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Sunday, July 12, 2020 | History

2 edition of Cost and benefits optimization model for fault-tolerant aircraft electronic systems found in the catalog.

Cost and benefits optimization model for fault-tolerant aircraft electronic systems

Cost and benefits optimization model for fault-tolerant aircraft electronic systems

final report.

  • 239 Want to read
  • 0 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center in Hampton, Va .
Written in English

    Subjects:
  • Airplanes -- Electronic equipment.

  • Edition Notes

    SeriesNASA contractor report -- 166043., NASA contractor report -- NASA CR-166043.
    ContributionsLangley Research Center., Boeing Commercial Airplane Company.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17667527M

    It makes an interesting case study, since the pilots were able to keep the aircraft in the air for a full 10 minutes before the crash, which is a reasonable amount of time for an online fault-tolerant system to take effect. The approach that we took in this case is (not surprisingly) based on model-predictive control. We address a fault tolerant control (FTC) issue about an unmanned aerial vehicle (UAV) under possible simultaneous actuator saturation and faults occurrence. Firstly, the Takagi-Sugeno fuzzy models representing nonlinear flight control systems (FCS) for an UAV with unknown disturbances and actuator saturation are established. Then, a normal H >-infinity tracking controller is presented using Cited by: 5.

    The paper presents fault tolerant operation in an aero engine based on real-time systems which is built for a very small set of mission-critical applications like space craft’s, avionics and.   A fault-tolerant air data and inertial navigation reference system utilizes skewed axis inertial sensors and fault-tolerant redundant electronics to provide higher redundancy with fewer parts. Parallelly operating processor circuits each receive the individual outputs of six skewed-axis gyros and six skewed-axis accelerometers.

    Correlation power analysis with a leakage model. In Marc Joye and Jean-Jacques Quisquater, editors, Cryptographic Hardware and Embedded Systems –CHES , volume of Lecture Notes in Computer Science, pages 16– Springer, Berlin, Heidelberg, August 1. Introduction. Any conventional aircraft utilizes a combination of hydraulic, electric, pneumatic and mechanical power transfer systems. Increasing use of electric power is seen as the direction of technological opportunity for advanced aircraft power systems based on rapidly evolving technology advancements in power electronics, fault-tolerant electrical power distribution systems and Cited by:


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Cost and benefits optimization model for fault-tolerant aircraft electronic systems Download PDF EPUB FB2

Cost and benefits optimization model for fault-tolerant aircraft electronic systems: final report. Fault Tolerant Architectures for Integrated Aircraft Electronics Systems Task 2 Karl N.

Levitt P. Michael Melliar-Smith Richard L. Schwartz SRI International Menlo Park, California Contract NAS June N/ A National Aeronautics and Space Aclm_n_strat_on LangleyResearchCenter Hampton Cited by: 2. Multiobjective optimization of fault-tolerant aircraft systems considering system degradation Chapter August with 68 Reads How we measure 'reads'.

An integrated design that combines sliding mode control with adaptive control to provide a robust fault tolerant flight controller that works for a wide range of faults is proposed in this : Afef Fekih. Reconfigurable Flight Control System for Fighter Aircraft Using MPC: Fault Tolerant Flight Control Design for Aircraft Utilizing Robustness Characteristics of Model Predictive Control [Bilal Siddiqui] on *FREE* shipping on qualifying offers.

In this work we studied Reconfigurable Flight Control Systems to achieve acceptable performance of a fighter aircraftAuthor: Bilal Siddiqui. A new scheme of robust fault-tolerant control allocation is designed for a discrete-time aerodynamic model in a research environment (ADMIRE) aircraft model in this paper.

The control strategy has two steps. In the first step, a discrete-time robust virtual controller is designed to produce three axis moments. benefits studies X-Planes: Near and Mid-term NASA Electrified Aircraft Technology (NEAT) Goal: Flight tests, ground demo’s and technology readiness by to support Entry into Service • Design and test electrified airplane powertrains that are flightweight, safe, reliable, fault tolerant • NASA’s STARC-ABL configuration to be.

power to optimize the performance and life cycle cost of the aircraft. The MEA requires a highly reliable, fault tolerant, autonomously controlled electrical power system to deliver higher quality power and electrical levels to the aircraft's 4 IEEE A&E SYSTEMS MAGAZINE, MARCH Loa _J s Engine syýpenis.

