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Enhancing Factory Modelling: Integrating Drone Technology and Automated Post Processing Systems2026-26-0307To be published on 01/16/2026
The growing environmental, economic, and social challenges have spurred a demand for cleaner mobility solutions. In response to the transformative changes in the automotive sector, manufacturers must prioritize digital validation of products, manufacturing processes, and tools prior to mass production. This ensures efficiency, accuracy, and cost-effectiveness. By utilizing 3D modeling of factory layouts, factory planners can digitally validate production line changes, substantially reducing costs when introducing new products. One key innovation involves creating 3D models using point cloud data from factory scans. Traditional factory scanning processes face limitations like blind spots and periodic scanning intervals. This research proposes using drones equipped with LiDAR (Light Detection and Ranging) technology for 3D scanning, enabling real-time mapping, autonomous operation, and efficient data collection. Drones can navigate complex areas, access small spaces, and optimize factory
Narad, Akshay Maruti, C H, Ajheyasimha, Vijayasekaran, Vinothkumar, FASGE, ABHISHEK
AIR120425-1AIR120425-1 (Current)12/04/2025
AIR120425-1
A-10 Aircraft Oxygen Equipment Committee
Measurement of Exterior Noise Produced by Aircraft Auxiliary Power Units (APUs) and Associated Aircraft Systems During Ground OperationARP1307C (Current)11/26/2025
Test procedures are described for measuring noise at specific receiver locations (passenger and cargo doors, and servicing positions) and for conducting general noise surveys around aircraft. Procedures are also described for measuring noise level and directivity at noise source locations to facilitate the understanding and interpretation of the data. Requirements are identified with respect to instrumentation; acoustic and atmospheric environment; data acquisition, reduction and presentation, and such other information as is needed for reporting the results. This document makes no provision for predicting APU or component noise from basic engine characteristics or design parameters, nor for measuring noise of more than one aircraft operating at the same time. No attempt is made to suggest acceptable levels of noise or suitable subjective criteria for judging acceptability. ICAO Annex 16 Volume I Attachment C provides guidance on recommended maximum noise levels.
A-21 Aircraft Noise Measurement Aviation Emission Modeling
Nitrogen Absorption/Desorption (Gas Dissolution) in Aircraft Shock AbsorbersAIR6942 (Current)11/26/2025
This document outlines the current state of the art in the understanding of gas in solution in shock absorber oils in unseperated shock absorbers. A literature review, overview of Henry's law, Henry's law coefficients for known gas and oil couples, in-service operational problems, lessons learned, and potential future work will be discussed in the document.
A-5B Gears, Struts and Couplings CommitteeNEW
Development and Qualification of Composite Landing GearsAIR5552A (Current)11/26/2025
This information report provides general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering: the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107(B).
A-5B Gears, Struts and Couplings CommitteeNEW
LED Landing, Taxiing, Runway Turnoff, and Recognition LightsARP6402B (Current)11/26/2025
This document includes recommendations of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a. Single engine personal and/or liaison type b. Light twin engine c. Large multiengine propeller d. Large multiengine turbojet e. Military high performance fighter and attack f. Helicopter which are subject to the following CFR Parts certification: Part 23 – Airworthiness Standards: Normal, Utility, Acrobatic and Commuter Aircrafts Part 25 – Airworthiness Standards: Transport Category Aircrafts Part 27 – Airworthiness Standards: Normal Category Rotorcraft Part 29 – Airworthiness Standards: Transport Category Rotorcraft
A-20B Exterior Lighting Committee
Environment Spectra and Corrosivity Monitoring Using Electrochemical and Electrical Resistance SensorsAIR6970 (Current)11/26/2025
This Aerospace Informational Report (AIR) provides guidance on using environmental, electrochemical, and electrical resistance measurements to monitor environment spectra and corrosivity of service environments, focusing on parameters of interest, existing measurement platforms, deployment requirements, and data processing techniques. The sensors and monitoring systems provide discrete time-based records of 1) environmental parameters such as temperature, humidity, and contaminants; 2) measures of alloy corrosion in the sensor; and 3) protective coating performance in the sensor. These systems provide measurements of environmental parameters, sensor material corrosion rate, and sensor coating condition for use in assessing the risk of atmospheric corrosion of the structure. Time-based records of environment spectra and corrosivity can help determine the likelihood of corrosion to assess the risk of corrosion damage of the host structure for managed assets, aiding in establishing
HM-1 Integrated Vehicle Health Management Committee
