Abstract: An automatic test generator (ATG) parses a computer-executable design model of operational software of an aircraft electronic device to identify design model data coupling and design model control coupling between functional modules of the design model. The ATG generates a plurality of test conditions configured to test whether the operational software of the aircraft electronic device satisfies the design model data coupling and the design model control coupling. A test procedure that implements the plurality of test conditions is generated. The test procedure is executed on the operational software of the aircraft electronic device. An indication of whether the operational software of the aircraft electronic device satisfies each respective one of the plurality of test conditions is output.

Abstract: An imager device disposed on a moving body captures first image data at a first time and second image data at a second, subsequent time. An inertial measurement unit (IMU) disposed on the moving body senses motion of the moving body between the first time and the second time. The first image data is registered to the second image data based on inertial measurement data corresponding to the sensed motion to produce first registered image data. In response to identifying that image features are common to both the first registered image data and the second image data, the first registered image data is registered to the second image data based on the identified common features to produce output registered image data. In response to determining that no image features are common to both the first registered image data and the second image data, the first registered image data is output.

Abstract: An electronic system of a device includes first and second circuit boards and a flexible connector configured to electrically connect the first and second circuit boards. The flexible connector includes a serpentine portion that includes first, second and third legs. The first leg that extends in a first direction, the second leg extends in a second direction opposite of the first direction, and the third leg extends in the first direction. The first, second and third legs are configured in a common plane when the device is in an operational state.

Abstract: An electronic system includes first and second circuit boards and a flexible circuit connector. The flexible circuit connector is configured to electrically connect the first and second circuit boards. The flexible circuit connector includes first and second connectors and a spiral portion. The first connector is configured to connect to the first circuit board. The second connector is configured to connect to the second circuit board. The spiral portion is connected between the first and second circuit boards and includes a circumferential portion that extends around the second connector.

Abstract: A sensor system includes a plurality of strain gauges and a passive compensation circuit. The plurality of strain gauges are configured to provide an output voltage indicative of a sensed pressure using an input voltage. The passive compensation circuit that includes a span resistor, first and second compensation resistors, and a zero offset resistor. The span resistor is connected between an input voltage and the pressure sensor and is configured to control a range of an output voltage for a pressure range of the pressure sensor. The first and second compensation resistors are operatively connected in parallel with the pressure sensor and are configured to control current provided to the pressure sensor. The zero offset resistor is operatively connected between the first and second compensation resistors and the pressure sensor and is configured to control a base value of the output voltage for zero pressure.

Abstract: An inertial measurement unit (IMU) includes an inertial sensor assembly including a plurality of accelerometers and a plurality of rate gyroscopes, an inertial sensor compensation and correction module, and a Kalman estimator module. The inertial sensor compensation and correction module is configured to apply a set of error compensation values to sensed acceleration and rotational rate to produce a compensated acceleration and a compensated rotational rate of the IMU. The Kalman estimator module is configured to determine a set of error correction values based on a difference between a change in integrated acceleration of the IMU and a change in true airspeed of the IMU. The inertial sensor compensation and correction module is further configured to apply the set of error correction values to each of the compensated acceleration and the compensated rotational rate to output an error-corrected acceleration and an error-corrected rotation rate.

Abstract: A pressure sensor comprising a housing, a diaphragm wafer, and an isolator configured to absorb lateral stress. The diaphragm wafer includes a fully exposed diaphragm, a fluid contact surface, a sensing element, and a support portion, where the support portion and the contact surface define a cavity. The isolator extends laterally from the support portion to the housing. The pressure sensor is easily drainable, eliminating the buildup of particulates, and the diaphragm can be directly wire-bonded to printed circuit boards, eliminating the need for extensive electrical feedthrough.

Abstract: Apparatus and associated methods relate to calculating position and/or range data of object(s) in a scene external to an aircraft. A light projector is configured to project, from an aircraft projector location, a collimated beam of light in a controllable direction onto the scene. The light projector is further configured to control the intensity of the projected light, based on the controlled direction of the collimated beam of light. The reflected beam is detected by a camera located apart from the light projector. An image processor is configured to use triangulation, to calculate position values and/or range data of the object(s) in the scene. The image processor can be further configured to identify the object(s) in the scene and to produce, based in object(s) in the scene, one or more maps of the scene. The intensity of the collimated beam can be controlled based on the produced maps.

Abstract: Apparatus and associated devices relate to a system for measuring a maximum size of super-cooled water droplets in a cloud atmosphere. The system includes a housing having a convex exterior surface on a forward end and having stabilizers projecting from an aft end. The system includes a gimballed mounting mechanism configured to attach the housing to an aircraft while permitting the housing to freely pitch and yaw with respect to the aircraft. When an airstream engages the stabilizers, the housing aligns with a direction of the engaging airstream. The system includes a sequence of indices on a corresponding sequence of ice-accretion regions of the convex exterior surface, each of the sequence of indices visible in the absence of ice accretion. The forward-most ice-free one of the sequence of indices is indicative of a maximum size of super-cooled water droplets.

