Correct-by-Construction Design of Aircraft Electric Power Systems

Pinto, Alessandro; Becz, Sandor; Reeve, Hayden

doi:10.2514/6.2010-9263

Cited by 15 publications

(17 citation statements)

References 6 publications

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“…Our methodology has similarities with [2], which deals with how to select the power generators and synthesize the EPS topology (interconnection among the various components) by formulating and solving a set of binary optimization problems. However, not all the requirements of an EPS can be accurately approximated by binary or mixed integer-linear constraints, which calls for an extension of the flow in [2], to enable synthesis of EPS control protocols subject to heterogeneous sets of system constraints. A number of recent papers have investigated the adoption of SysML for MBD and analysis of complex systems of systems, albeit not within a rigorously formalized methodology.…”

Section: Introductionmentioning

confidence: 99%

A Contract-Based Methodology for Aircraft Electric Power System Design

et al. 2014

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In an aircraft electric power system (EPS), a supervisory control unit must actuate a set of switches to distribute power from generators to loads, while satisfying safety, reliability and real-time performance requirements. To reduce expensive re-design steps in current design methodologies, such a control problem is generally addressed based on minor incremental changes on top of consolidated solutions, since it is difficult to estimate the impact of earlier design decisions on the final implementation. In this paper, we introduce a methodology for the design space exploration and virtual prototyping of EPS supervisory control protocols, following the platform-based design (PBD) paradigm. Moreover, we describe the modeling infrastructure that supports the methodology. In PBD, design space exploration is carried out as a sequence of refinement steps from the initial specification towards a final implementation, by mapping higher-level behavioral models into a set of library components at a lower level of abstraction. In our flow, the system specification is captured using SysML requirement and structure diagrams. State-machine diagrams enable verification of the control protocol at a high level of abstraction, while lowerlevel hybrid models, implemented in Simulink, are used to verify properties related to physical quantities, such as time, voltage and current values. The effectiveness of our approach is illustrated on a prototype EPS control protocol design.

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Section: Introductionmentioning

confidence: 99%

A Contract-Based Methodology for Aircraft Electric Power System Design

et al. 2014

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“…Given that the power conversion is driven by a power density (kW/kg) and the amount of power to convert, the weight of the power distribution system is independent from the generator-load combination. Hence, following a PBD methodology [14], the MEA power system is synthesized in two sequential steps [13], [15]: generator selection and generator-load pairing (GS&GLP), and power distribution design (PDD). The former selects a number of power sources (generator selection) and determines which loads are supplied by those power sources at any time (generator-load pairs or distribution paths).…”

Section: Design Formulationmentioning

confidence: 99%

“…In the former, the number of reliability constraints increase depending on the reliability requirements [11], so that the connectivity complexity is increased only if required by specification (otherwise, simpler topologies are feasible). In the latter, starting at an abstract representation (platform) of the system's functional and safety specifications, the design walks through a certain number of refinement steps until the platform is very close to final implementation [13]. Although these formulations synthesize a power system architecture based on functional and reliability requirements, there are further steps to be performed in order to bring the solution closer to a final implementation.…”

Section: Introductionmentioning

confidence: 99%

Optimal Weight Power System Design and Synthesis for More Electric Aircraft

Recalde

Bozhko

Atkin

2020

AIAA Propulsion and Energy 2020 Forum

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The synthesis of power distribution architecture for More Electric Aircraft requires optimization of weight in order to reduce energy consumption. Optimal weight of the power distribution system of the aircraft mainly depends on compliance of stringent safety requirements, as well as component selection and location. Safety is dictated by the reliability constraints that ensures distribution adequacy to maintain critical loads powered at all times. Optimal component selection and location is a combinatorial problem that determines a set of interconnected devices located in specific positions such that the resultant topology has minimum weight. Given the complexity in producing and solving such optimization formulation, this paper realizes a linear optimization design that is subject to reliability constraints to comply with safety requirements, and component selection and location constraints such that the weight of the electrical distribution system is minimized. The design formulation is presented as a Mixed Integer Linear Programming problem and a case study is used to exemplify the synthesis of a power distribution architecture that is optimal.

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“…An optimization oriented EPS design methodology following the PBD paradigm was instead proposed in [7]. However, the main focus of both [6] and [7] was on the selection of the generators and the design of the topology, i.e. the interconnection among different EPS components, rather than optimal design of the switching logic for the EPS contactors and load management.…”

Section: Introductionmentioning

confidence: 98%

“…In [6], the optimum voltage and power levels at various points of the network are determined to minimize the total weight, installation costs and fuel consumption. An optimization oriented EPS design methodology following the PBD paradigm was instead proposed in [7]. However, the main focus of both [6] and [7] was on the selection of the generators and the design of the topology, i.e.…”

Section: Introductionmentioning

confidence: 99%

Optimal load management system for Aircraft Electric Power distribution

Maasoumy

Nuzzo

Iandola

et al. 2013

52nd IEEE Conference on Decision and Control

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Aircraft Electric Power Systems (EPS) route power from generators to vital avionic loads by configuring a set of electronic control switches denoted as contactors. In this paper, we address the problem of designing a hierarchical optimal control strategy for the EPS contactors in the presence of system faults. We first formalize the system connectivity, safety and performance requirements in terms of mathematical constraints. We then show that the EPS control problem can be formulated as a Mixed-Integer Linear Program (MILP) and efficiently solved to yield load shedding, source allocation, contactor switching and battery charging policies, while optimizing a number of performance metrics, such as the number of used generators and shed loads. This solution is then integrated into a hierarchical control scheme consisting of two layers of controllers. The high-level controller provides control optimality by solving the MILP within a receding horizon approach. The low-level controller handles system faults, by directly actuating the EPS contactors, and implements the solution from the high-level controller only if it is safe. Simulation results confirm the effectiveness of the proposed approach.

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Correct-by-Construction Design of Aircraft Electric Power Systems

Cited by 15 publications

References 6 publications

A Contract-Based Methodology for Aircraft Electric Power System Design

A Contract-Based Methodology for Aircraft Electric Power System Design

Optimal Weight Power System Design and Synthesis for More Electric Aircraft

Optimal load management system for Aircraft Electric Power distribution

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