A Review of Literature on the Relationship Between Gas Turbine Engine Lubricants and Aircraft Cabin Air QualityAIR5784A (Current)11/26/2025
There has been a recent upsurge in interest from the media concerning the quality of the environment within aircraft cabins and cockpits especially in the commercial world. This has included (although by no means been limited to) the air quality, with particular reference to the alleged effects of contamination from the aircraft turbine lubricant. Possible exposure to 'organophosphates' (OPs) from the oil has raised special concerns from cabin crew. Such is the concern that government organisations around the world, including Australia, USA and UK, have set up committees to investigate the cabin air quality issue. Concern was also voiced in the aviation lubricants world at the way in which OP additives in turbine lubricants were being blamed in some reports for the symptoms being experienced by air crew and passengers. SAE Committee E-34 therefore decided that it should gather as much available information on the subject as possible. This would then enable E-34 to participate in
E-34 Propulsion Lubricants Committee
Aircraft Lightning Test MethodsARP5416B (Current)11/26/2025
This document is one of a set covering the whole spectrum of aircraft interaction with lightning. This document is intended to describe how to conduct lightning direct effects tests and indirect system upset effects tests. Indirect effects upset and damage tolerance tests for individual equipment items are addressed in DO-160/ED-14. Documents relating to other aspects of the certification process, including definition of the lightning environment, zoning, and indirect effects certification are listed in Section 2. This document presents test techniques for simulated lightning testing of aircraft and the associated systems. This document does not include design criteria nor does it specify which items should or should not be tested. Acceptable levels of damage and/or pass/fail criteria for the qualification tests must be approved by the cognizant certification authority for each particular case. When lightning tests are a part of a certification plan, the test methods described herein
AE-2 Lightning Committee
Fuel Flowmeters and IndicatorsAS407E (Current)11/26/2025
To specify minimum requirements for Fuel Flowmeters for use primarily in reciprocating engine powered civil transport aircraft, the operation of which may subject the instruments to the environmental conditions specified in Section 3.3. This Aeronautical Standard covers two basic types of instruments, or combinations thereof, intended for use in indicating fuel consumption of aircraft engines as follows: TYPE I - Measure rate of flow of fuel used. TYPE II - Totalize amount of fuel consumed or remaining.
AS407 Fuel Flowmeters
Performance based packaging standard for lithium batteries as cargo on aircraftAS6413 (Current)11/26/2025
This standard is intended to demonstrate and document the control of the potential hazards from lithium cells or batteries (UN 3090 and 3480) when transported as cargo on aircraft. [still need to identify if we are addressing global (external fire) or local (battery internal failures)] This standard addresses the need to control the hazards which might arise from a failure from an individual cell by containing the hazards within the package. This specific hazards addressed within this standard are: • Uncontrolled fire • Rapid overpressure pulse within compartment
G-27 Lithium Battery Packaging Performance
Guidelines for the Integration of Electronic Engine Control Systems for Transport Category (Part 25) and General Aviation (Part 23) AircraftAIR5924B (Current)11/26/2025
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general aviation, regional and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word “engine” is used to designate the aircraft propulsion system. The engine station designations used in this report are shown in Figure 1. Most of the material concerns an Electronic Engine Control (EEC) with its associated software, and its functional integration with the aircraft. However, the report also addresses the physical environment associated with the EEC and its associated wiring and sensors. Since most of today’s transport category
E-36 Electronic Engine Controls Committee
Standardized composite training programAIR6671 (Current)11/26/2025
SAE CACRC has produced several standards, each representing the best-practice, recommended minimum training syllabus for the aforementioned target groups. The purpose of this document is to promote the use of these SAE standards, particularly for developing training programs for employee training, qualification in airlines and maintenance organizations, and as reference in regulatory guidance material. It summarizes, as a quick reference, the content of each training document and its relation to and interaction with other training documents. Thereby it allows users to select the appropriate training documents and syllabi to establish a comprehensive, sequential training program build-up customized to the specific needs of the aforementioned functions (see figure). This document does not intend to introduce new training content/syllabus.
