Side window clarity and its effect on side mirror visibility plays major role in the driver comfort. Driving in inclement weather conditions such as rain can be stressful. Having optimal visibility under these conditions is ideal. However, extreme conditions can overwhelm exterior water management devices, resulting in rivulets of water flowing over the a-pillar and onto the vehicle’s side glass. Once on the side glass, these rivulets and the pooling of water they feed can significantly impair the driver’s ability to see the side mirror or to see outwardly when in situations such as changing lanes. Designing exterior water management features of a vehicle is a challenging exercise as traditionally, physical testing methods first require a full-scale vehicle for evaluations to be possible. Additionally, common water management devices such as grooves and channels often have undesirable aesthetic, drag, and wind noise implications.
Abstract The SPA-10 project, sponsored by U.S. National Science Foundation, is to acquire and qualify a replacement for the retired T-28 “storm penetration” aircraft previously used to acquire meteorological data to enable understanding and modelling of mid-continent thunderstorms. The National Science Foundation selected the Fairchild A-10 (bailed from the U.S. Air Force) as the platform to be adapted to perform the storm penetration mission to altitudes of eleven kilometers, and funded Naval Postgraduate School’s Center for Interdisciplinary Remotely-Piloted Aircraft Studies (CIRPAS) as prime contractor. An expert panel conducted a review of the SPA-10 project in 2014 and recommended a risk analysis addressing hazards to the aircraft and pilots, such as icing, hail, turbulence and lightning. This paper presents the results of the risk analysis performed in response to this need, including recommended mitigations.
This document establishes the minimum requirements for ground based aircraft deicing/anti-icing methods and procedures to ensure the safe operation of aircraft during icing conditions on the ground. This document does not specify the requirements for particular aircraft models. NOTE: Refer to particular aircraft operator or aircraft manufacturers’ published manuals and procedures. The application of the procedures specified in this document are intended to effectively remove and/or prevent the accumulation of frost, snow, slush or ice contamination which can seriously affect the aerodynamic performance and/or the controllability of an aircraft. The principal method of treatment employed is the use of fluids qualified to AMS1424 and AMS1428 (Type I, II, III, and IV fluids). All guidelines referred to herein are applicable only in conjunction with the applicable documents.
Types of aircraft passenger-escape systems An overview of existing and potential new methods for assuring aircraft occupant safety. SAE Skill India Initiative: S2I2 A new SAEINDIA collaboration aims to help young engineers acquire "industry-ready" skills. A technology-driven sustainable-agriculture solution Pumping more air into the cylinder is key to solving the CAFE puzzle, and engineers are hard at work figuring out the best ways to do it with turbocharger and supercharger innovation. Rotorcraft icing computational tool development 3D printing machines can't be built fast enough In the additive-manufacturing world, the costs of components are dropping, the technology is becoming more reliable and parts are fabricated faster, allowing industries beyond aerospace to adopt additive technologies, says Oak Ridge Lab's Ryan Dehoff.
This specification covers a glycol-base deicing/anti-icing material in the form of a liquid.
This test method provides stakeholders (runway deicing chemical manufacturers, deicing/anti-icing chemical operators and airport authorities) with a relative ice penetration capacity of runway deicing/anti-icing chemicals, by measuring the ice penetration as a function of time. Such runway deicing/anti-icing chemicals are often also used on taxiways and other paved areas. This test method does not quantitatively measure the theoretical or extended time of ice penetration capability of ready-to-use runway deicing/anti-icing chemicals in liquid or solid form.
This test method provides stakeholders (runway deicing chemical manufacturers, deicing/anti-icing chemical operators and airport authorities) with relative ice melting capacity of runway deicing chemicals, by measuring the amount of ice melted as a function of time. Such runway deicing chemicals are often also used on taxiways. This test method does not quantitatively measure the theoretical or extended time ice melting capability of ready-to-use runway deicing/anti-icing chemicals in liquid or solid form.
This test method provides stakeholders (runway deicing chemical manufacturers, deicing/anti-icing chemical operators and airport authorities) with relative ice undercutting capacity of runway deicing chemicals, by measuring the area of ice undercut pattern as a function of time. Such runway deicing chemicals are often also used on taxiways.
This procedure establishes a recommended practice for establishing the sensitivity of the chest displacement potentiometer assembly used in the Hybrid III family of Anthropomorphic Test Devices (ATDs, or crash dummies). This potentiometer assembly is used in the Hybrid III family to measure the linear displacement of the sternum relative to the spine (referred to as chest compression). An inherent nonlinearity exists in this measurement because a rotary potentiometer is being used to measure a generally linear displacement. As the chest cavity is compressed the potentiometer rotates, however the relationship between the compression and the potentiometer rotation (and voltage output) is nonlinear. Crash testing facilities have in the past used a variety of techniques to calibrate the chest potentiometer, that is to establish a sensitivity value (mm/ (volt/volt) or mm/ (mvolt/volt)).
