摘要 :
Modern aviation has been focusing on hybrid-electric propulsion in recent years, aiming for concepts with lower atmospheric and acoustic pollution to improve social acceptance of the sector. Development of such new enabling techno...
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Modern aviation has been focusing on hybrid-electric propulsion in recent years, aiming for concepts with lower atmospheric and acoustic pollution to improve social acceptance of the sector. Development of such new enabling technologies results in emergence of whole new aircraft concepts like Electric Vertical Take-Off and Landing (eVTOL) for urban air mobility. The present work focuses on the preliminary design of a hybrid-electric Vertical Take-Off and Landing (VTOL) air vehicle with multiple ducted fans. A theoretical preliminary sizing model is proposed and then implemented in Pacelab APD™, a commercial preliminary design tool developed by PACE Aerospace Engineering and Information Technology GmbH. The performance deck for electric ducted fans is developed in parallel using PROOSIS™, a separate dedicated propulsive system simulation software, using flight conditions as input and providing appropriate performance characteristics as output. The targeted powertrain is completed with a turbogenerator, also modelled in PROOSIS as a generic turboshaft engine with an additional electric generator efficiency accounting. After having sized it at cruise condition, a specific fuel consumption map is retrieved. A typical urban air mobility operational framework is considered when building the design mission - composed of vertical take-off, hover, cruise and vertical landing - as well as a range of off-design use case scenarios. Power requirement in vertical flight segments is also estimated. An example of the developed model application in Pacelab APD is provided; it is inspired by existing concepts on the market. It presents a hybrid-electric powertrain with eight ducted fans and a fully composite airframe. The model is implemented in a customized version of APD, along with coding of the missing engineering objects and the propulsive system performance decks exported from PROOSIS. The design mission is then simulated and analysed, suggesting a feasible aircraft solution, which is later subject to sensitivity studies.
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摘要 :
Modern aviation has been focusing on hybrid-electric propulsion in recent years, aiming for concepts with lower atmospheric and acoustic pollution to improve social acceptance of the sector. Development of such new enabling techno...
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Modern aviation has been focusing on hybrid-electric propulsion in recent years, aiming for concepts with lower atmospheric and acoustic pollution to improve social acceptance of the sector. Development of such new enabling technologies results in emergence of whole new aircraft concepts like Electric Vertical Take-Off and Landing (eVTOL) for urban air mobility. The present work focuses on the preliminary design of a hybrid-electric Vertical Take-Off and Landing (VTOL) air vehicle with multiple ducted fans. A theoretical preliminary sizing model is proposed and then implemented in Pacelab APDIM, a commercial preliminary design tool developed by PACE Aerospace Engineering and Information Technology GmbH. The performance deck for electric ducted fans is developed in parallel using PROOSIS1M, a separate dedicated propulsive system simulation software, using flight conditions as input and providing appropriate performance characteristics as output. The targeted powertrain is completed with a turbogenerator, also modelled in PROOSIS as a generic turboshaft engine with an additional electric generator efficiency accounting. After having sized it at cruise condition, a specific fuel consumption map is retrieved. A typical urban air mobility operational framework is considered when building the design mission - composed of vertical take-off, hover, cruise and vertical landing - as well as a range of off-design use case scenarios. Power requirement in vertical flight segments is also estimated. An example of the developed model application in Pacelab APD is provided; it is inspired by existing concepts on the market. It presents a hybrid-electric powertrain with eight ducted fans and a fully composite airframe. The model is implemented in a customized version of APD, along with coding of the missing engineering objects and the propulsive system performance decks exported from PROOSIS. The design mission is then simulated and analysed, suggesting a feasible aircraft solution, which is later subject to sensitivity studies.
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摘要 :
The growing interest into hybrid electric propulsion as a possible solution to reduce in-flight emissions has led to the investigations of many innovative propulsive system architectures that couple higher system efficiency with i...
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The growing interest into hybrid electric propulsion as a possible solution to reduce in-flight emissions has led to the investigations of many innovative propulsive system architectures that couple higher system efficiency with improved aerodynamic propulsion integration strategies. The paper presents a methodology to model and size generic hybrid electric propulsion system at the conceptual level allowing for a rapid exploration of the vast design space. The generalization of the propulsive system using a basic propulsive power unit object is discussed highlighting the control parameters needed to fully define the propulsive system architecture. Three case studies for a 2035 turbo-prop regional aircraft using parallel, series/parallel and distributed series configurations show that improvements to the fuel and energy consumption are affected by the system morphology, its control strategy and the maturity level assumed for its components. Using conservative estimations for the battery and electric components performances indicate that the best configurations can only provide a fuel reduction of around 5% while weighting 25% more than the reference design. Using more optimistic assumptions leads to a larger feasible design space where the best performing configuration, the series/parallel one, realizes more substantial fuel and energy reductions of 28% and 14% with a 24% higher take-off mass.
