International Telemetering Conference Proceedings / October 26-29, 1992 / Town and Country Hotel and Convention Center, San Diego, California / IRIG 106-86 Chapter 8 describes the standard for acquisition of MIL-STD-1553 traffic flow. All incoming words (command, status, or data) are transmitted and fill words are used to maintain continuous data output. If all incoming words are not needed, or if other data such as sampled analog data from transducers are also to be transmitted, then a different approach is warranted. Selected data from the avionics bus can be placed into predefined PCM words, eliminating the transmission of useless data, and optimizing the bandwidth available to a Class I telemetry system. The engineering considerations and constraints for avionics bus data acquisition and analysis will be explored in this paper.

ITC/USA 2013 Conference Proceedings / The Forty-Ninth Annual International Telemetering Conference and Technical Exhibition / October 21-24, 2013 / Bally's Hotel & Convention Center, Las Vegas, NV / In modern aircraft there is a proliferation of avionics buses. Some of these buses use industry wide standards such as ARINC 429 or AFDX while others are based on proprietary protocols. For many of the newer bus types there can be thousands of parameters on each bus. In a distributed data acquisition system the flight test engineer needs to record all of the data from each bus and monitor selected parameters in real time. There are numerous different approaches to acquiring, transmitting and recording data from avionics buses. In modern FTI there is also a proliferation of standards for recording and transmission including IRIG 106 Chapter 10, iNET and IENA. In this paper some common approaches to bus monitoring are compared and contrasted for popular buses such as ARINC 429, AFDX and Time Triggered Protocol. For each bus type the best approach is selected for reliable acquisition, speed of configuration, low latency telemetry and compact recording which is optimized for playback.

International Telemetering Conference Proceedings / October 17-20, 1994 / Town & Country Hotel and Conference Center, San Diego, California / The Central Multiplexer is a versatile data multiplexer designed to address emerging test requirements for recording data from many sources on digital rotary head recorders at high data rates. A modular design allows easy reconfiguration for airborne or laboratory use; simultaneous data input from 63 sources of data in any combination of PCM commutators, ARINC 429 buses, ARINC 629 buses, MIL- STD-1553 buses, and general-purpose high-speed serial data packets; simultaneous, independent programmable outputs to high-speed digital data recorders, quick-look displays, and engineering monitor and analysis systems; and setup and control from a remote panel, a dumb terminal, a laptop personal computer, a standalone test system, or a large control computer.

The aim of this master’s thesis is a design and a realization of an interface device for various aircraft buses. The work shows the issue of Aircraft Interface Device and describes the most used types of avionics buses. It deals with the theoretical design of the PCI/104–Express module and is using modularity for maximum configurability of the device. The work also brings the selection of appropriate components and their use in design. The last part describes a firmware architecture.

ITC/USA 2008 Conference Proceedings / The Forty-Fourth Annual International Telemetering Conference and Technical Exhibition / October 27-30, 2008 / Town and Country Resort & Convention Center, San Diego, California / ARINC 664 presents the designers of data acquisition systems challenges not previously seen on other aircraft avionic buses. Among the biggest challenges are providing the test instrumentation system with the capacity to process two redundant Ethernet segments that may be carrying packet traffic at near wire-line speed. To achieve this level of performance, the hardware and software must not only perform mundane operations, like time stamping and simple virtual link MAC filtering, but also need to implement core ARINC 664 functions like redundancy management and integrity checking. Furthermore, other TCP/IP operations, such as IP header checksum, must also be offloaded to the hardware in order to maintain real-time operation. This paper describes the implementation path followed by TTC during its development of an ARINC 664 network monitor used in a large commercial aircraft flight test program.

ITC/USA 2007 Conference Proceedings / The Forty-Third Annual International Telemetering Conference and Technical Exhibition / October 22-25, 2007 / Riviera Hotel & Convention Center, Las Vegas, Nevada / The deployment of networks has become ubiquitous in the avionics world, as they have opened the door to a rich suite of common and open hardware and software tools that provide greater functionality and interoperability. Unfortunately, a number of networked avionic and other related applications can be affected by vendor or application specific proprietary implementations. These “closed” implementations may reduce or eliminate the benefits of a standardized network, requiring the customization of the data acquisition system to allow it to properly operate with the other devices. This paper presents the approach that was recently employed for the development of a network interface module that can be quickly reconfigured to address the changing requirements of network applications, including monitoring of industry standard and proprietary networks, or providing the command and data interface to the data acquisition system itself. This reconfigurability of the module is shown in a review of four different specific applications.

