Abstract: A dual channel pressure sensor is provided. The pressure sensor includes a baseplate extending from a housing. The baseplate has a first end, a second end, and a body extending between the first end and the second end. The first end defining a first inlet port and the body defining a second inlet port.

Abstract: A seismic-detection sensor device includes two accelerometers having different sensitivities. The seismic-detection sensor device provides excellent precision and operability monitoring.

Abstract: The invention relates to a method for the computer-controlled display of speed information, which represents the movement speed of a real moving object relative to the surroundings of the object, using an image display device. The speed information is displayed by generating one or more visually perceptible moving graphical patterns using the image display device, wherein the movement speed of the real moving object is reproduced by the one or more graphical patterns in a qualitative manner. The invention further relates to a device for the computer-controlled display of speed information, to a flying object with such a device, and to a computer program for this purpose.

Abstract: The present invention provides a method and apparatus for enhanced monitoring of induced seismicity and industrial vibration to comprehensively measure all aspects of potentially damaging motion. The invention utilizes various combinations of multi-component low frequency linear seismic sensors and multi-component rotational seismic sensors. Sensors are jointly deployed in arrays on the free surface of the earth, and/or in arrays of shallow monitoring holes, which may be intended to be permanent deployments. The method has a wide range of risk/damage monitoring applications for industrial activity, and in oil and gas exploration and production for seismic surveys, hydraulic fracturing, and waste injection wells. This abstract is not intended to be used to interpret or limit the claims of this invention.

Abstract: A method of determining and utilizing a maximum stabilization height of a moving airplane includes: determining a nominal total height at any point of the nominal path of the airplane, determining a total height of the airplane, determining a nominal maximum total height that the airplane is able to reach from its current position corresponding to a nominal total height and according to an optimum total height variation law, determining the maximum stabilization height corresponding to the nominal maximum total height that the airplane is able to reach, and determining whether to continue or to interrupt a landing procedure during the final flight phase of the airplane based on the determined maximum stabilization height.

Abstract: This invention concerns a method of making airborne geophysical measurements. Such measurements may be made from fixed or moving wing airplanes or dirigibles. The method comprises the following steps: taking first real time measurements from one, or more, geophysical instruments mounted in an aircraft to produce geophysical data related to the ground below that instrument. Taking second real time measurements from navigation and mapping instruments associated with or carried by the aircraft. Computing a background response of each geophysical instrument using the second real time measurements to take account of its time varying altitude, and the time varying topography of the ground below it. Adjusting an operating or data processing condition of each geophysical instrument using the respective background response and the instrument's attitude to enhance the performance of that instrument.

Abstract: The portable self-contained horizontal and vertical level, angle and distance measuring device is suitable for indicating whether or when two or more points are level with each other and for measuring distances and angles between two or more points, a point and a line or a point and a plane. Moreover, the measuring device is capable of displaying such measurements to a user in real time. The measuring device includes a measuring point (3) for identifying from where measurements are to be calculated, a user actuated trigger (11) and a display (9) for displaying measurements to the user either in real time or in memory mode. The measuring device is compact and light-weight making it particularly convenient and portable. It is also very versatile and is capable of replacing a multiplicity of measuring devices commonly employed in DIY, engineering, and in trade in general.

Abstract: An angle measuring guide includes a housing having a plurality of monolithically formed walls and an annular opening formed within selected ones of the walls. The rear wall has a planar surface for being directly mated with the motorcycle. A transparent lens is monolithically formed with the housing and directly connected thereto. A buoyant member is situated within the opening and the cavity. A predetermined quantity of high viscous fluid is contained within the opening and the cavity such that the fluid freely flows therebetween and supports the buoyant member at a free and suspended position during operating conditions. The buoyant member includes a stationary weight member connected to a bottom portion thereof and thereby anchors the buoyant member while allowing the buoyant member to freely rotate about one or both of the x-axis and y-axis.