AMS CACRC Commercial Aircraft Composite Repair Committee
Water Spray and High Humidity Endurance Test Methods for AMS1424 and AMS1428 Aircraft Deicing/Anti-Icing FluidsAS5901E (Current)11/26/2025
This document establishes the minimum requirements for an environmental test chamber, and test procedures to carry out anti-icing performance tests according to the current materials specification for aircraft deicing/anti-icing fluids. The primary purpose for such a test method is to determine the anti icing endurance under controlled laboratory conditions of AMS1424 Type I and AMS1428 Type II, III, and IV fluids.
G-12ADF Aircraft Deicing Fluids
Aerospace - Test Methodology for Electrohydrostatic ActuatorsARP5879A (Current)11/26/2025
This document provides an overview of the tests and issues related to testing that are unique to Electrohydrostatic Actuators (EHAs). An EHA incorporates a linear or rotary hydraulic actuator and a variable speed, reversible electric servomotor driving a fixed displacement hydraulic pump for actuator control, and associated power drive electronics. The tests and issues documented are not necessarily all-inclusive. This document discusses both, the tests applicable to EHAs and the test methodologies to accomplish the test objectives. This document also lists tests that are not unique to EHAs, but are still applicable to EHAs. In these instances a discussion of such tests is not contained in this document, and as applicable, the reader may reference ARP1281 (Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For), which addresses test issues applicable to electrohydraulic flight control servoactuators. In the discussion of the tests and test
A-6B2 Electrohydrostatic Actuation Committee
Electrohydrostatic Actuation Applications on Aircraft ProgramsAIR6353 (Current)11/26/2025
This document will maintain a listing of all current and new EHA/EBHA aircraft applications, including parameters such as power, force, rate, etc, as is permissible for public offering.
A-6B2 Electrohydrostatic Actuation Committee
Guidelines for Specifying LVDTs and RVDTsARP5554 (Current)11/26/2025
As per Committee/Henry E. Harschburger recommendations
A-6B1 Hydraulic Servo Actuation Committee
Aerospace - Lightning Effects on Hydraulic Transport Elements on AircraftAIR6185A (Current)11/26/2025
<p>This SAE Aerospace Information Report (AIR) describes hydraulic system design and installation to minimize the effects of lightning, especially when the aircraft structure is composite. Techniques for effective electrical bonding, hydraulic system lightning protection, and lightning protection verification techniques are discussed.</p>
My new committee for commercial aircrafts
Verifying large alternate product code for an AIR document - AIR112425-1AIR1124250000000000000000/NEW1--1 (Current)11/24/2025
Verifying large alternate product code for an AIR document
A-10 Aircraft Oxygen Equipment Committee
Arresting Hook Installation, Land-Based AircraftARP1538C (Current)11/11/2025
This SAE Aerospace Recommended Practice (ARP) covers the recommended criteria and performance requirements for the design and installation of land-based aircraft emergency and operational arresting hooks for use on runway arresting systems. Design criteria for fully operational hooks and for carrier-based aircraft hook installations are contained in specification MIL-A-18717.
A-5B Gears, Struts and Couplings CommitteeNEW
Extraordinary and Special Purpose Landing Gear SystemsAIR4846B (Current)11/11/2025
A landing gear system comprises the most compelling assembly of engineering skills. Its importance to the successful design of an aircraft can be favorably compared with that of the aircraft's wings and engines. A landing gear system consists of several different engineering disciplines, and is continually in the public eye especially with regard to safety. The primary objective of AIR4846 is to present a record of a variety of interesting gears, gear/aircraft systems and patents, and to discuss wherever possible the lessons learned, and the reasons for the design. Thus, the document is not only a historical account, but a means of recording technical knowledge for the practical benefit of future landing gear designers. Commendable efforts have been made over the years by several individuals to make such recordings, and AIR4846 will make continual reference to them. This applies to all books, papers, or specifications that have the approval of the SAE A 5 Committee. AIR4846 also
A-5B Gears, Struts and Couplings CommitteeNEW
Landing Gear Component Heat DamageAIR5913B (Current)11/11/2025
The purpose of this report is to outline types of in-service heat damage that have been observed in high strength steel landing gear components, with an emphasis on a particular type that is referred to as “Ladder Cracking” which can develop in landing gear shock struts. The report discusses how ladder cracking can be detected visually and evaluated by non-destructive inspection methods, and how it can be repaired at overhaul with the prior approval of the Original Equipment Manufacturer. This report also describes the use of a bearing material that has resolved this problem without introducing other problems. Examples of other types of service induced heat damage are also discussed.
