aircraft fuel burn and CO2emissions and the current practices of the aircraft and engine manufacturers and the airline operators. We have taken, as our starting point, the aim of ICAO to reduce the fuel used per revenue tonne-kilometre performed and argue that the Breguet range equation, which captures all the relevant flight physics, should be the basis of the metric system underpinning the standard. Our overall conclusion is that Cir 337 provides an excellent basis for the initial regulation of aviation's CO2emissions and, further in the future, for developing measures to increase the fuel efficiency of the operational side of civil aviation. Our main criticism of the circular in its current form is that it does not address the ICAO goal of reducingfuel used per revenue tonne-kilometre performedand makes no reference to payload. This defect could be eliminated simply by omission of the exponent 0.24 of the Reference Geometric Factor (RGF) in the formula for the metric given in Chapter 2 (paragraph 2.2) of the circular. Retaining theRGFto the power unity in the metric and multiplying it by an appropriate value of the effective floor loading would convert it to what the 37thAssembly of ICAO called for – a statement of fuel used per revenue tonne-kilometre performed. Finally, correlating the amended metric against design range, as determined from the measured specific air range and the key certificated masses, provides a sound scientific basis for an initial regulation to cap passenger aircraft emissions.

scholarly journals Evaluation of the Climate Impact Reduction Potential of the Water-Enhanced Turbofan (WET) Concept

Aerospace ◽  
2021 ◽  
Vol 8 (3) ◽  
pp. 59
Author(s):  
Regina Pouzolz ◽  
Oliver Schmitz ◽  
Hermann Klingels
Keyword(s):  
Co2 Emissions ◽  
Aircraft Engine ◽  
Steam Injection ◽  
Climate Impact ◽  
Formation Mechanisms ◽  
Water Recovery ◽  
Impact Reduction ◽  
Fuel Burn ◽  
Starting Point ◽  
Reduction Of Co2

Aviation faces increasing pressure not only to reduce fuel burn, and; therefore, CO2 emissions, but also to provide technical solutions for an overall climate impact minimization. To combine both, a concept for the enhancement of an aircraft engine by steam injection with inflight water recovery is being developed. The so-called Water-Enhanced Turbofan (WET) concept promises a significant reduction of CO2 emissions, NOx emissions, and contrail formation. Representative missions for an A320-type aircraft using the proposed new engine were calculated. Applying a first-order one-dimensional climate assessment prospects the reduction of more than half of the Global Warming Potential over one hundred years, compared to an evolutionarily improved aero-engine. If CO2-neutrally produced sustainable aviation fuels are used, climate impact could be reduced by 93% compared to today’s aircraft. The evaluation is a first estimate of effects based on preliminary design studies and should provide a starting point for discussion in the scientific community, implying the need for research, especially on the formation mechanisms and radiation properties of potential contrails from the comparatively cold exhaust gases of the WET engine.

Ultra High Bypass Ratio Engine Sizing and Cycle Selection Study for a Subsonic Commercial Aircraft in the N+2 Timeframe

2011 ◽  
Author(s):  
Brian K. Kestner ◽  
Jeff S. Schutte ◽  
Jonathan C. Gladin ◽  
Dimitri N. Mavris
Keyword(s):  
Pressure Ratio ◽  
Important Variable ◽  
Direct Drive ◽  
Commercial Aircraft ◽  
Low Pressure Turbine ◽  
Fuel Burn ◽  
Technology Transition ◽  
Fundamental Research ◽  
Bypass Ratio ◽  
Engine Cycle

