Abstract: A method and system for detecting the variations of speed (R) of a rotor. Signals are measured representative of the march-past of the teeth of a measurement device secured to the rotor for a determined duration (T). The measurements are sampled, digitized and stored to obtain an initial digital vector (B). A detection signal is extracted around a known disturbing frequency (F). The detection signal is compared with a predetermined threshold (SO) and an alert message is delivered in the event of overshoot.

Abstract: A method and a device (D) for detecting and signaling the approach to a vortex domain by a rotorcraft, the device includes: first elements (1) for measuring the instantaneous vertical speed v of a rotorcraft; second elements (2) for measuring the instantaneous proper airspeed VP of a rotorcraft; third elements (3) constituting a database BDD relating to representing at least one instantaneous vortex domain; fourth elements (4) connected via first, second, and third connections (l1, l2, l3) respectively to the first, second, and third elements, the fourth elements being designed to detect the approach to a vortex domain by the rotorcraft; and fifth elements (5) for signaling the approach to a vortex domain by the rotorcraft, the fifth elements being connected to the fourth elements (4) via a connection (l4).

Abstract: A device supported by a user while the user is in locomotion on foot during an outing may monitor a performance parameter of the user. The performance parameter may comprise a pace and/or a speed of the user. Prior to the outing, the device may be configured to specify a first interval and second interval, corresponding to a first and second performance zone, respectively, for the outing. Each performance zone may be different from one another and each zone may comprise one of a zone of paces and a zone of speeds. During the first interval, an action may be taken with the device in response to determining that the monitored performance parameter has fallen outside of the first performance zone. During the second interval, an action may be taken with the device in response to determining that the monitored performance parameter has fallen outside the second performance zone.

Abstract: A user in locomotion on foot during an outing may identify a grade of a surface with at least one device supported by the user. A performance parameter of the user may be determined with the device based upon the grade of the surface, which may be based upon a measured physiological parameter of the user. An average foot contact time and an average pace of a user during a first outing may be identified and a relationship between them may be determined. No other average foot contact times or average paces identified during a different outing may be used to define the relationship. A single user-specific calibration contestant may define a relationship between foot contact times of a user and corresponding paces of the user, wherein no other user-specific calibration constants are used to define the relationship.

Abstract: A discrete event simulation (DES) and method of model development provide affordable, accurate, pre-validated, reusable and portable models and simulations that capture the complexity, interdependencies and stochastic nature of the operations and support (O&S) of weapons systems. A model of the O&S problem is created based on a service use profile (SUP) that describes a logical structure of delivery, maintenance, deployment, testing policy, infrastructure and logistics constraints. That model is translated into a DES, preferably using a “toolkit” including common attributes for the weapons and pre-validated common blocks and sub-models that define higher level functionality. The DES calculates a time-based prediction of weapons availability, maintenance activities, and spare parts stock over a life cycle of the weapons system.

Abstract: Methods and systems are described for a system for obtaining information regarding a flow. These methods and systems comprise a signal generator configured to generate an alternating current signal at a carrier frequency and a transformer arranged to receive the generated signal, wherein the transformer and carrier frequency are selected so that the generated signal resonates at the carrier frequency. The alternating signal is then used to cause plasma to form across a gap between two electrodes, wherein the voltage drop across the gap is directly proportional to the flow's velocity. This voltage may then be measured to determine the flow velocity.

Abstract: The invention relates to a method and an apparatus for measuring a rotational speed, in particular a rotational speed of a wheel of a motor vehicle, by means of a speed sensor, wherein the speed sensor produces an output signal characterizing the actual rotational speed and wherein the output signal of the speed sensor is sampled and further processed in accordance with sampled values thus obtained. For an—in hardware terms—simple realization, according to the invention it is provided that the output signal is sampled at a predetermined sampling rate over at least one measuring cycle, that in each case the amplitude of sampled values obtained in the measuring cycle is determined and that from the rate of occurrence of sampled values of an amplitude lying within a predetermined amplitude range at least one signal level occurring during the measuring cycle in the output signal is determined.

