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Viewing 1 to 30 of 1983
2016-09-20
Technical Paper
2016-01-1980
Syama M. Rao, Dineshkumar M
Abstract This paper studies admissible state trajectories for an unmanned aerial vehicle(UAV) by performing dynamic soaring technique in the wind gradient. An optimization problem is formulated by employing direct optimal piece wise control. A 3-DOF point mass model system dynamics of UAV is considered. The bank angle and lift co-efficient are identified as control variables. A UAV of mass 5.44kg is considered for this study. Performance measures considered are maximization of specific energy and maximization of specific energy rate extracted by the vehicle, and minimization of the control effort. The effects of linear and parabolic wind gradient on maximizing the specific energy of an autonomous dynamic soaring UAV is also studied and minimum linear gradient required is found. The loop radius of the loiter pattern is maximized for applications like surveillance and patrolling of a localized area along with energy maximization as objective function.
2016-09-20
Journal Article
2016-01-2051
Andreas Himmler, Lars Stockmann, Dominik Holler
Abstract The application of a communication infrastructure for hybrid test systems is currently a topic in the aerospace industry, as also in other industries. One main reason is flexibility. Future laboratory tests means (LTMs) need to be easier to exchange and reuse than they are today. They may originate from different suppliers and parts of them may need to fulfill special requirements and thus be based on dedicated technologies. The desired exchangeability needs to be achieved although suppliers employ different technologies with regard to specific needs. To achieve interoperability, a standardized transport mechanism between test systems is required. Designing such a mechanism poses a challenge as there are several different types of data that have to be exchanged. Simulation data is a prominent example. It has to be handled differently than control data, for example. No one technique or technology fits perfectly for all types of data.
2016-09-20
Technical Paper
2016-01-2052
Virgilio Valdivia-Guerrero, Ray Foley, Stefano Riverso, Parithi Govindaraju, Atiyah Elsheikh, Leonardo Mangeruca, Gilberto Burgio, Alberto Ferrari, Marcel Gottschall, Torsten Blochwitz, Serge Bloch, Danielle Taylor, Declan Hayes-McCoy, Andreas Himmler
Abstract This paper presents an overview of a project called “Modelling and Simulation Tools for Systems Integration on Aircraft (MISSION)”. This is a collaborative project being developed under the European Union Clean Sky 2 Program, a public-private partnership bringing together aeronautics industrial leaders and public research organizations based in Europe. The provision of integrated modeling, simulation, and optimization tools to effectively support all stages of aircraft design remains a critical challenge in the Aerospace industry. In particular the high level of system integration that is characteristic of new aircraft designs is dramatically increasing the complexity of both design and verification. Simultaneously, the multi-physics interactions between structural, electrical, thermal, and hydraulic components have become more significant as the systems become increasingly interconnected.
2016-09-20
Technical Paper
2016-01-2034
Tobias Kreitz, Frank Thielecke
Abstract The aviation industry is facing major challenges due to increased environmental requirements that are driven by economic constraints. For this reason, guidelines like "Flightpath 2050", the official guide of European aviation, call for significant reductions in pollutant emissions. The concept of the More Electric Aircraft offers promising perspectives to meet these demands. A key-enabler for this concept is the integration of new technologies on board of the next generation of civil transportation aircraft. Examples are electro-mechanical actuators for primary and secondary flight controls or the fuel cell technology as innovative electrical energy supply system. Due to the high complexity and interdisciplinarity, the development of such systems is an equally challenging and time-consuming process.
2016-09-20
Technical Paper
2016-01-2039
Prashant S. Vadgaonkar, Ullas Janardhan
Avionics industry is moving towards fly-by wire aircrafts with less reliance on mechanical systems leading to increase in the complexity of in-flight hardware elements. RTCA/DO-254 and EUROCAE ED-80 plays a vital role in the design assurance of airborne electronic hardware. RTCA/ DO-254 and EUROCAE ED-80 are the industry standards for Design Assurance Guidance for Airborne Electronic Hardware. The two different agencies FAA and EU regulate and apply this design assurance guidance to the regulatory law in CFR and EASA CS respectively. This paper discusses the need for DO-254 /ED-80 certification in Aerospace industry, the advantages and benefits to the avionics manufacturers. The paper presents the study made on similarities and differences between DO-254/ED-80.
