Integral equation mei applied to three-dimensional arbitrary surfaces

The authors present a new formulation of the integral equation of the measured equation of invariance (MEI) as a confined field integral equation discretised by the method of moments, in which the use of numerically derived testing functions results in an approximately sparse linear system with storage memory requirements and a CPU time for computing the matrix coefficients proportional to the number of unknowns.Peer ReviewedPostprint (published version

A Fault Tolerant System for an Integrated Avionics Sensor Configuration

An aircraft sensor fault tolerant system methodology for the Transport Systems Research Vehicle in a Microwave Landing System (MLS) environment is described. The fault tolerant system provides reliable estimates in the presence of possible failures both in ground-based navigation aids, and in on-board flight control and inertial sensors. Sensor failures are identified by utilizing the analytic relationships between the various sensors arising from the aircraft point mass equations of motion. The estimation and failure detection performance of the software implementation (called FINDS) of the developed system was analyzed on a nonlinear digital simulation of the research aircraft. Simulation results showing the detection performance of FINDS, using a dual redundant sensor compliment, are presented for bias, hardover, null, ramp, increased noise and scale factor failures. In general, the results show that FINDS can distinguish between normal operating sensor errors and failures while providing an excellent detection speed for bias failures in the MLS, indicated airspeed, attitude and radar altimeter sensors

Statistical methods for rapid system evaluation under transient and permanent faults

textTraditional solutions for test and reliability do not scale well for modern designs with their size and complexity increasing with every technology generation. Therefore, in order to meet time-to-market requirements as well as acceptable product quality, it is imperative that new methodologies be developed for quickly evaluating a system in the presence of faults. In this research, statistical methods have been employed and implemented to 1) estimate the stuck-at fault coverage of a test sequence and evaluate the given test vector set without the need for complete fault simulation, and 2) analyze design vulnerabilities in the presence of radiation-based (soft) errors. Experimental results show that these statistical techniques can evaluate a system under test orders of magnitude faster than state-of-the-art methods with a small margin of error. In this dissertation, I have introduced novel methodologies that utilize the information from fault-free simulation and partial fault simulation to predict the fault coverage of a long sequence of test vectors for a design under test. These methodologies are practical for functional testing of complex designs under a long sequence of test vectors. Industry is currently seeking efficient solutions for this challenging problem. The last part of this dissertation discusses a statistical methodology for a detailed vulnerability analysis of systems under soft errors. This methodology works orders of magnitude faster than traditional fault injection. In addition, it is shown that the vulnerability factors calculated by this method are closer to complete fault injection (which is the ideal way of soft error vulnerability analysis), compared to statistical fault injection. Performing such a fast soft error vulnerability analysis is very cruicial for companies that design and build safety-critical systems.Electrical and Computer Engineerin

An aircraft sensor fault tolerant system

The design of a sensor fault tolerant system which uses analytical redundancy for the Terminal Configured Vehicle (TCV) research aircraft in a Microwave Landing System (MLS) environment was studied. The fault tolerant system provides reliable estimates for aircraft position, velocity, and attitude in the presence of possible failures in navigation aid instruments and onboard sensors. The estimates, provided by the fault tolerant system, are used by the automated guidance and control system to land the aircraft along a prescribed path. Sensor failures are identified by utilizing the analytic relationship between the various sensor outputs arising from the aircraft equations of motion