Abstract: In one embodiment, an apparatus comprises a mount, a housing, and a sensor. The mount is adapted to be disposed at least partially underneath a shoelace of a shoe. The housing is configured and arranged to be placed in at least first and second states in relation to the mount, wherein in the first state the housing is movable with respect to the mount and in the second state the housing is immovable with respect to the mount. There is a tongue on one of the mount and the housing and a groove on the other of the mount and the housing, the tongue being adapted to engage the groove when the housing is in the second state in relation to the mount and to disengage the groove then the housing is in the first state with respect to the mount. The sensor, which senses motion of the shoe, is disposed within the housing such that the sensor remains disposed within the housing when the housing is placed in the first state in relation to the mount and the housing is moved with respect to the mount.

Abstract: The present invention relates to a pilot indicator for a rotorcraft provided with a main rotor and at least one gas turbine engine. The indicator has first and second sensors delivering information relating respectively to a first speed of rotation Nr corresponding to said main rotor, and a second speed of rotation NTL corresponding to the free turbine of said engine. The indicator is also provided with display means provided with a display screen for displaying the first and second present values respectively for the first and second speeds of rotation Nr and NTL. In addition, said processor means determines an estimated value for the first speed of rotation Nr.

Abstract: A pilot indicator is provided for an aircraft provided with at least one gas turbine engine. The indicator includes a set of sensors delivering information relating to different monitoring parameters of the engine, namely: the speed of rotation Ng of the gas generator, the temperature T4 of the gas at the inlet of the free turbine, and the torque Cm. The indicator is also provided with a processor for processing information from the sensors, and a display provided with a display screen. In addition, the processor determines an estimated value of a limiting parameter, where the limiting parameter is that one of the monitoring parameters that is closest to its limit.

Abstract: In one embodiment, a method involves determining at least one calculated parameter based upon at least one determined performance parameter of the user and at least one determined variable physiological parameter of the user. In another embodiment, a method involves identifying at least one of an existence of a non-zero grade of a surface and a value of the grade of the surface based upon at least one determined variable physiological parameter of a user.

Abstract: In one embodiment, a display unit to be mounted on a wrist of a user includes a display screen, a base, and at least one strap. The display unit is configured such that, when it is worn by the user, the display screen is oriented at an angle with respect to a surface of the user's wrist. In another embodiment, visually-perceptible information indicative of determined values of the instantaneous pace of a user and the average pace of the user are displayed, simultaneously. In another embodiment, visually-perceptible information indicative of the determined values of the at least one variable physiological parameter of the user and the at least one performance parameter of the user are displayed, simultaneously.

Abstract: In one embodiment, a method includes steps of: (a) identifying an average foot contact time of a user during a first outing; (b) identifying an average pace of the user during the first outing; (c) defining a relationship between foot contact times of the user and corresponding paces of the user, wherein the relationship is based upon the average foot contact time and the average pace identified during the first outing, and wherein no other average foot contact times and no other average paces identified during any different outings by the user are used to define the relationship; and (d) calibrating at least one device that monitors activity of the user in locomotion on foot based upon the defined relationship between foot contact times of the user and corresponding paces of the user.

Abstract: A terrain clearance measuring radio wave being emitted from an airplane is received, and changes in electric field intensity of the radio wave is input and recorded to a computer, whereby the time of occurrence of a sharply appearing peak value of the changes permits accurate measurement of the point-blank passing time, independent of flight frequency.

Abstract: The device is a miniature, self-contained solid state orientation sensor. The unit utilizes three magnetometers and three accelerometers to calculate pitch, roll, and yaw (compass heading) angles relative to the earth's magnetic and gravitational fields. The three orientation angles are output in digital RS232 or optional multi-drop RS485. The device can also be programmed to provide raw accelerometer and magnetometer data in true physical units. The device is capable of measuring angles from 0 to 360 degrees on the yaw axis, 0 to 360 degrees on the pitch axis, and −70 to +70 degrees on the roll axis. The yaw output is compensated for errors due to pitch and roll using embedded algorithms. Applications include fast solid state compassing, robotics, virtual reality, down-hole well drilling, and body position tracking for biomedical and multimedia applications.

Abstract: A method and system on-board a vehicle is provided for determining cycles to failure of the vehicle. The system includes a vehicle attitude reference or navigation system, a memory, and a processing component. The vehicle attitude reference system generates distance values in 6 degrees of freedom as a result of detected accelerations in the 6 degrees of freedom. The processing component converts the distance values to stress and strain values, and determines cycles-to-failure for one or more of the vehicle parts based on the stress and strain values and associated ductility and spring constant values stored in the memory. The processing component also subtracts the determined cycles to failure for each of the parts from previously-predicted cycles-to-failure, and stores the result of the subtraction in the memory for later use by operators of the vehicle.