The development of the next generation of Saab's multirole combat aircraft the JAS 39 Gripen includes developing a lot of new software for the aircraft's on-board computers. The new software has to be loaded into these computers routinely, in order to carry out testing on it. This is currently a slow and tedious process. In order to load the computers a protocol defined in the ARINC 615A standard is used. Today Saab uses commercial software applications implementing this protocol for the loading process. These applications have significant disadvantages, such as not being able to load several computers in parallel or only being able to load computers from a specific manufacturer. In this thesis we introduce a system using a client-server architecture that allows users to load the computers in parallel, regardless of the manufacturer. In Section 3.2.2 we show that our system reduces the time required to load the aircraft's on-board computers significantly. We also indicate some improvements that can be made in order to speed up the process even further. These improvements mainly involve improving the on-board computers themselves through the use of faster persistent storage and support for later revisions of the protocol involved.

This master's thesis summarizes theory on how to perform data load onto on-board computers of aircrafts. Specifically, how automated data load of Honeywell's Aspire 400 satellite data unit is done. First part of the text describes requirements and possible ways of the data load process, including standards that are applicable to this topic in the aeronautical industry. The second part describes the implementation of the data load process on the aforementioned unit.

ITC/USA 2010 Conference Proceedings / The Forty-Sixth Annual International Telemetering Conference and Technical Exhibition / October 25-28, 2010 / Town and Country Resort & Convention Center, San Diego, California / Modern data acquisition systems can be very time consuming to configure. The most time consuming aspect of configuring a data acquisition system is defining the measurements that the system will collect. Each measurement has to be uniquely identified in the system and the system needs to know what data the measurement will sample. Data acquisition systems are capable of sampling thousands of measurements in a single test flight. If all of the measurements are created by hand, it can take many hours to input all of the required measurements into the data acquisition system's setup software. This process can also be extremely tedious since many measurements are very similar. This paper will examine several possible solutions to the problem of rapidly creating large numbers of data acquisition measurements. If the list of measurements that need to be created already exists in an electronic format then the simplest approach would be to create an importer. The two main ways to import data are XML and comma separated value files. This paper will discuss the advantages and disadvantages of both approaches. In addition to importers, this paper will discuss a system that can be used to create large numbers of similar measurements very quickly. This system is ideally suited to MILSTD- 1553 and ARINC-429 bus data. It exploits the fact that most bus measurements are typically very similar to each other. For example, 1553 measurements typically differ only in terms of the command word and the selected data words. This system allows the user to specify ranges of data words for each command word. It can then create the measurements based on the user specified ranges.

International Telemetering Conference Proceedings / October 13-16, 1986 / Riviera Hotel, Las Vegas, Nevada / The Boeing Commercial Airplane Company presently uses an Airborne Data Analysis and Monitor System (ADAMS) to support extensive qualification testing on new and modified commercial aircraft. The ADAMS system consists of subsystems controlled by independent processors which preprocess serial PCM data, perform application-specific processing, provide graphic display of data, and manage mass storage resources. Setup and control information is passed between processors using the Ethernet protocol on a fiber optic network. Tagged data is passed between processors using a data bus with networking characteristics. During qualification tests, data are dynamically selected, analyses performed, and results recorded. Decisions to proceed or repeat tests are made in real time on the aircraft. Instrumentation in present aircraft includes up to 3700 sensors, with projections for 5750 sensors in the next generation. Concurrently, data throughput rates are increasing, and data preprocessing requirements are becoming more complex. Fairchild Weston Systems, Inc., under contract to Boeing, has developed an Acquisition Interface Assembly (AIA) which accepts multiple streams of PCM data, controls recording and playback on analog tape, performs high speed data preprocessing, and distributes the data to the other ADAMS subsystems. The AIA processes one to three streams in any of the standard IRIG PCM formats using programmable bit, frame and subframe synchronizers. Data from ARINC buses with embedded measurement labels, bus ID’s, and time tags may also be processed by the AIA. Preprocessing is accomplished by two high-performance Distributed Processing Units (DPU) operating in either pipeline or parallel environments. The DPU’s perform concatenation functions, number system conversions, engineering unit conversions, and data tagging for distribution to the ADAMS system. Time information, from either a time code generator or tape playback, may be merged with data with a 0.1 msec resolution. Control and status functions are coordinated by an embedded processor, and are accessible to other ADAMS processors via both the Ethernet interface and a local operator’s terminal. Because the AIA assembly is used in aircraft, the entire functional capability has been packaged in a 14-inch high, rack-mountable chassis with EMI shielding. The unit has been designed for high temperature, high altitude, vibrating environments. The AIA will be a key element in aircraft qualification testing at Boeing well into the next generation of airframes, and specification, design, development, and implementation of the AIA has been carried out with the significance of that fact in mind.