Browse Topic: Aircraft structures

Items (4,068)

Operating Characteristics of an Automotive Adjustable-Field Permanent Magnet Motors with 3D Magnetic Paths and Asymmetric Magnet Arrangement

2024-32-002704/18/2025

This paper describes a three-dimensional structure of an adjustable field magnetization permanent magnet (PM) motor and a high-power density rotor structure with asymmetric permanent magnet arrangement for both high torque and high efficiency operation in the high speed and low torque range. 3D-FEA has confirmed that it is possible to achieve both high torque density and adjustable field magnetization. Load testing using the prototype proposed motor confirmed that high motor efficiency can be achieved even during high-speed operation.

Hiyoshi, Yutaro, Doi, Kotaro, Noguchi, Toshihiko

Aircraft Cockpit Window Improvements Enabled by High-Strength Tempered Glass

01-17-02-0012

01/25/2024

This research was initiated with the goal of developing a significantly stronger aircraft transparency design that would reduce transparency failures from bird strikes. The objective of this research is to demonstrate the fact that incorporating high-strength tempered glass into cockpit window constructions for commercial aircraft can produce enhanced safety protection from bird strikes and weight savings. Thermal glass tempering technology was developed that advances the state of the art for high-strength tempered glass, producing 28 to 36% higher tempered strength.As part of this research, glass probability of failure prediction methodology was introduced for determining the performance of transparencies from simulated bird impact loading. Data used in the failure calculation include the total performance strength of highly tempered glass derived from the basic strength of the glass, the temper level, the time duration of the load, and the area under load.A high-strength transparency

Lampman, DeWitt

Measurement uncertainty and its influence on e-Drive optimization applications

2024-26-009701/16/2024

This paper gives insights in the theoretical measurement uncertainty of E-Drive rotor position dependent results, like Id and Iq calculations, done by a modern propulsion power analyzer (PA). The calculation of Id and Iq is fundamental to perform control optimization and application tasks for an E-Drive system. In order to optimize the E-Drive system application towards e.g. best efficiency, best performance, or improved NVH the importance of the testing toolchain is described: a power analyzer delivering the required results, an automation system, and a Design of Experiment tool to set improved target values. Consequently, inverters applications featuring field-oriented control (FOC) with permanent magnet synchronous machines (PMSM) are updated with a chosen control strategy. For achieving a certain behavior of an E-Drive, different degrees of freedom in the Inverter Control Unit are available; Lookup tables Id and Iq represent two fundamental application labels to be considered

Platzer, Thomas, Fechter, Michael, Kammerstetter, Heribert, Kolb, Philipp

Computational Investigation of a Flexible Airframe Taxiing Over an Uneven Runway for Aircraft Vibration Testing

01-17-02-0011

12/15/2023

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

NOISE ANALYSIS IN DIFFERENT FLAPPING MECHANISMS FOR EFFICIENT FLYING

2025-01-002105/05/2023

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

The applications of Acoustic Black Holes to attenuation of Coach/Bus Frame Structure Vibrations

2025-01-006505/05/2023

Abstract An acoustic black hole (ABH) is a structure whose cross-sectional thickness decreases exponentially to zero, and the phase velocity and group velocity of wave propagation in those structure acoustic black holes decrease as the thickness decreases until they are zero. ABH produce some very magical physical phenomena. For example, because the wave velocity decreases to zero, the wave can never reach the center of the ABH, so the wave propagation in the acoustic black hole has neither refraction nor reflection; that is to say the vibration wave will not go through the acoustic black hole. As a result, the wave energy is concentrated in the center of the ABH. The arrangements of those acoustic black holes in the structures could change the directions of the vibrational wave propagation in the structures at NVH engineers’ wills. These amazing phenomena could play a magical role in reducing structural vibration, structural noise radiation and structure-borne noise. Basic structures

Huang, Xianli

Designing Rubber Flaps for Resonance Management: High-Frequency Tuning in Electric Vehicles Using AI/ML Approaches

