Energy efficiency analysis of electric and conventional environmental control system on commercial aircraft

Jiang, Hongsheng; Dong, Sujun; Helin, Zhang

doi:10.1109/aus.2016.7748195

Cited by 7 publications

(2 citation statements)

References 7 publications

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“…Since the appearance of the earliest aircraft ECS to face the low pressure caused by the rising flight height in the 1940s, environmental control technologies have been developing continuously [5]. In the last decades, the ECSs evolved from double-wheel types, including simple type [6][7][8][9] and bootstrap type [10][11][12][13][14][15][16][17][18][19][20], to three-wheel [21][22][23][24] and four-wheel type [25], then from conventional types with bleed air to electric type [21,25,26].…”

Section: Introductionmentioning

confidence: 99%

Thermodynamic Optimization of Aircraft Environmental Control System Using Modified Genetic Algorithm

et al. 2022

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This paper presents an optimization method for the civil aircraft environmental control system (ECS) mainly involving two airstreams: the ram airstream for cooling and the bleed airstream for supplying the cabin. The minimum total fuel energy consumption rate (FECR), defined as the weighted sum of the shaft power extraction and propulsive power loss, is obtained under the precondition of the constant outputs in the cooling capacity and outlet pressure. A modified genetic algorithm (GA) is proposed to acquire the optimal values of the heat transfer areas, temperature ratio of bleed air, mass flow rate of ram air, and pressure ratios of the turbine, compressor, and fan. The statistical results show that the multipoint crossover and continuity improvement implemented in the modified GA improve convergence and distribution performance. The probability of reaching a satisfactory result using modified GA is 62.4% higher than standard GA. Due to the decrease of inlet parameters of bleed air and the elimination of power input in the compressor, the FECR of the optimization case can be lowered by 11.0%. In general, the evaluation method considering energy quality together with the modified optimization technique is proved effective in energy-saving design for such energy systems such as ECS with multiple inputs and outputs.

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Section: Introductionmentioning

confidence: 99%

Thermodynamic Optimization of Aircraft Environmental Control System Using Modified Genetic Algorithm

et al. 2022

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“…[1,2] In aerospace application, systems exergy has mainly been applied to aircraft design, analysis, and optimization. It has been applied in various system contexts including lunar base thermal energy designs [3], aircraft system design [4,5,6,7], analysis, and optimization, aircraft engine analysis [8,9,10,11,12], aircraft environmental control [13], pulsed detonation power devices [14], and hypersonics [1,15]. Interesting comparisons between exergy S balance equation and the Breguet range equation have also been done for aircraft [16].…”

Section: Introductionmentioning

confidence: 99%

System Exergy: System Integrating Physics of Launch Vehicles and Spacecraft

Watson

2018

Journal of Spacecraft and Rockets

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System Engineering of launch vehicles and spacecraft is a challenging and complex under taking. There are many diverse systems which must be integrated and balanced to produce an effective design. This involves a multiplicity of individual engineering relationships that are difficult to integrate and even more difficult to define in a best balance. Integration efforts involve many different approaches from process management to mass balance. But these approaches either do not directly address the launch vehicle or spacecraft performance or require many adjustments to be made to discover a balance. The system integrating physics, derived from the fundamental physics of the system, is the key to identifying a fully integrated system performance measure. Launch vehicles and spacecraft are thermodynamic systems with performance defined by thermodynamic properties. Thus, thermodynamic exergy, which integrates all of the systems thermodynamic properties, provides the system integrating relationships. This provides a basis for determining the most efficient design from among many different configuration options and for guiding the design activities from an integrated system level. This paper explores the current physics relationships used in launch vehicle system design and demonstrates that thermodynamic exergy provides a more explicit and complete approach to system integration.

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Technology selection for holistic analysis of hybrid-electric commuter aircraft

et al. 2022

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Electric powertrains have different characteristics than conventional powertrains with combustion engines and require unconventional aircraft designs to evolve their full potential. Therefore, this paper describes a method to identify potential aircraft designs with electrified powertrains. Promising technology options in the fields of powertrain architecture, aerodynamic interactions, onboard systems and operating strategies were collected by the project partners of the LuFo project GNOSIS. The effect of the technology options on a commuter aircraft was evaluated in terms of global emissions ($$\hbox {CO}_{2}$$ CO 2 ), local emissions ($$\text {NO}_{\text {X}}$$ NO X and noise) and operating costs. The evaluation considers an entry into service in 2025 and 2050 and is based on the reference aircraft Beechcraft 1900D. Literature review and simplified calculations enabled the evaluation of the aerodynamic interactions, systems and operating strategies. A preliminary aircraft design tool assessed the different powertrain architectures by introducing the two parameters ’power hybridization’ and ’power split’. Afterwards, compatible technology options were compiled into technology baskets and ranked using the shortest euclidean distance to the ideal solution and the farthest euclidean distance to the worst solution (Technique for Order Preference by Similarity to Ideal Solution (TOPSIS) method). An analysis of the CS 23 regulations leads to a high-wing design and excluded the partial turbo-electric powertrain architecture with the gas turbine in the aircraft tail. For 2025, a partial turbo-electric powertrain with two additional electric driven wingtip propellers was selected. A serial hybrid powertrain, which uses a gas turbine or fuel cell in combination with a battery, powers distributed electric propulsors at the wing leading edge in 2050. In both scenarios, the aircraft design includes an electric environmental control system, an electric driven landing gear and electro-hydraulic actuators for the primary flight control and landing gear.

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Energy efficiency analysis of electric and conventional environmental control system on commercial aircraft

Cited by 7 publications

References 7 publications

Thermodynamic Optimization of Aircraft Environmental Control System Using Modified Genetic Algorithm

Thermodynamic Optimization of Aircraft Environmental Control System Using Modified Genetic Algorithm

System Exergy: System Integrating Physics of Launch Vehicles and Spacecraft

Technology selection for holistic analysis of hybrid-electric commuter aircraft

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