37 results about "Attitude indicator" patented technology

An attitude indicator device for detecting, indicating, and / or logging the positional attitude of an individual in response to deviation from a set of one or more reference angles. By way of example and not of limitation, the device is mounted on the thigh of a patient and measurements are taken from an acceleration sensor within the device. The acceleration measurements are communicated to a receiver when the measurements deviate from acceptable thresholds, whereby the receiver indicates an alert condition. The device may be employed within numerous medical related applications, for example, to facilitate preventing patient egress and the prevention / detection of patient falls.

An attitude indicator device for detecting, indicating, and / or logging the positional attitude of an individual in response to deviation from a set of one or more reference angles. By way of example and not of limitation, the device is mounted on the thigh of a patient and measurements are taken from an acceleration sensor within the device. The acceleration measurements are communicated to a receiver when the measurements deviate from acceptable thresholds, whereby the receiver indicates an alert condition. The device may be employed within numerous medical related applications, for example, to facilitate preventing patient egress and the prevention / detection of patient falls.

The invention discloses an underwater object precision positioning system and a method. The system comprises a mother ship, a computer with a plurality of serial ports, a desk computer, an ultra short base line positioning system, a differential GPS (global positioning system), a compass, an ROV (remote-operated vehicle) system, a forward-looking sonar camera, a low-illuminance black and white video camera, an attitude indicator and a temperature-salinity depth profiling instrument. A shore-based transceiver, an ROV water surface system unit and the like of the ultra-short base line positioning system are carried by the mother ship, and underwater system units such as a transponder of the ultra-short base line positioning system, the forward-looking sonar camera and the like are carried by an ROV submersible vehicle, so that the underwater object precision positioning system is formed. By the aid of acoustic positioning between the shore-based transceiver and the transponder of the ultra-short base line positioning system and acoustic positioning of forward-looking sonar, the shortcoming that an existing underwater GPS positioning system only can position an object carried with anacoustic response device in a water area is overcome, and longitude and latitude coordinates of an optional unknown object in an optional water area can be positioned in a WGS (world geodetic system)84 ellipsoidal coordinate system in real time.

An auditory attitude indicator for aircraft that includes an audio source providing an audible signal, a′ stereo headset with a left side and a right side, an aircraft avionics system that provides at least aircraft pitch data and roll data to an audio processor unit. The audio processor unit includes at least one lookup table of coefficients corresponding to a plurality of possible aircraft pitch and roll orientations and at least two selectable multipoint finite impulse response filters. The first selectable multipoint finite impulse response filter having a first coefficient selected by the audio processing unit from the lookup table based upon the aircraft pitch data and roll data for varying the audible signal to the stereo headset left side. The second selectable multipoint impulse response filter for varying the audible signal to the stereo headset right side having a second coefficient selected by the audio processing unit from the lookup table based upon the aircraft pitch data and roll data.

Methods and systems are provided for displaying an unusual attitude of an aircraft in a head-up display system. The system comprises a projection unit configured to project the unusual attitude of the aircraft and a processor coupled to the LCD projection unit. The processor is configured to control the LCD projection unit during the unusual attitude of the aircraft to produce an attitude indicator of the aircraft and a horizon symbol. The horizon symbol divides the attitude indicator into a first region having a first display characteristic and a second region having a second display characteristic different from the first display characteristic. The first display characteristic is substantially uniform throughout the first region, and the first region indicates a ground with respect to the aircraft.

The invention relates to a submarine pipeline detection apparatus and a detection method thereof, and belongs to the technical fields of submarine pipeline routing, and external anticorrosive coating and the cathodic protection state detection. The apparatus comprises an underwater motion carrier, a perception device and a control terminal; the perception device is arranged on the underwater motion carrier; the control terminal is connected with the underwater motion carrier and the perception device; the underwater motion carrier adopts an underwater impeller propeller; the perception device comprises a pipeline routing detection probe, a potential measurement electrode, a lighting lamp, a camera, a pressure sensor and an attitude indicator; and the pipeline routing detection probe is arranged at the front end of a frame, the potential measurement electrode is arranged on the side elevation of the frame, the lamp and the camera are hoisted at the front end of the lower surface of the top plate of the frame, the pressure sensor is arranged in a sealed cabin, the probe contacts with seawater, and the attitude indicator is arranged on the flattened plane in the sealed cabin. The apparatus and the method have the advantages of no excavation in the detection process, long detection distance, accurate detection and low detection cost, and are suitable for the whole line detection of the submarine pipeline.