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摘要 :
The growing interest into hybrid electric propulsion as a possible solution to reduce in-flight emissions has led to the investigations of many innovative propulsive system architectures that couple higher system efficiency with i...
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The growing interest into hybrid electric propulsion as a possible solution to reduce in-flight emissions has led to the investigations of many innovative propulsive system architectures that couple higher system efficiency with improved aerodynamic propulsion integration strategies. The paper presents a methodology to model and size generic hybrid electric propulsion system at the conceptual level allowing for a rapid exploration of the vast design space. The generalization of the propulsive system using a basic propulsive power unit object is discussed highlighting the control parameters needed to fully define the propulsive system architecture. Three case studies for a 2035 turbo-prop regional aircraft using parallel, series/parallel and distributed series configurations show that improvements to the fuel and energy consumption are affected by the system morphology, its control strategy and the maturity level assumed for its components. Using conservative estimations for the battery and electric components performances indicate that the best configurations can only provide a fuel reduction of around 5% while weighting 25% more than the reference design. Using more optimistic assumptions leads to a larger feasible design space where the best performing configuration, the series/parallel one, realizes more substantial fuel and energy reductions of 28% and 14% with a 24% higher take-off mass.
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摘要 :
Historically, during aircraft conceptual design, only limited consideration has been given to the aircraft subsystems, which have traditionally been addressed in the subsequent design phases. However, the design of future All Elec...
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Historically, during aircraft conceptual design, only limited consideration has been given to the aircraft subsystems, which have traditionally been addressed in the subsequent design phases. However, the design of future All Electric Aircraft or More Electric Aircraft will require a paradigm shift due to the lack of historical data and the presence of significant interactions among subsystems. As a result, the conceptual phase designer of such aircraft will seek the capability to perform subsystem sizing and analysis in parallel with traditional aircraft and propulsion system sizing and analysis. However, a significant challenge arises from the fact that the conceptual phase designer has limited and incomplete information regarding the design. This work presents a methodology to integrate subsystem sizing with conceptual design phase aircraft and propulsor sizing, while utilizing only the limited information that is available during this phase. The sizing of subsystem components is driven by requirements definition and the identification of critical or constraining operating scenarios. The subsystems considered include the environmental control system and ice protection system, actuation subsystems for flight control surfaces, landing gear, braking, and nose-wheel steering, and an innovative electric taxiing concept. Using a single-aisle narrowbody aircraft as a test case, the proposed methodology is demonstrated by comparing a conventional subsystem architecture to an electric one at the vehicle and mission level, and feeding back subsystem characteristics to the vehicle and propulsor sizing process.
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摘要 :
Historically, during aircraft conceptual design, only limited consideration has been given to the aircraft subsystems, which have traditionally been addressed in the subsequent design phases. However, the design of future All Elec...
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Historically, during aircraft conceptual design, only limited consideration has been given to the aircraft subsystems, which have traditionally been addressed in the subsequent design phases. However, the design of future All Electric Aircraft or More Electric Aircraft will require a paradigm shift due to the lack of historical data and the presence of significant interactions among subsystems. As a result, the conceptual phase designer of such aircraft will seek the capability to perform subsystem sizing and analysis in parallel with traditional aircraft and propulsion system sizing and analysis. However, a significant challenge arises from the fact that the conceptual phase designer has limited and incomplete information regarding the design. This work presents a methodology to integrate subsystem sizing with conceptual design phase aircraft and propulsor sizing, while utilizing only the limited information that is available during this phase. The sizing of subsystem components is driven by requirements definition and the identification of critical or constraining operating scenarios. The subsystems considered include the environmental control system and ice protection system, actuation subsystems for flight control surfaces, landing gear, braking, and nose-wheel steering, and an innovative electric taxiing concept. Using a single-aisle narrowbody aircraft as a test case, the proposed methodology is demonstrated by comparing a conventional subsystem architecture to an electric one at the vehicle and mission level, and feeding back subsystem characteristics to the vehicle and propulsor sizing process.
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摘要 :
The ongoing efforts to reduce aviation related greenhouse gas emissions and fuel burn have led to advancements in power generation and distribution (PG&D) subsystem technology. Due to the absence of historical data, PG&D subsystem models must be created from first-order analysis without compromising crucial information on their characteristics. This paper demonstrates the development of parametric, physics-based subsystem models such as battery, electric motor, power distribution and management system, and propeller speed reduction unit for rapid and low-cost sizing, simulation and analysis at early design stages. A special focus was put on rechargeable battery technology and implementing a dynamic (rather than steady-state) discharge behavior into the propulsion architecture. A methodology to integrate the developed subsystem models was presented. A sample application was also provided to demonstrate the combined capabilities of the models. To this end, the models were applied within a sample parallel hybrid electric architecture using Dornier 328 as a test bed. The subsystem behaviors under varying power requirements were then analyzed. Finally, the importance of having more dimensionality at the subsystem level at early design stages was highlighted by comparing the results of two different architectural choices....