2025-01-012505/05/2023

High-frequency whine noise in electric vehicles (EVs) poses a significant challenge, affecting customer perception and the overall vehicle experience. One primary source of this undesirable noise is the interaction between motor pole resonance and the resonance of the engine mount rubber. This paper presents an innovative method for predicting and tuning the frequency response of engine mounts by precisely adjusting the dimensions of rubber flaps, specifically their length and width. The proposed solution employs a dual approach: fine-tuning rubber flap dimensions and utilizing machine learning (ML) techniques. An ML model, trained on historical data, predicts how varying flap dimensions impact frequency response, providing a data-driven foundation for optimization. This prediction capability is enhanced by a Python program that automates the optimization process using a linear combination formula, efficiently addressing resonance issues. By integrating ML insights with the linear

Hazra, Sandip, Khan, Arkadip

An Aerodynamic Equation of State—Part I: Introduction and Aerospace Applications - QA Test Tatsiana

01-17-01-0001

04/19/2023

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 Tatsiana

01-17-01-0001-TEST-REC04/19/2023

Burgers, Phillip

An Aerodynamic Equation of State—Part I: Introduction and Aerospace Applications

01-17-01-0001

04/19/2023

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

Re-imagining Brake Rotor Thermal Fatigue Testing to Relate to Field Use

2022-01-116309/19/2022

The validation of brake rotors has remained, to this day, heavily reliant on “Thermal Abuse” or “Thermal Cracking” type testing, with many procedures so dated that most engineers active in the industry today cannot even recall the origin of the test. These procedures - of which there are many variants - all share the trait of greatly accelerating durability testing by performing repeated high power (high speed and high deceleration) brake applies to drive huge temperature gradients and internal stress, and often allowing the rotor to get very hot, to where the strength of the material from which the rotor is constructed is significantly degraded. There is little debate about whether these procedures work; by and large rotor durability issues in the field are extremely rare. However, without the connection to the duty cycle in the field, it is extremely difficult to interpret results (especially since many standards allow significant cracking before a failure is declared), and this can

Antanaitis, David, Langhardt, Jerry

Design and Computational Investigations of Aerobot for Titan with maneuverability using momentum wheel and propeller equipped with droppable weather stations

2022-26-119105/26/2022

Titan, Saturn’s largest moon and the only celestial body which is found to have a landmass composed of liquid hydrocarbons. Nitrogen – The building block of all life that exists on earth is found to be abundant in Titan’s atmosphere of up to 97%. Aerobots provide a great platform for exploring a celestial body with an atmosphere such as Titan. They have modest power requirements, longer mission duration, and can cover a longer distance in a shorter time. They are powered by Radioisotope Thermoelectric Generator for optimal mission life. Aerobot’s altitude can be altered by varying the temperature of the air inside the balloon and yaw can be controlled using Reaction Wheel and a motor-driven propeller for forwarding thrust. The proposed Aerobot will be equipped with four miniature deployable fixed weather stations that can be dropped from the aerobot to titan’s surface. They can be deployed at diverse locations such as the equator and Polar Regions to deeply explore the Titan’s climate

Raja, Manoj Kumar, Sivasankaran, Abinash Nataraj, Saravana Mohan, Haribalan, Thangavel, Sabari, R, Vijayanandh, Gnanasekaran, Raj Kumar

Design and Parametric Investigations on Various Propellers for Nature Inspired Unmanned Amphibious Vehicle

2022-26-117405/26/2022

Unmanned Amphibious Vehicle (UAV) is an integrative working environments based vehicle, which doesn’t allocate the place for onboard pilots. Mostly, unmanned amphibians have been controlled through pre-provided algorithms in the predestined paths. Aerodynamic and hydrodynamic working conditions are the compositions of aforesaid integrative environments, wherein the possible lifespan affecting failure of UAV may chance to happen in a high manner. Thus, the multidisciplinary investigation on UAV and it's every component needs to be done in order to pick the suitable UAV parts for both missions executing conditions. This work deals the comprehensive computational investigations on a different number of blades equipped propellers for the proposed cum nature-inspired UAV under aerodynamic and hydrodynamic loading conditions. Three different propellers are uniquely constructed based on the aerodynamic environment reference with the guidance of analytical formulae and thereafter modeling