The invention relates to a digital autopilot system of a lightweight fixed-wing aircraft. The digital autopilot system comprises an autopilot computer 1, an attitude indicator 2, a state indication panel 3, a pitching steering engine 4, a rolling steering engine 5, a yawing steering engine 6, a mode control panel 7, a balancing adapter 8, a balancing relay 9, a steering wheel switch 10, an audio alarm box 11, a height selector 12, a course rate gyroscope 13, an atmosphere data computer 14, a control system steel rope 15, an aileron trimmer control system 16, an elevator trimmer control system 17, a power supply system 18, a balancing switch 19 and a navigation system 20. The system is complex in control law and is capable of controlling an aircraft to realize the automatic pilot and other functions based on signals input into a heading and attitude system, a pitot-static system, a radio navigation system and other systems of a receiver. Meanwhile, the operation stability of the entire aircraft is improved, and the operation intensity of a pilot is reduced. Moreover, the security and the reliability are improved, and the comfort level of passengers is improved.

This simplified self powered aircraft attitude survival indicator is easily and readily transportable from one aircraft to another and provides a simple indicator which gives a visual indication of aircraft attitude and alarms when the aircraft is in a dangerous attitude. The aircraft attitude indicator includes a housing containing a power source, multiple attitude sensors, and at least one piezoelectric alarm, and a front panel display with an arrangement of light emitting elements (electric bulbs or LEDs) providing visual attitude indicators.

Methods and systems are provided for displaying an unusual attitude of an aircraft in a head-up display system. The system comprises a projection unit configured to project the unusual attitude of the aircraft and a processor coupled to the LCD projection unit. The processor is configured to control the LCD projection unit during the unusual attitude of the aircraft to produce an attitude indicator of the aircraft and a horizon symbol. The horizon symbol divides the attitude indicator into a first region having a first display characteristic and a second region having a second display characteristic different from the first display characteristic. The first display characteristic is substantially uniform throughout the first region, and the first region indicates a ground with respect to the aircraft.

The invention provides a ship horizontal attitude indicator, belonging to the field of ship electric equipment. The ship horizontal attitude indicator comprises a single chip microcomputer, a liquid crystal display, keys, a communication level conversion module, a gravity accelerometer transducer, a buzzer and a stable-voltage power source module. A signal wire on a pin of the single chip microcomputer is respectively connected with the liquid crystal display, the keys, the communication level conversion module, the gravity accelerometer transducer and the buzzer; and the stable-voltage power source module is connected with the single chip microcomputer, the liquid crystal display, the communication level conversion module, the gravity accelerometer transducer and the buzzer by leads, and supplies power to the components. The ship horizontal attitude indicator uses a digital integrated circuit sensor LSM303DLH to communicate with a chip through the single chip microcomputer and reads component information of three earth gravity accelerations of the internal gravity acceleration sensor in a horizontal direction and a vertical direction, so that a front-back pitch angle and a left-right inclination angle of a ship can be calculated and displayed by using an LCD (Liquid Crystal Display) liquid crystal. When the front-back pitch angle or the left-right inclination angle exceeds a certain range, the buzzer also can be used for alarming.

Attitude and Configuration Indicator Display System and Method within the context of an Electronic Instrument System in which the configuration status of a piloted craft; typically the instant positions of lift inducing elements and drag inducing elements, are represented by symbol groupings integrated with an a parent icon, typically a chevron-type symbol representative of the piloted craft. The symbol groupings receive data from associated on-board sensors and are displayed singly or in combination with each other anytime the piloted craft is not in a clean configuration to instantly alert the pilot(s) of the configuration status with a single glance directed to the attitude indicator.

Methods and apparatus are provided for selectively rendering a standby attitude indicator or an airport map on an aircraft display. The system determines whether the aircraft is on the ground or in flight and, based on this determination, either the standby attitude indicator or the airport map are rendered on the display. If the aircraft is determined to be in flight, then the standby attitude indicator is rendered. Conversely, if the aircraft is determined to be on the ground, then either the standby attitude indicator or the airport map is selectively rendered.