Abstract: A differential pressure sensor is a body with first and second interior channels connected to process fluid inlets and separated by a barrier. Each side of a MEMS pressure sensing diaphragm in the barrier is fluidly connected to a process fluid inlet. The diaphragm is mounted on a hollow pedestal such that one side of the diaphragm is fluidly connected to a process fluid inlet through an interior channel in the pedestal that is adhesively attached to an annular bottom of a cylindrical cavity inside the body. The other side of the diaphragm is fluidly connected to the other process fluid inlet and is fluidly isolated from the first fluid inlet by the adhesive at the bottom of the pedestal. Deformation of the diaphragm due to a pressure difference between the process fluid inlets detected by sensors on the diaphragm indicates a differential pressure.

Abstract: Apparatus and associated methods relate to maximizing a signal to noise ratio of an accelerometer by inhibiting signals arising from movements of a proofmass in directions perpendicular to a direction of intended sensitivity. The direction of intended sensitivity of the accelerometer is along an axis of the proofmass. The accelerometer is rendered substantially insensitive to lateral accelerations of the proofmass by making the accelerometer axially symmetric. Two axially-asymmetric acceleration sensing devices are axially engaged in such a manner as to render the coupled sensing devices substantially axially-symmetric. In some embodiments, each acceleration sensor has an axially-thin membrane portion extending from a proofmass portion. The two acceleration sensors can be engaged in an antiparallel fashion at projecting ends of the proofmass portions.

Abstract: An angle of attack sensing system includes a rotatable vane, a first pressure sensing port, a second pressure sensing port, a vane position sensor, and a fault detector. The rotatable vane includes a first surface and a second surface opposite the first surface. The first pressure sensing port is disposed in the first surface. The second pressure sensing port is disposed in the second surface. The vane position sensor is configured to output a rotational position signal of the rotatable vane. The fault detector is configured to output an indication of a rotational fault condition based on a difference between a first sensed pressure from the first pressure sensing port and a second sensed pressure from the second pressure sensing port.

Abstract: Apparatus and associated methods relate to ranging an object nearby an aircraft by triangulation of spatially-patterned light projected upon and reflected from the object. The spatially patterned light can have a wavelength corresponding to infrared light and/or to an atmospheric absorption band. In some embodiments, images of the object are captured both with and without illumination by the spatially-patterned light. A difference between these two images can be used to isolate the spatially-patterned light. The two images can also be used to identify pixel boundaries of the object and to calculate ranges of portions of the object corresponding to pixels imaging these portions. For pixels imaging reflections of the spatially-patterned light, triangulation can be used to calculate range. For pixels not imaging reflections of the spatially-patterned light, ranges can be calculated using one or more of the calculated ranges calculated using triangulation corresponding to nearby pixels.

Abstract: Apparatus and associated methods relate to determining a size and/or density of Super-cooled Large Droplets (SLDs) in a cloud atmosphere by comparing detected optical signals reflected from small and large sampling volumes of a cloud atmosphere. In some embodiments, an optical pulse is generated and divergently projected from a first optical fiber. A collimating lens is aligned within the divergently projected optical pulse collimating a portion thereof. The collimated and uncollimated portions of the optical pulse are projected into the small and large sampling volumes of the cloud atmosphere, respectively. The ratio of the collimated to the uncollimated portions can be optically controlled. Signals corresponding to optical pulses having different collimated/uncollimated ratios are backscattered by the cloud atmosphere, detected and compared to one another.

Abstract: A method of making an air data probe may comprise forming a probe body, forming an interior cavity into the probe body, applying a protective shell to the probe body by an additive manufacturing technique, inserting a heating element into the interior cavity, machining a final profile of the air data probe, and forming a sensing port comprising a port passage defined through the probe body and lined by a portion of the protective shell.

Abstract: A system has a plurality of transmission-capable nodes. A method is provided for suppressing interference at a critical sensor situated within this system. The system is first three-dimensionally mapped. Next, phase shifts are estimated for transmissions from the nodes to produce net destructive interference at the critical sensor, based on the three-dimensional mapping of the system. An aggregate electromagnetic signal from the nodes is sensed at the critical sensor. The phase shifts are then adjusted based on the sensed aggregate electromagnetic signal.

Abstract: A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) that is electrically coupled with a first static pressure sensor. A second air data system for providing second aircraft air data parameter outputs is formed by a first electronics channel of a second MFP that is electrically coupled with a second static pressure sensor. A third air data system for providing third aircraft air data parameter outputs is formed by a second electronics channel of the first MFP that is electrically coupled with a second electronics channel of the first MFP.

Abstract: Apparatus and associated methods relate to coordinating targeting among multiple guided ordnances using inter-ordnance optical communications. An inter-ordnance communications channel is optically established between leading and trailing guided ordnances travelling in substantially the same direction. The leading guided ordnance emits an optical beacon in a direction aft of the direction of ordnance travel, and a trailing guided ordnance captures images that contain the optical beacon emitted by the leading guided ordnance. The trailing guided ordnance is configured to chart a trajectory of the leading guided ordnance. The trailing guided ordnance is configured to predict which, among multiple targets identified in the captured images, is a first target consistent with the charted trajectory of and therefore selected by the leading ordnance.

Abstract: A temperature sensor includes a sensor body and a wedge extension. The sensor body extends from a sensor base to an opposed sensor tip along a longitudinal axis. The sensor body has a leading edge and opposed trailing edge. The sensor body also has an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage. The wedge extension is on the sensor body between the sensor tip and the sensor base on the leading edge of the sensor body.