This paper presents an engine sizing and cycle selection study of ultra high bypass ratio engines applied to a subsonic commercial aircraft in the N+2 (2020) timeframe. NASA has created the Environmentally Responsible Aviation (ERA) project to serve as a technology transition bridge between fundamental research (TRL 1–4) and potential users (TRL 7). Specifically, ERA is focused on subsonic transport technologies that could reach TRL 6 by 2020 and are capable of integration into an advanced vehicle concept that simultaneously meets the ERA project metrics for noise, emissions, and fuel burn. An important variable in exploring the trade space is the selection of the optimal engine cycle for use on the advanced aircraft. In this paper, two specific ultra high bypass engine cycle options will be explored: advanced direct drive and geared turbofan. The advanced direct drive turbofan is an improved version of conventional turbofans. In terms of both bypass ratio and overall pressure ratio, the advanced direct turbofan benefits from improvements in aerodynamic design of its components, as well as material stress and temperature properties. By putting a gear between the fan and the low pressure turbine, a geared turbo fan allows both components to operate at optimal speeds, thus further improving overall cycle efficiency relative to a conventional turbofan. In this study, sensitivity of cycle design with level of technology will be explored, in terms of both cycle parameters (such as specific thrust consumption (TSFC) and bypass ratio) and aircraft mission parameters (such as fuel burn and noise). To demonstrate this sensitivity, engines will be sized for optimal performance on a 300 passenger class aircraft for a 2010 level technology tube and wing airframe, a N+2 level technology tube and wing air-frame, and finally on a N+2 level technology blended wing body airframe with and without boundary layer ingestion (BLI) engines.

Numerical calculation of fuel burn-up rate in a cylindrical nuclear reactor

2018 ◽  
Vol 319 (1) ◽  
pp. 459-470 ◽  
Author(s):  
Adebimpe Amos Amosun ◽  
Ayodeji Olalekan Salau ◽  
Olatomide Gbenga Fadodun ◽  
Mathew Ademola Jayeola ◽  
Taiwo Kemi Osanyin ◽  
...  
Keyword(s):  
Numerical Calculation ◽  
Nuclear Reactor ◽  
Fuel Burn

scholarly journals Skin-Spar Failure Detection of a Composite Winglet Using FBG Sensors

2017 ◽  
Vol 64 (3) ◽  
pp. 287-300 ◽  
Author(s):  
Monica Ciminello ◽  
Angelo De Fenza ◽  
Ignazio Dimino ◽  
Rosario Pecora
Keyword(s):  
Optical Fibers ◽  
Aerodynamic Drag ◽  
Structural Response ◽  
Failure Detection ◽  
Frequency Domain Analysis ◽  
Structural Failure ◽  
Fuel Burn ◽  
Bonding Failure ◽  
Short Time ◽  
Wing Tip

Abstract Winglets are introduced into modern aircraft to reduce wing aerodynamic drag and to consequently optimize the fuel burn per mission. In order to be aerodynamically effective, these devices are installed at the wing tip section; this wing region is generally characterized by relevant oscillations induced by flights maneuvers and gust. The present work is focused on the validation of a continuous monitoring system based on fiber Bragg grating sensors and frequency domain analysis to detect physical condition of a skin-spar bonding failure in a composite winglet for in-service purposes. Optical fibers are used as deformation sensors. Short Time Fast Fourier Transform (STFT) analysis is applied to analyze the occurrence of structural response deviations on the base of strain data. Obtained results showed high accuracy in estimating static and dynamic deformations and great potentials in detecting structural failure occurrences.

scholarly journals FLIGHT TRAJECTORIES COMPARISON IN THE BALTIC FAB / BALTIJOS FUNKCINIO ORO ERDVĖS BLOKO SKRYDŽIŲ TRAJEKTORIJŲ PALYGINIMAS

2018 ◽  
Vol 10 (0) ◽  
pp. 1-6
Author(s):  
Anrieta Dudoit ◽  
Jonas Stankūnas
Keyword(s):  
Service Providers ◽  
Great Circle ◽  
Flight Distance ◽  
Optimal Trajectories ◽  
Entry And Exit ◽  
Fuel Burn ◽  
The Us ◽  
Navigation Service ◽  
The Baltic ◽  
National Borders