R, Vijayanandh, Mathaiyan, Vijayakumar, Raji, Arul Prakash, Madasamy, Senthil Kumar, Gnanasekaran, Raj Kumar

Bird strike analysis on nanocomposite materials for aerospace applications

2022-26-114505/26/2022

Over the years, bird strike has become a serious threat as it is inevitable and can be catastrophic. Several accidents occur due to the bird collision with wing leading edges, causing serious structural damage that may be permanent. Therefore, the failure induced by birds on the leading edge has persuaded much research interest. To heighten the impact resistance during bird strike with the leading edge of the wing, nanocomposite materials are proposed as it has improved characteristics like high surface-to-volume ratio, enhanced mechanical properties like high ductility, fracture toughness with no decrease of strength in structure. In order to achieve material constants of the nanocomposites, the finite-element method (FEM) and representative volume element (RVE) which is a micromechanical analysis approach will be considered. A comparative study will be done on different volume fractions of nanofillers impregnated with the composite material to find the optimum material properties

Neigapula, Keerthana, Anand, Sumit, Devi, Monisha, Tiwari, Anawil, Kumar, Siddharth

Investigation of the effectiveness of plasma actuators at various chord positions of an airfoil for flow separation control

2022-26-113505/26/2022

This paper's principal aim is to investigate the effect of a plasma actuator on the airflow over an airfoil. Dielectric Barrier Discharge (DBD) Plasma actuators are lauded as one of the most efficient active control devices in the field of aerodynamics. It owes this to ionizing and consequently exerting body force on the air without increasing the structural complexity of the airfoil. However, it is imperative to know the characteristics of plasma positioning at a specific angle of attack to ensure optimum usage. NACA 0012 airfoil was used in the simulations to demonstrate the proficiency of multiple plasma actuators to delay flow separation at increasing angles of attack at various chord positions by using a steady-state RANS model solver on a two-dimensional geometry at subsonic speeds corresponding to a Reynolds Number of the order of 10^5. ANSYS Fluent solver was used to examine the significant increase in the numerically obtained Lift-to-Drag ratio, and the aerodynamic

Aryan, Suryansh, Ahmed, M Muzheir, Acharya, Sagar, Dubey, Sukanya

A comparative study between Flax-Fiber Reinforced Polymer and Balsa wood for Aero-structure applications.

2022-26-119905/26/2022

When air flows over a wing, a pressure difference is generated between the upper and lower camber of the wing. This pressure difference is responsible for lift generation. Since the wing is the primary lifting surface of all aircraft, the structure itself must be capable of handling all the loads imposed upon it. This study aims to perform a trade-off between Balsa wood and a natural fiber composite namely Flax Fiber Reinforced Polymer and evaluating their performance using ANSYS. Balsa wood is the most common material used for building homebuilt remote-controlled aircraft. This makes the aircraft light but restricts its performance as it cannot handle cyclic loads over a period of the cycle. Thus, a natural fiber composite is being chosen as a substitute for the conventional Balsa wood. The wing is modeled using SOLIDWORKS 2018 and includes 5 ribs and a rectangular spar at the maximum thickness/chord %. The composite material is built using ANSYS ACP wherein all the laminates and

Phatarphod, Soham, Swain, Prasant Kumar, Sharma, Narayan, Maiti PhD, Dipak Kumar

Gland Design, O-Ring and Other Seals

AS4716D (Current)

11/09/2021

This SAE Aerospace Standard (AS) provides standardized gland (groove) design criteria and dimensions for O-ring seal glands for static and dynamic applications, and other seals.

A-6C2 Seals Committee

Gland Design, O-Ring and Other Seals

AS4716D-TEST-REC (Historical)11/09/2021

This SAE Aerospace Standard (AS) provides standardized gland (groove) design criteria and dimensions for O-ring seal glands for static and dynamic applications, and other seals.

