Browse Topic: Fixed-wing aircraft

Items (465)

Next-Gen Maintenance Framework for Urban Air Mobility Vehicles

2022-26-116505/26/2022

Urban Air Mobility (UAM) vehicles are set to revolutionize the mobility of man and material in near future. One of the key areas to explore is how operational efficiency can be maximized through the next generation Maintenance framework. Compared to the traditional aircrafts, the UAM vehicles will introduce many new and unique maintenance challenges such as: 1. The volume of UAM vehicles is going to be very high and involves frequent, short trips resulting in increased need for maintenance. 2. UAMs may be of hybrid nature (rotary and fixed wing) with a complex interplay of actuation and propeller-based controls. In addition, UAMs will have Electric Motors which involve complex maintenance of parts. 3. High Power Battery is another key component which involves handling the removal, replacement and charging, which requires an effective Battery Management System. 4. Efficient Inventory/Parts Management including NFF reduction is going to play a vital role because Parts, not labor, are the

Kulkarni, Sandeep, Elahi, Imtiaz, Kadeppagari, Murali, Panicker, Renju

Minimum Operational and Maintenance Responsibilities for Aircraft Tire Usage

ARP5265C (Current)

09/20/2021

This SAE Aerospace Recommended Practice (ARP) sets forth criteria for the installation, inflation, inspection, and maintenance of aircraft tires and the maintenance of the operating environment to ensure the safety of support personnel and the safe operation of the aircraft.

A-5C Aircraft Tires Committee

Minimum Operational and Maintenance Responsibilities for Aircraft Tire Usage

ARP5265C-TEST-REC (Historical)09/20/2021

A-5C Aircraft Tires Committee

Night Vision Imaging System (NVIS) Compatible Illuminated Pushbutton Switches and Indicators

ARP4822A (Current)09/03/2021

This SAE Aerospace Recommended Practice (ARP) reviews the basics of NVIS compatibility and discusses the specific illuminated pushbutton switch and indicator requirements for sunlight readability, color, luminance, and NVIS radiance when used in NVIS compatible cockpits. The recommendations and special considerations set forth in this document are made to give the design engineer a better understanding of MIL-L-85762A and MIL-STD-3009 NVIS compatibility requirements and to provide information on the visual characteristics of NVIS compatible pushbutton switch and indicators. The recommendations are primarly for military aircraft since civilian aircraft FAR requirements typically do not cover NVIS applications with the exception of those covered by RTCA/DO-275.

A-20A Crew Station Lighting

Rotorcraft: Application of Existing Aircraft Designed Tires, Wheels and Brakes

ARP5632 (Current)04/23/2021

This document covers recommendations for the application of existing qualified and approved in-service fixed wing aircraft tires, wheels and brakes to military and commercial rotorcraft. NOTE: This document does not address the use of radial tires due to insufficient data to support their approved use on rotorcraft, see paragraph 4.3.14 for specific impact on ground resonance.

A-5 Aerospace Landing Gear Systems Committee

7.0.112 - Design and Development of Variable Valve Actuation (VVA) Mechanism Concept for Multi-Cylinder Engine

SAE-PP-0028802/04/2021

The desire for higher fuel economy, improved performance and driveability expectations of customers from engines are gradually increasing along with stringent emission regulations set by the government. Many original engine manufacturing companies are prompted to consider the application of higher function variable valve actuation mechanisms in their next generation vehicles as a solution. The VVA is a generalized term used to describe any mechanism or method that can alter the shape or timing of a valve lift event within an internal combustion engine. The VVA allows lift, duration or timing (in various combinations) of the intake and/or exhaust valves to be changed while the engine is in operation. Engine designers are prompted to consider Variable Valve Actuation (VVA) system because of the inherent compromises with fixed valve events. The major goal of a VVA engine is to control the amount of air inducted into the engine which is a direct measure of torque. This work presents a

6.0.109 - Comparison Study on Fuel Properties of Biodiesel from Jatropha, Palm and Petroleum Based Diesel Fuel

SAE-PP-0026502/04/2021

The increase of air pollution and global warming is a threat for human life. Besides, the price of petroleum is increasing rapidly and the resources are diminishing. This obliged scientists and engineers to look for alternative sources of energy, which are cleaner and more sustainable. Biodiesel, defined as mono-alkyls of esters from vegetable oils and animals fat, is a cleaner renewable fuel and has been considered as the best alternative for petroleum based diesel fuel hence it can be used in any compression ignition engines without any significant modification. The main advantages of using biodiesel are its renewability and better quality of exhaust gas emissions due to their higher content of oxygen. The produce less soot and hence the feed stuck is plant it will regenerate the CO2 by the photosynthesis which ensures the renewability and reduces global warming. But these alternative fuels have faced some obstacles while utilizing in CI engines which are due to some of their

