Model-driven development of reliable avionics architectures for Lunar Surface Systems

Borer, Nicholas K.; Claypool, I.; Clark, David; West, John; Odegard, Ryan; Somervill, Kevin; Suzuki, Nantel

doi:10.1109/aero.2010.5446723

Cited by 5 publications

(6 citation statements)

References 4 publications

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“…In a case study on a lateral-directional flight control system of a fighter aircraft, they demonstrated that using a quantitative system behavioral model allowed the assessment of the "degree of failure" along with degraded system operational modes [28]. In another study that utilizes system models to determine the effects of component failure on critical functions, Borer et al [29] evaluated two critical portions of proposed NASA Lunar Surface Systems. When physical components were mapped to system critical functions, a direct simulation of component dependencies (power, thermal etc.)…”

Section: Background and Literaturementioning

confidence: 99%

Evaluation of Off-Nominal Performance and Reliability of a Distributed Electric Propulsion Aircraft during Early Design

Bendarkar

Sarojini

Harrison

et al. 2021

AIAA Scitech 2021 Forum

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General Aviation (GA) is likely to be at the forefront of a paradigm change in aviation, where the introduction of novel concepts such as Urban Air Mobility (UAM), architectures like −VTOL, and technologies like Distributed Electric Propulsion (DEP) are expected to make aircraft more efficient and reduce their environmental footprint. However, these architectures carry with them an uncertainty related to the off-nominal operational risk they pose. The limitations and off-nominal operational considerations generally postulated during traditional safety analysis may not be complete or correct for new technologies. While a lot of the literature surveyed focuses on improving traditional methods of safety analysis, it still does not completely address the limitations caused due to insufficient knowledge and experience with transformative technologies. The research objective of the present work is to integrate the Bayesian safety assessment framework developed previously by the authors with conceptual and 6-DoF performance models for DEP aircraft to evaluate off-nominal performance and reliability using information that is typically available in conceptual or preliminary design phases. A case study on the electric power architecture of the the NASA Maxwell X-57 Mod. IV is provided. A maximum potential flight path angle metric, as well as trimmability considerations using a 6-DoF model constructed using available literature help determine hazard severity of power degradation scenarios. Bayesian failure rate posteriors are constructed for the different components in the traction power system, which are used in a Bayesian decision framework. The results indicate that while most of the components in the traction power architecture of the X-57 Mod. IV are compliant with failure rate requirements generated, the batteries, cruise motors, and cruise motor-inverters do not meet those requirements.

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Section: Background and Literaturementioning

confidence: 99%

Evaluation of Off-Nominal Performance and Reliability of a Distributed Electric Propulsion Aircraft during Early Design

Bendarkar

Sarojini

Harrison

et al. 2021

AIAA Scitech 2021 Forum

View full text Add to dashboard Cite

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“…The latter approach is similar to the concept of fault-tolerance that is embraced by developers of high reliability systems, such as modern human-rated spacecraft architectures. 26 Here, the presence of a single (or multiple) independent faults is assumed, and the system is designed to be able to contain these faults and either maintain acceptable performance to continue the mission, or gracefully degrade in such a way as to allow for safe return of the crew. Fault containment is achieved by building in multiple defenses ("slices of cheese") and designing the system such that latent conditions ("holes in the cheese") do not line up with each other.…”

Section: Figure 1 Adaptation Of Reason's "Swiss Cheese Model" Of Human Behavior 25mentioning

confidence: 99%

Development of a New Departure Aversion Standard for Light Aircraft

Borer

2017

17th AIAA Aviation Technology, Integration, and Operations Conference

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The Federal Aviation Administration (FAA) and European Aviation Safety Agency (EASA) have recently established new light aircraft certification rules that introduce significant changes to the current regulations. The changes include moving from prescriptive design requirements to performance-based standards, transferring many of the acceptable means of compliance out of the rules and into consensus standards. In addition, the FAA/EASA rules change the performance requirements associated with some of the more salient safety issues regarding light aircraft. One significant change is the elimination of spin recovery demonstration. The new rules now call for enhanced stall warning and aircraft handling characteristics that demonstrate resistance to inadvertent departure from controlled flight. The means of compliance with these changes in a safe, cost-effective manner is a challenging problem. This paper discusses existing approaches to reducing the likelihood of departure from controlled flight and introduces a new approach, dubbed Departure Aversion, which allows applicants to tailor the amount of departure resistance, stall warning, and enhanced safety equipment to meet the new proposed rules. The Departure Aversion approach gives applicants the freedom to select the most cost-effective portfolio for their design, while meeting the safety intent of the new rules, by ensuring that any combination of the selected approaches will be at a higher equivalent level of safety than today's status quo.

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“…Namely, it is desirable to know how these quantities change as system variables are modified. This approach has been used in the past for system reliability analysis [14,26], using only the component failure rates. In these cases, the absolute system reliability was of less concern than identifying those elements that drive the system loss probability.…”

Section: B System Availability and Expected Performancementioning

confidence: 99%

Multistate Design Approach to Analysis of Twin-Engine Aircraft Performance Robustness

Agte

Borer

Weck

2012

Journal of Aircraft

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This article introduces an integrated approach for the early-stage multistate design and analysis of aircraft requiring robust performance across a range of off-nominal system states. It is applied to the case study of an existing twin-engine aircraft, enabled by the development of a multimodal performance model calibrated with flight-test data collected at Edwards Air Force Base Flight Test Center. The methodology includes elements for determining responses in aircraft expected performance and availability to changes in static design variables (geometry), dynamic design variables (control gains), and component failure rates, which are the three driving input categories affecting performance robustness. This is accomplished using Markov chain analysis within the design loop to stochastically model state transitions based on failure rates as well as gain optimization through simulation to ensure controllability at each design point. Results showed unsafe performance in 15% of the King Air geometry-state responses under investigation. Although many occurred in the fully failed state and were expected, five occurred in partially degraded states where the majority of geometries were able to meet performance requirements. Furthermore, this behavior clearly exhibited itself in the resulting design sensitivities, confirming that such an approach allows designers to identify elements that might drive system loss through analysis of performance changes across system states and their respective response to changes in design variables.

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Model-driven development of reliable avionics architectures for Lunar Surface Systems

Cited by 5 publications

References 4 publications

Evaluation of Off-Nominal Performance and Reliability of a Distributed Electric Propulsion Aircraft during Early Design

Evaluation of Off-Nominal Performance and Reliability of a Distributed Electric Propulsion Aircraft during Early Design

Development of a New Departure Aversion Standard for Light Aircraft

Multistate Design Approach to Analysis of Twin-Engine Aircraft Performance Robustness

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