A theoretical analysis of the electromagnetic environment of the AS330 super Puma helicopter external and internal coupling

Numerical techniques such as Finite Difference Time Domain (FDTD) computer programs, which were first developed to analyze the external electromagnetic environment of an aircraft during a wave illumination, a lightning event, or any kind of current injection, are now very powerful investigative tools. The program called GORFF-VE, was extended to compute the inner electromagnetic fields that are generated by the penetration of the outer fields through large apertures made in the all metallic body. Then, the internal fields can drive the electrical response of a cable network. The coupling between the inside and the outside of the helicopter is implemented using Huygen's principle. Moreover, the spectacular increase of computer resources, as calculations speed and memory capacity, allows the modellization structures as complex as these of helicopters with accuracy. This numerical model was exploited, first, to analyze the electromagnetic environment of an in-flight helicopter for several injection configurations, and second, to design a coaxial return path to simulate the lightning aircraft interaction with a strong current injection. The E field and current mappings are the result of these calculations

Constraints on Recoil Leader Properties Estimated from X-ray Emissions in Aircraft-Triggered Discharges

During Airbus aircraft campaigns flying into thunderstorms in 2014–2016, X-rays were observed during two stages of aircraft-triggered lightning: nanosecond pulses of X-rays associated with negative leader steps and bursts of X-rays during recoil events. This work will focus on the observations of X-ray bursts associated with recoils. Recoils are observed as microsecond-fast changes in the local electric field, associated with large currents passing through the aircraft, and are found to sometimes be associated with bursts of X-rays. From over 200 aircraft-triggered lightning strikes, 54 recoil events were found to be associated with microsecond bursts of X-rays. The majority of the bursts consist of 1–3 X-ray pulses, with some bursts containing as many as 29 X-ray pulses. We compare the observed superposed X-ray spectrum with modeled spectra using a GEANT4 model of the detector and aircraft, to determine the source potential needed to accelerate the electrons that produce the observed X-rays. A model of the recoil leader was made to determine the gap distance and gap potential between the recoil leader and the aircraft. From the modeling, we determine a solution space for the gap and leader lengths where the gap length is constrained by the observed minimum and maximum times between the onset of the X-ray pulses and the onset of the current pulses detected at the aircraft (1 to 93 m). We also find two constraints from the fitting of the modeled spectra to the superposed spectrum, limiting the leader length to between 1 and ∼240 m.publishedVersio

A neurophysiological interpretation of the respiratory act

Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/47945/1/10254_2005_Article_BF02320667.pd

In-flight lightning damage assessment system ILDAS, Tests on-ground and in-flight

The In-flight lightning damage assessment system ILDAS resulted from a EU-FP6 cooperation of 12 partners. It has successfully been completed with demonstration of operation in 2009. Airbus decided to develop the system further with EADS and NLR. The paper describes the magnetic field sensor selected for this phase 2, and briefly discusses the test on-ground and tests in flights through thunderstorms carried out up to now

In-flight Lightning Damage Assessment System (ILDAS) : in-flight verification of multi-sensor measurement

The goal of the ILDAS programme is to develop an operational system for determining the current waveform and attachment points of lightning striking aircraft in-flight. During a flight campaign, the system’s performance was verified using a multi-sensor configuration, capable of real-time detection of lightning strikes on the aircraft and automatic high-rate synchronous measurement and subsequent recording of sensor data from eight magnetic and one electric-field sensors. The measurement setup is presented, calibration is addressed and the first results from the flight test are presented