Mutagaana, Festo

Enhancing Flight Path Separation to Reduce Birdstrikes with Ultraviolet Radiation 02032021084035

SAE-PP-0024302/03/2021

In the autumn of 2018 a pilot study using a prototype (PAR46 sized) landing light incorporating 5 ultraviolet light emitting diodes (UVLEDs) was attached on a one-quarter scale remote controlled (RC) 6 plane. The plane was flown in the direction of birds to measure their behavioral response to the 7 approaching plane with landing light either turned ON or OFF. Data were collected from multiple sources 8 including cameras on the plane and the ground, and a bird radar unit to measure the flight path separation 9 between the plane and the birds. The purpose of this study was to determine the effectiveness of using 10 UVLEDs integrated into a PAR46 landing light to trigger bird avoidance behavioral responses that would 11 increase flight path separation to reduce the incidence of birdstrikes. The findings showed the mean 12 distance of the avoidance response was statistically significantly greater when the PAR46 with UVLEDs 13 were turned ON than OFF. Field test data were used to create a

Anthony, Lindsay

Enhancing Flight Path Separation to Reduce Birdstrikes 1 with Ultraviolet Radiation

SAE-PP-0023402/03/2021

Anthony, Lindsay

Aircraft Protection Systems

TBMG-3789410/01/2020

Northrop Grumman Corporation Falls Church, VA 1-703-280-2900

Designing Connectivity Solutions for an Electric Aircraft Future

TBMG-3788710/01/2020

Designing Connectivity Solutions for an Electric Aircraft Future

20AERP10_0310/01/2020

The levels of voltage and current needed in electric-powered vertical takeoff and landing aircraft (eVTOL), personal air vehicles (PAVs), and rotorcraft systems are high and going higher. That's because electric propulsion motors, inverters, controllers, batteries, and sensor-laden electric aircraft require significant amounts of power. High voltages and high kW peak outputs present many implementation challenges. Designers can meet these challenges by understanding how proper product selection and a “follow-the-wire” design approach enable high-power connectivity solutions. Some of the hurdles that designers need to overcome include the following.

Aircraft Asset Lifecycle and Digital Data Standards Overview

AIR7501 (Current)

09/18/2020

This SAE Aerospace Information Report (AIR) reviews technical, operational, and maintenance data being exchanged between key stakeholders in aerospace asset lifecycle and data standards available for such exchanges. It identifies gaps and non-availability of data standards in certain areas. The scope of the current document is limited to aircraft operations, maintenance and disposal stages post-build phase, and does not include the detailed interactions during the aircraft build phase.

G-31 Electronic Transactions for Aerospace Committee

Aircraft Asset Lifecycle and Digital Data Standards Overview

AIR7501-TEST-REC (Historical)09/18/2020

G-31 Electronic Transactions for Aerospace Committee

Information on Parking Brake Systems

AIR6441 (Current)09/16/2020

This SAE Aerospace Information Report (AIR) provides information on the parking brake system design for a variety of aircraft including part 23, 25, 27, and 29. The document includes a discussion of key technical issues with parking brakes. This document does NOT provide recommended practices for parking brake system design.

A-5A Wheels, Brakes and Skid Controls Committee

Lighting, Aircraft Interior, Installation of

AS18276B (Current)08/28/2020

This specification covers the installation of aircraft interior lighting for military aircraft.

A-20C Interior Lighting

Series Fuzzy PID with Anti-windup Controller for Intelligent Vehicle

2020-01-011304/14/2020

A series fuzzy PID controller with anti-windup scope (SFPCA) is proposed in this paper to address saturation nonlinear problem and control disturbance caused by uncertainty of actuator model. In order to achieve novel dynamic and steady-state performance, the fuzzy controller and PID controller are fused into series, which realizes excellent dynamic performance of fast response and low overshoot like pure fuzzy controller at the initial response stage, and the excellent steady-state performance of stable and no static difference like PID control at the later response stage. The Hurwitz low is employed to configure PID parameters and 49 rules are designed for fuzzy controller. Since the input of the actuator could not be infinite, the actuator being saturated for a long time could reduce the stability of system and, even lead to irreversible damage. Moreover, after exiting the saturation state, it is difficult to quickly recover to the fast and stable response state of the original

Luo, Chao

High-Performance, Piezoelectric, Hybrid Synthetic Jet Actuators

TBMG-3618103/01/2020

NASA Langley Research Center has invented three serial high-performance, piezoelectric, hybrid synthetic jet actuators to provide active flow control for current and future wing-borne vehicles in subsonic, transonic, and supersonic flow. Effective active flow control results in reduced vehicle drag and the prevention of events that can lead to catastrophic loss.

