New IMA architecture approach based on IMA resources

Kornek-Percin, Beatrice; Petersen, Benno; Reichle, Martin; Bader, Joachim

doi:10.1109/dasc.2015.7311442

Cited by 10 publications

(2 citation statements)

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“…By placing these close to "IO hotspots" the signals of peripherals like sensors and actuators can be concentrated locally and transformed into signals transmitted over a high-speed data network, which connects all IMA modules. One evolutionary step further, is the introduction of hybrid modules containing additional computing resources to host applications while being distributed remotely (Kornek-Percin et al, 2015). In general, the IMA platform is considered a provider system for computation power and data transmission in the scope of all aircraft OBS.…”

Section: Characteristics Of Avionics Designmentioning

confidence: 99%

Seamless Transitions from Logical to Physical Avionics Architecture Models for Preliminary Aircraft Systems Design

Broehan,

Kuelper,

Thielecke

2023

INCOSE International Symp

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The transition of federated aviation electronics (avionics) systems to Integrated Modular Avionics (IMA) concepts leads to a higher integration of functions, which reduces the amount of equipment and therefore system mass. However, these benefits are accompanied by a strong increase in system complexity and more interdependencies. Moreover, further digitalization and automation of aircraft functions lead to a higher impact of avionics in terms of equipment number and energy consumption. One challenge arises from the fact that the IMA platform design starts in parallel to the design of other aircraft on‐board systems, for which the platform shall provide resources like computing power. This leads to a high uncertainty during early design phases on the one hand and to a complex design process including many data and tool interfaces on the other hand. In order to meet these challenges, seamless model‐based design approaches are being broadly investigated. For this purpose, standardized and automated interfaces between different design steps, tools, and stakeholders are needed. In this work, a formalized avionics architecture design process is proposed to support a seamless model‐based tool chain from systems architecting to detailed system design. Methods to handle uncertainties, to provide standardized model interfaces, and to automate transitions between model abstraction levels are included. Overall, this reduces manual effort and the introduction of errors that would lead to high costs during system implementation.

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Section: Characteristics Of Avionics Designmentioning

confidence: 99%

Seamless Transitions from Logical to Physical Avionics Architecture Models for Preliminary Aircraft Systems Design

Broehan,

Kuelper,

Thielecke

2023

INCOSE International Symp

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“…Meanwhile, the backplane bus applied in the field of industrial measurement and control is usually extended on the basis of the general backplane bus such as extending the PCI bus to the PXI bus [4] and the VME bus to the VXI bus [5]. With the development of the new generation integrated modular avionics (IMA) system [6], data communication between line replaceable modules (LRMs) requires higher reliability, high fault tolerance, and fault isolation of the system. Therefore, Honeywell proposed the ARINC 659 bus standard which provides the highest level of reliability, integrity, and redundancy among the currently used aviation data buses [7,8].…”

Section: Introductionmentioning

confidence: 99%

Implementation of ARINC 659 Bus Controller for Space-Borne Computers

et al. 2019

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As one of the key technologies of Honeywell, the aeronautical radio incorporated (ARINC) 659 bus is popular in current space-borne computers. However, Honeywell does not design ARINC 659 bus controller separately, and there are only a few papers about FPGA-based ARINC 659 bus controllers. Accordingly, to promote the extremely high performance needs of space-borne computers, this paper designs an ARINC 659 bus controller chip which integrates two independent bus interface units (BIUs), one 8-bit MCU, and several peripheral interfaces (i.e., UART, SPI, and I2C). Because the two BIUs are identical and mutually checked, the symmetry problem is emphatically dealt with in the design of this bus controller, and effective timing convergence is realized, which makes the bus controller work reliably and stably. In addition, due to the circuit’s large scale, design for testability (DFT) is also considered. Accordingly, on-chip clock (OCC) and scanning compression test technique are used to realize the at-speed test and shorten the test time, respectively.

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Model-based transition of IMA architecture into configuration data

Halle

Thielecke

2016

2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)

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New IMA architecture approach based on IMA resources

Cited by 10 publications

References 0 publications

Seamless Transitions from Logical to Physical Avionics Architecture Models for Preliminary Aircraft Systems Design

Seamless Transitions from Logical to Physical Avionics Architecture Models for Preliminary Aircraft Systems Design

Implementation of ARINC 659 Bus Controller for Space-Borne Computers

Model-based transition of IMA architecture into configuration data

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