Abstract: A system is disclosed for using camera attitude sensors with a camera. A camera assembly includes a tripod base, a tripod head interface mounted on the tripod base, a tripod head mounted on the tripod head interface and a camera mounted on the tripod head. The tripod head enables the camera to pan and tilt. The system also includes a first optical encoder for detecting the amount that the camera has been panned and a second optical encoder for detecting the amount that the camera has been tilted. Two inclinometers are mounted on the tripod head interface to measure attitude of the tripod head. Two gyroscopes (“gyros”) are mounted on the camera assembly. Data from the encoders, gyros and inclinometers are packaged and sent to graphics production equipment to be used for enhancing video captured by the camera.

Abstract: A system and associated method where a vertical flight dynamic sensor is stabilized using pitch rate gyro information combined with azimuth rate gyro information corrected by scaling the azimuth rate gyro information in accordance with feedback derived from the difference between the vertical flight dynamic sensor signal and the corrected vertical flight dynamic output. In one embodiment, the vertical flighy dynamic sensor may be a vertical speed sensor. In another embodiment, the vertical flight dynamic sensor may be a pitch attitude sensor derived from the difference between an inertial based acceleration signal and a velocity based acceleration signal. The velocity based acceleration signal may be based on airspeed or GPS velocity.

Abstract: A device, method and computer program for generating and displaying graphical displays symbolic of current and available operational modes of instrument systems, such as navigation and autopilot systems. Accordingly, the method of the invention includes receiving a signal representative of a current mode of operation of one or more instrument systems, interpreting the current mode of operation signal to determine the current mode of operation, outputting a control signal informing a pictographic representation symbolic of the current mode of operation, and displaying the pictographic representation of the current mode of operation on a display device, such as a cockpit panel display.

Abstract: A compact, lightweight, cost effective, self-contained standby electronic navigation system with high signal-to-noise ratio and good dynamic stability is provided. The system includes a first sensor module for providing a plurality of rotational rate signals, a second sensor module for providing a plurality of compensation signals, and a microcontroller module for processing the rotational rate signals and the compensation signals and sending the signals to a display for displaying attitude information, directional information, and turn coordinate information on a single screen simultaneously. In one embodiment, the first sensor module includes a plurality of rotational sensors made of piezoelectric elements. The piezoelectric elements are made from a single sheet of piezoelectric material so that the elements possess uniform characteristics, and are arranged to reduce systematic drift and random noise normally present in a rotational rate sensor. The sensors can be configured on a single multi-sensor chip.

Abstract: An oscillation type of micro gyro sensor equipped with two vibrators is provided. The gyro sensor has a monitoring electrode, a signal processor, and a driving electrode attached to both the vibrators. The monitoring electrode monitors a vibration of only one of the two vibrators to output signal indicative of the monitored vibration. The signal processor drives the two vibrators in mutually opposite phases, by using the signal from said monitoring electrode. The driving electrode drives both the vibrators on the basis of the two driving signals.

Abstract: A survival device for use in an emergency situation includes a battery, a lamp, and a detection circuit for detecting an occurrence of the emergency situation and for switching the lamp to be powered by the battery when such an occurrence is detected. In one form, the detection circuit detects a presence of water along a surface of the device, with safety tools for escaping from an submerged vehicle being provided. In another form, the detection circuit detects a failure of electrical service within a building, with safety tools for escaping a fire being provided.

Abstract: A 3D angle measurement instrument includes a casing having a top and bottom with side walls extending therebetween. A gyroscope is positioned within the casing and electrically connected to a battery power source. The gyroscope is capable of measuring acceleration and deceleration velocities of the casing indicative of angular rotation thereof. A microprocessor is positioned within the casing and is electrically connected to the gyroscope and battery. The microprocessor receives an output signal from the gyroscope and is capable of calculating an angular displacement value using the output signal and a corresponding time factor. The angular displacement value is displayed on an electronic display in angular degrees from a reference point.