Fluid, Aircraft Deicing/Anti-Icing, Non-Newtonian (Pseudoplastic), SAE Types II, III, and IV, NON-GLYCOL
The foundation specification (AMS1428) and the category specifications (AMS1428/1 and AMS1428/2) cover deicing/anti- icing materials in the form of a fluid. 1.1.1 Foundation and Category Specifications The foundation specification establishes the requirements for all Type I deicing/anti-icing fluids and defines the terms Glycol (Conventional and Non-Conventional) and Non-Glycol and contains technical and other requirements that apply to both Glycol (Conventional and Non-Conventional) and Non-Glycol based fluids. The category specification AMS1428/1 covers Glycol (Conventional and Non-Conventional) based fluids whereas the category specification AMS1428/2 covers Non-Glycol based fluids. 1.2 Other Scope Requirements Other Scope requirements are set in AMS1428.
Fluid, Aircraft Deicing/Anti-Icing, Non-Newtonian (Pseudoplastic), SAE Types II, III, and IV, glycol
1.1 Form The foundation specification (AMS1424M) and the category specifications (AMS1424/1 and AMS1424/2) cover deicing/anti-icing materials in the form of a fluid. 1.1.1 Foundation and Category Specifications The foundation specification establishes the requirements for all Type I deicing/anti-icing fluids and defines the terms Glycol (Conventional and Non-Conventional) and Non-Glycol and contains technical and other requirements that apply to both Glycol (Conventional and Non-Conventional) and Non-Glycol based fluids. The category specification AMS1424/1 covers Glycol (Conventional and Non-Conventional) based fluids whereas the category specification AMS1424/2 covers Non-Glycol based fluids. 1.2 Other Scope Requirements Other Scope requirements are set in AMS1424M.
This methodology can be used for all calculations of HIC, with all test devices having an upper neck triaxial load cell mounted rigidly to the head, and head triaxial accelerometers.
This Recommended Practice can apply to both Original Equipment Manufacturer and Aftermarket route-guidance and navigation system functions for passenger vehicles. The methods apply only to the presentation of visual information and the use of manual control inputs to accomplish a navigation or route guidance task. They do not apply to visual monitoring tasks which do not require a manual control input, such as route following. Voice-activated controls or passenger operation of controls are also excluded.
The purpose and scope of this SAE Recommended Practice is to provide a basis for classification of the extent of vehicle deformation caused by vehicle accidents on the highway. It is necessary to classify collision contact deformation (as opposed to induced deformation) so that the accident deformation may be segregated into rather narrow limits. Studies of collision deformation can then be performed on one or many data banks with assurance that the data under study are of essentially the same type. The seven-character code is also an expression useful to persons engaged in automobile safety, to describe appropriately a field-damaged vehicle with conciseness in their oral and written communications. Although this classification system was established primarily for use by professional teams investigating accidents in depth, other groups may also find it useful.
This procedure establishes a recommended practice for performing a Low Speed Thorax Impact Test to the Hybrid III Small Female Anthropomorphic Test Device (ATD or crash dummy). This test was created to satisfy the demand by the industry to have a certification test which results in peak chest deflection similar to current full vehicle, frontal impact tests. An inherent problem exists with the current certification procedure because the normal (6.7 m/s) thorax impact test has test results for peak chest deflection that are greater than those currently seen in full vehicle, frontal tests. The intent of this document is to develop a low speed thorax certification procedure for the H-III5F dummy with a 3.0 m/s impact similar to the SAE J2779 procedure for the H-III50M dummy.
This recommended practice provides a procedure for measuring quantitatively the physical characteristics of linear impactors that are believed to effect impact test accuracy, repeatability, and reproducibility. Suggested values and tolerance are also provided for specific applications of linear impactor testing (i.e. Ejection Mitigation tests, Head form Impact tests, Body Block tests). Two functional groups of linear impactors are considered, those whose function is related primarily to displacement and those related to measuring acceleration or force.
Digital Design Tools Simulating Thermal Expansion in Composites with Expanded Metal Foil for Lightning Protection Rugged Computing Designing VME Power Systems with Standard Modules Optical Sensors Optical Ice Sensors for UAVs Rotorcraft Technology Rotorcraft Icing Computational Tool Development RF & Microwave Technology Curled RF MEMS Switches for On-Chip Design: Design Software Supports BAE System's Mixed-Signal Chip Design
This specification is intended to be used as a general standard for industry use for design and construction of air transport galley equipment and inflight food service systems.
This detail specification AMS1424/3 covers the use of In-Truck Manufacturing of a deicing SAE Type I deicing/anti-icing fluid. This detailed specification contains technical and other requirements that apply for the In-Truck Manufacturing of Type I deicing/anti-icing fluid.
This SAE Aerospace Standard (AS)/Minimum Operational Performance Specification (MOPS) specifies the minimum performance requirements of Remote On-Ground Ice Detection Systems (ROGIDS). These systems are ground-based. They provide information that indicates whether frozen contamination is present on aircraft surfaces. Section 1 provides information required to understand the need for the ROGIDS, ROGIDS characteristics, and tests that are defined in subsequent sections. It describes typical ROGIDS applications and operational objectives and is the basis for the performance criteria stated in Section 3 through Section 5. Section 2 provides reference information, including related documents, abbreviations, and definitions. Section 3 contains general design requirements for the ROGIDS. Section 4 contains the Minimum Operational Performance Requirements for the ROGIDS, which define performance in icing conditions likely to be encountered during ground operations.
