X-57 power and command system design

Clarke, Sean; Redifer, Matthew; Papathakis, Kurt V.; Samuel, Aamod; Foster, Trevor

doi:10.1109/itec.2017.7993303

Cited by 40 publications

(31 citation statements)

References 1 publication

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“…Authors in [11] identify that the electrical system Strategic Fault Response (SFR) can often be counter-intuitive when influenced by the whole aircraft design. For example, on NASA's X-57 Maxwell aircraft, if one of the wing tip thrusters were to fail, the rudder cannot correct the imbalance.…”

Section: B Review Of Fmss and Design Framework For Epamentioning

confidence: 99%

A Fault Management-Oriented Early-Design Framework for Electrical Propulsion Aircraft

Flynn

Jones

Norman

et al. 2019

IEEE Trans. Transp. Electrific.

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Electrical propulsion has been identified as a key enabler of greener, quieter, more efficient aircraft. However, electrical propulsion aircraft will need to demonstrate a level of safety and reliability at least equal to current aircraft to be a viable alternative. Therefore, a robust and reliable fault management system is needed to prevent electrical faults causing loss of propulsion and critical flight functions. To date, fault management of the electrical propulsion system has not been considered in detail for future electrical propulsion aircraft, nor has it been effectively integrated into the electrical architecture design. This poses a risk that the proposed electrical architectures will be infeasible from a fault management perspective, and key fault management technologies may not be sufficiently developed. Therefore, a methodology to incorporate fault management into the early stages of design of electrical architectures is required to determine viable fault management solutions for a given electrical propulsion aircraft concept. This paper describes a novel, systems-level electrical architecture design framework for electrical propulsion aircraft which incorporates fault management from the outset. This methodology captures the significant assumptions in the design and acknowledges the novel interfaces which exist between the electrical, conceptual and fault management design of electrical propulsion aircraft.

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Section: B Review Of Fmss and Design Framework For Epamentioning

confidence: 99%

A Fault Management-Oriented Early-Design Framework for Electrical Propulsion Aircraft

Flynn

Jones

Norman

et al. 2019

IEEE Trans. Transp. Electrific.

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“…In [4] the aircraft system goal under fault conditions is shown to determine the FM system goal. From the operation of the architectures described in the literature [7]- [9], [12], [39], [40], the FM goal is identified and mapped in Table II. For example, in [10] the system goal is maintain power to the array of propulsor motors during a fault, and the electrical system is configured such that the FM reconfiguration can only occur in a de-energized state after all the power sources connected to the faulted bus have been isolated.…”

Section: Importance Of Fm Goal In Fm Strategy Mapmentioning

confidence: 99%

“…From Table II, it is clear that there is a significant difference in the FM technology specifications and level of oversizing which is required between small demonstrator aircraft (such as the NASA Maxwell concept [40]) and larger passenger concepts (such as the ECO-150 aircraft [10]). There is also a notable change when the electrical aircraft has the same limited range of FM technologies at high confidence level as the STARC-ABL concept, yet unlike STARC-ABL, cannot rely on a given level of thrust from gas turbine engines if there is a critical failure in the electrical propulsion system.…”

Section: B Aspects Of Electrical and Wider System Oversizingmentioning

confidence: 99%

Protection and Fault Management Strategy Maps for Future Electrical Propulsion Aircraft

Flynn

Sztykiel

Jones

et al. 2019

IEEE Trans. Transp. Electrific.

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Electrical propulsion has been identified as a key enabler of greener, quieter, more efficient aircraft. However, electrical propulsion aircraft (EPA) will need to demonstrate a level of safety and fault management at least equal to current aircraft. This will rely heavily on the capability and design of the electrical fault management (FM) system. Given the functional limitations and current lack of availability of FM technologies suitable for a future EPA application, strategic development of FM devices is required. Whilst there are a variety of roadmaps for EPA concepts and some of the key electrical components, the necessary strategic development of FM solutions targeted towards EPA has yet to be established. This paper proposes FM strategy maps which go beyond projections of expected development in various FM technologies to scope the feasibility of key FM solutions. This method can then be used to present FM technology projections, electrical oversizing and wider system redundancy alongside the various aircraft concepts in development. This results in strategy maps which capture the impact of any FM technology barrier on the viability of a given aircraft concept, enabling critical FM solutions to be integrated into the wider electrical system development. Index TermsFault management strategy map, electrical propulsion aircraft, electrical power systems, protection technology development. I. INTRODUCTIONElectrical propulsion has been identified as a key enabler of greener, quieter, more efficient aircraft. Novel electrical propulsion aircraft (EPA) will depend on the development of a range of electrical technologies, many of which are currently at low TRL (Technology Readiness Level). Given the risk that an EPA concept may rely on key technologies which may not be sufficiently developed as desired at the aircraft's point of entry into service, it is important to develop understanding of the particular challenges which must be addressed in bringing technologies to maturity. One of the most challenging set of technologies for EPA are the fault management (FM) devices,

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“…1) with goals to reduce the energy required for cruise by 4.8x without sacrificing cruise speed or takeoff distance [9]. Since the X-57, there has been a significant increase in the amount of research regarding DEP for thin-haul commuters in areas such as economics [10], multidisciplinary modeling requirements [11], wing aerodynamic analysis [8,9,12], motor design [13], avionics [14], hybrid propulsion [15], trajectory thermal considerations [16], certification and landing safety [17] and large scale multidisciplinary optimization of design and trajectory [7].…”

Section: Introductionmentioning

confidence: 99%

Takeoff and Performance Trade-Offs of Retrofit Distributed Electric Propulsion for Urban Transport

Moore

Ning

2019

Journal of Aircraft

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While vertical takeoff and landing aircraft have shown promise for urban air transport, distributed electric propulsion on existing aircraft may offer immediately implementable alternatives. Distributed electric propulsion could potentially decrease takeoff distances enough to enable thousands of potential inter-city runways. This conceptual study explores the effects of a retrofit of open-bladed electric propulsion units. To model and explore the design space we use blade element momentum method, vortex lattice method, linear-beam finite element analysis, classical laminate theory, composite failure, empirically-based blade noise modeling, motor and motor-controller mass models, and gradient-based optimization. With liftoff time of seconds and the safe total field length for this aircraft type undefined, we focused on the minimum conceptual takeoff distance. We found that 16 propellers could reduce the takeoff distance by over 50% compared to the optimal 2 propeller case. This resulted in a conceptual minimum takeoff distance of 20.5 meters to clear a 50 ft (15.24 m) obstacle. We also found that when decreasing the allowable noise by approximately 10 dBa, the 8 propeller case performed the best with a 43% reduction in takeoff distance compared to the optimal 2 propeller case. This resulted in a noise-restricted conceptual minimum takeoff distance of 95 meters.

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X-57 power and command system design

Cited by 40 publications

References 1 publication

A Fault Management-Oriented Early-Design Framework for Electrical Propulsion Aircraft

A Fault Management-Oriented Early-Design Framework for Electrical Propulsion Aircraft

Protection and Fault Management Strategy Maps for Future Electrical Propulsion Aircraft

Takeoff and Performance Trade-Offs of Retrofit Distributed Electric Propulsion for Urban Transport

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