2016-09-20
Technical Paper
2016-01-2069
Zied Aloui, Nawfal Ahamada, Julien Denoulet, Martin Rayrole, Francine Pierre, Marc Gatti
Abstract Avionics is one kind of domain where prevention prevails. Nonetheless failures occur, sometimes due to pilot misreacting, flooded in information. Sometimes information itself would be better verified than trusted. To avoid some kind of failure, it has been thought to add,in midst of the ARINC664 aircraft data network, a new kind of monitoring.
2016-09-20
Technical Paper
2016-01-2067
Qingchuan Shi, Kartik Lakshminarashimhan, Christopher Noll, Eelco Scholte, Omer Khan
Abstract Modern aircraft systems employ numerous processors to achieve system functionality. In particular, engine controls and power distribution subsystems rely heavily on software to provide safety-critical functionality, and are expected to move towards multicore architectures. The computing hardware-layer of avionic systems must be able to execute many concurrent workloads under tight deterministic execution guarantees to meet the safety standards. Single-chip multicores are attractive for safety-critical embedded systems due to their lightweight form factor. However, multicores aggressively share hardware resources, leading to interference that in turn creates non-deterministic execution for multiple concurrent workloads. We propose an approach to remove on-chip interference via a set of methods to spatio-temporally partition shared multicore resources.
2016-09-19
Book
This is the electronic format of the Journal.
2016-09-14
WIP Standard
AIR4886A
The purpose of this document is to establish the requirements for Real-Time Communication Protocols (RTCP). Systems for real-time applications are characterized by the presence of hard deadlines where failure to meet a deadline must be considered a system fault. These requirements have been drive predominantly, but not exclusively, by aerospace type military platforms and commercial aircraft, but are generally applicable to any distributed, real-time, control systems. These requirements are primarily targeted for the Transport and Network Layers of peer to peer protocols, as referenced in the Open System Interconnect Reference Model (2.2.1 and 2.2.2), developed by the International Standards Organization (ISO). These requirements are intended to complement SAE AS4074 (2.1.1) and AS4075 (2.1.2), and future SAE communications standards.
2016-09-14
WIP Standard
AS15532A
The emphasis in this standard is the development of data word and message formats for AS15531 or MIL-STD-1553 data bus applications. This standard is intended as a guide for the designer to identify standard data words and messages for use in avionics systems and subsystems. These standard words and messages, as well as the doumentation format for interface control document (ICD) sheets, provide the basis for defining 15531/1553 systems. Also provided in this standard is the method for developing additional data word formats and messages that may be required by a particular system but are not covered by the formats provided herein. It is essential that any new word formats or message formats that are developed for a 15531/1553 application follow the fundamental guidelines estalbished in this standard in order to ease future standardization of these words an messages. The standard word formats presented represent a composite result of studies conducted by the U.S.
2016-09-14
WIP Standard
AS4074B
This standard specifies the characteristics of the SAE Linear Token Passing Bus (LTPB) Interface Unit. The LTPB provides a high reliability, high bandwidth, low latency serial interconnection network suitable for utilization in real time military and commercial applications. Multiple redundant data paths can be implemented to enhance reliability and survivability in those applications which require these attributes. The token passing and data exchange protocols are optimized to provide low latency and fast failure detection and correction. Physical configurations with bus lengths up to 1000 m can be accommodated.
2016-09-14
WIP Standard
AIR4271A
This Aerospace Information Report (AIR) has been prepared by the Systems Applications and Requirements Subcommittee of SAE Committee AS-2. It is intended to provide guidance primarily, but not exclusively, for specifiers and designers of data communication systems for real time military avionics applications within a platform. The subject of high speed data transmission is addressed from two standpoints 1) the influence of developments in technology on avionics architectures as a whole and 2) the way in which specific problems, such as video, voice, closed loop control, and security may be handled. While the material has been prepared against a background of experience within SAE AS-2 relating to the development of a family of high speed interconnect standards, reference to specific standards and interconnect systems is minimized.