A-6C2 Seals Committee

Hybrid Laminated Panels Addressing Acoustic Issues in Vehicles

2021-01-108608/31/2021

Laminated steel body panels are used in different applications in vehicles, such as dash panels and wheel wells. A part made out of laminated steel has the potential to provide structure-borne noise reduction and also improve the airborne noise reduction of the part compared to a monolithic part. The use of laminated steel has been more critical when there are deep draws on the part as the deep draws cause localized resonances which degrade the acoustic performance significantly. However, due to lightweighting demands, hybrid laminated panels, commonly known as acoustic patch laminates have become very attractive. This paper discusses the damping and sound transmission loss performances of a dash panel part with monolithic, laminated, and acoustic patch panels. The paper discusses the damping performance below 1000 Hz, including the data analysis process and the effectiveness of the acoustic patch laminates for both structure borne and airborne noise studies including coincidence dip

Saha, Pranab, Patil*, Sagar, Figueroa**, Antonio, Telenko, Michael

Crashworthy Landing Gear Design

AIR4566A (Current)

08/09/2021

The intent of this SAE Aerospace Information Report (AIR) is to document the design requirements and approaches for the crashworthy design of aircraft landing gear. This document covers the field of commercial and military airplanes and helicopters. This summary of crashworthy landing gear design requirements and approaches may be used as a reference for future aircraft.

A-5B Gears, Struts and Couplings Committee

Study on the Influence of Mass Flow Rate over a National Advisory Committee for Aeronautics 6321 Airfoil Using Improved Blowing and Suction System for Effective Boundary Layer Control

01-14-02-0011

08/06/2021

The numerical analysis of the three-dimensional (3D) flow over a National Advisory Committee for Aeronautics (NACA) 6321 airfoil to evaluate the mass flow rate by using a novel method Improved Blowing and Suction System (IBSS) to control the boundary layer is presented in this study. Analysis is performed based on 3D Reynolds-Averaged Navier-Stokes (RANS) equation with a K-omega SST solver. The aerodynamic performance of the NACA 6321 is analyzed at a Mach number of 0.10 with three different mass flow rates, namely, 0.08 kg/s, 0.10 kg/s, and 0.12 kg/s. From the study, it is seen that when the mass flow rate decreased, the aerodynamics performance also reduced, and the aerodynamic performance improved with the increase in mass flow rate. Results also show that a mass flow rate of 0.10 kg/s improved the stalling angle of attack (AoA) by 60% and coefficient of lift (CL) by 50%, enabling optimum efficiency of the aircraft wing in all aspects compared to the baseline airfoil model. The mass

Karuppiah, Balaji, Wessley, Jims John

Aircraft Tail Bumpers

AIR1800B (Current)

06/22/2021

This SAE Aerospace Information Report (AIR) covers the field of civilian, commercial and military airplanes and helicopters. This summary of tail bumper design approaches may be used by design personnel as a reference and guide for future airplanes and helicopters that require tail bumpers. Those described herein will consist of simple rub strips, structural loops with a wear surface for runway contact, retractable installations with replaceable shock absorbers and wear surfaces and complicated retractable tail landing gears with shock strut, wheels and tires. The information will be presented as a general description of the installation, its components and their functions.

A-5B Gears, Struts and Couplings Committee

Overview of Aircraft Landing Gear Shimmy Analysis Methods

AIR6280 (Current)

06/10/2021

This SAE Aerospace Information Report (AIR) provides an overview of the tire properties, strut properties, damper properties, and other landing gear mechanical properties that contribute to shimmy stability and are required for shimmy analysis. A variety of analysis techniques and assumptions are presented.

A-5 Aerospace Landing Gear Systems Committee

Overview of Aircraft Landing Gear Shimmy Analysis Methods

AIR6280-TEST-REC (Historical)06/10/2021

A-5 Aerospace Landing Gear Systems Committee

Landing Gear Alignment

AIR5556 (Current)04/23/2021

The purpose of this Aerospace Information Report is to provide the industry with methodologies for measuring tire/wheel gear alignment and the range of acceptable alignment settings for various types of non-military landing gear. This AIR will focus on the general aviation, corporate, and regional aircraft landing gear but could have applicability to commercial aircraft.

