International Telemetering Conference Proceedings / November 04-07, 1991 / Riviera Hotel and Convention Center, Las Vegas, Nevada / During the requirements definition process for a new telemetry and data acquisition product, Veda Systems engineers had the opportunity to examine the requirements for the ideal bus architecture to support future needs. Design goals and requirements were solicited from major users in flight test, space ground station data monitoring and command applications, and C41, as well as Veda’s own engineers. The process resulted in a bus architecture design which could potentially set the standard for the next generation of telemetry and data acquisition systems. This paper outlines the design goals selected and the thought process that yielded the goals in an attempt to promote advancement of current bus design approaches and increased availability of standard architectures and operating environments.

International Telemetering Conference Proceedings / October 26-29, 1992 / Town and Country Hotel and Convention Center, San Diego, California / This paper gives detailed ideas and methods about the design and development of high performance MIL-STD-1773 airborne fiber optic data bus. To reject impulsive interference efficaciously, the large core and large numerical aperture fiber optics are adopted, as well as high- emitted power LEDs and a low noise optical receiver structure to get high signal-to-noise ratio at decision time. Two new modulation technique----digital frequency shift keying and partial tri-level Manchester are recommended, which are very attractive in the design of modern optical bus. Meanwhile, VLSI chips COM1553B are used to construct bus control interface unit, thus many advantages have been brought out.

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International Telemetering Conference Proceedings / October 22-25, 2001 / Riviera Hotel and Convention Center, Las Vegas, Nevada / NASA/Marshall Space Flight Center (MSFC) is continually looking for methods to reduce cost and schedule while keeping the quality of work high. MSFC is NASA’s lead center for space transportation and microgravity research. When supporting NASA’s programs several decisions concerning the avionics system must be made. Usually many trade studies must be conducted to determine the best ways to meet the customer’s requirements. When deciding the flight data system, one of the first trade studies normally conducted is the determination of the data bus architecture. The schedule, cost, reliability, and environments are some of the factors that are reviewed in the determination of the data bus architecture. Based on the studies, the data bus architecture could result in a proprietary data bus or a commercial data bus. The cost factor usually removes the proprietary data bus from consideration. The commercial data bus architecture’s range from Versa Module Euro card (VME) to Compact PCI to STD 32 to PC 104. If cost, schedule and size are prime factors, VME is usually not considered. If the prime factors are cost, schedule, and size then Compact PCI, STD 32 and PC 104 are the choices for the data bus architecture. MSFC’s center director has funded a study from his discretionary fund to determine an optimal low cost commercial data bus architecture. The goal of the study is to functionally and environmentally test Compact PCI, STD 32 and PC 104 data bus architectures. This paper will summarize the results of the data bus architecture study.

ITC/USA 2005 Conference Proceedings / The Forty-First Annual International Telemetering Conference and Technical Exhibition / October 24-27, 2005 / Riviera Hotel & Convention Center, Las Vegas, Nevada / This paper suggests a reconfigurable sensor network (data bus) which is well suited for telemetry mission of rockets and launch vehicles. Reconfiguration of sensors’ channel information can be achieved without additional software and hardware. The proposed network consists of a central unit and multiple remote units with RS-485 data bus. Since those units need only an FPGA and a programmable ROM to be implemented, the network can provide minimum costs and high reliability. And this paper also presents reliability prediction result of a unit based on MIL-HDBK-217F and Monte Carlo simulation.

International Telemetering Conference Proceedings / October 23-26, 2000 / Town & Country Hotel and Conference Center, San Diego, California / Selecting an airborne data acquisition system involves compromises. No single data acquisition system can be at the same time, lowest cost, smallest, easiest to use and most accurate. The only way to come to a reasonable decision is to carefully plan the project, taking into account what measurements will be required, what are the physical environments involved, what personnel and resources will be needed and of course, how much money is available in the budget? Getting the right mix of equipment, resources and people to do the job within the schedule and the budget is going to involve a number of tradeoffs. A good plan and a thorough knowledge of available resources and equipment will allow you make the necessary decisions. Hopefully, this paper will offer some suggestions that will aid in preparing your plan and give some insight into available system alternatives.

