Browse Topic: Business and general aviation aircraft

Items (1,097)
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 engines use dual-channel full-authority digital engine control (FADEC) systems, this is the configuration which is addressed. A typical FADEC system configuration is shown in Figure 2.
E-36 Electronic Engine Controls Committee
This ARP covers three common light sources, incandescent, electroluminescent and light emitting diode that, when NVG filtered, can be used to illuminate NVG compatible aerospace crew stations. It is recognized that many other different light sources can also be used for this purpose. Also see 2.1.1 for other SAE documents that cover particular applications within the crew station environment. This ARP sets forth recommendations for the design of NVG compatible lighting, utilizing these light sources, that will meet the requirements of MIL-L-85762 Lighting, Aircraft, Interior, Night Vision Imaging System (NVIS) Compatible. This also includes the replacement document MIL-STD-3009: Lighting, Aircraft, Night Vision Imaging System (NVIS) Compatible. Although this ARP concentrates on lamp light sources for illumination, the information contained within this ARP may be directly applied to incandescent, electroluminescent and light emitting diode information display devices. Regardless of the light source, the focus of this document is the understanding that the radiometric energy that can be amplified by the Night Vision Goggles (NVG’s) must be filtered to such an extent that it will not impact the operational use of the NVG’s while still allowing sufficient visible (photometric) energy to be viewed by the pilot.
A-20A Crew Station Lighting Committee
This SAE Aerospace Standard (AS) establishes the minimum design and performance requirements for galleys to be certified and installed in transport category airplanes.
S-9B Cabin Interiors and Furnishings Committee
This SAE Aerospace Recommended Practice (ARP) defines a means of assessing the credibility of computer models of aircraft seating systems used to simulate dynamic impact conditions set forth in Title 14, Code of Federal Regulations (14 CFR) Parts 23.562, 25.562, 27.562, and 29.562. The ARP is applicable to lumped mass and detailed finite element seat models. This includes specifications and performance criteria for aviation specific virtual anthropomorphic test devices (v-ATDs). This document provides a recommended methodology to evaluate the degree of correlation between a seat model and dynamic impact tests. This ARP also provides best practices for testing and modeling designed to support the implementation of analytical models of aircraft seat systems. Supporting information within this document includes procedures for the quantitative comparison of test and simulation results, as well as test summaries for data generated to support the development of v-ATDs and a sample v-ATD calibration report.
Aircraft SEAT Committee
Seat furnishings are installed around seats and are intended to enhance passenger privacy and comfort. They may have provisions for additional occupants to be seated when the aircraft is in-flight, but would not be occupied during taxi, take-off, and landing (TTL). This Aerospace Standard (AS) establishes the minimum design, performance and qualification requirements for seat furnishings with and without upper attachments (see Figures 1 and 2) to be installed in large transport category airplanes. This standard excludes seat furnishing designs that are directly attached to the seat assembly, for which AS8049 is the applicable standard. Integrated items (desk tops, cabinets, shelves, stowage areas, closeouts, dividers, etc.) connected to seat furnishings shall comply with the requirements of this AS as part of the seat furnishings.
Aircraft SEAT Committee
This SAE Aerospace Recommended Practice (ARP) defines additional documentation, environmental considerations, in-service damage limits, test and evaluation criteria necessary to support certification of aircraft seats manufactured using composite materials, in addition to requirements in AS8049 and ARP5526. This document is limited to aircraft seat composite parts in the seat primary load path from the occupant to the attachments of the seat to the aircraft. The term “composite” is inclusive of any fiber-reinforced polymer matrix materials such as carbon fiber-reinforced plastics, sandwich panels and bonded structure.
Aircraft SEAT Committee
This Aerospace Recommended Practice (ARP) defines acceptable methods for determining the seat reference point (SRP), and the documentation requirements for that determination, for passenger and crew seats in Transport Aircraft, Civil Rotorcraft, and General Aviation Aircraft.