A-5B Gears, Struts and Couplings CommitteeNEW
Sponsor ChjangeARP050911 (Current)10/13/2025
Test
A-6A Systems Subsystem Integration Steering Group
Minimum Standard for Portable Gaseous, Oxygen EquipmentAS1046D (Current)09/29/2025
This standard is intended to apply to portable compressed gaseous oxygen equipment. When properly configured, this equipment is used either for the administration of supplemental oxygen, first aid oxygen or smoke protection to one or more occupants of either private or commercial transport aircraft.
A-10 Aircraft Oxygen Equipment Committee
SAE TOMORROW TODAY - Women Breaking Barriers in Aerospace & Beyond1352107/01/2025
Despite decades of progress, the number of women in engineering remains stubbornly low -- especially in aerospace and mechanical engineering. But that isn't stopping the winner of the Aerospace/Defense category in the inaugural Women in Engineering: Rising Star Awards. Heather Cummings is Senior Engineer, Flight Controls & Autonomy for Sikorsky, a Lockheed Martin company. She leads the development of hybrid electric propulsion controls and vehicle management systems for Sikorsky's next-gen HEX and RBW, including groundbreaking work on fully autonomous cargo aircraft. A licensed pilot, Heather is passionate about improving flight safety through automation and mentoring the next generation of aspiring engineers. In this special episode, Heather and Chitra Sethi, Director of Editorial & Digital Content, SAE Media Group, discuss the mission behind the Rising Star Awards, the importance of visibility for women in STEM, and why inspiring the next generation is just as critical as
Hineman, Marcie
Basic Science and Art of Aircraft Wreckage ReconstructionR-48004/23/2025
Basic Science and Art of Aircraft Wreckage Reconstruction is a unique title which addresses important aspects of investigating crashes, who does this kind of work, and how a healthy attitude and open mind are required to properly perform investigations. It also discusses what to expect from the on-scene part of the investigation, and the fundamental approaches to common types of wreckage reconstruction. Written by Don Knutson, a veteran of this industry, Basic Science and Art of Aircraft Wreckage Reconstruction is intended for the practitioner, student, or those who are simply curious about how aircraft wreckage is reconstructed. Full references are provided in the various chapters for additional reading and research. Many examples of aircraft crash scenarios and circumstances are presented in a "generic" form but relate to actual investigations, which should prove as a useful investigative resource whether you are an apprentice or an experience professional with a government aviation
Knutson, Donald F.
EDITORIAL: Farewell and thanks, Mr. Birch21AUTP06_0401/27/2025
“We pay close attention to the SAE magazines because your guy in Europe writes interesting articles,” a BMW engineering executive told me one year at the Frankfurt Motor Show. He was referring to Stuart Birch, our veteran European Editor, who has recently decided - after nearly 37 years of outstanding reporting for SAE International - to hang up his keyboard and spend more time with his wife, Kim, their family and friends in the British countryside, and his classic Porsche 911. Our staff had been dreading the day that Stuart would announce his retirement, foremost because he's been a great friend as well as a colleague. And because journalists with his qualities - professionalism, perspective, a powerful work ethic and great wit - are increasingly rare in the mobility-technology space. As SAE's global audience knew, Stuart Birch delivered compelling technical and business information. He covered product, processes and people with equal poise. And he thrived on the R&D beat: Virtual
Brooke, Lindsay
SAE TOMORROW TODAY: Reshaping Air Freight with Blended Wing Body Design1349401/06/2025
For more than 60 years, the air freight industry has adapted passenger aircraft for cargo fleets resulting in limited capacity and diminished fuel efficiency. However, a long-overdue shift toward a volume-optimized blended wing body (BWB) design is enabling freight aircrafts to carry 40-50% more in cargo capacity per trip while also reducing greenhouse gas emissions. Leading the way is Natilus, a company that develops hyper-efficient cargo and passenger BWB aircraft that dramatically improve aerodynamic efficiency and provide a powerful increase in internal volume. The result? Less fuel burn, lower emissions, higher payloads, and lower operating costs. To learn more, we sat down with Aleksey Matyushev, CEO and Co-Founder, to discuss how Natilus' next-generation BWB aircraft design can improve economic efficiency and sustainability, as well as the company's foray into the passenger aircraft space. We'd love to hear from you. Share your comments, questions and ideas for future topics and
Hineman, Marcie
Cat’s Eye-Inspired Vision System for Autonomous RoboticsTBMG-5218012/01/2024
Researchers led by Professor Young Min Song from the Gwangju Institute of Science and Technology (GIST) have unveiled a vision system inspired by feline eyes to enhance object detection in various lighting conditions. Featuring a unique shape and reflective surface, the system reduces glare in bright environments and boosts sensitivity in low-light scenarios. By filtering unnecessary details, this technology significantly improves the performance of single-lens cameras, representing a notable advancement in robotic vision capabilities.