This Aerospace Recommended Practice (ARP) covers a brief discussion of the icing problem in aircraft fuel systems and different means that have been used to test for icing. Fuel preparation procedures and icing tests for aircraft fuel systems and components are proposed herein as a recommended practice to be used in the aircraft industry for fixed wing aircraft and their operational environment only. In the context of this ARP, the engine (and APU) is not considered to be a component of the aircraft fuel system, for the engine fuel system is subjected to icing tests by the engine/APU manufacturer for commercial and specific military applications. This ARP is written mostly to address fuel system level testing. It also provides a means to address the requirements of 14 CFR 23.951(c) and 25.951(c). Some of the methods described in this document can be applied to engine and APU level testing or components of those application domains.
Base-engine value engineering for higher fuel efficiency and enhanced performance Continuous improvement in existing engines can be efficiently achieved with a value engineering approach. The integration of product development with value engineering ensures the achievement of specified targets in a systematic manner and within a defined timeframe. Integrated system engineering for valvetrain design and development of a high-speed diesel engine The lead time for engine development has reduced significantly with the advent of advanced simulation techniques. Cars poised to become 'a thing' Making automobiles part of the Internet of Things brings both risks and rewards. Agility training for cars Chassis component suppliers refine vehicle dynamics at the high end and entry level with four-wheel steering and adaptive damping.
This SAE Standard provides test procedures, requirements, and guidelines for stop lamps intended for use on vehicles of less than 2032 mm in overall width.
Rollover test methods that have been used is provided. Published papers discussing methods used to develop, evaluate, or test components, subsystems, or full vehicles under rollover conditions were reviewed and are described.
This document provides information and guidance material to assist in assessing the need for and feasibility of developing deicing facilities, the planning (size and location) and design of deicing facilities, and assessing environmental considerations and operational considerations associated with de-icing facilities. The document presents relevant information necessary to define the need for a deicing facility and factors influencing its size, location and operation. The determination of the need for deicing facilities rests with Airports. Although this document intends to provide information to airport operator and deicing facility planner/designer, all stakeholders, including deicing service providers, should be involved in the development process.
The objective of this document is to enhance the test procedure that is used for ejection mitigation testing per the NHTSA guidelines as mentioned in the FMVSS226 Final Rule document (NHTSA Docket No. NHTSA-2011-0004). The countermeasure for occupant ejection testing is to be tested with an 18kg mass on a guided linear impactor using the featureless headform specifically designed for ejection mitigation testing. SAE does not endorse any particular countermeasure for ejection mitigation testing. However, the document reflects guidelines that should be followed to maintain consistency in the test results. Examples of currently used countermeasures include the Inflatable Curtain airbags and Laminated Glass.
A review of droplet sizing instruments used for icing research is presented. These instruments include the Forward Scattering Spectrometer Probe, the Optical Array Probe, the Phase Doppler Particle Analyzer, the Malvern Particule Size Analyzer, the oil slid technique, and the rotating multicylinder. The report focuses on the theory of operation of these instruments and practical considerations when using them in icing facilities.
Software's role continues to expand Design teams use different technologies to create new software and link systems together. Emissions regulations and engine complexity With the European Commission announcing a Stage V criteria emissions regulation for off-highway, scheduled to phase-in as earlly as 2019, there will be an end to a brief era of harmonized new-vehicle regulations. Will this affect an already complex engine development process? Evaluating thermal design of construction vehicles CFD simulation is used to evaluate two critical areas that address challenging thermal issues: electronic control units and hot air recirculation.
Abstract Numerical models of Hybrid III had been widely used to study the effect of underbody blast loading on lower extremities. These models had been primarily validated for automotive loading conditions of shorter magnitude in longer time span which are different than typical blast loading conditions of higher magnitude of shorter duration. Therefore, additional strain rate dependent material models were used to validate lower extremity of LSTC Hybrid III model for such loading conditions. Current study focuses on analyzing the mitigating effect of combat boots in injury responses with the help of validated LSTC Hybrid III model. Numerical simulations were run for various impactor speeds using validated LSTC Hybrid III model without any boot (bare foot) and with combat boot.
Abstract A detailed finite element model of a 2012 Toyota Camry was developed by reverse engineering. The model consists of 2.25M elements representing the geometry, thicknesses, material characteristics, and connections of relevant structural, suspension, and interior components of the mid-size sedan. This paper describes the level of detail of the simulation model, the validation process, and how it performs in various crash configurations, when compared to full scale test results. Under contract with the National Highway Traffic Safety Administration (NHTSA) and the Federal Highway Administration (FHWA), the Center for Collision Safety and Analysis (CCSA) team at the George Mason University has developed a fleet of vehicle models which has been made publicly available. The updated model presented is the latest finite element vehicle model with a high level of detail using state of the art modeling techniques.