Huisman, H.O.: Fault tolerant flight control based on real-time physical model identification and nonlinear dynamic inversion. Master’s thesis, Delft University of Technology, Faculty of Aerospace Engineering, Control and Simulation Division, June 20 () Google ScholarCited by: 1.

constraints (weight, power consumption and overall cost), taking different maintenance and repair modes into consideration. Keywords. Unmanned aerial vehicle (UAV), flight control system, structural optimization, reliability model, fault-tolerant system.

Key Terms. Structural Design Optimization, Mathematical Modeling, Markov modelAuthor: Yuriy Pashchuk, Bohdan Volochiy, Yuriy Salnyk, Volodymyr Ozharevskyi. This paper proposes a reliability monitoring scheme for active fault tolerant control systems using a stochastic modeling method.

The reliability index is defined based on system dynamical responses and a safety region; the plant and controller are assumed to have a multiple regime model structure, and a semi-Markov model is built for reliability evaluation based on the safety behavior of each Cited by: 5.

architectures are possible for future aircraft systems. The difficulty is to achieve the same safety and availability requirements with additional operational reliability (required by airlines). The challenge that faces the engineers is to design mass-produced fault-tolerant systems with reasonable cost.

(AvSP). Thus, fault tolerant control (FTC) for a transport aircraft plays an important role in preventing LOC aircraft accidents due to control upset or failure. The concept of FTC has been used for various applica-tions [6]–[8] including flight control.

In general, the FTC systems can be categorized into two classes: passive and active [9]. A trajectory tracking system based on the proposed fault-tolerant model predictive controller is demonstrated using the ground simulator of the VFW ATTAS (Advanced Technologies Testing Aircraft System), showing feasibility and adequate performance.

Keywords: Model predictive control, Fault-tolerant control, Domain of attraction, Target. The benefits are considerable in terms of cost, efficiency, and reduced pilot risk.

In order to complete a mission efficiently and with a high level of safety and security, the following key design points must be met: • the flight control system must be robust against the.

Fault tolerance is achieved through multiply redundant hardware systems in large civil aircraft. This means of achieving fault tolerance is infeasible for small compact unmanned aerial vehicles. In this paper we apply a fault tolerant control system which exploits analytical redundancy rather than hardware redundancy to an actual UAV model currently in operation via model-in-the-loop Cited by: 1.

Reconfigurable Fault Tolerant Flight Control based on Nonlinear Model Predictive Control D. Kufoalor and T. Johansen Abstract—Constrained Nonlinear Model Predictive Control (NMPC) is shown to have potentials for reconfigurable fault tolerant control of highly nonlinear, intrinsically unstable, high performance Size: KB.

PROCEEDINGS OF THE IEEE, VOL, NO. 10, OCTOBER SIFT: Design and Analysis of a Fault-Tolerant Computer for Aircraft Control JOHN H. WENSLEY, LESLIE LAMPORT, JACK GOLDBERG, SENIOR MEMBER, IEEE, AND CHARLES B. WEINSTOCK MILTON W. GREEN, KARL N. LEVI'IT, P.

MELLIAR-SMITH, ROBERT E. SHOSTAK, Abstmt-SIFT (Softwue Implemented Fault Cited by: Fault Tolerant Control Design for the Longitudinal Aircraft Dynamics using Quantitative Feedback Theory Daniel Ossmann Institute of System Dynamics and Control German Aerospace Center (DLR), Wessling, Germany Flight control laws of modern aircraft are scheduled with respect to.

Unless the voter is per/ect, NVP does not compete cost-wise with the other two methods. Indeed, in some cases it is worse than a simph'x system. cost modelling,fault-tolerant software, system reliabilio" There have been some attempts to model the cost of multiversion fault-tolerant by: 4.

Looye, Gertjan und Lombaerts, Thomas und Chu, Qiping und Mulder, Jan Albert () Design and simulation of fault tolerant flight control based on a physical approach. Aerospace Science and Technology, 23 (1), Seiten Elsevier.

DOI: / ISSN Dieses Archiv kann nicht den gesamten Text zur Verfügung by: In the integrated flight propulsion control system, the integration control laws are developed as an off-line process and stored in an on-board computer for implementation. Also real-time optimization improves the performance further compared to pre-programmed optimization.

This results in an optimum integrated flight propulsion control.operating cost and hence the wavering power quality. To demonstrate the e ectiveness of the novel methodology, the FTC system will be initially applied on a wind turbine system and will be further employed for other renewable energy systems.

Keywords Fault tolerant control, fault diagnosis, economic model predictive control, wind turbine.