A-5 Aerospace Landing Gear Systems Committee

Landing Gear Storage

ARP5936 (Current)04/23/2021

This document categorizes the different types of storage requirements, either on the aircraft or new unused or overhauled on the shelf, for aircraft landing gears/components. Recommendations and examples of proper landing gear storage are outlined. Reclamation recommendations are provided for aircraft landing gear returning from long-term storage.

A-5 Aerospace Landing Gear Systems Committee

Wheel Chocks

AIR4905A (Current)04/08/2021

The purpose of this document is to present general considerations for the design and use of aircraft wheel chocks. The design and use of aircraft wheel chocks is a good deal more complicated than it may appear at first glance.

AGE-3 Aircraft Ground Support Equipment Committee

Aircraft Tow Bar

ARP1915E (Current)04/08/2021

This SAE Aerospace Recommended Practice (ARP) specifies dimensional and physical requirements of tow bar connections to tractor and aircraft (see Figure 1). It is applicable to all types of commercial transport category aircraft tow bar. The purpose of this SAE Aerospace Recommended Practice (ARP) is to standardize tow bar attachments to airplane and tractor according to the mass category of the towed aircraft, so that one tow bar head with different shear levels can be used for all aircraft that are within the same mass category and are manufactured in compliance with AS1614 or ISO 8267.

AGE-3 Aircraft Ground Support Equipment Committee

A Novel Approach to Dynamic Contact Analysis in the Course of Aircraft Assembly Simulation

2021-01-000403/02/2021

A new numerical approach is proposed for studying possible vibrations caused by drilling during the assembly of aircraft structures. It is based on modelling of the stress-strain state of assembled structures by solving the corresponding transient contact problem. This approach is intended for fast dynamic analysis of the structure in the drilling area. It includes a time discretization algorithm, a special reduction technique and a reformulation of contact problem in terms of quadratic programming. The high speed of the algorithm allows one to combine the non-stationary calculations with variation analysis in order to check the possible deviations in the shape of assembled parts. The proposed approach is validated by commercial software and it is also applied for analysis of a test problem.

Vasiliev, Alexey, Minevich, Olga, Lapina, Evgeniia, Shinder, Julia, Lupuleac, Sergey, Barboule, Joel

Augmentation of Gas-Turbine Performance Using Inlet Air Cooling and Turbine Blade Cooling: A Thermodynamic Approach

2021-01-003103/02/2021

A systematic and comprehensive first law analysis of a cooled gas turbine cycle subjected to vapor compressor inlet air cooling (VC-IAC) has been conducted in our study. Film air cooling technique has been implemented to cool the gas turbine (GT) buckets. The gas turbine is subjected to variation of various operating and ambient parameters and the corresponding effect is analyzed to find out the optimal one. The integration of VC-IAC has been reported to further enhance the plant specific work and plant efficiency of gas turbine cycle, the enhancement being higher in regions having a hot and dry climate. This increase in cycle performance due to VC-IAC has been found superior in case of bucket cooled GT cycle when compared to uncooled one. It has further been witnessed that the plant specific work increases by more than 0.35 % and the plant efficiency increases by little above 0.1 % for every 1o C drop in CIT. The work ratio representing the excess of work of turbine over work of