2016-09-14
WIP Standard
AS4074/2B
This slash sheet specifies the operational parameters and characteristics of a particular implementation of the SAE Linear, Token Passing Bus (LTPB) Interface Unit. This slash sheet defines the following: a. the physical media interface: this slash sheet specifies the characteristics of the optical interface to the physical bus media; b. the minimum and maximum timing requirements for operation of this implementation of the LTPB; c. the data coding used to encode and decode the data for transmission; and d. the default values to be loaded into the timers of the LTPB interface at power-up prior to intervention by the host processor.
2016-09-14
WIP Standard
AIR5683A
MIL-STD-1553 establishes requirements for digital command/response time division multiplexing (TDM) techniques on military vehicles, especially aircraft. The existing MIL-STD-1553 network operates at a baud rate of 1 Mbps and is limited by the protocol to a maximum data payload capacity of approximately 700 kilobits per second. The limited capacity of MIL-STD-1553 buses coupled with emering data rich applications for avionics platforms plus the expense involved with changing or adding wires to thousands of aircraft in the fleet has driven the need for expanding the data carrying capacity of the existing MIL-STD-1553 infrastructure.
2016-09-14
WIP Standard
AS4074/3B
This slash sheet specifies the operational parameters and characteristics of a particular implementation of the SAE Linear, Token Passing Bus (LTPB) Interface Unit. This slash sheet defines the following: a. the physical media interface: this slash sheet specifies the characteristics of the optical interface to the physical bus media; b. the minimum and maximum timing requirements for operation of this implementation of the LTPB; c. the data coding used to encode and decode the data for transmission; and d. the default values to be loaded into the timers of the LTPB interface at power-up prior to intervention by the host processor.
2016-09-14
WIP Standard
AS4074/1B
This slash sheet specifies the operational parameters and characteristics of a particular implementation of the SAE Linear, Token Passing Bus (LTPB) Interface Unit. This slash sheet defines the following: a. the physical media interface: this slash sheet specifies the characteristics of the optical interface to the physical bus media; b. the minimum and maximum timing requirements for operation of this implementation of the LTPB; c. the data coding used to encode and decode the data for transmission; and d. the default values to be loaded into the timers of the LTPB interface at power-up prior to intervention by the host processor.
2016-09-14
WIP Standard
AIR4295A
This document contains guidance for using SAE publications, AS 4112 through AS 4117 (MIL-STD-1553 related Test Plans). Included herein are the referenced test plan paragraphs numbers and titles, the purpose of the test, the associated MIL-STD-1553 paragraph, commentary concerning test methods and rationale, and instrumentation requirements.
2016-08-25
WIP Standard
ARP6856
This recommended practice provides users with the technical requirements and methods for accessing, viewing, and processing raw GNSS receiver measurements for improved unmanned vehicle navigation solutions.
2016-08-25
WIP Standard
ARP6857
This recommended practice defines the technical requirements for a terrestrial based PNT system to improve unmanned vehicle navigation solutions and ensure critical infrastructure security.
2016-08-17
WIP Standard
ARP4553B
This SAE Aerospace Recommended Practice (ARP) is intended to provide design and qualification requirements for self-displacing hydraulic accumulators.

These requirements are intended to be included in the Producrement Specification for the accumulator. Those requirements identified by the use of "shall" are considered to be essential requirements; those requirements identified by the use of "should" are considered to be optional requirements for inclusion in the Specificaiton at the discretion of the Purchaser.

In addition, test methods for production acceptance and qualification purposes are provided.

The accumulator is intended for use in military aerospace hydraulic systems with rated pressures of up to 8000 psi (55,158 kPa) and of the following types as specified in SAE AS 5440: Type I: -65 to +160 °F (-54 to +71 °C) fluid temperature; Type II: -65 to +275 °F (-54 to +135 °C) fluid temperature.

