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Technical Paper

Adaptive Protection Methods for Aircraft Applications

2010-11-02
2010-01-1750
Complex certification issues aside, aircraft electrical systems possess a number of attributes that present good opportunities for the implementation of adaptive protection systems. Rather than experiencing the complex upgrade process faced in the application of adaptive protection to grid based networks, the opportunity to incorporate their functionality at the design stage of new aircraft systems encourages their use and even offers the potential to implement highly integrated protection and control systems. The physically compact nature of aircraft electrical systems and the presence of an existing communications infrastructure should permit the use of both local and remotely obtained power system data within the adaptive protection systems, maximizing the opportunities for achieving highly capable systems.
Technical Paper

Average-Value Diode Rectifier Modeling for Aerospace Applications

2011-10-18
2011-01-2621
Modern aerospace power systems commonly make use of uncontrolled rectifiers to satisfy many power conversion needs on board the aircraft. Whilst being highly accurate, an analytically detailed simulation of the aircraft power system, which includes all electric machine dynamics, semiconductor switching states, and power system dynamics, is often very computationally demanding. Average-value models of power electronic converters, with their reduced computational requirement, offer one potential solution to this issue. However, of the many converter topologies presented in the literature, average-value models of uncontrolled diode rectifiers are perhaps the most challenging to develop. The dependence of the rectifier's operating state on its loading conditions and the surrounding network topology complicates the derivation of average-value models.
Journal Article

Parametric Average-Value Converter Modeling for Aerospace Applications

2012-10-22
2012-01-2156
Uncontrolled rectifiers are featured heavily in aircraft electrical power systems performing a number of the power conversion and conditioning functions. Detailed modeling and simulation of these and other converters as part of a wider aircraft power system, whilst accurate, can be very computationally intensive, resulting in impractically slow simulation speed. One potential solution to this issue is the use of average-value converter models, which offer a much lower computational requirement and can utilize larger time steps. Of the average-value diode rectifier modeling methods presented in the research literature the parametric method is particularly well suited to system-level simulation because it can be readily derived to represent all modes of rectifier operation. To date however, published results utilizing this methodology have been limited to simpler power system architectures.
Journal Article

An Optimisation Based Design Approach for Aircraft Electrical Power Systems

2014-09-16
2014-01-2121
The More Electric Aircraft (MEA) concept coupled with recent advances in power electronics has seen an increasing number of on-board tasks being facilitated by electrical power, as opposed to more conventional hydraulic, mechanical and pneumatic power systems. The migration to a predominantly electrical power system is expected to bring significant cost and performance benefits; however, the devices used to facilitate this change have led to an increasingly complicated electrical power system with heightened levels of system sophistication and interdependence. These developments have the potential to drastically alter the solution space of all feasible aircraft Electrical Power System (EPS) designs. The technological advancements facilitating the MEA progression have allowed for a broader range of design solutions to exist that increase the size of the solution space. Meanwhile increasing system sophistication has led to an increasingly non-linear and complex solution space.
Journal Article

A Method for the Evaluation of the Effectiveness of Turboelectric Distributed Propulsion Power System Architectures

2014-09-16
2014-01-2120
Radical new electrically propelled aircraft are being considered to meet strict future performance goals. One concept design proposed is a Turboelectric Distributed Propulsion (TeDP) aircraft that utilises a number of electrically driven propulsors. Such concepts place a new and significant reliance on an aircraft's electrical system for safe and efficient flight. Accordingly, in addition to providing certainty that supply reliability targets are being met, a contingency analysis, evaluating the probability of component failure within the electrical network and the impact of that failure upon the available thrust must also be undertaken for architecture designs. Solutions that meet specified thrust requirements at a minimum associated weight are desired as these will likely achieve the greatest performance against the proposed emissions targets.
Journal Article

Impact of Converter Interface Type on the Protection Requirements for DC Aircraft Power Systems

2012-10-22
2012-01-2224
The utilization of converter interfaces has the potential to significantly alter the protection system design requirements in future aircraft platforms. However, the impact these converters will have can vary widely, depending on the topology of converter, its filter requirements and its control strategy. This means that the precise impact on the network fault response is often difficult to quantify. Through the analysis of example converter topologies and literature on the protection of DC networks, this paper tackles this problem by identifying key design characteristics of converters which influence their fault response. Using this information, the converters are classified based on their general fault characteristics, enabling potential protection issues and solutions to be readily identified. Finally, the paper discusses the potential for system level design benefits through the optimisation of converter topology and protection system design.
Journal Article

Modeling and Simulation Enabled UAV Electrical Power System Design

2011-10-18
2011-01-2645
With the diversity of mission capability and the associated requirement for more advanced technologies, designing modern unmanned aerial vehicle (UAV) systems is an especially challenging task. In particular, the increasing reliance on the electrical power system for delivering key aircraft functions, both electrical and mechanical, requires that a systems-approach be employed in their development. A key factor in this process is the use of modeling and simulation to inform upon critical design choices made. However, effective systems-level simulation of complex UAV power systems presents many challenges, which must be addressed to maximize the value of such methods. This paper presents the initial stages of a power system design process for a medium altitude long endurance (MALE) UAV focusing particularly on the development of three full candidate architecture models and associated technologies.
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