Mishra, Alok, Srivastava, Anshuka, Mohapatra, Alok Kumar

Gland Design: Scraper, Landing Gear, Installation

AS4052B-TEST-REC (Historical)02/03/2021

This SAE Aerospace Standard (AS) covers an alternate gland design for the installation of scraper/wiper rings in the lower end of landing gear shock struts for the purpose of contaminant exclusion. The defined scraper gland covered by this document, as shown in Table 1, is a variant of AS4716, the accepted gland standard for MS28775, O-ring packing seals. Piston rod diameters, gland internal diameters, groove sidewall angles and the surface finish are all defined by AS4716, but the gland outer retaining wall diameter is changed. The traditional scraper design installed into the glands detailed in Table 1 typically utilize components made from urethane or nitrile materials. These scraper designs, while still acceptable, must be reviewed in consideration to deicing, cleaners and disinfectant fluids applied to or in contact with the landing gear, as the materials of construction for the installed scrapers may not be compatible to these fluids. Exposure of the scraper to incompatible

A-5B Gears, Struts and Couplings Committee

Aircraft Tail Bumpers

AIR1800A (Historical)02/03/2021

A-5B Gears, Struts and Couplings Committee

Gland Design: Scraper, Landing Gear, Installation

AS4052B (Historical)

02/03/2021

A-5B Gears, Struts and Couplings Committee

Designation of Direction of Rotation of Helicopter Rotors

ARP570B (Current)

01/14/2021

S-12 Powered Lift Propulsion Committee

Description of High Lift Control Systems

AIR6016 (Current)

12/10/2020

This SAE Information Report (AIR) provides descriptions of High Lift Systems of commercial and military aircraft. The main focus is on mechanical systems which may be actuated hydraulically or electrically.

A-6B3 Electro-Mechanical Actuation Committee

Description of High Lift Control Systems

AIR6016-TEST-REC (Historical)12/10/2020

A-6B3 Electro-Mechanical Actuation Committee

Multirotor Aircraft Noise Reduction

TBMG-3820112/01/2020

Noise produced by multirotor vehicles may be objectionable to some, especially as industry moves toward drone deliveries and potentially air taxi operations. Multirotor aircraft typically create a significant amount of tonal noise from each rotor. Groups of rotors operating at the same rotation rate with an appropriate phase offset can be used to reduce the tonal noise of the aircraft when there are multiple rotors on each side of the aircraft. Reducing tonal noise, depending on the aircraft design, can effectively reduce the total noise output for a given flight scenario.

Aerospace Rod Scraper Gland Design Standard

AS4088F-TEST-REC (Historical)11/03/2020

This SAE Aerospace Standard (AS) defines gland details for scrapers for rod diameters from 1/4 to 15-1/2 inch (6.35 to 393.70 mm) inclusive, corresponding to AS568 O-ring Dash No. sizes -108/-111, -206/-222, -325/-349, and -425/-460. The gland details herein allow the use of more stable, efficient, and reliable scraper devices than MS33675 glands.

A-6C2 Seals Committee

Aerospace Rod Scraper Gland Design Standard

AS4088F (Current)

11/03/2020

A-6C2 Seals Committee

Tire Overspeed Landing Test

ARP5257B (Current)09/18/2020

This document covers the basis of, and test procedure for, an overspeed landing test on aircraft tires with rated speeds of 190 mph (306 km/h) and above. The conditions requiring an overspeed test, alternatives, test requirements and pass/fail criteria are addressed.

A-5C Aircraft Tires Committee

Tire Pressure Monitoring Systems (TPMS) for Aircraft

ARP6137 (Current)09/18/2020

A tire pressure monitoring system (TPMS) is a means to electronically measure and report the current tire pressure. Some systems are capable of transmitting the information to the flight deck while other systems are for use on the ground by maintenance personnel (only). This SAE Aerospace Recommended Practice (ARP) document is intended to establish overall component and system function guidelines and minimum performance levels for a TPMS. The system should visually indicate the tire inflation pressure status. These guidelines include, but are not limited to: a) Design recommendations for system components, which: 1 monitor tire inflation, and, 2 are located in/on the tire/wheel assembly, landing gear axle, and/or aircraft avionics compartment. b) Recommended performance and safety guidelines for a TPMS.

A-5C Aircraft Tires Committee

ARP5481A (Current)09/17/2020

This SAE Aerospace Recommended Practice (ARP) provides the recommended procedure for obtaining desired preloads in aircraft wheel tie bolts when mounting tires and assembling the wheel. It is generally referred to as the snug-angle bolted joint assembly procedure. It is also known as the “torque-turn” procedure in the heavy equipment ground vehicle industry.

