Converter topology analysis for aircraft application

Brombach, J.; Jordan, Michael Guilherme; Grumm, Florian; Schulz, Detlef

doi:10.1109/speedam.2012.6264483

Cited by 22 publications

(8 citation statements)

References 5 publications

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“…The heatsink weight and the inductor weight are considered when drawing the conclusion for each aerospace application where the power loss is not as important as the weight in aerospace applications. Around half of the electrical power distribution system weight is caused by the converters approximately 400kg at short-and midrange aircraft [30]. Therefore, a weight optimization of these internal converters can highly contribute to the weight reduction of the whole electrical power system.…”

Section: Scope Of Work and Study Limitationmentioning

confidence: 99%

Optimal switching frequency for aerospace power converter systems

Thavaratnam¹

2021

Preprint

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Switching frequency is one of the main deciding factors in development of a power converter system for aerospace applications. The filter is one of the major components that significantly contribute to the overall system weight and efficiency. The design of the filter, including inductor and capacitor is determined by the switching frequency. On the other hand, the device switching loss is proportional to the loss, which in turn changes the design of thermal system. Thus selection of optimal switching frequency is essential for power converter systems used in aerospace industry. The objective of this study is to select the optimal switching frequency when the overall converter weight is minimal. In this study, switching frequencies ranging from 9kHz to 20kHz is selected based on current IGBT technology. Proven design algorithm for passive filter is adopted in the optimization. Partial verification for power efficiency is conducted via simulation and experiment results.

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Section: Scope Of Work and Study Limitationmentioning

confidence: 99%

Optimal switching frequency for aerospace power converter systems

Thavaratnam¹

2021

Preprint

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“…The weight saving potential of this architecture is small compared to the architecture in Fig 4. In this topology all cabin loads have HVDC, too. With DC supplied loads the internal converters could be build much lighter because a heavy PFC is not required anymore [3] [4]. The current consumption of a Constant-Power-Load is not proportional to the supply voltage.…”

Section: Aircraft Power Supply Systemmentioning

confidence: 99%

“…Furthermore, electrical power is often converted to different voltage levels several times in modern aircraft [3] [4]. For example a generator voltage of 230 V AC is transformed to 115 V AC for the supply of cabin loads and converted to 28 V DC for the avionic system.…”

Section: Introductionmentioning

confidence: 99%

Influence of small Constant-Power-Loads on the power supply system of an aircraft

Brombach

Jordan

Grumm

et al. 2013

2013 International Conference-Workshop Compatibility and Power Electronics

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Today most electrical consumers in an aircraft grid are electronic loads. Compared to resistive or motoric loads these loads have constant power consumption, which is independent of the supply voltage. This characteristic may have a negative effect on the stability of a power supply system. In addition real Constant-Power-Loads can have some other peculiarities. Depending of the topology or the supplied voltage type (AC or DC) the dynamic characteristic differs. This paper deals with a characterization of 4 types of Constant-Power-Loads in an actual and future aircraft grid. The investigations are focused to the dynamic characterization of different loads. Theoretical investigations are combined with measurements in an artificial aircraft grid with realistic supply voltage variations.

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“…Matrix converter can be suitable for aircraft system as it provides all silicon solution by directly converting line frequency AC to high frequency AC [6], [7], [10]- [13] and [16]. A 3x1 matrix topology followed by high frequency isolation transformer and diode rectifier has been used for telecommunication and electrical vehicle charging applications [9], [14], and [16].…”

Section: Introductionmentioning

confidence: 99%

A novel matrix based isolated three phase AC-DC converter with reduced switching losses

Singh

Das

Panda

2015

2015 IEEE Applied Power Electronics Conference and Exposition (APEC)

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This paper presents a matrix based isolated three phase AC-DC converter suitable for aircraft application. A three -phase to single-phase (3x1) matrix topology with novel modulation scheme named as Switched Rectifier Inverter (SRI) is introduced for direct line frequency AC to high frequency AC conversion which in effect, eliminates the requirement of bulky DC link capacitor and therefore, provides high power density essential for the aircraft systems. The high frequency AC output of the matrix (3x1) converter is processed by high frequency transformer followed by rectifier to obtain isolated DC output voltage. The operation of the proposed converter with SRI modulation scheme is explained. Moreover, the input power quality under the proposed modulation scheme is discussed for wide load range. Comprehensive simulation is carried out in PSIM for an example converter of input 120 V (rms), 400 Hz AC to 400 V DC with 8 kW power.

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Converter topology analysis for aircraft application

Cited by 22 publications

References 5 publications

Optimal switching frequency for aerospace power converter systems

Optimal switching frequency for aerospace power converter systems

Influence of small Constant-Power-Loads on the power supply system of an aircraft

A novel matrix based isolated three phase AC-DC converter with reduced switching losses

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