Abstract

Visual corona tests have been broadly applied for identifying the critical corona points of diverse high-voltage devices, although other approaches based on partial discharge or radio interference voltage measurements are also widely applied to detect corona activity. Nevertheless, these two techniques must be applied in screened laboratories, which are scarce and expensive, require sophisticated instrumentation, and typically do not allow location of the discharge points. This paper describes the detection of the visual corona and location of the critical corona points of a sphere-plane gap configurations under different pressure conditions ranging from 100 to 20 kPa, covering the pressures typically found in aeronautic environments. The corona detection is made with a low-cost CMOS imaging sensor from both the visible and ultraviolet (UV) spectrum, which allows detection of the discharge points and their locations, thus significantly reducing the complexity and costs of the instrumentation required while preserving the sensitivity and accuracy of the measurements. The approach proposed in this paper can be applied in aerospace applications to prevent the arc tracking phenomenon, which can lead to catastrophic consequences since there is not a clear protection solution, due to the low levels of leakage current involved in the pre-arc phenomenon.

Highlights

  • Current aircraft architectures include complex systems and technologies, constituting the core equipment necessary for energizing and flying the aircrafts

  • The aviation industry is developing the generation of more electric aircrafts (MEA) with the final objective of the all-electric aircraft (AEA), which are friendlier from an environmental point of view

  • Due to the increment of electrical power installed in more electric aircrafts, the tendency is to setup (20, 30, and 40 mm gap)

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Summary

Introduction

Current aircraft architectures include complex systems and technologies, constituting the core equipment necessary for energizing and flying the aircrafts. The goal is to maximize performance and lower weight [1], reducing O&M costs, increasing overall reliability and power density and reducing greenhouse gas emissions, fuel consumption, and system complexity. This goal can be achieved by means of a gradual introduction of lighter and more compact electrical systems to substitute onboard mechanic, pneumatic, and hydraulic systems [1] used for powering landing gear systems, flight controls, anti-ice systems, brakes, or thrust reversers, as well as to pressurize the cabin or to start the engines

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