Abstract: Using an inertial master box mounted on a carrier for measuring its movements with respect to a geographic frame of reference of fixed directions along three axes Xg, Yg, Zg, a measuring method provides for continuously measuring an orientation of a frame of reference Xm, Ym, Zm tied to the inertial master box. Positioning is provided by applying a sequence of cycles of eight inversions of the inertial master box while keeping the axis Ym in a direction parallel to the axis Yg. A first motor causes a gimbal to pivot on a first axle secured to the carrier, while a second motor causes the inertial master box to pivot about a second perpendicular axle secured to the gimbal. A processor calculates three attitude angles by running a first inertial navigation program of the strapdown type and controls the first and second motors by running a second program.

Abstract: The invention relates to an apparatus for determining postures, in particular the attitude (&thgr;) and the inclination (&phgr;) of an aerodyne, comprising: a strap-down gyrometer device providing the components of the vector ({right arrow over (&OHgr;)}) of instantaneous rotation of the aerodyne, means for calculating, from gyrometric measurements, a matrix of postures ({right arrow over (b)}1, {right arrow over (b)}2, {right arrow over (b)}3), accelerometers integral with the said gyrometric device, and means for comparing data calculated from the accelerometers with data calculated from the gyrometers so as to provide corrections for compensating for the errors or drifts of the gyrometric device. This apparatus is characterized in that the comparison is performed between a vertically directed vector {right arrow over (U)}g provided by the gyrometric device and a vertically directed vector {right arrow over (U)}a provided by the accelerometers.

Abstract: A method of automatically determining attitude of a moving vehicle. Acceltion of the moving vehicle is measured with gyro stabilized accelerometers. The measurement is converted to a motion related vector in a first frame of reference. The coordinates are read into a computer. The cosine value and the sine value for an Euler rotation of the first frame of reference are read into the computer. The computer produces coordinates of the vector in a rotated frame of reference. The above two steps are repeated a number of times to arrive at a final frame of reference. The attitude of the vehicle is provided with respect to a final frame of reference with the aid of final produced coordinates.

Abstract: A gyroscopic artificial horizon comprises a gyroscope suspended in a gimbal ount which has an inner frame and an outer frame pivoted, one within the other, about two orthogonal axes. It also comprises a device for sensing the spatial position of the axis of the gyroscope and for displaying this position in the form of an artificial horizon. To simplify the mechanical structure and to increase the reliability of the gyroscopic artificial horizon, the device for sensing and displaying the spatial position of the gyroscope axis comprises a luminous display screen rotationally coupled to the outer frame of the gimbal mount. It further comprise a sensor for sensing the angular position of the inner frame relative to the outer frame and a processor device adapted to display this angular position on the screen in the form of an artificial horizon.

Abstract: As a method and device for representing the horizon on board an aircraft, there is displayed on the cathode tube of a collimator an image comprising a circle of small size inside which there are, on the one hand, a horizon line inclined to the horizontal by an angle equal to but opposite the rolling angle of the aircraft, the horizon line being remote from the center of the circle by a distance which is a function of the pitching angle in the upward direction when the aircraft is diving and in the downward direction when the aircraft is pulling the nose up, and which delimits to zones of different brightness and, on the other hand, a point representing a pole situated on the median line of the horizon line at a distance from the latter corresponding to a pitching angle of 90.degree.. A "head up" type control system is essentially provided.

Abstract: An aircraft performance instrument which provides a first indicator which represents the line of level flight of the aircraft and a second indicator representative of the maximum permissible angle of attack of the aircraft.

Abstract: A turn-and-bank indicator can integrate with regard to time the displacement of a pointer of the turn-and-bank indicator, the pointer indicating the turning rate of the airplane. It includes a non-contact converter which outputs an electrical signal in proportion to the deflection of the pointer; an amplifier which amplifies the output of the non-contact converter; an integrator which integrates the output of the amplifier with respect to time; and a digital display unit which displays the output from the integrator at a close position with the pointer.

Abstract: The invention relates to an aircraft attitude indicator having a gyro controlled spherical display with delineations of regularly spaced meridians that maintain a vertical orientation and spaced parallels transverse to the meridians, one of which is an equator that divides the sphere into upper and lower hemispheres and corresponds to a horizon. The lower hemisphere has triangular pointer indicia, each symmetrical to a delineated meridian and with a base on a parallel and an apex proximal to the equator. The pointer indicia cooperate with a reference delineation that is relatively fixed with respect to the aircraft and substantially centered on the display. The pointer indicium nearest the reference designates the "up" direction; those adjacent to it provide information about changes in aircraft attitude relative to "up" that will result from possible maneuvers from the existing attitude.

