Browse Topic: Flight recorders

Items (199)

Study on Influencing Factors of Hippocampal Injury in Closed Head Impact Experiments of Rats Using Orthogonal Experimental Design Method

2023-01-0001

04/11/2023

The hippocampus plays a crucial role in brain function and is one of the important areas of concern in closed head injury. Hippocampal injury is related to a variety of factors including the strength of mechanical load, animal age, and helmet material. To investigate the order of these factors on hippocampal injury, a three-factor, three-level experimental protocol was established using the L(3) orthogonal table. A closed head injury experiment regarding impact strength (0.3MPa, 0.5MPa, 0.7MPa), rat age (eight- week-old, ten-week-old, twelve-week-old), and helmet material (steel, plastic, rubber) were achieved by striking the rat's head with a pneumatic-driven impactor. The number of hippocampal CA3 cells was used as an evaluation indicator. The contribution of factors to the indicators and the confidence level were obtained by analysis of variance. The results showed that impact strength was the main factor affecting hippocampal injury (contribution of 89.2%, confidence level 0.01

Wang, Peng, Song, Xuewei, Zhu, Xiyan, Qiu, Jinlong, Yang, Shuaijun, Zhao, Hui

682 Guidance for Air Transport Service Bulletins (TEST POPST CT and APPSEARCH)

ARINC682 (Current)09/21/2022

This document provides industry guidance to supplement ATA standards and airframe requirements, addressing gaps and vague areas to move suppliers/vendors and airframers toward a common standard for format and wording in Vendor Service Bulletins (VSB) for Air Transport components. This document supplements the VSB guidance of iSpec 2200, providing clarity of requirements and resulting in a common standard wording and format of VSBs from all suppliers on all aircraft types. The guidance in this document is intended to be applied to VSBs created and released subsequent to the release of the guidance document and will not require the retroactive update of VSBs released prior to the creation and release of the guidance.

PHM system with comprehensive data analytics to provide localized reasoning for a failure prediction

2022-26-123005/26/2022

Aircraft system contains components to perform system core functionality, monitor system health and record the health status. The recorded health status data provides useful information that leads to the root cause of a failure. The maintenance activities are performed based on the routine procedure and manual approach to identify failure. Most system maintenance are ignored due to the failure to identify system health deterioration. The failure in aircraft systems is monitored periodically from various types of data in the aircraft such as Flight Data recorder (FDR), Aircraft Condition Monitoring System (ACMS), Weather, Maintenance and Pilot Report (PIREP) data. The fault data is embedded in these collections of data however the actual reasoning of the system failure is very difficult and cumbersome to identify and end up in the replacement of the failed component without understanding the cause of the failure. This is because the typical field failure analysis is performed in

Sundaramurthy, Ajay Byappanahalli

Halfshaft Joints Lifetime Prediction Method and Tool Development

2022-01-029003/29/2022

This study is inspired by the technological developments across all product development areas for the elimination of physical testing based on data analytics. As one of the important driveline components, halfshaft fatigue performance is mostly limited by CV Joints life. That being the case, product development engineering teams are challenged to deal with black box CV joint designs from various suppliers and validate them for different applications. In this paper, it's mentioned about the method development of road load data usage to have robust lifetime prediction for CV joints. Instantaneous joint angles which are not possible to acquire during vehicle testing with conventional equipments are one of the main parameters for the damage rating. A solution is provided to generate a correlation between theoretical angle calculations and available parameters from the given road load data. At the end of the study, calculated CV joint fatigue life in mileage are compared with the real life

Ayber, Barış, Kaplan, Murat, Genc, Utku, ÖZEN, Erman, POSA, Chris, ATKINSON, Nancy

Physics-guided Sparse Identification of Nonlinear Dynamics for Prediction of Vehicle Cabin Occupant Thermal Comfort

2022-01-018003/29/2022

Thermal cabin comfort is the largest consumer of battery energy second only to propulsion in Battery Electric Vehicles (BEV’s). Accurate prediction of thermal comfort in the vehicle cabin with fast turnaround times will allow engineers to study the impact of various thermal comfort technologies and develop energy efficient Heating, Ventilation and Air Conditioning (HVAC) systems. In this study a novel data-driven model based on physics-guided Sparse Identification of Nonlinear Dynamics (SINDy) method was developed to predict Equivalent Homogeneous Temperature (EHT), Mean Radiant Temperature (MRT) and cabin air temperature under transient conditions and drive cycles. EHT is a recognized measure of the total heat loss from the human body that can be used to characterize highly non-uniform thermal environments such as a vehicle cabin. The SINDy model was trained on drive cycle data from Climatic Wind Tunnel (CWT) for a representative Battery Electric Vehicle. The performance of the

