Abstract: A MEMS sensor device comprises a support substrate, a proof mass movably connected to the support substrate, a first drive comb fixedly connected to the support substrate in a first orientation and adjacent to the proof mass, and a second drive comb fixedly connected to the support substrate in a second orientation and adjacent to the proof mass. The second orientation is opposite of the first orientation such that the first and second drive combs face toward each other. A parallel plate sense electrode is located under the proof mass on the support substrate. The drive combs and the parallel plate sense electrode are each electrically charged and configured with respect to the proof mass such that a combination of a levitation force and a parallel plate force produces a linear out-of-plane actuation that depends only on an applied voltage.

Abstract: An embodiment of a gyroscope subsystem that is configured to reduce, or to eliminate, the effect of bias includes a gyroscope assembly, a calibration assembly, a determining circuit, and a bias-reducing circuit. The gyroscope assembly is configured to generate a gyroscope signal in response to a calibration angular velocity and another angular velocity about a sense axis, and the calibration assembly is configured to generate, about the sense axis, the calibration angular velocity. The determining circuit is configured to determine the other angular velocity in response to the gyroscope signal, and the bias-reducing circuit is configured to reduce a bias component of the determined other angular velocity in response to the gyroscope signal. For example, such a gyroscope subsystem can yield a value of an angular velocity having a bias component that is significantly less than the bias component of a value yielded by a conventional gyroscope subsystem.

Abstract: A microelectromechanical systems (MEMS) device comprises an optical directional coupler comprising: a first waveguide having a first and a second end, wherein a light beam is introduced into the first end; a second waveguide having a third and a fourth end, wherein the light beam is evanescently coupled between the two waveguides in the central region; a first photodetector to detect first optical power in the light beam at the second end; and a second photodetector to detect second optical power in the light beam at the fourth end; a vibrating proof mass adjacent to the coupler in a first direction from the coupler, wherein when inertial forces are applied to the MEMS device in a second direction, the proof mass moves in the first direction; a processor to determine the displacement of the proof mass from the coupler as a function of the first and the second optical power.

Abstract: A shock-isolated mounting device and a method and system are provided. For example, the shock-isolated mounting device includes an enclosure configured to support the mounting device, at least one damper attached between the mounting device and the enclosure, and a thermally-conductive element disposed on a surface of the mounting device and configured to thermally couple the mounting device to the enclosure. The thermally-conductive element facilitates the dissipation of heat generated by electronic components mounted onto the shock-isolated mounting device.

Abstract: A microelectromechanical systems (MEMS) device comprises an optical directional coupler comprising: a first waveguide having a first and a second end, wherein a light beam is introduced into the first end; a second waveguide having a third and a fourth end, wherein the light beam is evanescently coupled between the two waveguides in the central region; a first photodetector to detect first optical power in the light beam at the second end; and a second photodetector to detect second optical power in the light beam at the fourth end; a vibrating proof mass adjacent to the coupler in a first direction from the coupler, wherein when inertial forces are applied to the MEMS device in a second direction, the proof mass moves in the first direction; a processor to determine the displacement of the proof mass from the coupler as a function of the first and the second optical power.

Abstract: A shock-isolated mounting device and a method and system are provided. For example, the shock-isolated mounting device includes an enclosure configured to support the mounting device, at least one damper attached between the mounting device and the enclosure, and a thermally-conductive element disposed on a surface of the mounting device and configured to thermally couple the mounting device to the enclosure. The thermally-conductive element facilitates the dissipation of heat generated by electronic components mounted onto the shock-isolated mounting device.

Abstract: A MEMS sensor device comprises a support substrate, a proof mass movably connected to the support substrate, a first drive comb fixedly connected to the support substrate in a first orientation and adjacent to the proof mass, and a second drive comb fixedly connected to the support substrate in a second orientation and adjacent to the proof mass. The second orientation is opposite of the first orientation such that the first and second drive combs face toward each other. A parallel plate sense electrode is located under the proof mass on the support substrate. The drive combs and the parallel plate sense electrode are each electrically charged and configured with respect to the proof mass such that a combination of a levitation force and a parallel plate force produces a linear out-of-plane actuation that depends only on an applied voltage.