Acquiring and Telemetering Test Data from Hypersonic PlatformsTBMG-5212012/01/2024
AI-Trained Vehicles Can Adjust to Extreme Turbulence on the FlyTBMG-5212512/01/2024
In nature, flying animals sense coming changes in their surroundings, including the onset of sudden turbulence, and quickly adjust to stay safe. Engineers who design aircraft would like to give their vehicles the same ability to predict incoming disturbances and respond appropriately. Indeed, disasters such as the fatal Singapore Airlines flight this past May in which more than 100 passengers were injured after the plane encountered severe turbulence, could be avoided if aircraft had such automatic sensing and prediction capabilities combined with mechanisms to stabilize the vehicle.
What is Drone Jamming and How Can it Be Countered?TBMG-5212412/01/2024
Deliberate RF jamming of drones has become one of the most common battlefield tactics in Ukraine. But what is jamming, how does it work and how can it be countered by unmanned aerial vehicles (UAVs) in the field?
DC-DC Converters for High Reliability eVTOL Auxiliary Power SystemsTBMG-5214712/01/2024
EVOLUTION OF 360 DEGREE LOCAL SITUATIONAL AWARENESS (LSA) TO AID THE WARFIGHTER2024-01-345111/15/2024
ABSTRACT Northrop Grumman has developed a software and hardware solution to provide enhanced 360 degree local situational awareness (LSA) to enable the warfighter with an overmatch capability on today’s modern battlefield. The architecture exploits technological gains in cameras, video processing, and video compression. The approach allows rapid comprehension of local and remote situational views presented with operational relevance for a ground combat platform or tactical wheeled platform crew. The 360 Degree LSA approach provides direct visualization of relative positioning of targets, threats, and lines of fire; and additionally offers common situational understanding / operational picture from the dismounted soldier to higher echelon commands. The approach provides prioritized information through LSA software to provide an enhanced view to the warfighter whereas the squad leader becomes an integral part of the crew with a view of the common operating picture (mounted) and
Viscovich, Christopher, Geoghegan, Susan, Worthy, David
400Hz High Speed Static Transfer Switch2008-01-287711/11/2024
The objective of this project was to replace electromechanical power line contactors with a Static Transfer Switch (STS) to improve the transfer of electrical power between aircraft generators and decrease required maintenance. The switch requirements include high reliability, lightweight, and high speed (less than 15mS) power transfer. An STS can shorten the bus transfer time to less than the “ride-through” of aircraft electronic loads and therefore have the ability to control and transfer electrical power while maintaining critical mission requirements. The content of this paper and presentation will discuss the initial problem, the research and development approach, design, and initial testing of the STS.
Cooper, Ronald C., Cooper, Evan C.
Data Dictionary for Quantities Used in Cyber Physical Systems (Enhanced License)AS6969_DA (Current)07/29/2024
Enhanced License for Data Dictionary for Quantities Used in Cyber Physical Systems (AS6969) allowing for greater usage as outlined in the terms of the Enhanced License. Terms can be reviewed prior to purchase once item is added to the cart. Data Dictionary for Quantities Used in Cyber Physical Systems (AS6969) This data dictionary provides a mathematically coherent set of definitions for quantity types used in data models for unmanned systems. In this data dictionary, a quantity is defined as a property of a phenomenon, substance, or body whose value has magnitude.
AS-4UCS Unmanned Systems Control Segment Architecture
SAE TOMORROW TODAY: Has Amelia Earhart's Aircraft Been Found?1346106/21/2024
Sonar data from a deep sea drone recently shed light on one of aviation's most enduring mysteries: the disappearance of Amelia Earhart. By pursuing the missing aircraft using the "Date Line theory," Deep Sea Vision, a South Carolina-based marine robotics firm, searched across 5,200 square miles of the Pacific Ocean floor, more than all previous searches combined. Equipped with a modified version of the company's flagship HUGIN 6000 commercial autonomous underwater vehicle (AUV), the DSV team discovered an image which mirrors the unique dual tails and scale of Earhart's aircraft. To learn more about this intriguing technology and what's next when it comes to verifying this discovery, we sat down with Tony Romeo, CEO, Deep Sea Vision. Listen in as he shares his unique background, the power of his company's AUV technology, and what's next for the future of underwater exploration.