Warey, Alok, Kaushik, Shailendra, Han, Taeyoung

Evaluating the effect of Suspension Damping on Ride and Handling Trade-Off in a Passenger Car

2021-26-008109/22/2021

In a Passive suspension, damping force is generated by a shock absorber by pressurizing the oil flow between chambers. Typically, vehicle responds with suspension deflection which significantly depends on damping forces and velocity. Tuning damping forces for various road and steering input is a Black box. In any setting, damping force w.r.t velocity is tuned for optimum ride and handling. Practically, to achieve a balance between the two is a tedious task as the choices & arrangements of inner parts like piston, port, valve etc., which defines the forces set up [soft / hard] are infinite. The objective of this paper is to measure, objectify and evaluate the performance of two such optimum setting in various ride and handling events. A passenger car set up with an optimum soft & hard suspension damping force, is studied for various ride and handling sub-attributes and their conflicts are examined in detail from a performance point of view.

Sahoo, Satyaranjan, Reuben, Eric Pranesh De, BAKSHI, Deepak, Krishnan, Hari, Singh, Amardeep

High-Efficiency Megawatt Motor

TBMG-3813712/01/2020

Innovators at NASA Glenn Research Center have designed a High-Efficiency Megawatt Motor (HEMM), a wound-field partially superconducting machine. The HEMM implements a combination of superconducting and non-superconducting elements, along with an integrated cryocooler, to achieve some of the benefits of a superconducting motor without the need for an external cryogenic system.

Unsettled Topics Concerning Adopting Blockchain Technology in Aerospace

EPR2020021

10/30/2020

In the aerospace industry, competition is high and the need to ensure safety and security while managing costs is paramount. Furthermore, stakeholders—who gain the most by working together—do not necessarily trust each other. Now, mix that with changing enterprise technologies, management of historical records, and customized legacy systems. This issue touches all aspects of the aerospace industry, from frequent flyer miles to aircraft maintenance and drives tremendous inefficiency and cost.Technology that augments, rather than replaces, is needed to transform these complex systems into efficient, digital processes. Blockchain technology offers collaborative opportunities for solving some of the data problems that have long challenged the industry.This SAE EDGE™ Research Report by Rhonda D. Walthall examines how blockchain technology could impact the aerospace industry and addresses some of the unsettled concerns surrounding its implementation.{"uri":[{"xlink:href":"https://www.sae.org

Walthall, Rhonda

Development of a Secure Private Neural Network Capability

20AERP09_0409/01/2020

Machine Learning (ML) tools like Deep Neural Networks (DNNs) have gained widespread popularity due to their ability to quickly and accurately perform discriminative tasks, such as object detection and classification. However, current implementations of this concept have several drawbacks. First, traditional DNNs require access to unprotected (unencrypted) data. Even if the data is secured and the ML tool is made compatible for use with encrypted data, the resulting operational performance is slowed to the point that it renders the approach intractable. Second, recent research has shown many DNNs are susceptible to white box (full access to the machine learning tool and operations) and black box (only access to system input and output) attacks, allowing adversaries to maliciously manipulate the ML tool's output. In its short history, this concept has been successfully applied to a broad spectrum of problems: speech and image recognition, medical imagery diagnostics, drug discovery

Development of a Secure Private Neural Network Capability

TBMG-3761409/01/2020

CONTACTS, ELECTRICAL, CONNECTOR, SOCKET, CRIMP REMOVABLE (FOR AS81714 TERMINAL JUNCTION SYSTEM SERIES II)

AS39029/22E (Historical)08/25/2020

AE-8C1 Connectors Committee

Aerospace - Passive Side Stick Unit General Requirements for Fly-by Wire Transport and Business

ARP6001B-TEST-REC (Historical)04/23/2020

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

Aerospace - Passive Side Stick Unit General Requirements for Fly-by Wire Transport and Business

ARP6001B (Current)

04/23/2020

A-6A3 Flight Control and Vehicle Management Systems Cmt

A Development of Battery Aging Prediction Model Based on Actual Vechile Driving Pattern

