Data-Driven Modeling of Aircraft Engine Fuel Burn in Climb Out and Approach

2018 ◽  
Vol 2672 (29) ◽  
pp. 1-11 ◽  
Author(s):  
Yashovardhan S. Chati ◽  
Hamsa Balakrishnan
Keyword(s):  
Model Development ◽  
Gaussian Process Regression ◽  
Ground Truth ◽  
Aircraft Engine ◽  
Engine Fuel ◽  
Fuel Flow ◽  
Fuel Burn ◽  
Aircraft Performance ◽  
Aircraft Trajectory ◽  
Data Driven Modeling

Fuel burn is a key driver of aircraft performance, and contributes to airline costs and emissions. Low-altitude fuel burn and emissions, such as those that occur during climb out and approach, have a significant impact on the environment in the vicinity of airports. This paper proposes a new methodology to statistically model fuel burn in the climb out and approach phases using the trajectory of an aircraft. The model features are chosen by leveraging a physical understanding of aircraft and engine dynamics. Model development is conducted through the use of Gaussian Process Regression on a limited Flight Data Recorder archive, which also provides ground truth estimates of the fuel flow rate and total fuel burn. The result is a class of models that provide predictive distributions of the fuel burn corresponding to a given aircraft trajectory, thereby also quantifying the uncertainty in the predictions. The performance of the proposed models is compared with other frequently used Aircraft Performance Models. The statistical models are found to reduce the error in the estimated total fuel burn by more than 73% in climb out and by 59% in approach.

Empirical Method for Estimating Aircraft Fuel Consumption in Ground Operations

2020 ◽  
Vol 2674 (12) ◽  
pp. 385-394
Author(s):  
Han-Joong Kim ◽  
Hojong Baik
Keyword(s):  
Empirical Method ◽  
Civil Aviation ◽  
Flow Index ◽  
Trajectory Data ◽  
Time Duration ◽  
System A ◽  
Fuel Flow ◽  
Fuel Burn ◽  
Aircraft Fuel ◽  
Aircraft Trajectory

This study proposes a novel procedure for estimating aircraft fuel burn during ground operations using aircraft trajectory data acquired from an airport surface surveillance system. A fundamental assumption employed throughout the study is that aircraft fuel burn on the ground depends on taxi phases and corresponding thrust settings. The computational process is split into three steps: (1) define a taxi phase for each data point by analyzing the trajectory data; (2) find the fuel flow index appropriate for each taxi phase of each engine type from the International Civil Aviation Organization (ICAO) Engine Emissions Databank which contains fuel flow indices for four flight status of every commercial engine; and (3) estimate the total fuel burn on the ground for each flight by multiplying the time duration at each taxi phase by the corresponding fuel flow rate. Using 24-hour surface trajectory data collected from the Airport Surface Detection Equipment (ASDE) system at Seoul/Incheon International Airport, all flights operated on the day were analyzed applying this procedure. The results indicate that suggested taxi fuel burn rates are estimated to be about 17% lower than the ICAO values. The proposed procedure is expected to be used as an alternative method for ground fuel burn estimation.

scholarly journals Aircraft Engine Fuel Flow Prediction Using Process Neural Network

2014 ◽  
Vol 7 (3) ◽  
pp. 53-62 ◽  
Author(s):  
Yu Guangbin ◽  
Gang Ding ◽  
Lin Lin ◽  
Zhao Xingfu ◽  
Zhao Yang
Keyword(s):  
Neural Network ◽  
Aircraft Engine ◽  
Engine Fuel ◽  
Fuel Flow ◽  
Flow Prediction

The Engineering Doctorate — An ‘Enhanced’ Doctoral Programme for Engineers Incorporating Business Decision-Making Skills: A Gas-Turbine Engineering Perspective