Abstract: An embodiment of a gyroscope subsystem that is configured to reduce, or to eliminate, the effect of bias includes a gyroscope assembly, a calibration assembly, a determining circuit, and a bias-reducing circuit. The gyroscope assembly is configured to generate a gyroscope signal in response to a calibration angular velocity and another angular velocity about a sense axis, and the calibration assembly is configured to generate, about the sense axis, the calibration angular velocity. The determining circuit is configured to determine the other angular velocity in response to the gyroscope signal, and the bias-reducing circuit is configured to reduce a bias component of the determined other angular velocity in response to the gyroscope signal. For example, such a gyroscope subsystem can yield a value of an angular velocity having a bias component that is significantly less than the bias component of a value of yielded by a conventional gyroscope subsystem.

Abstract: A method of displaying navigation limits for a planned travel route of a vehicle is presented here. The method calculates estimated navigation limits for the vehicle using an onboard subsystem of the vehicle, where the estimated navigation limits represent self-assessed navigation accuracy of the vehicle relative to the planned travel route. Contracted navigation limits are acquired for the vehicle, where the contracted navigation limits represent specified navigation accuracy of the vehicle, relative to the planned travel route, as mandated by a third party navigation controller. A navigation display is rendered on an onboard display element such that it includes graphical representations of the planned travel route, at least one of the estimated navigation limits, and at least one of the contracted navigation limits.

Abstract: An airport surface collision-avoidance system (ASCAS). An exemplary system includes sensors (e.g., radar) at light modules about an aircraft, with user interface devices located with airport ground personnel and in the cockpit of the aircraft. The system helps to avoid collisions on the airport surface, i.e., during taxiing clear of airport buildings, during taxiing close to airport buildings, during gate operations (push-back and standing), etc. The system includes components for communicating sensor information to ground service equipment (tug tractor, baggage cart, refueling truck, etc.). The system can determine possible collision for any part of the aircraft (wingtip, tail assembly, engine cowl, fuselage, door, etc).

Abstract: A method and software program for providing a weather prediction of atmospheric parameters for an aircraft, includes collecting (202) at least one of a statistical description of the weather forecast or the historical weather data, processing (210) current atmospheric data received from sensors on-board the aircraft, forming (230) modeled data based on the processed current atmospheric data and the at least one of a statistical description of the weather forecast or the historical weather data, blending (250) the modeled data with the at least one of a statistical description of the weather forecast or the historical weather data, and predicting (270) atmospheric parameters based on the blending step.

Abstract: Methods and systems are provided for executing a single continuous altitude change by an aircraft to cruise altitude using an electronic flight bag via a flight management system. The method comprises the determination of an altitude change in a flight plan during the cruise phase of the flight plan. Based on the altitude change and a mathematical model of the aircraft an optimum vertical trajectory profile or the aircraft is determined from which an angle of attack (AOA) and a thrust is derived to achieve the optimum vertical trajectory. From the AOA and the thrust, the required aircraft control variables are determined that may be applied to the engines and the control surface actuators of the aircraft.

Abstract: A method of displaying navigation limits for a planned travel route of a vehicle is presented here. The method calculates estimated navigation limits for the vehicle using an onboard subsystem of the vehicle, where the estimated navigation limits represent self-assessed navigation accuracy of the vehicle relative to the planned travel route. Contracted navigation limits are acquired for the vehicle, where the contracted navigation limits represent specified navigation accuracy of the vehicle, relative to the planned travel route, as mandated by a third party navigation controller. A navigation display is rendered on an onboard display element such that it includes graphical representations of the planned travel route, at least one of the estimated navigation limits, and at least one of the contracted navigation limits.

Abstract: A method and software program for providing a weather prediction of atmospheric parameters for an aircraft, includes collecting (202) at least one of a statistical description of the weather forecast or the historical weather data, processing (210) current atmospheric data received from sensors on-board the aircraft, forming (230) modeled data based on the processed current atmospheric data and the at least one of a statistical description of the weather forecast or the historical weather data, blending (250) the modeled data with the at least one of a statistical description of the weather forecast or the historical weather data, and predicting (270) atmospheric parameters based on the blending step.