scholarly journals Design and Optimization of Ram Air-Based Thermal Management Systems for Hybrid-Electric Aircraft

Aerospace ◽  
2020 ◽  
Vol 8 (1) ◽  
pp. 3
Author(s):  
Hagen Kellermann ◽  
Michael Lüdemann ◽  
Markus Pohl ◽  
Mirko Hornung
Keyword(s):  
Thermal Management ◽  
Sensitivity Analyses ◽  
Management Systems ◽  
Dimensional System ◽  
System Sensitivity ◽  
Design And Optimization ◽  
Fuel Burn ◽  
Electric Aircraft ◽  
Power Split ◽  
Hybrid Electric

Ram air-based thermal management systems (TMS) are investigated herein for the cooling of future hybrid-electric aircraft. The developed TMS model consists of all components required to estimate the impacts of mass, drag, and fuel burn on the aircraft, including the heat exchangers, coldplates, ducts, pumps, and fans. To gain a better understanding of the TMS, one- and multi-dimensional system sensitivity analyses were conducted. The observations were used to aid with the numerical optimization of a ram air-based TMS towards the minimum fuel burn of a 180-passenger short-range turboelectric aircraft with a power split of up to 30% electric power. The TMS was designed for the conditions at the top of the climb. For an aircraft with the maximum power split, the additional fuel burn caused by the TMS is 0.19%. Conditions occurring at a hot-day takeoff represent the most challenging off-design conditions for TMS. Steady-state cooling of all electric components with the designed TMS is possible during a hot-day takeoff if a small puller fan is utilized. Omitting the puller fan and instead oversizing the TMS is an alternative, but the fuel burn increase on the aircraft level grows to 0.29%.

Characterization of High-Density Aircraft Electronic and Thermal Management Systems

2021 ◽  
Author(s):  
Joshua Kasitz ◽  
David Huitink
Keyword(s):  
Thermal Management ◽  
Electronic Devices ◽  
Electronic Cooling ◽  
High Density ◽  
Management Systems ◽  
Local Cooling ◽  
Cooling Systems ◽  
Electric Aircraft ◽  
Hybrid Electric ◽  
Electric Powertrains

Abstract As aircrafts move toward electrification with the research and development of hybrid-electric powertrains, the focus has begun to shift to the reliability challenges of electronic devices subject to flight. Electronic components in aircraft applications are subject to two main sources of failure inducing stresses: the thermomechanical stresses that develop due to unequal coefficients of thermal expansion of different materials used in the components, and the stresses developing due to shocks and vibrations during flight as well as landing and takeoff. While the challenge of dealing with CTE mismatches is applicable to electronic devices in general, the ambient conditions surrounding the aircraft in flight, combined with weight and space constrains add significant logistical issues to any cooling mechanism. This paper will focus on the environmental influence on the thermal dissipation profile that will ultimately lead to CTE failures. The push toward more-electric-aircraft (MEA) increases the need to further advance the power and versatility of electronic cooling systems to adequately manage high density power modules, which until recently were not highly incorporated in aviation systems. Environmental conditions will play a large role in the design space and limitations of potential cooling solutions and will dictate the effectiveness of current thermal management systems. In arising scenarios where high-density electronics cannot be contained within a pressurized and temperature-controlled cabin, drastic pressure and temperature swings, facilitated by the external environment, will lead to an extra source of fluctuating stress on the cooling system. This is likely to be a prevalent factor in hybrid-electric and all-electric powertrains as requiring environmental controlled spaces for major components could be limited. This can easily be seen in current attempts to examine and redesign local cooling systems for electric motors in aviation. Representing just one of the major cooling requirements on an electric aircraft, motor cooling systems demonstrate the universal cooling problems limiting all aspects of the powertrains system. This paper aims to define the impact of the changing environment, through a flight profile of an aircraft, on high density electronic cooling systems by assessing the potential system stressors that significantly impact performance, efficiency, and reliability of the cooling systems. It will also utilize local cooling efforts for motors to relate the general problems to applicable design considerations that must be understood to further the performance capability of the overall propulsion system.

Integrated Propulsive and Thermal Management System Design for Optimal Hybrid Electric Aircraft Performance

2020 ◽  
Author(s):  
Philip C. Abolmoali ◽  
Adam B. Donovan ◽  
Soumya S. Patnaik ◽  
Patrick McCarthy ◽  
Dominic Dierker ◽  
...  
Keyword(s):  
System Design ◽  
Thermal Management ◽  
Management System ◽  
Thermal Management System ◽  
Electric Aircraft ◽  
Aircraft Performance ◽  
Hybrid Electric

Synergistic hybrid-electric liquid natural gas drone: S.H.I.E.L.D

2020 ◽  
Vol 92 (5) ◽  
pp. 757-768 ◽  
Author(s):  
Thierry Sibilli ◽  
Capucine Senne ◽  
Hugo Jouan ◽  
Askin T. Isikveren ◽  
Sabrina Ayat
Keyword(s):  
Thermal Management ◽  
Synergistic Effects ◽  
Energy System ◽  
Sensitivity Study ◽  
Coolant Temperature ◽  
Electrical System ◽  
Content Type ◽  
Electric Aircraft ◽  
Aircraft Performance ◽  
Hybrid Electric

Purpose With the objective to assess potentially performant hybrid-electric architectures, this paper aims to present an aircraft performance level evaluation, in terms of range and payload, of the synergies between a hybrid-electric energy system configuration and a cryogenic fuel system. Design/methodology/approach An unmanned aerial vehicle (UAV) is modeled using an aircraft performance tool, modified to take into account the hybrid nature of the system. The fuel and thermal management systems are modeled looking to maximize the synergistic effects. The electrical system is defined in series with the thermal engine and the performance, in terms of weight and efficiency, are tracked as a function of the cooling temperature. Findings The results show up to a 46 per cent increase in range and up to 7 per cent gain on a payload with a reference hybrid-electric aircraft that uses conventional drop-in JP-8 fuel. The configuration that privileges a reduction in mass of the electric motors by taking advantage of the cryogenic coolant temperature shows the highest benefits. A sensitivity study is also presented showing the dependency on the modeling capabilities. Practical implications The synergistic combination of a cryogenic fuel and the additional heat sources of a hybrid-electric system with a tendency to higher electric component efficiency or reduced weight results in a considerable performance increase in terms of both range and payload. Originality/value The potential synergies between a cryogenic fuel and the electrical system of a hybrid-electric aircraft seem clear; however, at the present, no detailed performance evaluation at aircraft level that includes the fuel, thermal management and electric systems, has been published.

scholarly journals Range Equation for Hybrid-Electric Aircraft with Constant Power Split

2020 ◽  
Vol 57 (3) ◽  
pp. 552-557 ◽  
Author(s):  
Reynard de Vries ◽  
Maurice F. M. Hoogreef ◽  
Roelof Vos
Keyword(s):  
Constant Power ◽  
Electric Aircraft ◽  
Power Split ◽  
Hybrid Electric ◽  
Range Equation
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