2020-01-105904/14/2020

The battery of the real vehicle accelerates the battery aging due to the dark current of the black box, the high ambient temperature, the shortage of the battery charge rate and the customer complaints such as intermittent occurrence of ISG intermittently entering the vehicle and bad start. In addition, the existing battery durability verification requires a long period of more than 4 months through the deep discharge and it has not secured the advance verification technology through battery durability verification and battery aging simulation that reflect the various actual vehicle driving conditions of the customer. In order to improve this, it is aimed to develop a battery aging prediction model that reflects various operating conditions of actual vehicle driving pattern based customer. The NREL battery lifetime model has been adapted for AGM lead-acid batteries using experimental test data. Battery stress statistics are created with a battery thermal/electric simulation and then

LIM, YOUNGCHUL, Edel, Zachary

CONTACTS, ELECTRICAL, CONNECTOR, SOCKET, CRIMP REMOVABLE (FOR AS81714 TERMINAL JUNCTION SYSTEM SERIES II)

AS39029/22D (Historical)03/24/2020

AE-8C1 Connectors Committee

Design and Handling Guide Radio Frequency Absorptive Type Wire and Cables (Filter Line, AS85485)

AIR4465A (Current)01/31/2020

This document presents design and application information which will allow optimized utilization of filter line wire and cable purchased to AS85485. Filter line wire is defined and design information is presented. The electrical and mechanical performance characteristics of the wire, along with recommended harnessing methods and techniques, are also presented.

AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install

Wheel and Wheel Trim Weathering Testing for Paint Coatings

J2633_201910 (Current)10/21/2019

This SAE lab test procedure should be used when performing the following specialized weathering tests for wheels; Florida Exposure, QUV, Xenon and Carbon Weatherometer. In addition to these procedures, some additional post-weathering tests may be specified. Please refer to customer specifications for these requirements.

Wheel Standards Committee

Technology Reveals How AI Makes Decisions

TBMG-3533910/01/2019

Researchers have developed a technology that reveals the criteria AI systems use when making decisions. The innovative Spectral Relevance Analysis (SpRAy) method based on Layer-wise Relevance Propagation technology provides a first peek inside the “black box”.

System Enables Direct Data Transmission Between Underwater and Airborne Devices

TBMG-3416504/01/2019

Today, underwater sensors cannot share data with those on land, as both use different wireless signals that only work in their respective mediums. Radio signals that travel through air die very rapidly in water. Acoustic signals, or sonar, sent by underwater devices mostly reflect off the surface without ever breaking through. This causes inefficiencies and other issues for a variety of applications such as ocean exploration and submarine-to-plane communication.

Increasing Development Assurance for System and Software Development with Validation and Verification Using ASSERT™

2019-01-137003/19/2019

System design continues to trend toward increasing complexity as more functionality is added to aviation systems and the level of automation is increased. Since exhaustive validation and verification of this functionality becomes increasingly difficult, reliance on development assurance is needed to provide confidence that errors in requirements, design and implementation have been identified and corrected. To address this need for increased development assurance, GE is introducing a tool called ASSERT™ (Analysis of Semantic Specifications and Efficient generation of Requirements-based Tests). The system developer uses this tool to capture requirements in an unambiguous way with built-in semantic error checking. The requirements analysis engine is then used to assist in requirements validation to identify common problems which may include requirements that conflict with one another, requirements that do not fully specify the behavior of a function, requirements that are not independent

McMillan, Craig, Crapo, Andy, Durling, Michael, Li, Meng, Moitra, Abha, Manolios, Panagiotis, Stephens, Mark, Russell, Daniel

Cybersecurity Considerations for Heavy Vehicle Event Data Recorders

11-01-02-000612/14/2018

Trust in the digital data from heavy vehicle event data recorders (HVEDRs) is paramount to using the data in legal contests. Ensuring the trust in the HVEDR data requires an examination of the ways the digital information can be attacked, both purposefully and inadvertently. The goal or objective of an attack on HVEDR data will be to have the data omitted in a case. To this end, we developed an attack tree and establish a model for violating the trust needed for HVEDR data. The attack tree provides context for mitigations and also for functional requirements. A trust model is introduced as well as a discussion on what constitutes forensically sound data. The main contribution of this article is an attack tree-based model of both malicious and accidental events contributing to compromised event data recorder (EDR) data. A comprehensive list of mitigations for HVEDR systems results from this analysis.

