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Article
Publication date: 1 May 2006

Changduk Kong, Myoung‐cheol Kang, Chang‐ho Lee and Dong‐ju Han

To set‐up a specific design procedure for the smart unmanned aerial vehicle (UAV) fuel supply system which has been developed by Korean Aerospace Research Institute, and…

Abstract

Purpose

To set‐up a specific design procedure for the smart unmanned aerial vehicle (UAV) fuel supply system which has been developed by Korean Aerospace Research Institute, and to design it preliminarily with the fuel system requirement and target reliabilities.

Design/methodology/approach

The fuel system layout and fuel tank were determined through consideration of total fuel volume, fuel flow rate, reliability, weight, centre of gravity, etc. In sizing of components such as booster pumps, jet pumps, piping system, vent subsystem, refuelling and defuelling subsystem, engine fuel flow requirement, pressure loss, component failure rate, weight and centre of gravity were considered. Finally, the reliability analysis of the preliminary designed fuel system was carried out.

Findings

According to the reliability analysis and weight estimation results, it was confirmed that the proposed fuel system agreed well with the design specifications and target reliabilities required by the vehicle system.

Research limitations/implications

In current preliminary design phase, the most important consideration is the reliability of the fuel system. Therefore, the weight estimation of the designed fuel system to meet this reliability requirement could not meet partially the system's requirements. In the next design step, the proper fuel system for weight reduction will be performed through an optimization process between weight and reliability.

Originality/value

A specific design procedure components' sizing to meet system requirement target reliability for UAV vertical take‐off/landing was proposed.

Details

Aircraft Engineering and Aerospace Technology, vol. 78 no. 3
Type: Research Article
ISSN: 0002-2667

Keywords

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Article
Publication date: 1 February 1974

THE FUEL SYSTEM is a simple state‐of‐the‐art system which is designed to minimise system maintenance and provide a very high probability of mission success. It requires no…

Abstract

THE FUEL SYSTEM is a simple state‐of‐the‐art system which is designed to minimise system maintenance and provide a very high probability of mission success. It requires no fuel management or manipulation of system controls during a normal mission. It is designed to use MIL‐J‐5624G, grades JP‐4 and JP‐5 turbine fuel.

Details

Aircraft Engineering and Aerospace Technology, vol. 46 no. 2
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 August 1973

Fuel measuring and control systems have become progressively more sophisticated as aircraft performance has been extended both in the number of operating regimes and in…

Abstract

Fuel measuring and control systems have become progressively more sophisticated as aircraft performance has been extended both in the number of operating regimes and in operational capability. The fuel tank arrangements for the conventional aircraft types of the pre‐supersonic era, both piston and jet‐engined, allowed fairly straight‐forward fuel gauging and management. The tank dispositions were usually in line from left to right across the span of the wing. The advent of the swept wing aircraft introduced the complexities of fore and aft fuel balance in order to limit excursions of the CG about aft of the centre of lift. At the same time the operating economics of both military and civil aircraft, with massive fuel rate demand, required the development of fuel management systems capable of measuring and indicating fuel consumption and quantities to higher orders of accuracy.

Details

Aircraft Engineering and Aerospace Technology, vol. 45 no. 8
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 June 1998

Terry Ford

Explains the fuel system of the Boeing 777‐200 aircraft. Looks at the system’s features, the fuel feed, the fuel jettison and the flight deck displays in terms of the fuel system.

Abstract

Explains the fuel system of the Boeing 777‐200 aircraft. Looks at the system’s features, the fuel feed, the fuel jettison and the flight deck displays in terms of the fuel system.

Details

Aircraft Engineering and Aerospace Technology, vol. 70 no. 3
Type: Research Article
ISSN: 0002-2667

Keywords

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Article
Publication date: 1 May 1996

Terry Ford

Discusses the requirements for refuelling civil airliners, particularly under pressure refuelling. Analyses the problems that can arise and demonstrates how advancing…

Abstract

Discusses the requirements for refuelling civil airliners, particularly under pressure refuelling. Analyses the problems that can arise and demonstrates how advancing technology has changed the appearance and efficiency of many components, particularly with reference to the control panel. Describes in detail the workings of a typical system; aspects of control of fuel quantity in refuelling; refuel control panels; and fuel gauges, with particular reference to the Boeing 777.

Details

Aircraft Engineering and Aerospace Technology, vol. 68 no. 5
Type: Research Article
ISSN: 0002-2667

Keywords

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Article
Publication date: 1 April 1967

C.E.G. Payne

CONTROL SYSTEM PHILOSOPHY THE prime functions of any engine control system arc to provide stable speed governing and protection against overstressing the engine. Speed…

Abstract

CONTROL SYSTEM PHILOSOPHY THE prime functions of any engine control system arc to provide stable speed governing and protection against overstressing the engine. Speed control is usually effected by hydro‐mechanical or hydro‐electrical governing of the fuel flow; overstressing is normally avoided by limiting engine temperature, turbine entry temperature, pressure, overspeeding and acceleration.