A method for providing flight information related to an unmanned aerial vehicle (UAV) includes receiving, at a remote terminal, UAV state information comprising at least attitude information of the UAV when the UAV is airborne; determining, based on sensing data from one or more sensors of the remote terminal, remote terminal state information; processing the received UAV state information and the remote terminal state information to determine a spatial relationship between the UAV and the remote terminal; and simultaneously displaying, in a same display area on a display of the remote terminal, the determined spatial relationship between the UAV and the remote terminal, and a non-numeric, graphical attitude indicator that indicates the attitude information of the UAV.

The invention provides an elevator car top distributor attitude indicator. The elevator car top distributor attitude indicator is installed on the top of an elevator car and comprises a STM32 processor, a HMC5883 three-axis magnetometer and a MPU6050 three-axis movement processing assembly, wherein the MPU6050 three-axis movement processing assembly comprises an accelerometer and a gyroscope; the STM32 processor is in communication connection with the HMC5883 three-axis magnetometer, the three-axis accelerometer and the three-axis gyroscope respectively, receives and process data from the three-axis accelerometer, the three-axis gyroscope and the HMC5883 three-axis magnetometer, and transmits processed data to an elevator master controller of an elevator mainboard through a CAN (Controller Area Network) bus. The elevator car top distributor attitude indicator has the advantages that an elevator operation situation can be known in real time, problem roots can be quickly found during shaking, a curve can be drawn through an accelerated speed, and the comfort of the elevator is debugged. The elevator car top distributor attitude indicator has the advantages of simple circuit, few peripheral elements and convenience in producing and debugging, and simpleness and easiness in use, and a great quantity of checking and repairing time can be saved for overhauling maintenance personnel.

The invention relates to a positioning and movement identification system, which belongs to the technical field of the positioning device structure. The positioning and movement identification system consists of a moving group and a fixed group, wherein the moving group comprises a head, a cursor device, a distance measuring device, an electronic gyro attitude indicator and a data processing module b; and the fixed group comprises an image acquisition device and a data processing module a used for processing a shot image in real time, wherein the image acquisition device and the data processing module a are installed in a space formed by a protective shell and an outer cover, and the protective shell is fixedly installed on a base. The system can accurately obtain the movement position of a user, the rotation angle of the head, the height of the user and the leftward and rightward inclination, head rising and head lowering angles of the head of the user in a real space in real time, and causes the movement position of the user, the rotation angle of the head, the height of the user and the leftward and rightward inclination, head rising and head lowering angles of the head of the user in the real space to correspond to the movement, the height and the head movement of the user in virtual reality, the movement of the user in the real space keeps consistent with the movement in the virtual reality, spinning sensation is eliminated, and the real-time positioning and the head movement identification of multiple users can be realized. In addition, the positioning and movement identification system is simple in structure, low in manufacture cost and convenient in use.

The invention provides a primary flight display instrument in which a symbol—such as a small star or triangle—indicates the bearing to the current waypoint in the flight navigation plan. The display may also show a bearing indication symbol showing a follow-on waypoint in the flight plan. These symbols are preferably located on the horizon line of the primary flight display (or the attitude indicator) providing bearing to the current waypoint in the flight plan and / or to the following waypoint. An image processing unit generates the display, including earth ground and horizon, in a view substantially conformal with a VMC view from the aircraft.

A device for improving a golf stance and swing has a clip, an arm, a mount, and an indicator block. The clip allows the device to be secured to a golf club, while the arm allows the mount and connected indicator block to be centered with respect to the golf club. The mount has a carriage which slides along a corresponding track on the arm, and a perpendicular rod about which the indicator block can rotate. The indicator block has three faces, two lateral faces and a top face. When the indicator block is centered on a head of a golf club, it can be used to gauge the correct distance from the ball a golfer should stand. Only the top face of the indicator block will be visible when standing the correct distance from the ball. The faces of the indicator block are color coded to increase usability.