Hineman, Marcie
Longitudinal Air-Breathing Hypersonic Vehicle Nonlinear Dynamic Simulation with Different Control Inputs01-17-02-001503/04/2024
The air-breathing hypersonic vehicle (AHV) holds the potential to revolutionize global travel, enabling rapid transportation to low-Earth orbit and even space within the next few decades. This study focuses on investigating the nonlinear dynamic simulation, trim, and stability analysis of a three-degrees-of-freedom (3DOF) longitudinal model of a generic AHV for variable control surface deflection,and. A simulation is developed to analyze the burstiness of the AHV’s nonlinear longitudinal behavior, considering the complete flight envelope across a wide range of Mach numbers, from= 0 to 24, for selected stable. The presented simulation assesses trim analysis and explores the dynamic stability of the AHV through its flight envelope and bifurcation method analysis is carried out to gain insight and validate the dynamic stability using eigen value approach.
Singh, Ritesh, Prakash, Om, Joshi, Sudhir, Sharma, Rakesh Chandmal
Designing an Uncrewed Aircraft Systems Control Model for an Air-to-Ground Collaborative System01-17-02-001402/19/2024
Abstract In autonomous technology, uncrewed aircraft systems have already become the preferred platform for the research and development of flight control systems. Although they are subjected to following and satisfying complicated scenarios of control stations, this high dependency on a specific control framework limits them in their application process and reduces the flight self-organizing network. In this article, we present a developed multilayer control system protocol with the additional supportive manned aircraft layer (Tender). The novelty of the introduced model is that uncrewed aircraft systems are monitored and navigated by the tender, and then based on the suggested scheme, data flows are controlled and transferred across the network by the developed cloud–robotics approach in the ground station layer. Therefore, it has been tried to design a semi-autonomous control network to gather data that combines human observation and the automotive nature of uncrewed aircraft
Millar, Richard C., Laliberté, Jeremy, Mahmoodi, Armin, Hashemi, Leila, Meyer, Robert Walter
Computational Investigation of a Flexible Airframe Taxiing Over an Uneven Runway for Aircraft Vibration Testing01-17-02-001112/15/2023
Ground vibration testing (GVT) is an important phase of the development, or the structural modification of an aircraft program. The modes of vibration and their associated parameters extracted from the GVT are used to modify the structural model of the aircraft to make more reliable dynamics predictions to satisfy certification authorities. Due to the high cost and the extensive preparations for such tests, a new method of vibration testing called taxi vibration testing (TVT) rooted in operational modal analysis (OMA) was recently proposed and investigated by the German Institute for Aerospace Research (DLR) as alternative to conventional GVT. In this investigation, a computational framework based on fully coupled flexible multibody dynamics for TVT is presented to further investigate the applicability of the TVT to flexible airframes. The time domain decomposition (TDD) method for OMA was used to postprocess the response of the airframe during a TVT. The framework was then used to
Al-bess, Lohay, Khouli, Fidel
Nonlinear Observer for Estimating Gravity Vector and Flight Path Angles of a High-Performance Aircraft01-17-01-000708/14/2023
This paper proposes a nonlinear observer for the estimation of gravity vector and angles with respect to velocity vector (flight path angle, bank angle) of a high-performance aircraft. The technique is computationally simpler than the extended Kalman filter (EKF) and hence is suitable for onboard implementations when the digital flight control computer (DFCC) has computational burdens. Flight test data of a highly maneuvering flight such as wind-up turns and full rolls have been used to validate the technique.