Ice and Rain Minimum Qualification Standards for Pitot and Pitot-static Probes

AS5562 (Current)02/11/2020

This SAE Aerospace Standard (AS) establishes minimum ice and rain performance criteria for electrically-heated pitot and pitot-static probes intended for use on the following classes of fixed-wing aircraft and rotorcraft. The classes of fixed-wing aircraft are defined by aircraft flight envelopes and are shown in Figure 1. The flight envelopes generally fall into the classes as shown below: The user of this standard must evaluate the aircraft level installation requirements for the probe against the class definition criteria to ensure adequate coverage for the application. It may be necessary to step up in class or modify the test conditions in order to meet the applicable installation requirements. NOTE: Class 2 is divided into two subgroups identified as either Class 2a or Class 2b. Class 2a probe applications typically include aircraft that operate within the mid to lower end of the Class 2 altitude range and that only use probe output to display basic airspeed and/or altitude. As

AC-9C Aircraft Icing Technology Committee

Aircraft Vertical Takeoff and Landing

TBMG-3528410/01/2019

NASA’s Langley Research Center developed an inexpensive, long-endurance, vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV). It is capable of flying for 24 hours, landing in a 50 × 50 zone, and can be loaded into the back of a cargo van for easy transport. In addition, it can land in either a horizontal or vertical flight configuration.

Air Conditioning Systems for Subsonic Airplanes

ARP85G (Current)09/25/2019

This SAE Aerospace Recommended Practice (ARP) contains guidelines and recommendations for subsonic airplane air conditioning systems and components, including requirements, design philosophy, testing, and ambient conditions. The airplane air conditioning system comprises that arrangement of equipment, controls, and indicators that supply and distribute air to the occupied compartments for ventilation, pressurization, and temperature and moisture control. The principal features of the system are: a A supply of outside air with independent control valve(s). b A means for heating. c A means for cooling (air or vapor cycle units and heat exchangers). d A means for removing excess moisture from the air supply. e A ventilation subsystem. f A temperature control subsystem. g A pressure control subsystem. Other system components for treating cabin air, such as filtration and humidification, are included, as are the ancillary functions of equipment cooling and cargo compartment conditioning

AC-9 Aircraft Environmental Systems Committee

Perspectives on Integrating Structural Health Monitoring Systems into Fixed-Wing Military Aircraft

AIR6245 (Current)09/18/2019

This SAE Aerospace Information Report (AIR) is prepared for stakeholders seeking information about the evolution, integration, and approval of SHM technologies for military aircraft systems. The report provides this information in the form of (a) two military organizations’ perspectives on requirements, and (b) general SHM challenges and industry perspectives. The report only provides information to generate awareness of perspectives for military aircraft and, hence, assists those who are involved in developing SHM systems understanding the broad range of regulations, requirements, and standards published by military organizations that are available in the public domain from the military organizations.

Aerospace Industry Steering Committee on Structural Health

Flight Optimization Model on Global and Interval Ranges for Conceptual Studies of MEA Systems

2019-01-190609/16/2019

In development of more electric aircraft applications, it is important to discuss aircraft energy management on various level of aircraft operation. This paper presents a computationally efficient optimization model for evaluating flight efficiency on global and interval flight ranges. The model is described as an optimal control problem with an objective functional subjected to state condition and control input constraints along a flight path range. A flight model consists of aircraft point-mass equations of motion including engine and aerodynamic models. The engine model generates the engine thrust and fuel consumption rate for operation condition and the aerodynamic model generates the drag force and lift force of an aircraft for flight conditions. These models is identified by data taken from a published literature as an example. First, approximate optimization process is performed for climb, cruise, decent and approach as each interval range path. Next, optimization for global

Shibuya, Yotsugi, Oyori, Hitoshi, Sugawara, Hirotaka, Seki, Naoki

Collins Aerospace provides avionics for C-130H modernization program

SAE-MA-0000209/03/2019

The Lockheed C-130H Hercules fleet operated by the Air National Guard and U.S. Air Force Reserve is getting new Collins Aerospace Systems avionics that will help extend the life of the legacy aircraft by 20 years.

Kucinski, William

Safety Assessment of General Aviation Airplanes and Rotorcraft in Commercial Service

ARP5151A (Current)08/20/2019

This document describes a process that may be used to perform the ongoing safety assessment for (1) GAR aircraft and components (hereafter, aircraft), and (2) commercial operators of GAR aircraft. The process described herein is intended to support an overall safety management program. It is to help a company establish and meet its own internal standards. The process described herein identifies a systematic means, but not the only means, to assess continuing airworthiness. Ongoing safety management is an activity dedicated to assuring that risk is identified and properly eliminated or controlled. The safety management process includes both safety assessment and economic decision-making. While economic decision-making (factors related to scheduling, parts, and cost) is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. This ongoing safety assessment process includes safety problem identification and corrective action

S-18C ARP5150A and ARP5151A Working Group

NASA crash landing is a complete success

SAE-MA-0354906/24/2019

The test was conducted to better understand the dynamic forces on an aircraft and its passengers during a crash landing. Findings form the event will support a new FAA performance-based rule that will simplify aircraft certification by eliminating or minimizing the use of special conditions.