Attitude and Configuration Indicator Display System and Method within the context of an Electronic Instrument System in which the configuration status of a piloted craft; typically the instant positions of lift inducing elements and drag inducing elements, are represented by symbol groupings integrated with an a parent icon, typically a chevron-type symbol representative of the piloted craft. The symbol groupings receive data from associated on-board sensors and are displayed singly or in combination with each other anytime the piloted craft is not in a clean configuration to instantly alert the pilot(s) of the configuration status with a single glance directed to the attitude indicator.

The invention relates to the technical field of aerospace measurement and control and particularly relates to a method and system of an airborne high-precision shaft stable tracking servo turntable. According to the method, speed feedforward and acceleration feedforward are added based on traditional PID adjustment, a signal is provided by machine attitude information, so a servo system obtains fast dynamic response, a traditional PID control algorithm is combined, the accuracy of the system is ensured, and the rapidity of the system is ensured at the same time. The system comprises a GPS module, a three-axis gyroscope, an attitude indicator, a controller, a driver, a direct drive motor and a communication antenna, the accurate positioning of a target position and the transmission of the attitude information of a carrier aircraft can be achieved, and a feedforward signal is provided for the controller.

Methods and apparatus are provided for selectively rendering a standby attitude indicator or an airport map on an aircraft display. The system determines whether the aircraft is on the ground or in flight and, based on this determination, either the standby attitude indicator or the airport map are rendered on the display. If the aircraft is determined to be in flight, then the standby attitude indicator is rendered. Conversely, if the aircraft is determined to be on the ground, then either the standby attitude indicator or the airport map is selectively rendered.

A system, device, and method for generating and presenting an aircraft attitude indicator are disclosed. The attitude indicator presenting system may include a presentation system comprised of one or more display units receiving image data from an image generator (IG). The IG may be configured to acquire navigation data and generate the image data as a function of the navigation data. The navigation data could include data representative of aircraft roll and / or pitch attitude, and the image data could be representative of at least of an image of the attitude indicator comprised of a sky area and a ground area. The ground area may be visually presented by either a first texture or a second texture depending on whether a trigger attitude has been met or exceeded.

The invention provides an operating lever internally provided with an attitude indicator. The operating lever comprises a rotating part, a fixed seat, a handle lever and the attitude indicator, wherein the rotating part adopts a hollow shell and is arranged in and in limiting rotating connection with the fixed seat, and further fixedly connected with the handle lever; the attitude indicator is fixed at the rotation center in the rotating part and used for sensing and outputting rotation attitude signals of the rotating part. The invention further provides an electric vehicle provided with the operating lever; the electric vehicle controls the driving state thereof through rotation of the operating lever. The operating lever and the electric vehicle are compact in structure, and convenient to control.

Provided is a motorized high precision sandy shoreline and mud shoreline measuring device, comprising a mobile device which is provided with a vertical measuring bar; the measuring bar is provided with a CORS receiver, a record book, and an attitude indicator. The front end middle position of the mobile device is provided with a laser emitter which can emit a laser beam used for positioning a shoreline position. The mobile device is also provided with an information processor which is in connection with the record book and the attitude indicator through data lines, wherein the record book and the CORS receiver are in both-way communication; the information processor is internally provided with a processing module. The motorized high precision sandy shoreline and mud shoreline measuring device is a professional device for sandy shoreline and mud shoreline measurement, and can precisely position a coastline position, and perform correction treatment on an obtained sandy shoreline and mud shoreline through the information processor, thereby rapidly and accurately measuring sandy shoreline and mud shoreline positions.

The invention discloses an agricultural unmanned pesticide sprayer. An opening in the top of a main engine room is buckled with a main engine room cover; the center of the main engine room cover is embedded with a lockset; the lower end of a lock cylinder is fixedly provided with a following block; four suspended ends of the following block respectively correspond to four guide blocks; each guideblock is provided with a lock rod; the outer ends of the lock rods penetrate through guide holes correspondingly formed in the guide blocks and can extend in elastic lock folders arranged on the innerwall of the top end of the main engine room; and an attitude indicator is located in an equipment room, the bottom of the attitude indictor is provided with a locating plate, positions, close to fourcorners, at the bottom of the locating plate are supported on a partition plate by dampers, and the damper comprises an upper guide cylinder, a lower guide cylinder and a rubber column. By using theagricultural unmanned pesticide sprayer, the locking reliability of the main engine room cover on the main engine room can be guaranteed, and the agricultural unmanned pesticide sprayer is convenient,fast and labor-saving; and the attitude indicator is supported by the four dampers distributed in a rectangle, so that not only is the mounting firmness of the attitude indicator guaranteed, but alsoinfluences of airborne vibration to the attitude indicator can be effectively reduced, and furthermore, the reliability of the attitude indicator is guaranteed.

