Abstract: A system and method for testing an antenna-under-test (AUT). A multi-probe antenna array transmitter is moved to a plurality of positions within a scan area. At each position, each probe antenna element of the transmitter transmits a near-field (NF) over-the-air (OTA) signal to the AUT. An alignment procedure is performed to align transmission locations for signals transmitted by different ones of the plurality of probe antenna elements. Correction factors are determined that characterize amplitude and phase discrepancies between the probe antenna elements of the transmitter. The correction factors are applied to the signals, and the corrected signals are combined at each transmission location to obtain average signals. A far-field (FF) reception pattern for the AUT is determined based on a discrete Fourier transform of the average signals and stored in a non-transitory computer readable memory medium.

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) surrounding a plenum (17) and having a first side portion (21), a second side portion (27), an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), wherein the leading edge panel (13) includes micro pores (45), wherein a first port device (49) is arranged in the first side portion (21) fluidly connected to the plenum (17) via a duct (53) defined by a duct structure (105), and wherein the first port device (49) comprises a first door (55) pivotable by a first hinge (57) about a first hinge axis (59).

Abstract: A system and method for testing an antenna-under-test (AUT). A multi-probe antenna array receiver is moved to a plurality of positions within a scan area. At each position, each probe antenna element of the receiver receives a near-field (NF) over-the-air (OTA) signal from the AUT. An alignment procedure is performed to align reception locations for signals received by different ones of the plurality of probe antenna elements. Correction factors are determined that characterize amplitude and phase discrepancies between the probe antenna elements of the receiver. The correction factors are applied to the received signals, and the corrected signals are combined at each reception location to obtain average signals. A far-field (FF) transmission pattern for the AUT is determined based on a discrete Fourier transform of the average signals and stored in a non-transitory computer readable memory medium.

Abstract: A system and method for testing an antenna-under-test (AUT). A multi-probe antenna array transmitter is moved to a plurality of positions within a scan area. At each position, each probe antenna element of the transmitter transmits a near-field (NF) over-the-air (OTA) signal to the AUT. An alignment procedure is performed to align transmission locations for signals transmitted by different ones of the plurality of probe antenna elements. Correction factors are determined that characterize amplitude and phase discrepancies between the probe antenna elements of the transmitter. The correction factors are applied to the signals, and the corrected signals are combined at each transmission location to obtain average signals. A far-field (FF) reception pattern for the AUT is determined based on a discrete Fourier transform of the average signals and stored in a non-transitory computer readable memory medium.

Abstract: A system and method for testing an antenna-under-test (AUT). A multi-probe antenna array receiver is moved to a plurality of positions within a scan area. At each position, each probe antenna element of the receiver receives a near-field (NF) over-the-air (OTA) signal from the AUT. An alignment procedure is performed to align reception locations for signals received by different ones of the plurality of probe antenna elements. Correction factors are determined that characterize amplitude and phase discrepancies between the probe antenna elements of the receiver. The correction factors are applied to the received signals, and the corrected signals are combined at each reception location to obtain average signals. A far-field (FF) transmission pattern for the AUT is determined based on a discrete Fourier transform of the average signals and stored in a non-transitory computer readable memory medium.

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27), an inner surface (33) and an outer surface (37), wherein the leading edge panel (13) having micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein a first air inlet/outlet device (49) is arranged in the first side portion (21) and a second air inlet outlet/device (51) is arranged in the second side portion (27), fluidly connected to the plenum (17), and wherein the first air inlet/outlet device (49) comprises a pivotable first door (55) and the second air inlet outlet/device (51) comprises a pivotable second door (61).

Abstract: A system and method for testing devices such as integrated circuits (IC) with integrated antenna arrays configured for wireless signal reception. The method performs a calibration operation on a reference device under test (DUT). During the calibration operation, the DUT receives a series of first signals from a first far-field (FF) location and a series of array transmissions from a second near-field (NF) location using different beamforming settings, and determines therefrom a set of calibration parameters. The calibration parameters may be used by a probe antenna system (PAS) to transmit an array transmission to the DUT from the second NF location to emulate a single probe or multi-probe transmission from the first FF location.

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27), an inner surface (33) and an outer surface (37), wherein the leading edge panel (13) having micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein a first air inlet/outlet device (49) is arranged in the first side portion (21) and a second air inlet outlet/device (51) is arranged in the second side portion (27), fluidly connected to the plenum (17), and wherein the first air inlet/outlet device (49) comprises a pivotable first door (55) and the second air inlet outlet/device (51) comprises a pivotable second door (61).

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) surrounding a plenum (17) and having a first side portion (21), a second side portion (27), an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), wherein the leading edge panel (13) includes micro pores (45), wherein a first port device (49) is arranged in the first side portion (21) fluidly connected to the plenum (17) via a duct (53) defined by a duct structure (105), and wherein the first port device (49) comprises a first door (55) pivotable by a first hinge (57) about a first hinge axis (59).

Abstract: A system and method for testing devices such as integrated circuits (IC) with integrated antenna arrays configured for wireless signal reception. The method performs a calibration operation on a reference device under test (DUT). During the calibration operation, the DUT receives a series of first signals from a first far-field (FF) location and a series of array transmissions from a second near-field (NF) location using different beamforming settings, and determines therefrom a set of calibration parameters. The calibration parameters may be used by a probe antenna system (PAS) to transmit an array transmission to the DUT from the second NF location to emulate a single probe or multi-probe transmission from the first FF location.

Abstract: Method for detecting a defective node which is connected to a bus, the node incrementing an internal error counter in a normal operating state when an error is detected, and the node switching to an isolated operating state, in which the node does not exchange any messages via the bus if the internal error counter of the node exceeds a predetermined error threshold value, and the node switching from the isolated operating state to the normal operating state when a condition is fulfilled and that change in state being detected, and the node being detected as being defective if a rate of the detected state changes exceeds an adjustable change rate or a number of detected state changes exceeds an adjustable state change threshold value.