Daily, Jeremy, Gardiner, Ben

Integrated Rudder and Brake Pedal Unit, General Requirements for Fly-By Wire Transport and Business Aircraft

ARP6252 (Current)10/15/2018

This Aerospace Recommended Practice (ARP) provides general requirements for a generic, integrated rudder and brake pedal unit, incorporating a passive force-feel system that could be used for fixed-wing fly-by wire transport and business aircraft. This ARP addresses the following: The functions to be implemented The mechanical interconnection between captain and F/O station The geometric and mechanical characteristics The mechanical, electrical, and electronic interfaces The safety and certification requirements

A-6A3 Flight Control and Vehicle Management Systems Cmt

Aerospace - Passive Side Stick Unit General Requirements for Fly by Wire Transport and Business

ARP6001A (Historical)10/04/2018

This SAE Aerospace Recommended Practice (ARP) provides general 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

Guide to Civil Aircraft Electromagnetic Compatibility (EMC)

ARP60493 (Current)10/25/2017

This guide provides detailed information, guidance, and methods for demonstrating electromagnetic compatibility (EMC) on civil aircraft. This guide addresses aircraft EMC compliance for safety and functional performance of installed electrical and electronic systems. The EMC guidance considers conducted and radiated electromagnetic emissions and transients generated by the installed electrical and electronic systems which may affect other installed electrical and electronic systems on the aircraft. Application of appropriate electrical and electronic equipment EMC requirements are discussed. Methods for aircraft EMC tests and analysis are described. This guide does not address aircraft compatibility with the internal electromagnetic environments of portable electronic devices (PED) or with the external electromagnetic environments, such as high-intensity radiated fields (HIRF), lightning, and precipitation static.

AE-4 Electromagnetic Compatibility (EMC) Committee

The Sensitivity of Transient Response Prediction of a Turbocharged Diesel Engine to Turbine Map Extrapolation

2017-24-001909/04/2017

Mandated pollutant emission levels are shifting light-duty vehicles towards hybrid and electric powertrains. Heavy-duty applications, on the other hand, will continue to rely on internal combustion engines for the foreseeable future. Hence there remain clear environmental and economic reasons to further decrease IC engine emissions. Turbocharged diesels are the mainstay prime mover for heavy-duty vehicles and industrial machines, and transient performance is integral to maximizing productivity, while minimizing work cycle fuel consumption and CO2 emissions. 1D engine simulation tools are commonplace for “virtual” performance development, saving time and cost, and enabling product and emissions legislation cycles to be met. A known limitation however, is the predictive capability of the turbocharger turbine sub-model in these tools. One specific concern is accurate extrapolation of turbine performance beyond the narrow region populated by supplier-measured data to simulate non-steady

Mason, Alexander, Costall, Aaron W., McDonald, John R.

Automated Transfer Function Generator

TBMG-2752109/01/2017

When designing or analyzing electrical systems, it is important to understand the relationship between input and output. Power conversion occurs in a “black box,” and transfer functions can be used to provide a better understanding of the processes occurring in this black box. Although they provide a useful analysis tool, transfer functions are not often utilized because they require complicated, time-consuming derivation that ignores nonlinear behavior common in real-world systems.

ENHANCED AIRBORNE FLIGHT RECORDER

ARINC767-1 (Current)05/29/2017

This document is intended to provide design guidance for the development and installation of an Enhanced Airborne Flight Recorder (EAFR). The EAFR standard addresses combinations of any or all of the following in a single Line Replaceable Unit (LRU), a Digital Flight Data Recorder (DFDR) function, a Cockpit Voice Recorder (CVR) function, a data link recording function, and an image recording function. This document does not address the overall flight data recorder system requirements but considers interface and system standards. This document does not replace ARINC Characteristic 747 which defines DFDRs. This document addresses the details of the voice recording function but does not describe the audio distribution system. It does not replace ARINC Characteristic 757 which defines CVRs. The EAFR may be used in a single or dual-redundant installation as permitted by regulation. Both configurations are addressed in this Characteristic.