2000 ◽  
Author(s):  
Paul C. Ivey ◽  
Michael L. Sanderson ◽  
Vivien Morris ◽  
Derek G. Ferguson
Keyword(s):  
Decision Making ◽  
Gas Turbine ◽  
Aircraft Engine ◽  
Product Launch ◽  
Engine Fuel ◽  
Design Development ◽  
Business Decision ◽  
Course Structure ◽  
Fuel Burn ◽  
The Uk

This paper describes a new UK initiative in the post graduate education of Engineers. The new ‘enhanced’ degree of Engineering Doctorate educates graduate Engineers in their respective technical disciplines whilst at the same time integrating the world of commerce and business into the technical decision making process. The paper describes the initial candidate selection methodology, project selection, course structure, assessment, thesis structure and outputs. The advantages of this enhanced postgraduate training are demonstrated, as are the objectives for the UK in adopting such a scheme. An example is presented from a joint Rolls Royce / Cranfield case study of the Design, Development and Product launch of a new type of Gas Turbine Instrumentation. This is set in a Gas Turbine Engineering perspective, in particular the consideration of active control of compressor surge to benefit aircraft engine fuel burn and increased flight range.

Fluidics in Aircraft Engine Controls

1981 ◽  
Vol 103 (4) ◽  
pp. 324-330 ◽  
Author(s):  
G. E. Davies
Keyword(s):  
Pressure Ratio ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Appropriate Technology ◽  
Engine Fuel ◽  
Engine Control System ◽  
Fuel Flow ◽  
Basic Engine ◽  
Wide Range ◽  
Compressor Inlet

Fluidics is a particularly appropriate technology for engine controls as it is capable of measuring pressure ratio, one of the basic engine performance parameters, as a fundamental quantity. This results in improved accuracy of measurement and obviates the need of conventional systems to utilize nonoptimum, but easier to measure, control parameters. A wide range of aircraft engine controls has been developed covering controls for compressor inlet guide vanes, compressor bleed valves, engine fuel flow including engine instrumentation. Total fluidic unit deliveries exceed 4200 and the civil operating hours exceed 13.5 million. As a further development, a completely fluidic engine control system is proposed with an electronic computer controlled secondary control or trim system for efficiency optimization.

scholarly journals Organic Rankine cycle for turboprop engine application

2021 ◽  
pp. 1-21
Author(s):  
G.E. Pateropoulos ◽  
T.G. Efstathiadis ◽  
A.I. Kalfas
Keyword(s):  
Waste Heat ◽  
Organic Rankine Cycle ◽  
Weight Ratio ◽  
Rankine Cycle ◽  
Aircraft Engine ◽  
Working Fluid ◽  
Engine Fuel ◽  
Exhaust Gases ◽  
Waste Heat Recovery System ◽  
Turboprop Engine

ABSTRACT The potential to recover waste heat from the exhaust gases of a turboprop engine and produce useful work through an Organic Rankine Cycle (ORC) is investigated. A thermodynamic analysis of the engine’s Brayton cycle is derived to determine the heat source available for exploitation. The aim is to use the aircraft engine fuel as the working fluid of the organic Rankine cycle in order to reduce the extra weight of the waste heat recovery system and keep the thrust-to-weight ratio as high as possible. A surrogate fuel with thermophysical properties similar to aviation gas turbine fuel is used for the ORC simulation. The evaporator design as well as the weight minimisation and safety of the suggested application are the most crucial aspects determining the feasibility of the proposed concept. The results show that there is potential in the exhaust gases to produce up to 50kW of power, corresponding to a 10.1% improvement of the overall thermal efficiency of the engine.

