Migration of Integrated Modular Avionics to space

Doss, M.; Liebel, K.; Lee, S.; Calcagni, K.; Crum, R.

doi:10.1109/dasc.1996.559146

Cited by 2 publications

(3 citation statements)

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“…SAFEbus has limited bus length, but has a transmission rate of 60 MB/s. It is considered to be very dependable for safety critical functions, but it is very expensive (Doss et al, 1996). The hardware is redundant as a pair of pairs at all levels.…”

Section: Distributed Control In Safety-critical Applications: a Brief Reviewmentioning

confidence: 99%

Design and reliability prediction of a distributed landing gear control system

Lei²

2010

Aircraft Engineering and Aerospace Technology

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Purpose -Proper function of landing gear plays a crucial role in the safe operation of an airplane. Traditional landing gear control system utilizes centralized control technology. The relatively heavy wire harness and low reliability accompanied with this technology make it logical to transfer from traditional control to real-time distributed control. This paper aims to look into a new landing gear control system based on time-triggered architecture (TTA). Design/methodology/approach -In this paper, a new landing gear control system based on TTA is proposed. The reliability of the proposed system is investigated using a combination of Markov analysis and MIL-HDBK-217 methods. Findings -The results show that by integration of TTP/C and TTP/A technologies, the advantages of both are achieved. A very high level of reliability is obtained. This increases the confidence when adopting distributed landing gear control technology. Originality/value -The paper presents a new landing gear control system based on TTA, the reliability of which is very high.

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Section: Distributed Control In Safety-critical Applications: a Brief Reviewmentioning

confidence: 99%

Design and reliability prediction of a distributed landing gear control system

Lei²

2010

Aircraft Engineering and Aerospace Technology

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“…Integrated modular avionics (IMAs) is an answer to complex system design, and its use in UAVs is rising (Lopez et al, 2008). IMA has been widely used since the beginnings of the 1990s, both in aeronautics and space applications (Doss et al, 1996). Being used for the first time in Boeing 777, this technology has led to step improvement The current issue and full text archive of this journal is available at www.emeraldinsight.com/1748-8842.htm in system quality, reliability, safety, and maintainability, while reducing cost (Morgan, 1991).…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Development and validation of on‐board systems control laws

Medici

Viola

Corpino

et al. 2012

Aircraft Engineering and Aerospace Technology

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Purpose -The purpose of this paper is to describe the tool and procedure developed in order to design the control laws of several UAV (Unmanned Aerial Vehicle) sub-systems. The authors designed and developed the logics governing: landing gear, nose wheel steering, wheel braking, and fuel system. Design/methodology/approach -This procedure is based on a general purpose, object-oriented, simulation tool. The development method used is based on three-steps. The main structure of the control laws is defined through flow charts; then the logics are ported to ANSI-C programming language; finally the code is implemented inside the status model. The status model is a Matlab-Simulink model, which uses an embedded Matlabfunction to model the FCC (Flight Control Computer). The core block is linked with the components, but cannot access their internal model. Interfaces between FCCs and system components in the model reflect real system ones. Findings -The user verifies systems' reactions in real time, through the status model. Using block-oriented approach, development of the control laws and integration of several systems is faster. Practical implications -The tool aims to test and validate the control laws dynamically, helping specialists to find out odd logics or undesired responses, during the pre-design. Originality/value -The development team can test and verify the control laws in various failure scenarios. This tool allows more reliable and effective logics to be produced, which can be directly used on the system. NomenclatureDefinitions, acronyms and abbreviations FCC ¼ flight control computer FS ¼ fuel system GCS ¼ ground control station HALE ¼ high altitude long endurance IMA ¼ integrated modular avionic LASE ¼ low altitude short endurance LDG ¼ landing gear system MALE ¼ medium altitude long endurance NWS ¼ nose wheel steering system PS ¼ pressure sensor SOV ¼ shut off valve SSC ¼ supervision and coordination station SMAT ¼ advanced environment monitoring system TCS ¼ tactical control station UAS ¼ unmanned aerial system UAV ¼ unmanned aerial vehicle WBS ¼ wheel braking system WOW ¼ weight on wheels To purchase reprints of this article please

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Migration of Integrated Modular Avionics to space

Cited by 2 publications

References 0 publications

Design and reliability prediction of a distributed landing gear control system

Design and reliability prediction of a distributed landing gear control system

Development and validation of on‐board systems control laws

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