Airlines Electronic Engineering Committee

SAE International Journal of Transportation Cybersecurity and Privacy

E-JOURNAL-1101/01/2017

Co-Editors: Thomas M. Forest, General Motors Research & Development, USA Kevin Harnett, Department of Transportation (DOT)/Volpe National Transportation Systems Center, USA Dr. André Weimerskirch, Lear Corporation, USA Indexed in CNKI Scopus Author Resources Call for Papers Library Recommendation Form Published Volumes Subscription Options Aims and Scope The SAE International Journal of Transportation Cybersecurity and Privacy is a scholarly publication of original high-quality scientific articles focusing on the Cyber Physical System (CPS) related areas of transportation cybersecurity and privacy. Articles can present methods, tools, implementations, and applications of research in transportation cybersecurity and privacy around technologies, cybersecurity engineering process, and security economics and environment. The natural scope includes passenger vehicles and commercial and heavy-duty vehicles, as well as aerospace systems. Additional transportation systems, such as rail and

Information on Hard Landings

AIR5938 (Historical)11/11/2016

This document provides information on the current practices used by commercial and military operators in regards to hard landings (or overload events designated as hard landings). Since detailed information on inspections would be aircraft specific, this AIR provides only a general framework. Detailed information and procedures are available in the maintenance manuals for specific aircraft. Because hard landings potentially affect the entire aircraft, guidelines are listed here for non-landing gear areas. But, the primary focus of the document is the landing gear and related systems. The document may be considered to be applicable to all types of aircraft. This document does NOT provide recommended practices for hard landing inspections, nor does it provide recommendations on the disposition of damaged equipment. Refer to ARP 4915 and ARP 5600. Also, this document does not necessarily address overloads from circumstances other than landings, such as from tow vehicles, runway bumps

A-5B Gears, Struts and Couplings Committee

Information on Hard Landings

AIR5938-TEST-REC (Historical)11/11/2016

A-5B Gears, Struts and Couplings Committee

CONTACTS, ELECTRICAL, CONNECTOR, SOCKET,CRIMP REMOVABLE (FOR AS81714 TERMINAL JUNCTION SYSTEM SERIES II)

AS39029/22C (Historical)08/12/2016

AE-8C1 Connectors Committee

Avionics Upgrades

TBMG-2524808/01/2016

ARC® Avionics Corporation (ARC) Kirkland, WA 425-576-5030

EDIF Connectivity, Volume 2

EIAEDIF2 (Current)06/16/2016

Systems Management Council

Signal compression technology enables E-Fan's flight, potential enhanced ‘black box’ possibilities

15MEIP12_1212/01/2015

V-Nova Ltd. demonstrated the capabilities of its PERSEUS data compression technology for aerospace applications as part of Airbus' all-electric E-Fan technology demonstrator aircraft's flight across the English Channel. During the flight, PERSEUS enabled up- and downstream HD (high-definition, 720p 25 frames/sec) video telemetry over standard, publically accessible 3G mobile networks, with a more than 80% bandwidth reduction compared to traditional technology under similar conditions, said V-Nova.

Broge, Jean L.

Mobility Engineering: December 2015

15MEIP1212/01/2015

Uncertainty quantification The technique is a must for next-generation simulation tools. Oil-pump sizing Researchers from Hinduja Tech investigate options for low friction and power consumption. The future of Indian commercial aviation The growth in traffic that airport modernization has supported has also made a significant contribution to the local and national economies, while the improved infrastructure has been positive for the perception of India in the global market. Driving EVs toward lower cost The race ison to reduce battery and electric-drive systems cost while improving efficiency. Powering on Rolls-Royce's Chief Engineer discusses new technologies that inspire current R&D design and evaluation work as part of its strategic roadmap for future big commercial programs. HMIs extend beyond the cab Telematic functions are being integrated into multi-function user interfaces. Tenneco unveils emission-control solutions for Euro 6c FPT plans engines for complex market New pulse

Signal Compression Technology Enables E-Fan's Flight, Potential Enhanced 'Black Box' Possibilities

TBMG-2357412/01/2015

V-Nova Ltd. demonstrated the capabilities of its PERSEUS data compression technology for aerospace applications as part of Airbus’ all-electric E-Fan technology demonstrator aircraft’s flight across the English Channel.