2016-08-01
Magazine
Seeing the Light Achieving Full-Color, Day or Night Readability for Flat-Panel Displays Multiple Node Networking Using PCIe Interconnects PCI Express (PCIe) interconnects, and how they can be used to support multiple node low latency data transfers over copper or optical cables, is gaining momentum in embedded computing solutions. Zero-Emissions Electric Aircraft Theory vs Reality Analyzing Radar Signals With Demodulation Combining Software and Hardware for Highly Specialized Multichannel Spectrum Monitoring Advanced Thermal Management Solutions Thermoelectric Cooling Thermal Ground Planes Thermal Management of Laser Diodes The Effect of Substrate Emissivity on the Spectral Emission of a Hot-Gas Overlayer Process Approach to Determining Quality Inspection Deployment Experimental Setup to Assess Blast and Penetration-Induced Secondary Debris in a Military Operations in Urban Terrain (MOUT) Environment Non-Contact Circuit for Real-Time Electric and Magnetic Field Measurements
CURRENT
2016-07-18
Standard
AIR4094A
This SAE Aerospace Information Report (AIR) supplies information on the flight control systems incorporated on various current and historic fixed wing, rotary wing, and tilt rotor aircraft. A brief description of the aircraft is followed by a description of the flight control system, some specific components, drawings of the internal arrangement, block diagrams, and schematics. System operation redundancy management is also presented.
CURRENT
2016-07-12
Standard
AIR6237
The scope of this document is to provide review of recent history of loss-of-control accidents during airline revenue operations.
2016-05-31
WIP Standard
AIR4653A
The information contained in this document is based on line experience with current systems. It should be used as a basis for ongoing research and development including the human factors aspects of future flight management systems and their interaction with the ATC environment.
CURRENT
2016-05-24
Standard
ARP988B
This recommended practice is intended as a guide for the specification of electrohydraulic mechanical feedback servoactuators used for position control. It provides performance definitions and capabilities that are specific to mechanical-feedback servoactuators and different from those applicable to electrical-feedback servoactuators.
CURRENT
2016-05-24
Standard
AS8009C
This SAE Aerospace Standard (AS) specifies minimum performance requirements for pressure altimeter systems other than air data computers. This document covers altimeter systems that measure and display altitude as a function of atmospheric pressure. The pressure transducer may be contained within the instrument display case or located remotely. Requirements for air data computers are specified in AS8002. Some requirements for nontransducing servoed altitude indicators are included in AS791. This document does not address RVSM requirements because general RVSM requirements cannot be independently detailed at the component level. The instrument system specified herein does not include aircraft pressure lines. Unless otherwise specified, whenever the term “instrument” is used, it is to be understood to be the complete system of pressure transducer components, any auxiliary equipment, and display components.
2016-05-17
WIP Standard
JA6268
This Aerospace Recommended Practice (ARP) was created to help industry deal with existing barriers to the successful implementation of Integrated Vehicle Health Management (IVHM) technology in the aerospace and automotive sectors. That is,given the common barriers that exist, this ARP can be applied not only to aerospace but also to the automotive, commercial and military vehicle sectors. Original Equipment Manufacturers (OEMs) in all of these sectors are heavily dependant upon a large number of component suppliers in order to design and build their products. The advent of IVHM technology has accentuated the need for improved coordination and communication between the OEM and its suppliers –to ensure that suppliers design health ready capabilities into their particular components.
2016-05-06
WIP Standard
AS5725C
This standard defines implementation requirements for the electrical interface between: a. aircraft carried miniature store carriage systems and miniature stores b. aircraft parent carriage and miniature stores c. surface based launch systems and miniature stores The interface provides a common interfacing capability for the initialization and employment of smart miniature munitions and other miniature stores from the host systems. Physical, electrical, and logical (functional) aspects of the interface are addressed.
2016-05-05
WIP Standard
AS6523
This data dictionary provides a mathematically coherent set of definitions for quantity types used in data models for unmanned systems. In this data dictionary, a quantity is defined as a property of a phenomenon, substance, or body whose value has magnitude.
Viewing 1 to 30 of 1983

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