Aircraft SEAT Committee
This SAE Aerospace Standard (AS) defines minimum performance standards, qualification requirements, and minimum documentation requirements for passenger and crew seats in civil rotorcraft, transport aircraft, and general aviation aircraft. The goal is to achieve comfort, durability, and occupant protection under normal operational loads and to define test and evaluation criteria to demonstrate occupant protection when a seat/occupant/restraint system is subjected to statically applied ultimate loads and to dynamic impact test conditions set forth in Title 14, Code of Federal Regulations (14 CFR) parts 23, 25, 27, or 29 (as applicable to the seat type, see Table 1). Guidance for test procedures, measurements, equipment, and interpretation of results is also presented to promote uniform techniques and to achieve acceptable data. While this document addresses system performance, responsibility for the seating system is divided between the seat supplier and the installation applicant. The seat supplier's responsibility consists of meeting all the seat system performance requirements and obtaining and supplying to the installation applicant all the data prescribed by this document. The installation applicant has the ultimate system responsibility in assuring that all requirements for safe seat installation have been met.
Aircraft SEAT Committee
Many electric vertical take-off and landing (eVTOL) aircraft intended for the urban air mobility (UAM) market are currently being designed with multirotor configurations using variable speed fixed-pitch, rigid rotors for lift. These types of rotors, which are similar in construction to general aviation airplane propellers, are simpler than helicopter rotors and have no moving parts in the rotating frame. This paper discusses wind-tunnel testing of a full-scale, UAM multirotor size, fixed-pitch, rigid rotor with a focus on vibratory blade loads and on the ability to predict these loads with comprehensive analysis. Test results show that vibratory loads are very high, with peak-to-peak magnitudes up to three times greater than the steady component. Correlation of test data to comprehensive analysis using geometrically exact composite beam structural elements and dynamic inflow wake modeling captures the trends in the steady and vibratory loads, but under-predicts the magnitudes by up to 50%. The paper also discusses the physical sources of the observed vibratory loads and suggests potential options for mitigating their magnitude.
Staruk, WilliamBonny, EvanButt, LaurenGray, CodyHennig, GarrettRepresa, DiegoToner, Richard
This document establishes the minimum training and qualification requirements for ground-based aircraft deicing/anti-icing methods and procedures. All guidelines referred to herein are applicable only in conjunction with the applicable documents. Due to aerodynamic and other concerns, the application of deicing/anti-icing fluids shall be carried out in compliance with engine and aircraft manufacturers’ recommendations. The scope of training should be adjusted according to local demands. There are a wide variety of winter seasons and differences of the involvement between deicing operators, and therefore the level and length of training should be adjusted accordingly. However, the minimum level of training shall be covered in all cases. As a rule of thumb, the amount of time spent in practical training should equal or exceed the amount of time spent in classroom training.
G-12T Training and Quality Programs Committee
This SAE Aerospace Recommended Practice (ARP) provides recommendations for design and test requirements for a generic “passive” side stick that could be used for fly-by wire transport and business aircraft. It addresses the following: The functions to be implemented The geometric and mechanical characteristics The mechanical and electrical interfaces The safety and certification requirements
A-6A3 Flight Control and Vehicle Management Systems Cmt
Design of the Control Surfaces for an Aircraft Destined to the Competition SAE BRAZIL AERODESIGN2019-36-02141/13/2020
This work aims to present a methodology for the design of conventional control surfaces for light aircraft. Based on renowned aeronautical engineering references and standards, the theoretical framework presents the concepts of calculation for each flight phase particularity for each control surface in addition to a database with intervals of surfaces and their respective deflections of various aircraft. The methodology used takes into account the suggested steps for the aircraft design, where the dimensions are present in the preliminary design, according to the characteristics intended in the conceptual stage to develop conventional control surfaces aiming at the simplicity of design and the optimal response of control. The use of MATLAB and CFD software for data calculation and iterations are essential for the correct observance and evaluation of the obtained results. A comparative table and graphs will be elaborated for better visualization of the efficiency and behavior of each dimensioned model aiming at the best levels of acceptability according to the norms used in the design of aircraft, observing their occurrence through flight analysis and direct feedback of the pilot. Finally, the optimally sized surface will be used.