Aviation is one of the types of transport which has a crucial role in the modern world and develops with unprecedent speed. As the number of flights tends to increase, the Air Traffic Management (ATM) system has to ensure the safety of these flights and effectiveness of them. The design and use of the European routes and use of the air route network are considered to be a major causal factor of flight inefficiencies in the continent. The present ATM system needs to be reorganised to satisfy airspace operator needs and maintain safety levels, because of the recent and future predicted traffic growth and not always satisfactory indicators of the efficiency of the ATM system.The airspace is currently fragmented along national borders that is why the efficiency of flights is not assured i.e. to perform flights along optimal trajectories avoiding delays, excessive fuel burn and emissions. One of the conditions for ATM system to be more effective is connection of the airspace blocks, into Functional Airspace Blocks (FAB), within which more efficient flight could be conducted based on more direct routes connecting entry and exit points of the FAB. According to the analysis on European and US ATM systems, where the European ATM system is the sum total of a large number of separate Air Navigation Service Providers (ANSP) whereas the US system is operated by a single ANSP, it was analysed and stated that the less fragmentation there is, the more efficient flights are.The focus of this paper is to show the differences between fixed routes and direct trajectories (Great Circle) in the Baltic FAB in terms of flight distance, fuel burn and emission. The airspace is currently fragmented along national borders that is why the efficiency of flights is not assured i.e. to perform flights along optimal trajectories avoiding delays, excessive fuel burn and emissions. One of the conditions for ATM system to be more effective is connection of the airspace blocks, into Functional Airspace Blocks (FAB), within which more efficient flight could be conducted based on more direct routes connecting entry and exit points of the FAB. According to the analysis on European and US ATM systems, where the European ATM system is the sum total of a large number of separate Air Navigation Service Providers (ANSP) whereas the US system is operated by a single ANSP, it was analysed and stated that the less fragmentation there is, the more efficient flights are. The focus of this paper is to show the differences between fixed routes and direct trajectories (Great Circle) in the Baltic FAB in terms of flight distance, fuel burn and emission. Santrauka Aviacija – viena iš greitai augančių transporto šakų, kuri yra svarbi šiuolaikiniame moderniajame pasaulyje. Kadangi skrydžių nuolatos daugėja, oro eismo valdymo (OEV) sistema turi užtikrinti skrydžių saugą ir efektyvumą. Europos oro maršrutų išdėstymas ir naudojimas laikomi svarbiausiais skrydžių neefektyvumo veiksniais žemyne. Dėl esamo ir numatomo oro eismo augimo ir ne visados patenkinamų OEV sistemos efektyvumo rodiklių esama OEV sistema turi būti reorganizuota, siekiant užtikrinti oro erdvės naudotojų poreikius ir palaikyti reikalingą saugos lygį.Šiuo metu oro erdvė yra sudalyta pagal kiekvienos šalies valstybines ribas, dėl to skrydžių efektyvumas nėra optimalus, t. y. atliekami skrydžiai nevykdomi pagal optimalias trajektorijas vengiant užlaikymų, mažinant naudojamo kuro sąnaudas ir emisijas. Viena sąlyga, siekiant OEV sistemą padaryti efektyvesnę, – sujungti oro erdvės blokus į funkcinius oro erdvės blokus (FOEB), kur skrydžiai būtų vykdomi tiesesniais maršrutais tarp įskridimo ir išskridimo į FOEB taškų.Atlikus Europos OEV ir JAV sistemų analizę matyti, kad Europos OEV sistema susideda iš daugybės atskirtų oro navigacijos paslaugų teikėjų, o JAV sistemą valdo vienas oro navigacijos paslaugų teikėjas. Konstatuota, kad ten, kur fragmentacija mažesnė, skrydžių efektyvumas didesnis.Straipsnio tikslas – parodyti skirtumus tarp fiksuotųjų ir laisvųjų maršrutų Baltijos funkciniame oro erdvės bloke skrydžių atstumo, sunaudojamo kuro ir emisijų faktoriais.

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