Details

Aircraft Engineering and Aerospace Technology, vol. 39 no. 4
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 17 October 2018

Raghu Chaitanya Munjulury, Ingo Staack, Adrián Sabaté López and Petter Krus

This paper aims to present a knowledge-based fuel system, implementation and application, oriented towards its use in aircraft conceptual design.

Abstract

Purpose

This paper aims to present a knowledge-based fuel system, implementation and application, oriented towards its use in aircraft conceptual design.

Design/methodology/approach

Methodology and software tools oriented to knowledge-based engineering applications (MOKA) is used as a foundation for the implementation and integration of fuel systems.

Findings

Including fuel systems earlier in the design process creates an opportunity to optimize it and obtain better solutions by allocating suitable locations in an aircraft, thereby reflecting on the centre of gravity of the aircraft.

Research limitations/implications

All geometries are symbolic, representing a space allocation inside the aircraft for the fuel system. A realistic representation of the real components could be realized in detail design.

Practical implications

Fuel weight is a significant part of take-off weight and decisive in aircraft sizing and range estimations. The three-dimensional geometry provides a better estimation of the volume that is available to allocate the necessary entities. It also provides fast measures for weight and balance, fuel capacity, relative tank positions and a first estimation of piping length.

Originality/value

Fuel systems appear early in the design process, as they are involved in several first estimations. By using a knowledge-based engineering approach, several alternatives can be visualized and estimated in the conceptual design process. Furthermore, using the weights and centre of gravity at different angles of pitch and roll of each fuel tank, the aircraft could be optimized for handling qualities by using automatically generated system simulation models.

Details

Aircraft Engineering and Aerospace Technology, vol. 90 no. 7
Type: Research Article
ISSN: 1748-8842

Keywords

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Article
Publication date: 10 June 2021

Sinan Keiyinci and Kadir Aydin

The endurance of small unmanned air vehicles (UAVs) is directly associated with the energy density of the propulsion system used. As the batteries commonly used in small…

Abstract

Purpose

The endurance of small unmanned air vehicles (UAVs) is directly associated with the energy density of the propulsion system used. As the batteries commonly used in small UAVs have a relatively low energy density, they are not sufficient for long-term endurance tasks. The purpose of this paper is to offer a solution to increase the endurance of a concept small UAV with combination of different power sources. The design, construction and ground tests of fuel cell-powered hybrid propulsion systems are presented in this paper.

Design/methodology/approach

The power requirements of a concept UAV were calculated according to aerodynamic calculations and then, hybrid propulsion system sources are determined. The hybrid system consists of a 100 W scale proton-exchange membrane (PEM) type fuel cell stack, lithium-polymer battery, solar cells and power management system (PMS). Subsequently, this hybrid power system was integrated with the new design of PMS and then series of ground tests were carried out.

Findings

This experimental study proved that it is theoretically possible to obtain an endurance of around 3 h for concept UAV with the proposed hybrid system.

Practical implications

The research study shows that fuel cell-based hybrid propulsion system with the proposed PMS can be widely used to obtain extended endurance in small UAVs.

Originality/value

A hybrid propulsion system with a novel PMS unit is proposed for small UAVs and the ground tests were implemented.

Details

Aircraft Engineering and Aerospace Technology, vol. ahead-of-print no. ahead-of-print
Type: Research Article
ISSN: 1748-8842

Keywords

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Article
Publication date: 1 May 1953

DOWTY Equipment Limited began the study of fuel systems for gas turbines in 1944, following the adoption by the de Havilland Engine Company of the Dowty Live Line Pump as…

Abstract

DOWTY Equipment Limited began the study of fuel systems for gas turbines in 1944, following the adoption by the de Havilland Engine Company of the Dowty Live Line Pump as the most promising type for conversion to a fuel pump. The resulting co‐operation hd to a widening interest and in 1945 the first design schemes for a complete fuel system were initiated.

Details

Aircraft Engineering and Aerospace Technology, vol. 25 no. 5
Type: Research Article
ISSN: 0002-2667

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Article
Publication date: 1 February 1995

Terry Ford

A conference at the Institution of Mechanical Engineers detailed many features concerned with fuel systems in airframes and the aspects of refuelling today's…

Abstract

A conference at the Institution of Mechanical Engineers detailed many features concerned with fuel systems in airframes and the aspects of refuelling today's large‐capacity aircraft. The influence of the aircraft requirements on both civil and military aircraft fuelsystem specifications were dealt with, the former by British Aerospace Airbus.

Details

Aircraft Engineering and Aerospace Technology, vol. 67 no. 2
Type: Research Article
ISSN: 0002-2667

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