In early 2001, the US Federal Aviation Administration embarked on a multi-year effort to develop a new computer model, the System for assessing Aviation’s Global Emissions (SAGE). Currently at Version 1.5, the basic use of the model has centered on the development of yearly global inventories of commercial aircraft fuel burn and emissions of various pollutants to serve as the basis for scenario modeling. This paper describes the algorithms and data used in the model as well as the results from initial validation assessments. SAGE results indicate that global fuel burn and nitrogen oxide (NOx) emissions decreased by over 6% from 2000 to 2001 (fuel burn and NOx), and then steadily increased to over 12% (fuel burn) and 15.5% (NOx) above 2000 levels in 2005. Comparisons to the results from previous studies have shown that SAGE tends to agree more closely with fuel burn and NOx than with CO and HC. Validation assessments have shown that SAGE can predict per flight fuel burn to within 3% on an average basis with no apparent bias, when compared to about 60,000 flight’s worth of data from a major US airline and about 20,000 flight’s worth of data from two major Japanese airlines.

System for assessing Aviation's Global Emissions (SAGE), Part 1: Model description and inventory results

Aircraft noise prediction

This paper provides an analysis of the BADA aircraft performance model capabilities and addresses the BADA model ability to provide accurate modeling of aircraft performances over the complete flight envelope for a number of aircraft types and different ways in which an aircraft can be operated during the flight. The focus of the paper is the support of complex aircraft operations by BADA. A short description of the two existing BADA families and their main characteristics is given. The complex flight instructions and operating regimes — economy climb, cruise and descent based on cost index, maximum range cruise, long range cruise, optimum altitude and maximum endurance cruise — identified as key features in support to optimized flight execution are discussed. The optimization procedures and equations in which they derive are presented and the ability of the BADA model to support these flight operations is demonstrated. It is shown that BADA 4 can be successfully used with complex instructions and operating regimes, whereas the use of BADA 3 is limited. Finally, the results of a validation experiment dedicated to BADA thrust models are presented.

Advanced aircraft performance modeling for ATM: Analysis of BADA model capabilities

This paper describes an optimisation study concerning arrival trajectories that has been conducted using a recently developed tool for the analysis and design of noise abatement procedures around airports. This new tool combines a noise model, a geographic information system, and a dynamic trajectory optimisation algorithm. The optimisation algorithm generates routings and flight-paths that minimise the noise impact in the residential communities surrounding the airport, while satisfying all imposed operational and safety constraints. The study on arrival trajectories presented herein complements an earlier study involving departure trajectories. Although the numerical results shown pertain to a particular example airport, viz Amsterdam Airport Schiphol, the study actually focuses on the development of a generic methodology that could be applied to any given airport. The results clearly demonstrate the effectiveness and flexibility of the developed tool.

Optimisation of noise abatement arrival trajectories

The impact of aircraft noise on health is of growing concern. We investigated the relationship between this exposure and mortality from cardiovascular disease, coronary heart disease, myocardial infarction, and stroke. We performed an ecological study on 161 communes (commune being the smallest administrative unit in France) close to the following three major French airports: Paris-Charles de Gaulle, Lyon Saint-Exupery, and Toulouse-Blagnac. The mortality data were provided by the French Center on Medical Causes of Death for the period 2007-2010. Based on the data provided by the French Civil Aviation Authority, a weighted average exposure to aircraft noise (L den AEI) was computed at the commune level. A Poisson regression model with commune-specific random intercepts, adjusted for potential confounding factors including air pollution, was used to investigate the association between mortality rates and L den AEI. Positive associations were observed between L den AEI and mortality from cardiovascular disease [adjusted mortality rate ratio (MRR) per 10 dB(A) increase in L den AEI = 1.18; 95% confidence interval (CI): 1.11-1.25], coronary heart disease [MRR = 1.24 (1.12-1.36)], and myocardial infarction [MRR = 1.28 (1.11-1.46]. Stroke mortality was more weakly associated with L den AEI [MRR = 1.08 (0.97-1.21]. These significant associations were not attenuated after the adjustment for air pollution. The present ecological study supports the hypothesis of an association between aircraft noise exposure and mortality from cardiovascular disease, coronary heart disease, and myocardial infarction. However, the potential for ecological bias and the possibility that this association could be due to residual confounding cannot be excluded.

Does exposure to aircraft noise increase the mortality from cardiovascular disease in the population living in the vicinity of airports? Results of an ecological study in France.