Chandrasekaran, Kamali, Jain, Shikha
Sonic Boom Velocity and Altitude Sensitivity Analysis of a Hypersonic Aircraft Concept2025-01-003505/05/2023
During the last decades there has been a renewed interest in the development of a new generation of supersonic aircraft for civil purposes. However, the noise generated by supersonic aircraft during supersonic flight, commonly referred to as "sonic boom", is still creates annoyance to community on the ground that prohibits supersonic overland flight. To prepare for the advent of a new generation of supersonic aircraft and to define new regulations for them, an increasing number of sonic boom studies is being published. This paper presents numerical simulations of the sonic boom of a hypersonic (Mach 5) aircraft concept. The study describes a sensitivity analysis of the two parameters velocity and altitude. The extensive simulations characterize the sonic boom carpet of the aircraft for different speeds between Mach 1.2 and Mach 5.0, and for two altitudes of 11.3 km and 28.0 km above sea level. The simulation approach is divided into two main regions. This approach is well understood
Graziani, Samuele, Jäschke, Jacob Jens, Viola, Nicole, Gollnick, Volker
NOISE ANALYSIS IN DIFFERENT FLAPPING MECHANISMS FOR EFFICIENT FLYING2025-01-002105/05/2023
In a variety of intricate and dynamic settings, flying animals, like birds and insects [5],[8], can fly with efficiency. Despite being stated as "unsteady aerodynamics", the flapping of birds was the first biological mechanism that inspired humans to fly. Though flapping wings is the most efficient way of flying, the main hindrance is its unsteady nature of gaining a counter-lift for each flap. Compared to current manned aerial vehicles, flying animals fly at a lower Reynolds number. A fluid's ratio of viscous to inertial forces is represented by the Reynolds number, which is a dimensionless quantity. The ratio of forward speed to flapping frequency is represented by the dimensionless number known as the decreased frequency. Yet, by utilizing these beneficial animal flying traits, unmanned aerial vehicles (UAVs) functioning in the low Reynolds number zone can be enhanced. The primary aim of this project is to analyze two flapping mechanisms: straight continuous wing and swept & bent
Keshav Kumar, A B, Patric, Alan, R, Asad Ahmed, Srinivasan, Venkatramanan, Mani, Midhun, Jayachandran, Rohith
Research on Clustered Multi-channel Active Noise Control System in Car2025-01-001605/05/2023
In order to solve the problem of intermittent engine intervention during charging and discharging of diesel-electric hybrid vehicles, this paper proposes a semi-coupled cluster control strategy with better comprehensive performance based on the traditional multi-channel Active Noise Control (ANC) system and the advantages of centralized control strategy and decentralized control strategy. Compared with the centralized control strategy, the computational cost of the cluster control strategy is reduced by about 50%, and the noise attenuation performance is comparable to that of the centralized control strategy. Compared with the decentralized control strategy, the stability is obviously better, and the noise reduction effect is outstanding. Based on the MATLAB simulation platform, a variety of cluster control strategies and traditional control strategies in the vehicle are compared and analyzed, and the road test experiments of a range-extended electric vehicle are carried out under its
deng, huiping, Lu, Chihua, Liu, Zhien, Ji, Huijun, Dou, Sirui, Sun, Menglei
Indirect blocked force measurement of a hydraulic power pack for structural vibration transmission into an airframe2025-01-005205/05/2023
Centralization of electrically driven hydraulic power packs into the body of aircraft have increased the attention on the noise and vibration characteristics of the system. A hydraulic power pack consists of a pump coupled to an electrical motor, accumulator, reservoir, and associated filter manifolds. In previous studies, the characteristics of the radiated acoustic noise and fluid borne noise were studied. In this paper, we focus on the structure borne forces generated by the hydraulic pump characterized through blocked force measurements. The blocked force of the pump was determined experimentally using an indirect measurement method. The indirect method required operation with part under test fixed to an instrumented receiver structure. Measured operational accelerations on the receiver plate were used in conjunction with transfer function measurements to predict the blocked forces. Blocked forces were validated by comparing directly measured accelerations to predicted
Smither, Matthew, Tuyls, Zachary, Patel, Pratik, Yan, Xin, Herrin, David
Noise Reduction in High-Speed Sonic Under expanded jets using Slanted Perforated Tabs2025-01-003205/05/2023
