Abstract: A fin retention and deployment mechanism includes a detent in each of a plurality of fins, a mechanism that engages the detent, and at least one spring clip that maintains each of the fins in a non-deployed position. The mechanism also includes a gas generator, a manifold, coupled to the gas generator and having a plurality of cylinders in fluid communication with gas from the gas generator, and a plurality of pistons disposed in the cylinders. A bottom of each of the pistons is coupled to each of the fins to provide deployment thereof when a corresponding top of each of the pistons is acted upon by gas from the gas generator. In response to the gas generator expelling gas, the pistons may move the fins to a deployed position.

Abstract: A method for evaluating a collective alignment of rotor blades for an aircraft while the aircraft is on the ground is disclosed. The method includes determining an air density altitude, and determining a torque value for each engine of the aircraft, while the aircraft rotor blades are operated at a normal speed and the rotor blades are set to a full down position for ground operations via a collective controller. The method further includes evaluating the collective condition by comparing the torque value to a predetermined flat pitch torque alignment limit for the air density altitude, and providing an indication of the collective condition.

Abstract: A system for reducing reactive components in ullage of a fuel tank, typically the fuel tank of an airplane. The system includes an air driven unit for creating a fluidic motive force to remove ullage from the fuel tank, and a main catalytic unit for receiving the ullage and reducing the reactive components to yield processed ullage for return to the fuel tank.

Abstract: A bearing system for a spin-stabilized projectile including bearing configurations that permit selective relative rotation between a spindle and a body portion and which facilitate automatic centering of the spindle. Each bearing configuration includes a conical bearing surface rotatable with respect to a corresponding conical body surface. One bearing configuration is in a forward portion of the body portion and selectively engages a first body surface upon the projectile experiencing set-back forces to direct forces away from bearing elements, and another bearing configuration is in a rearward portion of the body portion and engages a second body surface upon the projectile experiencing set-forward forces to direct forces away from the bearing elements.

Abstract: An example method includes receiving output voltage data from an array of at least four thermopiles placed around the circumference of a projectile such that for any rotation of the projectile during flight thereof, at least a pair of the thermopile having upwardly-facing fields of view referenced to the earth-fixed coordinate system. The method includes determining the pair of upwardly-facing thermopiles based on the output voltage data from the array, with the respective pair of thermopiles including a thermopile p and next adjacent thermopile p+1. The method includes determining a ratio of the output voltage data from thermopiles p and p+1, and applying the ratio to a function associating, for any pair of thermopiles n and n+1, a ratio of output voltage data from thermopiles n and n+1, and a roll angle ?n of thermopile n referenced to the earth-fixed coordinate system.

Abstract: An apparatus for synchronizing devices includes a central access point node configured to utilize a low latency protocol to transmit a series of synchronization messages to the devices, transmit and receive data acquisition commands and responses from the devices using a high reliability protocol different from the low latency protocol, and calculate and apply relative clock offsets for each device based on the series of synchronization messages. The apparatus may also account for failure in delivery of a portion of the series of synchronization messages by recording timestamp data at the devices to send to the central access point prior to the central access point calculating the relative clock offsets.

Abstract: In one aspect, column load cells are described herein. In some embodiments, a column load cell comprises a load bearing column, a plurality of first strain gauges coupled to surfaces of the load bearing column for determining axial strain and a load receiving surface comprising a plurality of load guides, the load guides substantially aligned with the first strain gauges.

Abstract: An example method includes receiving output voltage data from an array of at least four thermopiles placed around the circumference of a projectile such that for any rotation of the projectile during flight thereof, at least a pair of the thermopile having upwardly-facing fields of view referenced to the earth-fixed coordinate system. The method includes determining the pair of upwardly-facing thermopiles based on the output voltage data from the array, with the respective pair of thermopiles including a thermopile p and next adjacent thermopile p+1. The method includes determining a ratio of the output voltage data from thermopiles p and p+1, and applying the ratio to a function associating, for any pair of thermopiles n and n+1, a ratio of output voltage data from thermopiles n and n+1, and a roll angle ?n of thermopile n referenced to the earth-fixed coordinate system.

Abstract: An example apparatus includes a controller configured to control operation of a salient-type, multiphase motor in accordance with a technique including periodic on and off-times, the motor including a stator and a rotor. The controller is configured to calculate or receive values representing changes in current to the motor during the respective on and off-times or measurements proportional thereto, and calculate an inductance of the motor as a function of the values and a supply voltage to the motor. And the controller is configured to determine a position of the rotor based on the inductance of the motor, and control operation of the motor based on the position of the rotor.

Abstract: A health and usage monitoring system for use in monitoring health and usage of one or more components of a vehicle. In various embodiments, the present invention uses at least one roving wireless sensor that can be temporarily placed in a first position to monitor one or more components of the vehicle and then moved to another position to monitor one or more other components of the vehicle, thus reducing the total number of sensors used to monitor the vehicle. In some embodiments, a system according to the present invention may comprise at least one or more roving wireless sensors. Other embodiments may comprise one or more roving wireless sensors used in conjunction with one or more wired sensors. The present invention also provides similar embodiments for a method of monitoring the health and usage of one or more components of a vehicle.