Takano e Silva, Yoko LucilaKieling, Antonio Claudiode Azevedo, Emile Diana MendesVilaça, Neilson LuniereJanzen, Renan Araújode Oliveira, Sanches Ismael
This document recommends design and performance criteria for aircraft lighting systems used to illuminate flight deck controls, luminous visual displays used for transfer of information, and flight deck background and instrument surfaces that form the flight deck visual environment. This document is for commercial transport aircraft except for applications requiring night vision compatibility.
A-20A Crew Station Lighting Committee
Safety Assessment of General Aviation Airplanes and Rotorcraft in Commercial ServiceARP5151A (Current)8/20/2019
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, tracking of problems, the application of “lessons learned” to improve the efficiency of the process, and reduction of the time to achieve corrective action in the field. ARP5150 is the recommended practice for the safety assessment of Transport Airplanes in Commercial Service. ARP5151 is the recommended practice for the safety assessment process for GAR aircraft in commercial services. While the processes are similar, their implementations are different due to operations, data availability, and sizes of individual operations.
S-18C ARP5150A and ARP5151A Working Group
A Smart Icing Detection System for Any Location on the Outer Aircraft Surface2019-01-19316/10/2019
Given approximately one million small and light aircraft in operation worldwide, icing detection and icing quantification of in-flight icing are still an open research topic. Despite technical means are available to de-ice on ground, there is a lack of a suitable control system based on sensor data to de-ice while the aircraft is airborne. Most often, it is still task of the pilot to visually inspect the icing status of the airfoil and/or other critical parts of the aircraft such as engine air intakes, which distracts the flight crew from flying the aircraft especially in IMC conditions. Based on preliminary simulation and tests in 2014 in a collaborative research project lasting from 2015 until 2018, the technology of energy self-sustaining, wireless, self-adhesive smart sensors for industrial sensing in an aerodynamically critical environment (i.e. wind turbines) was further investigated to fulfil general aviation requirements. Prototype hardware setups have been designed and built for application on aircraft. In test flights carried out in Scotland in late 2017, the functionality of the system could be demonstrated. It could be shown that a wireless, energy self-sustaining detection system for early icing can be implemented based on currently available technologies and components. Additionally, it could be shown that detection sensitivity is sufficient to detect ice at very thin layers.
Schlegl, ThomasMoser, MichaelLoss, TheresaUnger, Thomas
The intent of this AIR is twofold: (1) to present descriptive summary of aircraft nosewheel steering and centering systems, and (2) to provide a discussion of problems encountered and “lessons learned” by various airplane manufacturers and users. This document covers both military aircraft (land-based and ship-based) and commercial aircraft. It is intended that the document be continually updated as new aircraft and/or new “lessons learned” become available.
A-5B Gears, Struts and Couplings Committee NEW Name Goes Her
Automated 6DOF Model Generation and Actuator Sizing within AFSIM2019-01-13363/19/2019
The Air Force Research Laboratory has interest in automatically generating the extensive aerodynamic databases essential for six degree of freedom (6DOF) models and the use of 6DOF models for design. To be most useful, automation must include all aspects of producing the database including meshing, control surface deflections, running the CFD solution, and storage of the results. This effort applies newly-developed software to produce the desired results. Firstly, AFRL software called Computational Aircraft Prototype Syntheses (CAPS) allows automated meshing using the Advancing Front Local Reconnection (AFLR) software from Mississippi State University1 and automated control surface deflection using Engineering Sketch Pad (ESP) software from MIT/Syracuse. CAPS includes the ability to run the NASA CFD code FUN3D and interpret the FUN3D results via an Application Interface Module (AIM). This may sound like a complicated process. However, it is quite simple using a python interface to CAPS called pyCAPS. The automated generation of the aerodynamic database for the 6DOF model is handled by use of a short python script that includes nested loops that handle the numerous CFD runs to capture the combinations of angle-of-attack, sideslip angle, and control surface deflections needed for the database. This database is then paired with an appropriate controller and other information, like propulsion data and mass property data, to form the complete 6DOF model. Of interest is the design of actuators that are attached to the aircraft control surfaces. The 6DOF model is then used to fly the aircraft through an Operational Analysis (OA) scenario in AFSIM (Advanced Framework for Simulation, Integration and Modeling) where maneuvers and environmental conditions like gusts or turbulence are simulated. The entire process is shown to be tractable and accessible.