Studies on High-Speed Jet control is of prime importance to aerospace as well as related industries. Proper mixing of Jet of a fuel with the surrounding air is indispensable in the combustion chamber of a propulsive system, this contributes to the need of enhancing mixing of Jet with ambient air. The noise radiated by a jet engine is also a major problem for many cities around the world and this method also reduces the Jet associated noise which is of immense environmental concern for transport aircrafts. The High-speed Jet control is achieved by using two different methods. They are active Control method and passive control method. In active control method, the idea is to introduce stream wise vortices into the mixing layer of the jet. Passive control of the jet can be achieved by adding geometrical modifications. The present study deals with an innovative passive control of jet using slanted perforated tabs. which focuses on the method of changing the structures in turbulent free
R, Asad Ahmed, SUBRAMANIAN, THANIGAIARASU
Sonic Boom propagation using high and low-fidelity methods2025-01-003405/05/2023
A bottle neck to the introduction of civil supersonic aircraft is represented by the noise produced by shock waves during the cruise flight, the so-called "sonic boom". Authorities prohibit supersonic flight over land due to the exceeding noise levels produced by sonic boom. This work deals with a comprehensive methodology for assessing the aircraft sonic-boom signature at ground level starting from an accurate estimation of the near-field pressure signature caused by shock-wave pressure. High fidelity computational fluid dynamics (CFD) is typically used to calculate near-field sonic booms, whereas proper models are used for propagating at long distances, since CFD becomes computationally demanding as propagation distances exceed 10 km. The present study focuses on assessing a low-fidelity technique (e.g. Whitam's equation) against the direct application of a high-fidelity CFD method for sonic boom propagation at a medium distance. The former propagates the pressure signature through
Glorioso, Antimo, Fasulo, Giovanni, Petrosino, Francesco, Barbarino, Mattia
An Aerodynamic Equation of State—Part I: Introduction and Aerospace Applications - QA Test Tatsiana01-17-01-000104/19/2023
Abstract In subsonic aircraft design, the aerodynamic performance of aircraft is compared meaningfully at a system level by evaluating their range and endurance, but cannot do so at an aerodynamic level when using lift and drag coefficients, CL and CD , as these often result in misleading results for different wing reference areas. This Part I of the article (i) illustrates these shortcomings, (ii) introduces a dimensionless number quantifying the induced drag of aircraft, and (iii) proposes an aerodynamic equation of state for lift, drag, and induced drag and applies it to evaluate the aerodynamics of the canard aircraft, the dual rotors of the hovering Ingenuity Mars helicopter, and the composite lifting system (wing plus cylinders in Magnus effect) of a YOV-10 Bronco. Part II of this article applies this aerodynamic equation of state to the flapping flight of hovering and forward-flying insects. Part III applies the aerodynamic equation of state to some well-trodden cases in fluid
Burgers, Phillip
An Aerodynamic Equation of State—Part I: Introduction and Aerospace Applications - QA Test Tatsiana01-17-01-0001-TEST-REC04/19/2023
Abstract In subsonic aircraft design, the aerodynamic performance of aircraft is compared meaningfully at a system level by evaluating their range and endurance, but cannot do so at an aerodynamic level when using lift and drag coefficients, CL and CD , as these often result in misleading results for different wing reference areas. This Part I of the article (i) illustrates these shortcomings, (ii) introduces a dimensionless number quantifying the induced drag of aircraft, and (iii) proposes an aerodynamic equation of state for lift, drag, and induced drag and applies it to evaluate the aerodynamics of the canard aircraft, the dual rotors of the hovering Ingenuity Mars helicopter, and the composite lifting system (wing plus cylinders in Magnus effect) of a YOV-10 Bronco. Part II of this article applies this aerodynamic equation of state to the flapping flight of hovering and forward-flying insects. Part III applies the aerodynamic equation of state to some well-trodden cases in fluid
Burgers, Phillip
An Aerodynamic Equation of State—Part I: Introduction and Aerospace Applications01-17-01-000104/19/2023
In subsonic aircraft design, the aerodynamic performance of aircraft is compared meaningfullyby evaluating their range and endurance, but cannot do so atwhen using lift and drag coefficients,and, as these often result in misleading results for different wing reference areas. This Part I of the article (i) illustrates these shortcomings, (ii) introduces a dimensionless number quantifying the induced drag of aircraft, and (iii) proposes anfor lift, drag, and induced drag and applies it to evaluate the aerodynamics of the canard aircraft, the dual rotors of the hoveringMars helicopter, and the composite lifting system (wing plus cylinders in Magnus effect) of a YOV-10. Part II of this article applies this aerodynamic equation of state to the flapping flight of hovering and forward-flying insects. Part III applies the aerodynamic equation of state to some well-trodden cases in fluid mechanics found in fluid-mechanics textbooks.
Burgers, Phillip
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