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The ongoing efforts to reduce aviation related greenhouse gas emissions and fuel burn have led to advancements in power generation and distribution (PG&D) subsystem technology. Due to the absence of historical data, PG&D subsystem models must be created from first-order analysis without compromising crucial information on their characteristics. This paper demonstrates the development of parametric, physics-based subsystem models such as battery, electric motor, power distribution and management system, and propeller speed reduction unit for rapid and low-cost sizing, simulation and analysis at early design stages. A special focus was put on rechargeable battery technology and implementing a dynamic (rather than steady-state) discharge behavior into the propulsion architecture. A methodology to integrate the developed subsystem models was presented. A sample application was also provided to demonstrate the combined capabilities of the models. To this end, the models were applied within a sample parallel hybrid electric architecture using Dornier 328 as a test bed. The subsystem behaviors under varying power requirements were then analyzed. Finally, the importance of having more dimensionality at the subsystem level at early design stages was highlighted by comparing the results of two different architectural choices.
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摘要 :
The ongoing efforts to reduce aviation related greenhouse gas emissions and fuel burn have led to advancements in power generation and distribution (PG&D) subsystem technology. Due to the absence of historical data, PG&D subsystem models must be created from first-order analysis without compromising crucial information on their characteristics. This paper demonstrates the development of parametric, physics-based subsystem models such as battery, electric motor, power distribution and management system, and propeller speed reduction unit for rapid and low-cost sizing, simulation and analysis at early design stages. A special focus was put on rechargeable battery technology and implementing a dynamic (rather than steady-state) discharge behavior into the propulsion architecture. A methodology to integrate the developed subsystem models was presented. A sample application was also provided to demonstrate the combined capabilities of the models. To this end, the models were applied within a sample parallel hybrid electric architecture using Dornier 328 as a test bed. The subsystem behaviors under varying power requirements were then analyzed. Finally, the importance of having more dimensionality at the subsystem level at early design stages was highlighted by comparing the results of two different architectural choices....
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The ongoing efforts to reduce aviation related greenhouse gas emissions and fuel burn have led to advancements in power generation and distribution (PG&D) subsystem technology. Due to the absence of historical data, PG&D subsystem models must be created from first-order analysis without compromising crucial information on their characteristics. This paper demonstrates the development of parametric, physics-based subsystem models such as battery, electric motor, power distribution and management system, and propeller speed reduction unit for rapid and low-cost sizing, simulation and analysis at early design stages. A special focus was put on rechargeable battery technology and implementing a dynamic (rather than steady-state) discharge behavior into the propulsion architecture. A methodology to integrate the developed subsystem models was presented. A sample application was also provided to demonstrate the combined capabilities of the models. To this end, the models were applied within a sample parallel hybrid electric architecture using Dornier 328 as a test bed. The subsystem behaviors under varying power requirements were then analyzed. Finally, the importance of having more dimensionality at the subsystem level at early design stages was highlighted by comparing the results of two different architectural choices.
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This work pertains to the analysis of electric control surface actuation for a More Electric Aircraft at the actuator, vehicle, and mission levels. Two different actuation solutions utilizing electrohydrostatic and electromechanic...
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This work pertains to the analysis of electric control surface actuation for a More Electric Aircraft at the actuator, vehicle, and mission levels. Two different actuation solutions utilizing electrohydrostatic and electromechanical actuators were identified, and their pertinent characteristics were developed using Pacelab SysArc, an aircraft system architecture modeling and analysis tool. The existing capabilities of the tool were augmented as required to facilitate the proposed analysis. Using the Boeing 737-800 aircraft as a test case, the performance of both the configurations was evaluated over the course of a typical aircraft mission. The intent of this work is to analyze whether one of the two selected architectures significantly outperforms the other with regard to a vehicle-level and a mission-level metric, or whether the choice between these two architectures in a future More Electric Aircraft is likely to be driven predominantly by other considerations.
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摘要 :
This work pertains to the analysis of electric control surface actuation for a More Electric Aircraft at the actuator, vehicle, and mission levels. Two different actuation solutions utilizing electrohydrostatic and electromechanic...
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This work pertains to the analysis of electric control surface actuation for a More Electric Aircraft at the actuator, vehicle, and mission levels. Two different actuation solutions utilizing electrohydrostatic and electromechanical actuators were identified, and their pertinent characteristics were developed using Pacelab SysArc, an aircraft system architecture modeling and analysis tool. The existing capabilities of the tool were augmented as required to facilitate the proposed analysis. Using the Boeing 737-800 aircraft as a test case, the performance of both the configurations was evaluated over the course of a typical aircraft mission. The intent of this work is to analyze whether one of the two selected architectures significantly outperforms the other with regard to a vehicle-level and a mission-level metric, or whether the choice between these two architectures in a future More Electric Aircraft is likely to be driven predominantly by other considerations.
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