The Federal Aviation Administration, Office of Environment and Energy (FAA, AEE-100) has developed Version 7.0 of the Integrated Noise Model (INM) with support from the John A. Volpe National Transportation Systems Center, Acoustics Facility (Volpe Center) for development of the acoustic computation module, and from the ATAC Corporation for systems integration, development of the graphical interface, and methods for computing aircraft flight profiles and constructing flight paths, which are processed by the acoustics module. This Technical Manual describes the core technical components in INM Version 7.0, including the flight-path methodology (Chapter 2), along with the basic methodology employed by the INM to compute noise levels or time-based metrics at a single, user-specified observer, or at an evenly-spaced, regular grid of observers (Chapter 3). The noise/time computation methodology includes a description of: (1) computation of the flight-segment geometric and physical parameters; (2) flight-segment noise-level interpolation process; (3) atmospheric absorption adjustment; (4) acoustic impedance adjustment; (5) flight-segment noise-fraction adjustment for exposure-based metrics; (6) aircraft speed adjustment for exposure-based metrics; (7) updated lateral attenuation adjustment; (8) ground-based directivity adjustment for observers behind start-of-takeoff-roll, as well as for computing metrics associated with run-up operations; (9) new helicopter noise modeling capabilities and associated adjustments (including advancing tip mach number, lateral directivity, static directivity and static duration adjustments); (10) metric computation process; and (11) development of a recursively-subdivided irregular grid methodology, which is used for computing noise contours (Chapter 4).

https://rosap.ntl.bts.gov/view/dot/12188/dot_12188_DS1.pdf

Integrated Noise Model (INM) Version 7.0 Technical Manual

The Federal Aviation Administration, Office of Environment and Energy, Noise Division (FAA, AEE-100) has developed Version 7.0 of the Integrated Noise Model (INM) with support from the ATAC Corporation and the Department of Transportation Volpe National Transportation Systems Center. The FAA Integrated Noise Model is widely used by the civilian aviation community for evaluating aircraft noise impacts in the vicinity of airports. The model is typically used in the U.S. for FAR Part 150 noise compatibility planning, FAR Part 161 approval of airport noise restrictions, and for environmental assessments and environmental impact statements under the current version of FAA Order 1050.1E. New features in INM 7.0 include: lateral attenuation calculations based on SAE-AIR-5662; flight path segmentation, flight procedure step types, bank angle calculations, and thrust reverser implementation based on ECAC Doc 29; helicopter modeling methods based on Version 2.2 of FAA’s Heliport Noise Model (HNM); an HNM study import function; a scenario annualization function allowing operations to be adjusted after performing a run; a multi-threaded run mode; fixed-spacing contour grid functionality; increased differentiation between different type of aircraft (civil, military, and helicopter); the ability to input location values in lat/long or X/Y; and many extended database fields. INM Version 7.0 software runs on PCs using a minimum hardware configuration of a Pentium III processor, Microsoft Windows 2000 or XP operating systems, 1.0-Gb RAM, mouse input device, hard disk drive, and CD-ROM drive.

https://rosap.ntl.bts.gov/view/dot/12187/dot_12187_DS1.pdf

Integrated Noise Model (INM) Version 7.0 User's Guide

Community noise near airports is a major aviation noise concern, prompting the development of various modeling tools to predict the noise changes due to airport expansion and fleet changes. Once aircraft leave the terminal area and reach high altitudes, the aircraft noise received on the ground is assumed to be insignificant relative to urban ambient noise and is often neglected. However, this might not be the case, under either of the following conditions: (1) when aircraft fly over areas with very low ambient noise levels, such as in wildness areas, or (2) when an aircraft is powered by advanced propulsion systems that produces high noise levels. There is an increasing need to address both of these issues. Over the past 2 decades, some limited noise modeling capabilities and related research have begun to quantify the high‐altitude aircraft noise or “en‐route” noise. The purpose of this paper is to review and summarize related noise prediction research conducted through direct technical exchange with re...

Overview of aircraft en‐route noise prediction.

In this paper, the damage effectiveness of a single projectile of small caliber (30-35 mm) anti-aircraft gun under multi-error constraints is studied. Based on the known prior information of target motion and the dispersion mathematical model of prefabricated fragment warhead, under the constraints of fragment effective killing radius and target equivalent size, the fuze starting characteristic factor is introduced to establish the integrated model of fuze and warhead. Based on the Monte-Carlo method, the variation law of the damage effectiveness of a single projectile under the joint constraints of the gun firing angle error and the fuze fixed range error is analyzed. The simulated annealing (SA) algorithm is used to find the global optimal solution of the model. The optimal damage effectiveness of a single projectile under multi-error constraints is found. The results show that the damage effectiveness of single projectile is increased by 26.91% without changing the state of existing weapon and equipment.

/pdf/study-on-damage-effectiveness-of-single-projectile-of-small-1hc7b6cz.pdf

Bill He

Papers

Integrated Noise Model (INM) Version 7.0 Technical Manual

Integrated Noise Model (INM) Version 7.0 User's Guide

Overview of aircraft en‐route noise prediction.

Study on Damage Effectiveness of Single Projectile of Small Caliber Anti-aircraft Gun Under Multi-error Constraints