A-5A Wheels, Brakes and Skid Controls Committee

Development and Qualification of Composite Landing Gears

AIR5552 (Current)09/17/2020

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 Committee

Rear Fuselage Packer

TBMG-3759909/01/2020

Kaman UK Darwen, UK +44 1254 706000

Identification and Assessment of Damage to Composite Aircraft Structures Training Document

AIR6825-TEST-REC (Historical)08/03/2020

Individuals who complete the applicable modules aligned with this training document will be able to define the type of damage, define the extent of damage, determine if further inspection is required, evaluate the damage against published allowable damage limits, and provide accurate documentation of the damage. The intended outcome of the training is increased safety such that no aircraft is released with unknown damage and that the aircraft meets continued airworthiness requirements. The goal is to change the culture from damage discovery to damage reporting while also reducing or eliminating flight delays due to incorrect or insufficient information. Teaching levels have been assigned to the curriculum to define the knowledge, skills, and abilities graduates will need. Minimum hours of instruction have been provided to ensure adequate coverage of all subject matter including lecture and practical exercise. These minimums may be exceeded and may include an increase in the total

AMS CACRC Commercial Aircraft Composite Repair Committee

Identification and Assessment of Damage to Composite Aircraft Structures Training Document

AIR6825 (Current)

08/03/2020

AMS CACRC Commercial Aircraft Composite Repair Committee

Landing Gear Shock Absorption Testing of Civil Aircraft

ARP5644A (Current)

07/14/2020

The intent of this document is to provide recommended practices for conducting shock absorption testing of civil aircraft landing gear equipped with oleo-pneumatic shock absorbers. The primary focus is for Part 25 aircraft, but differences for Part 23, 27, and 29 aircraft are provided where appropriate.

A-5B Gears, Struts and Couplings Committee

Advanced Assembly Solutions for the Airbus RACER Joined-Wing Configuration

20AERP06_0306/01/2020

Compound helicopters, featuring lateral rotors as well as a primary rotor, are increasingly seen as the future of rotorcraft design. Capable of supporting a range of service applications, compound rotorcraft have the potential to deliver increased efficiencies and higher speeds relative to traditional rotorcraft. The Rapid And Cost Effective Rotorcraft (RACER) demonstrator is being developed by Airbus Helicopters (AH) to further validate the compound rotorcraft configuration. AH have chosen to employ a joined-wing design, which increases the stiffness relative to a traditional wing design. The RACER de sign also includes two lateral rotors, mounted aft of the Nacelles at the outboard extent of the wings, as depicted in Figure 1. Two assembly methodologies were considered for the RACER wing structures - determinate assembly or traditional assembly set by jigs. Determinate assembly, also known as ‘part-to-part’ or ‘jig-less’ assembly relies on the precision manufacturing of a few

Advanced Assembly Solutions for the Airbus RACER Joined-Wing Configuration

TBMG-3710506/01/2020

Compound helicopters, featuring lateral rotors as well as a primary rotor, are increasingly seen as the future of rotorcraft design. Capable of supporting a range of service applications, compound rotorcraft have the potential to deliver increased efficiencies and higher speeds relative to traditional rotorcraft. The Rapid And Cost Effective Rotorcraft (RACER) demonstrator is being developed by Airbus Helicopters (AH) to further validate the compound rotorcraft configuration. AH have chosen to employ a joined-wing design, which increases the stiffness relative to a traditional wing design. The RACER design also includes two lateral rotors, mounted aft of the Nacelles at the outboard extent of the wings, as depicted in Figure 1.

Leaf-Inspired Surface Prevents Frost Formation

TBMG-3685805/01/2020

Researchers have discovered a new way to significantly reduce frost formation on any surface. The finding could help decrease the amount of energy needed for defrosting and could potentially result in fewer canceled flights, which can be grounded by even the slightest layer of frost.

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