Flight performance monitoring with optimal filtering applications

2019 ◽  
Vol 124 (1272) ◽  
pp. 170-188
Author(s):  
V. A. Deo ◽  
F. Silvestre ◽  
M. Morales
Keyword(s):  
Kalman Filter ◽  
Performance Monitoring ◽  
The Body ◽  
Flight Performance ◽  
Performance Parameters ◽  
Sideslip Angle ◽  
Fuel Flow ◽  
Aircraft Performance ◽  
Lift And Drag

ABSTRACTThis work presents an alternative methodology for monitoring flight performance during airline operations using the available inboard instrumentation system. This method tries to reduce the disadvantages of the traditional specific range monitoring technique where instrumentation noise and cruise stabilisation conditions affect the quality of the performance monitoring results. The proposed method consists of using an unscented Kalman filter for aircraft performance identification using Newton’s flight dynamic equations in the body X, Y and Z axis. The use of the filtering technique reduces the effect of instrumentation and process noise, enhancing the reliability of the performance results. Besides the better quality of the monitoring process, using the proposed technique, additional results that are not possible to predict with the specific range method are identified during the filtering process. An example of these possible filtered results that show the advantages of this proposed methodology are the aircraft fuel flow offsets, as predicted in the specific range method, but also other important aircraft performance parameters as the aircraft lift and drag coefficients (CL and CD), sideslip angle (β) and wind speeds, giving the operator a deeper understanding of its aircraft operational status and the possibility to link the operational monitoring results to aircraft maintenance scheduling. This work brings a cruise stabilisation example where the selected performance monitoring parameters such as fuel flow factors, lift and drag bias, winds and sideslip angle are identified using only the inboard instrumentation such as the GPS/inertial sensors, a calibrated anemometric system and the angle-of-attack vanes relating each flight condition to a specific aircraft performance monitoring result. The results show that the proposed method captures the performance parameters by the use of the Kalman filter without the need of a strict stabilisation phase as it is recommended in the traditional specific range method, giving operators better flexibility when analysing and monitoring fleet performance.

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.

scholarly journals Multibody Kinematics Optimization for the Estimation of Upper and Lower Limb Human Joint Kinematics: A Systematized Methodological Review

2018 ◽  
Vol 140 (3) ◽  
Author(s):  
Mickaël Begon ◽  
Michael Skipper Andersen ◽  
Raphaël Dumas
Keyword(s):  
Degrees Of Freedom ◽  
Inertial Sensors ◽  
Model Development ◽  
Simulated Data ◽  
Ground Truth ◽  
Joint Kinematics ◽  
Sensitivity Analyses ◽  
Geometrical Parameters ◽  
Joint Models ◽  
Human Joint

Multibody kinematics optimization (MKO) aims to reduce soft tissue artefact (STA) and is a key step in musculoskeletal modeling. The objective of this review was to identify the numerical methods, their validation and performance for the estimation of the human joint kinematics using MKO. Seventy-four papers were extracted from a systematized search in five databases and cross-referencing. Model-derived kinematics were obtained using either constrained optimization or Kalman filtering to minimize the difference between measured (i.e., by skin markers, electromagnetic or inertial sensors) and model-derived positions and/or orientations. While hinge, universal, and spherical joints prevail, advanced models (e.g., parallel and four-bar mechanisms, elastic joint) have been introduced, mainly for the knee and shoulder joints. Models and methods were evaluated using: (i) simulated data based, however, on oversimplified STA and joint models; (ii) reconstruction residual errors, ranging from 4 mm to 40 mm; (iii) sensitivity analyses which highlighted the effect (up to 36 deg and 12 mm) of model geometrical parameters, joint models, and computational methods; (iv) comparison with other approaches (i.e., single body kinematics optimization and nonoptimized kinematics); (v) repeatability studies that showed low intra- and inter-observer variability; and (vi) validation against ground-truth bone kinematics (with errors between 1 deg and 22 deg for tibiofemoral rotations and between 3 deg and 10 deg for glenohumeral rotations). Moreover, MKO was applied to various movements (e.g., walking, running, arm elevation). Additional validations, especially for the upper limb, should be undertaken and we recommend a more systematic approach for the evaluation of MKO. In addition, further model development, scaling, and personalization methods are required to better estimate the secondary degrees-of-freedom (DoF).

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