Abstract: A circuit for use in aircraft navigation equipment includes operational amplifiers to drive a cockpit indicator such as an electric meter linearly over a first predetermined range, constantly over a second predetermined range, and out of view over a third predetermined range. A first operational amplifier circuit provides a linear drive to the indicator and a second operational amplifier circuit controls the constant drive current to the meter and defines first and second breakpoints which begin the constant in view and constant out of view responses, respectively. The circuit needs only a single input signal for operation.

Abstract: A push-button mechanism, for example, for a telephone instrument of the type which from a first stable initial position of the push-button is locked in a second stable position when depressed and returns to the initial position when again depressed. The push-button mechanism contains a push-button, a rectangular body part and a cover which includes contact elements. A locking device inside the cover consists of a movably disposed plate one surface of which is constructed with a cavity in the form of a heart-shaped cam and with a concave-convex elevated part in the center of the cavity. A ball is located in a groove in the lower part of the push-button and runs along the outline of the heart-shaped cam and along the edges of the elevated part when the button is depressed.

Abstract: The indications of attitude indicators at two different indicating locations that are indicating the same parameter but actuated from different sources, are monitored for the same indication by electrically interconnecting two transolvers that are mechanically coupled to the respective attitude indicator at each location. A monitor, at one indicating location, furnishes the excitation for the transolver at the other location and by the magnitudes of the sine and cosine outputs of the local transolver furnishes flag indication of any system defects of either indicator at each location.

Abstract: A manually manipulatable gyro-stabilized indicating instrument which may be used by pipefitters, carpenters, builders, land and road graders and the like for solving a construction problem involving determining the orientation in space of an unknown geometrical plane with reference to a known geometrical plane, or using a known or unknown geometrical plane as a reference and either establishing in space a geometrical plane having a predetermined orientation with reference to the known or unknown geometrical plane. The instrument has at least one straight planar surface and a gyroscope or gyroscopes operatively connected to the straight planar surface and having motive means for driving the gyroscope or gyroscopes to a continuous stabilized condition relative to the straight planar surface in any fixed position and location assumed by the straight planar surface at the time the gyroscope becomes gyroscopes become stabilized.

Abstract: An orientation system adapted to be mounted within a vehicle, comprising a display including a rotational heading indicating compass card fabricated from an image retaining electronic display panel responsive to bearing data signals.

Abstract: A structural body is monitored in angular position about at least one axis by utilizing a tilt sensor responsive to tilt about the one axis and a sensor responsive to angular acceleration of the body about the one axis. The tilt sensor also responds to the tangential component of angular acceleration and the angular acceleration sensor output contains a component which results from linear acceleration sensitivity along a cross axis of the angular acceleration sensor. The cross axis of the angular accelerameter is aligned with the sensitive axis of the tilt sensor and a portion of the tilt sensor output related to the ratio of the two sensor scale factors is injected into the angular acceleration sensor output to cancel the cross axis sensitivity. A portion of the angular acceleration sensor output related to the distance between the one axis and the mounting position of the tilt sensor is injected into the tilt sensor output to cancel the tangential component of angular acceleration.

Abstract: A structural body is monitored in angular position about at least one axis by utilizing a level sensor and a sensor responsive to angular motion of the body about the axis being monitored. An output indicative of long term angular variations of the body about the axis is provided by the level sensor and short term angular variations are indicated by the output from the sensor responsive to angular motion about the axis. The signals indicative of long term and short term angular variations are combined to provide a broad band output signal indicative of angular position which is immune to high frequency translational variations appearing at the level sensor output, but which is responsive to high frequency angular inputs. The fast response angular sensor output is compared with the slow response level sensor output and an error signal is produced which drives the angular sensor output signal into coincidence with the level sensor output signal.