Multi-Body Model of a Fixed-Wing Large Passenger Aircraft for Nonlinear State Estimation

2015-01-258509/15/2015

This paper proposes a solution for utilizing multi-body models in nonlinear state observers, to directly estimate the loads acting on the aircraft structure from measurement data of sensors that are commonly available on modern aircraft, such as accelerometers on the wing, rate gyros and strain gages. A high-fidelity aeroelastic multi-body model of a fixed-wing large passenger aircraft is presented, suitable for the monitoring of landing maneuvers. The model contains a modally reduced flexible airframe and aerodynamic forces modeled with a doublet-lattice method. In addition, detailed multi-body models of the nose and main landing gear are attached to the flexible structure, allowing to accurately capture the loads during a hard landing event. It is expected that this approach will make way for embedding non-linear multi-body models, with a high number of degrees of freedom, in state estimation algorithms, and hence improve health monitoring applications.

Benoit, Tuur, Lemmens, Yves, Desmet PhD, Wim

COCKPIT VOICE RECORDER (CVR)

ARINC757-6 (Current)08/05/2015

This document provides guidance for the development and installation of a Cockpit Voice Recorders (CVR) with solid-state memory. Supplement 6 provides the following: " The optional interfaces to data link services and On-Board Maintenance System (OMS) were revised to clarify that if the optional interface is implemented, then it shall be implemented in a specific way. " The power input section was revised to clarity the need for the CVR to be designed to accept 115 Vac power and 28 Vdc power from the aircraft. " The time correlation requirement was revised to specify that the CVR should receive its time signal from the same source as the Flight Data Recorder (FDR). " The OMS interface was updated to describe the correct ARINC 429 Sign Status Matrix (SSM) encoding for new CVR designs.

Airlines Electronic Engineering Committee

Shape Optimization by an Adjoint Solver based on a near-wall Turbulence Model

2015-01-135804/14/2015

The aim of this paper is to present the adjoint equations for shape optimization derived from steady incompressible Navier-Stokes (N-S) equations and an objective functional. These adjoint Navier-Stokes equations have a similar form as the N-S equations, while the source terms and the boundary conditions depend on the chosen objective. Additionally, the gradient of the targeted objective with respect to the design variables is calculated. Based on this, a modification of the geometry is computed to arrive at an improved objective value. In order to find out, whether a more sophisticated approach is needed, the adjoint equations are derived by using two different approaches. The first approach is based on the frozen turbulence assumption and the second approach, which is advanced in this paper, is derived from the near wall k − ζ − f turbulence model. Furthermore, it is important to note that the adjoint method based on the k − ε turbulence model usually requires the use of adjoint wall

Rainer, Matthias, Haase, Gundolf, Basara, Branislav, Offner, Guenter

Survivability of Event Data Recorder Data in Exposure to High Temperature, Submersion, and Static Crush

2015-01-144904/14/2015

Event data recorder (EDR) data are currently only required to survive the crash tests specified by Federal Motor Vehicle Safety Standard (FMVSS) 208 and FMVSS 214. Although these crash tests are severe, motor vehicles are also exposed to more severe crashes, fire, and submersion. Little is known about whether current EDR data are capable of surviving these events. The objective of this study was to determine the limits of survivability for EDR data for realistic car crash conditions involving heat, submersion, and static crush. Thirty-one (31) EDRs were assessed in this study: 4 in the pilot tests and 27 in the production tests. The production tests were conducted on model year (MY) 2011-2012 EDRs enclosed in plastic, metal, or a combination of both materials. Each enclosure type was exposed to 9 tests. The high temperature tests were divided into 3 oven testing conditions: 100°C, 150°C, and 200°C. In the submersion tests, EDRs were submerged to a depth of 3 meters in either distilled

Tsoi, Ada H., Hinch, John, Winterhalter, Michael, Gabler, H.

Wheel and Wheel Trim Weathering Testing for Paint Coatings

J2633_201503 (Historical)03/19/2015

Wheel Standards Committee

Flight Imagery Recorder Locator (FIRLo) and High-Temperature Radome

TBMG-21266

01/01/2015

LDSD (Low Density Supersonic Decelerator) is a Mars EDL (entry, descent, and landing) Technology Development Project that launches three test vehicles out of the Pacific Missile Range Facility in Kauai. On the test vehicle, most mission science data can be recorded safely on land; however, high-speed and high-resolution imagery cannot be telemetered due to bandwidth constraints. Therefore, all information had to be recorded solely onboard the test vehicle; this unit is called the flight imagery recorder (FIR). A typical commercial airliner “black box” is only capable of recording on the order of gigabytes of data, whereas this work required on the order of terabytes (a few orders of magnitude larger).