Abstract: Wireless communication may be provided between an access point and one or more wireless devices, such as wireless sensors used in avionics applications for sensing, monitoring and control systems. Synchronization of wireless devices may be required so that certain actions, such as data acquisition, are performed at precisely controlled time instances. The system described herein provides for rapid synchronization of wireless devices that does not require the use of prior timing data and that may be performed without communication directly between the wireless devices. Further, techniques are provided for addressing packet losses and packet propagation delays.

Abstract: Detecting video phenomena, such as fire in an aircraft cargo bay, includes receiving a plurality of video images from a plurality of sources, compensating the images to provide enhanced images, extracting features from the enhanced images, and combining the features from the plurality of sources to detect the video phenomena. Extracting features may include determining an energy indicator for each of a subset of the plurality of frames. Detecting video phenomena may also include comparing energy indicators for each of the subset of the plurality of frames to a reference frame. The reference frame corresponds to a video frame taken when no fire is present, video frame immediately preceding each of the subset of the plurality of frames, or a video frame immediately preceding a frame that is immediately preceding each of the subset of the plurality of frames. Image-based and non-image based techniques are described herein in connection with fire detection and/or verification and other applications.

Abstract: Determining health of a component includes using at least one processor to perform processes including acquiring a plurality of measured values corresponding to the condition indicators. Synchronous noise components are removed from the measured values to provide revised measured values, and the revised measured values are used to determine noise-filtered condition indicator values. The noise-filtered condition indicator values may be used in algorithms to determine the health of the component. Removing synchronous noise components may include determining a predicted value thereof using covariance and autocovariance of the measured values. The component may be a split torque gearbox.

Abstract: A wireless sensor system for an aircraft including a central access point and a plurality of slave nodes arranged in a star network in which the central access point wirelessly exchanges data with the slave nodes in a bidirectional manner. At least one of the antenna at the central access point and the antenna of each of the slave nodes is circularly polarized.

Abstract: In vibration based mechanical diagnostics, algorithms may extract some feature of a component which may be used as a statistic of the components' health. A measured condition indicator corresponding to the analysis of the components' health may be a function of transmission error (TE). Because there exists a relationship between TE and the CI for a component that is faulted, the CI is correlated with power transmitted. In drive train components, power may be proportional to measured torque. In terms of diagnostics or trending of a component, it is desirable to reduce the scatter in the measured CI and account for this torque. The relationship between measured CI and torque may be captured over time. An increase in the correlation of torque with the CI would indicate an increase of TE which indicates the propagation of a fault.

Abstract: A fin retention and deployment mechanism includes a detent in each of a plurality of fins, a mechanism that engages the detent, and at least one spring clip that maintains each of the fins in a non-deployed position. The mechanism also includes a gas generator, a manifold, coupled to the gas generator and having a plurality of cylinders in fluid communication with gas from the gas generator, and a plurality of pistons disposed in the cylinders. A bottom of each of the pistons is coupled to each of the fins to provide deployment thereof when a corresponding top of each of the pistons is acted upon by gas from the gas generator. In response to the gas generator expelling gas, the pistons may move the fins to a deployed position.

Abstract: A sensor system for providing control of an electric motor having an inductive angle sensor system including a first inductive coil configured for affixation to a rotor shaft of the electric motor wherein rotation of the rotor shaft causes corresponding rotation of the first inductive coil. A second inductive coil fixedly mounted in spaced relationship to the first inductive coil. An evaluation circuit coupled to the second inductive coil and to the electric motor operative to determine a rotor shaft angle for the rotor shaft of the electric motor through evaluation of an induced magnetic field between the first and second inductive coils.

Abstract: An aircraft sensor system including a primary module configured to be attached to an aircraft portion and operative to transmit electrical power wirelessly. A secondary module configured to be attached to an aircraft component, the secondary module operative to receive electrical power wirelessly from the primary module. At least one sensor configured to be operatively attached to a portion of the aircraft component and electrically coupled to the secondary module, wherein the at least one sensor is operative to measure a desired parameter of the aircraft component.

Abstract: Disclosed is a sinkless electric generator for generating electrical power from temperature cycles encountered by the structure of an aircraft. The sinkless electric generator includes a thermoelectric generator which is in thermal contact with the structure of the aircraft (e.g., the aircraft's skin); an insulated housing containing a thermal mass; and a circuit for providing the energy generated by the thermoelectric generator during the temperature cycles encountered by the structure of the aircraft to a device. The insulated housing is positioned in thermal contact with the thermoelectric generator; wherein during the temperature cycles encountered by the structure of the aircraft, energy is created by the thermoelectric generator when heat is released from the thermal mass contained within the housing through the thermoelectric generator to the aircraft's structure and when heat is supplied from the aircraft's structure through the thermoelectric generator to the thermal mass.

Abstract: A fin retention and deployment mechanism includes a detent in each of a plurality of fins, a mechanism that engages the detent, and at least one spring clip that maintains each of the fins in a non-deployed position. The mechanism also includes a gas generator, a manifold, coupled to the gas generator and having a plurality of cylinders in fluid communication with gas from the gas generator, and a plurality of pistons disposed in the cylinders. A bottom of each of the pistons is coupled to each of the fins to provide deployment thereof when a corresponding top of each of the pistons is acted upon by gas from the gas generator. In response to the gas generator expelling gas, the pistons may move the fins to a deployed position.