ITC/USA 2011 Conference Proceedings / The Forty-Seventh Annual International Telemetering Conference and Technical Exhibition / October 24-27, 2011 / Bally's Las Vegas, Las Vegas, Nevada / The higher bandwidth capacities available with the adoption of Ethernet technology for networked FTI data acquisition systems enable more data to be acquired by the Data Acquisition Unit (DAU) from high-speed data busses, with higher channel densities, faster sampling rates, and sample resolution. Ethernet offers increased flexibility, interoperability, and simplicity in terms of the FTI system topology. However, the adoption of Ethernet has numerous implications for the design and operation of the DAU in terms of supporting network protocols for synchronization, configuration, and the transmission of the acquired data. This paper explores these issues and discusses the merits of adopting Ethernet.

<p>The main purpose of a Flight Data Recorder (FDR) is to facilitate the investigation of incidents. In order to interpret the data that has been recorded in the FDR the data has to be visualized in some way. This can be done with software on a computer or with hardware that is specific for the model of aircraft that the data originates from.</p><p>The aim of this project is to visualize data for six parameters from the FDR of Saab 2000 in an avionics rig. The avionics rig resembles the cockpit of Saab 2000 and the displays in it are identical to the ones found in the plane. All six parameters are shown on the same display.</p><p>Due to safety regulation vital systems in aircraft are doubled, with one system on the left side and one on the right. Because of the architecture of the rig it was decided that data from the right-hand side systems were to be visualized on the right-hand side display. It is not possible to guarantee that no incorrect values are shown for the parameter altitude when values are taken from the right-hand side, but it can be done for values from the left side. This is the reason why values are taken from the left-hand side for altitude. In the rig a computer with an ARINC429-card and the software Data Bus Analyzer was accessible to transmit data to the displays. DBA can save received data in ASCII-files and also open and transmit the data in such files. Data that has been extracted from an FDR can be converted to the format which DBA can read with macros that have been written in the project. After conversion the data can be transmitted to the display on which it is supposed to be visualized.</p>

The main purpose of a Flight Data Recorder (FDR) is to facilitate the investigation of incidents. In order to interpret the data that has been recorded in the FDR the data has to be visualized in some way. This can be done with software on a computer or with hardware that is specific for the model of aircraft that the data originates from. The aim of this project is to visualize data for six parameters from the FDR of Saab 2000 in an avionics rig. The avionics rig resembles the cockpit of Saab 2000 and the displays in it are identical to the ones found in the plane. All six parameters are shown on the same display. Due to safety regulation vital systems in aircraft are doubled, with one system on the left side and one on the right. Because of the architecture of the rig it was decided that data from the right-hand side systems were to be visualized on the right-hand side display. It is not possible to guarantee that no incorrect values are shown for the parameter altitude when values are taken from the right-hand side, but it can be done for values from the left side. This is the reason why values are taken from the left-hand side for altitude. In the rig a computer with an ARINC429-card and the software Data Bus Analyzer was accessible to transmit data to the displays. DBA can save received data in ASCII-files and also open and transmit the data in such files. Data that has been extracted from an FDR can be converted to the format which DBA can read with macros that have been written in the project. After conversion the data can be transmitted to the display on which it is supposed to be visualized.

International Telemetering Conference Proceedings / October 26-29, 1992 / Town and Country Hotel and Convention Center, San Diego, California / MIL-STD-1553 multiplex data buses are commonly used to link complex software-controlled systems in modern aircraft. The software in these aircraft is routinely updated; each update requires flight testing. Also, sophisticated weapons and electronic warfare systems which are integrated into operationally-ready aircraft must be routinely evaluated. The simplest way to perform the required evaluation is to record all the data from the multiplex data buses during an operational flight; these data can then be replayed and examined after the flight. Traditionally, some operational systems had to be disabled or removed from an aircraft to allow installation of a data acquisition system. This paper discusses a MILSTD- 1553 multiplex bus Record-All Small Data Acquisition System (RASDAS) installed in a McDonnell Douglas CF-188 fighter aircraft to record all data from two 1553 multiplex data buses without displacing any operational equipment. The specific requirements and constraints associated with evaluating the integrated systems of a CF-188 aircraft are examined; further, RASDAS implementation in this aircraft type is discussed from planning to flight evaluation.