Kucinski, William

Experimental Aerodynamic Simulation of Glaze Ice Accretion on a Swept Wing

2019-01-198706/10/2019

Aerodynamic assessment of icing effects on swept wings is an important component of a larger effort to improve three-dimensional icing simulation capabilities. An understanding of ice-shape geometric fidelity and Reynolds and Mach number effects on iced-wing aerodynamics is needed to guide the development and validation of ice-accretion simulation tools. To this end, wind-tunnel testing was carried out for 8.9% and 13.3% scale semispan wing models based upon the Common Research Model airplane configuration. Various levels of geometric fidelity of an artificial ice shape representing a realistic glaze-ice accretion on a swept wing were investigated. The highest fidelity artificial ice shape reproduced all of the three-dimensional features associated with the glaze ice accretion. The lowest fidelity artificial ice shapes were simple, spanwise-varying horn ice geometries intended to represent the maximum ice thickness on the wing upper surface. The results presented in this paper show

Broeren, Andy P., Potapczuk, Mark G., Lee, Sam, Woodard, Brian S., Bragg, Michael B., Smith, Timothy G.

Facing the Challenges of Supercooled Large Droplet Icing: Results of a Flight Test Based Joint DLR-Embraer Research Project

2019-01-198806/10/2019

Today’s airplanes are well equipped to cope with most common icing conditions. However, some atmospheric conditions consisting of supercooled large droplets (SLD) have been identified as cause of severe accidents over the last decades as existing countermeasures even on modern aircraft are not necessarily effective against SLD-ice. In 2014, the new Appendix O to the certification regulations (FAR Part 25 / CS-25) had been issued to guarantee the safe operation of future airplane when encountering SLD conditions. But as the SLD topic is quite new for the majority of aircraft manufacturers and research institutes in a same way, DLR (German Aerospace Center) and Embraer established a joint research cooperation in 2012 to obtain a better understanding of the distinct influences of SLD-ice shapes on aircraft characteristics and to evaluate proper ways for future airplane certification under App. O. Furthermore, one additional scientific goal of the cooperation was to develop and test new

Deiler, Christoph, Ohme, Per, Raab, Christian, Mendonca, Celso, Silva, Daniel

JAUS Autonomous Capabilities Service Set

AS8024 (Current)06/10/2019

This document defines a set of standard application layer interfaces called JAUS Autonomous Capabilities Services. JAUS Services provide the means for software entities in an unmanned system or system of unmanned systems to communicate and coordinate their activities. The Autonomous Behaviors Services represent the platform-independent capabilities commonly found in platforms across domains, including air, maritime, and ground. At present five (5) services are defined in this document. These services are: Comms Lost Policy Manager: Detect and recover from loss of communications with a control station Retrotraverse: Return along a path previously traveled Self-Righting: Attempt to recover from a tip over condition Cost Map 2D: Provides information about the current operating environment of the platform Path Reporter: Provides information about the previous or future planned path of the platform

AS-4JAUS Joint Architecture for Unmanned Systems Committee

Coating Technology Enables Effective Missile Countermeasures

TBMG-3453006/01/2019

Heat-seeking missiles have been in use against both rotorcraft and fixed wing aircraft since the mid-1950s, and countermeasures to deceive their guidance systems have been employed for nearly as long. Typically, countermeasures operate by generating a strong infrared signature which confuses the missile tracking system. At the heart of these systems is some form of powerful infrared emitting source. Often this source requires optical coating(s) to perform wavelength filtering needed for optimum operation. However, both the mechanical configuration of the thin film filter coatings used and the operating extremes to which they are subjected present challenges for the manufacturer.

Coating Technology Enables Effective Missile Countermeasures

19AERP06_0406/01/2019

Landing Gear Structural Health Monitoring

AIR6168A (Current)05/23/2019

This SAE Aerospace Information Report (AIR) discusses past and present approaches for monitoring the landing gear structure and shock absorber (servicing), opportunities for corrosion detection, methods for transient overload detection, techniques for measuring the forces seen by the landing gear structure, and methods for determining the fatigue state of the landing gear structure. Landing gear tire condition and tire pressure monitoring are detailed in ARP6225, AIR4830, and ARP6137, respectively. Aircraft Brake Temperature Monitoring Systems (BTMS) are detailed in AS1145.

A-5 Aerospace Landing Gear Systems Committee

Arresting Hook Installation, Land-Based Aircraft

ARP1538B (Historical)

04/17/2019

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 Committee