Abstract: Methods and apparatus for predicting tire uniformity, preferably a harmonic component of force variation (radial, lateral, or tangential) for a production tire operating at a high speed, and also method and apparatus for manufacturing tires and controlling the manufacturing of tires in response to quality control based on a comparison of a production tire's predicted uniformity versus predetermined criteria. A production tire's predicted tire uniformity is determined by a calculation using a prediction curve with parameters which are determined for the production tire by collecting measurement data for the production tire using a factory floor tire uniformity machine operated at a plurality of intermediate test speeds, and then fitting the prediction curve to the measurement data, preferably using a least squares curve fitting process. Higher speed measurements are optionally given greater weight in the curve fitting process as compared to lower speed measurements.

Abstract: An altimeter which contains within it means for storing the Static Source Error Correction (SSEC) for the aircraft. The altimeter includes means for downloading the SSEC and for transferring it to a new altimeter which may then be used in place of the original altimeter without losing the information built up over time or having to re-calibrate the new altimeter based on new tests. The altimeter also includes means for uploading a known SSEC thereto.

Abstract: A system and method for automatic weapon allocation and scheduling of the present invention. The inventive method includes the steps of providing data with respect to threats, weapons, weapon allocation options; weapon allocation rules; and temporally dependent constraints with respect thereto; evaluating the data; and temporally allocating the weapons to the threats automatically in accordance with the evaluation. The invention computes the optimal pairing and the best time to deploy each weapon system against threat(s) it is paired with in arriving at the pairing. This results in an optimal assignment where weapon resource constraints are not exceeded and therefore guarantee availability of sufficient resources for engagement of every threat that is paired with a weapon system.

Abstract: In one embodiment, a method involves, in response to movement of a user during at least one footstep taken by the user, generating a signal that experiences changes during a time period that the foot is airborne during the at least one footstep. At least one change in the signal generated after the foot has become airborne and before the foot contacts a surface is identified that is indicative of the foot being airborne during the at least one footstep. In another embodiment, a method involves generating a signal in response to movement of a user during at least one footstep taken by the user. The signal is monitored to determine when the signal has experienced a minimum degree of smoothness for at least a given period of time. In response to determining that the signal has experienced the minimum degree of smoothness for at least the given period of time, it is identified that the foot of the user is airborne.

Abstract: A method for engaging one or several aerial targets by means of a firing group (10) of autonomous, but cooperating, firing units (12, 112), wherein each firing group has a fire control unit (14, 114) and at least one weapon (16, 116). Several firing units (12, 112) are linked by a signal transmission system (70), which connects their fire control units (14, 114). Each fire control unit (14, 114) autonomously monitors its airspace area for enemy aerial targets. Subsequently, each fire control unit (14, 114) determines a threat assessment, for which the monitoring results of all fire control units (14, 114) are used. The selection of an aerial target to be engaged by a firing unit (12, 122) is subsequently made by the associated fire control unit (14, 114) on the basis of,the threat assessment and on the basis of the status of the weapons (16, 116) of the entire firing group (10).

Abstract: Input parameters which correspond to operational flight data of an aircraft within a predetermined flight domain, are defined through measured variable state parameters generated during aircraft flight, utilizing a neural network trained by exemplars corresponding to such variable state parameters and reference information on the aircraft for data processing of real time values of the variable state parameter measurement to calculate values of the input parameters and provide a corresponding output as a reliable estimate of aircraft flight data such as airspeed, sideslip and angle of attack.

Abstract: A smart probe system for an aircraft receives an input from a heated total air temperature sensor. When on the ground, the heater for the total air temperature probe is cycled so that when a preselected temperature is indicated by the temperature sensing element in the total air temperature probe, the heater power is turned off, and as the total air temperature probe cools, changes. Changes in indicated temperature from the temperature sensing element are measured and the changes analyzed and used for determining outside air temperature. The outside air temperature can be calculated by determining the rate of change in the temperature while the probe cools. A complimentary method is to determine when the indicated temperature stabilizes, after the heater is turned off, and deriving outside air temperature from the stabilized temperature signal from the sensing element.