Allison, DarcyShimmin, KyleSchley, WilliamBryson, Dean
The Application of Additive Manufacturing to the 2018 SAE Aero Design Challenge2019-01-13283/19/2019
This project focuses on the application of polymer additive manufacturing to the 2018 SAE Aero Design Regular Class competition for North Carolina A&T State’s 2017/2018 senior project team. The Regular Class SAE Aero Design challenge requires participating teams to create a high lift, high efficiency remote controlled aircraft that is designed to carry as many passengers and additional cargo mass as possible while still being able to meet land and air performance requirements defined by the competition rules. Constraints set by the competition rules include material constraints, a max gross weight of 55 lb, a limited power supply of 1000 W, a 12-ft wingspan limitation, enclosed cargo and passenger bays, the ability to unload and load all cargo and return the plane to a flight ready configuration within 1 minute, and a takeoff distance of 200 ft. The wide use of additive manufacturing and hot wire foam cutting for this aircraft design has allowed for accurate and efficient component production, as well as increased design complexity compared to traditional manufacturing methods seen at competition. Most importantly, the use of these manufacturing methods has allowed for efficient design change implementations and quick turnaround times. Specific examples include the light weight, high fineness ratio fuselage that efficiently used space and integrated landing gear and mounting structures, which was made with ABS and polycarbonate polymers. Additional examples include the implementation of shock absorbing landing gear wheels, which were made of fatigue resistant PETG. Results show that the use of innovate manufacturing methods such as additive manufacturing and hot wire foam cutting helped to increase prototyping and testing efficiency, and enabled quick production of an organically shaped, high performing RC aircraft.
Blake, Nathan DavidWaters, CynthiaEsau, SimonKizito, John
Aircraft electric propulsion technology review – A shift from turbofan to the ethrust era2018-36-00969/3/2018
Following the electrification trend observed in the automotive industry, the idea of an electric propulsion aircraft has also drawn attention and investments from a range of aviation industry stakeholders (including the world's largest aerospace companies) focused on both fuel burning reduction and environmental performance improvement (greenhouse gases (GHG), pollutants and noise emissions) potential of electric propulsion technology. Electric propulsion has the potential to provide more efficient, cleaner, quieter and more profitable aviation services, with potential benefits to both airlines and passengers. Furthermore, with its inherent quiet feature, it has also the potential to lead to a reassessment of the role of airports along the world cities, as well as revitalize regional short-haul flights and helps the launch of air service into underserved regions around the world. From a technical perspective , the aviation propulsion electrification strategy might involves the integration of electric powetrains into aircrafts into the i) all electric; ii) hybrid and iii) turboelectric approach. The former might rely solely on batteries as energy sources and requires engines up to 300 times more powerful than current available electric aviation motors (currently used for two-seater prototypes). The hybrid configuration uses gas turbines, for turbofan propulsion, and to charge batteries (with turbogenerators), which also provides energy for electric propulsion for one or more phases of flight. Finally, turboelectric configurations do not rely on batteries to supply propulsion energy. Rather, they use gas turbines to drive electric generators to feed distributed electric driven fans, with their inherent aerodynamic benefits associated with distributed propulsion. Hybrid architectures might provide a more realistic near-term pathway, while key enabling technologies - batteries, high power electric motors and superconducting electric power - reach the required improvement, into an expected 10 to 20 year timeframe. The most likely niche of the industry to first commercially launch this groundbreaking technology is the commuter and regional jet category, with a 50 to 70 passenger capacity and a short to mid range. This work is supposed to present an overview of aircraft electric propulsion technology, followed by an assessment of its potential operational, environmental and economic benefits, as well as the required technological breakthrough to reach the electric thrust era.
Barbosa, Fábio Coelho
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