Performance analysis of electrical environmental control and ice protection systems in a commercial transport aircraft

IF 1.2 4区工程技术 Q3 ENGINEERING, AEROSPACE Aircraft Engineering and Aerospace Technology Pub Date : 2023-12-18 DOI:10.1108/aeat-01-2023-0019

Hamdi Ercan, Cüneyt Öztürk, Mustafa Akın

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Abstract

Purpose

This paper aims to assess the impact of electrifying the environmental control system (ECS) and ice protection system (IPS), the primary pneumatic system consumers in a conventional commercial transport aircraft, on aircraft weight, range, and fuel consumption.

Design/methodology/approach

The case study was carried out on Airbus A321-200 aircraft. Design, modelling and analysis processes were carried out on Pacelab SysArc software. Conventional and electrical ECS and IPS architectures were modelled and analysed considering different temperature profiles.

Findings

The simulation results have shown that the aircraft model with ±270 VDC ECS and IPS architecture is lighter, has a more extended range and has less relative fuel consumption. In addition, the simulation results showed that the maximum range and relative fuel economy of all three aircraft models increased slightly as the temperature increased.

Practical implications

Considering the findings in this paper, it is seen that the electrification of the conventional pneumatic system in aircraft has positive contributions in terms of weight, power consumption and fuel consumption.

Social implications

The positive contributions in terms of weight, power consumption and fuel consumption in aircraft will be direct environmental and economic contributions.

Originality/value

Apart from the conventional ECS and IPS of the aircraft, two electrical architectures, 230 VAC and ±270 VDC, were modelled and analysed. To see the effects of the three models created in different temperature profiles, analyses were done for cold day, ISA standard day and hot day temperature profiles.

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商用运输机电气环境控制和防冰系统的性能分析

目的本文旨在评估环境控制系统（ECS）和冰保护系统（IPS）电气化对飞机重量、航程和油耗的影响。设计、建模和分析过程均在 Pacelab SysArc 软件上进行。模拟结果表明，采用 ±270 VDC ECS 和 IPS 结构的飞机机型重量更轻、航程更远、相对油耗更低。此外，模拟结果表明，随着温度的升高，三种飞机型号的最大航程和相对燃油经济性都略有增加。社会影响在飞机重量、功耗和油耗方面的积极贡献将是对环境和经济的直接贡献。原创性/价值除了飞机的传统 ECS 和 IPS 外，还对 230 VAC 和 ±270 VDC 两种电气结构进行了建模和分析。为了解在不同温度条件下创建的三种模型的效果，对冷天、ISA 标准天和热天的温度条件进行了分析。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Aircraft Engineering and Aerospace Technology 工程技术-工程：宇航

CiteScore

3.20

自引率

13.30%

发文量

168

审稿时长

8 months

期刊介绍： Aircraft Engineering and Aerospace Technology provides a broad coverage of the materials and techniques employed in the aircraft and aerospace industry. Its international perspectives allow readers to keep up to date with current thinking and developments in critical areas such as coping with increasingly overcrowded airways, the development of new materials, recent breakthroughs in navigation technology - and more.