Abstract: The present invention is a system for monitoring, storing, and reporting the accumulation of fatigue occurrences experienced by an aircraft. The system according to the present invention uses existing aircraft instrumentation to monitor fatigue occurrences. Data is collected on the magnitude and cycles of any turbulence encounters; magnitude and number of gloading accrued by aircraft maneuvering; the number of pressurization cycles that the aircraft has experienced; and the number of takeoffs/landing cycles that have occurred. These data are stored in electronic memory for later review by the flight crew or maintenance personnel. Additionally, the number of accumulated wing flap cycles and landing extensions/retractions may also be monitored to facilitate the maintenance operations of these two critical flight controls.

Abstract: A data processing system for automating the process of managing flight data and generating reports based on that data. The system accesses flight data transmitted on an airborne databus, where the data represents sensor readings indicative of various flight parameters. The accessed flight data is sampled, filtered, decoded, encrypted, and subjected to an adaptive compression process prior to being stored on a portable, self-protected secure memory device. After the flight ends, the portable, self-protected secure memory device is transferred to ground personnel. The data stored on the memory device is then accessed by authorized personnel, decompressed and decrypted. The flight data is analyzed and used to evaluate pilot performance and monitor the operation of the aircraft through the generation of flight reports. Various data analysis techniques, including artificial intelligence based algorithms and expert systems may be used to examine the flight data and determine its significance.

Abstract: A portable, re-usable, battery-powered, electronic device for storing, displaying and modifying air traffic control information. The electronic flight data strip receives input data from an external data source via infrared or radio transmission, stores the data in an on-board memory device, displays selected portions of the received data for viewing by an air traffic controller, and receives and displays inputs from the air traffic controller either directly through integral switches or via aforesaid communications channels. All input and output data messages and air traffic controller commands may be stored and time tagged for later retrieval. The contents of the stored memory can also be interrogated and modified by external data processing devices. Following completion of the flight, the contents of the internal memory can be interrogated for the purpose of archiving or investigation and/or cleared for subsequent re-use on another flight.

Abstract: An aircraft having a reduced-load wing structure is provided with a controllable canard stabilizer (5G, 5D) at the front end of the aircraft and a controller that controls the canard stabilizer. The controller generates a turn command corresponding to an increase in the lift of the canard stabilizer when, simultaneously, the turn command applied by the pilot to the elevational control surfaces (6G, 6D) exceeds a threshold and the measurement of the vertical acceleration of the aircraft exceeds a threshold.

Abstract: The time period that a foot is in contact with the ground during a stride taken by a user, and the period that the foot is not in contact with the ground between strides taken by the user are determined by processing and analyzing the output signal of an accelerometer. The accelerometer is mounted on the user such that its acceleration sensing axis senses acceleration in a direction substantially parallel to the bottom of the user's foot. The output of the accelerometer is high-pass filtered, amplified, and fed to the input of a micro-controller, which monitors the signal for positive and negative signal spikes that are indicative, respectively, of the moment that the foot of the user leaves the ground and the moment that the foot impacts with the ground. By measuring time intervals between these positive and negative spikes, average "foot contact times" and "foot loft times" of the user may be calculated.

Abstract: A process and system for determining the flight configurations of an aircraft are disclosed. The process includes the steps of defining various possible flight configurations of the aircraft, determining a plurality of flight phases representative of the flight configurations, determining a plurality of characteristic parameters capable of being measured on the aircraft, measuring values of the characteristic parameters for each of the flight phases of the aircraft, calculating a fuzziness index for each of the flight configurations from the measured values of the characteristic parameters for the flight phases, the fuzziness index being representative of the flight configuration in a specified metric system, and defining an actual flight phase of the aircraft.

Abstract: The invention is directed to a helicopter health and usage monitoring system utilizing a neural network for estimating gross weight and center of gravity location from measured flight condition parameter inputs; and includes means for measuring a plurality of variable flight condition parameters during flight of the helicopter; memory means for successively receiving and storing parameter input signals as well as estimates of gross weight and center of gravity location; and processing means responsive to the signals received from the measurement means for generating the gross weight and center of gravity location estimates.

Abstract: The invention is directed to a system, utilizing a neural network, for estimating helicopter airspeed in the low airspeed flight range of below about 50 knots using only fixed system parameters as inputs to the neural network.