The invention relates to a measuring instrument for multisite distance and azimuth in an acoustic test and belongs to the field of hydroacoustic positioning and navigation and underwater acoustic detection. The invention aims to solve the problems that in the prior art, a GPS (Global Position System) handset, a radio base station and the like cannot simultaneously receive information of multiple substations, do not have the ability of resolving the distance azimuth of all substations and a master station, are inconvenient for real-time comparison with measurement results of a sonar system andthe like. The measuring instrument involved in the invention is characterized in that a master control unit is connected with a logic control unit through a bus and is connected with a human-machine interface unit through an FPC interface; the master control unit is separately connected with an azimuth attitude indicator and a GPS receiver through serial ports; the master control unit is connectedwith an external radio station through an Ethernet port; and a connection is established between the logic control unit and external sonar equipment. According to the invention, by using a GPS positioning technique and an underwater positioning technique, the measuring instrument involved in the invention has the functions of synchronously comparing the time with the solar system, providing adjustable higher-precision synchronizing pulse for the solar system, comparing with the measurement results of the solar system in real time and the like.

The invention discloses a three-dimensional virtual attitude indicator implementation method, the attitude indicator is used for indicating aircraft attitude angle information, an attitude angle of anaircraft describes an included angle between an aircraft body shafting and a ground shafting, the attitude angle comprises a pitch angle, a yaw angle and a roll angle, and the method comprises the following steps: 1, constructing a spatial three-dimensional model for an attitude indicator through sphere modeling; 2, drawing corresponding scale information for the surface of the attitude ball by using a texture mapping technology; 3, adding a space rotation effect to visually display flight attitude angle parameters; 4, applying Blinn-Phong illumination rendering to enhance the spatial stereoscopic impression of the attitude ball; and 5, drawing a dial plate and an auxiliary control. According to the three-dimensional virtual attitude indicator implementation method, the three-dimensionaleffect is obviously enhanced, the man-machine work efficiency is better met, and the airborne display requirement is met.

An aeroplane attitude indicator device includes a mobile rod which includes a first end connected by a link to a support fastened to the aeroplane and a second end to which is connected a moving body, at least one actuator for controlling the motions of the rod, and a system for piloting the at least one actuator as a function of information originating from an attitude detection system of the aeroplane, so as to orient the rod in a vertical direction. The assembly of rod and moving body correspond to a pendulum-like artefact. Also described is an aeroplane cockpit equipped with an attitude indicator device.

The invention discloses a stress strain all-weather monitoring spherical device based on a high stress condition. A communication line is connected with a nine-axis attitude indicator chip; the nine-axis attitude indicator chip is positioned inside a sphere; the communication line is positioned inside a stainless steel tube; the communication line is connected with a data acquisition main board; adata signal conversion module, a data analysis and processing module, a data acquisition module and a data storage module are arranged in the data acquisition main board; a semiarc and an equatorialplane supporting axial surface are arranged at the exterior of a core sphere; a stress strain gage is arranged in a position where the semiarc is connected with an upper and lower chord supporting axial surface; a stress strain gage is arranged in a position where the semiarc is connected with the equatorial plane supporting axial surface; the communication line connected with a position between the stress strain gage and the data acquisition module penetrates through a data wire guide and enters the interior of the core sphere. The stress strain all-weather monitoring spherical device can beapplied to big data and cloud computing technical platforms, and provides effective data acquisition and analysis technical support for the future geological disaster monitoring work.

The present invention relates to an underwater dynamic high-precision magnetic force measurement method and device. The method comprises the following steps of: the step A: calibrating three axes of amagnetometer itself to maintain orthogonality among the three axes of the magnetometer, comprising the following sub steps: the step A1: obtaining a value of an external fixed interference magnetic force Hh except a carrier, the step A2: employing the least square method to obtain [Xi], the step A3: solving a symmetric matrix A, the step A4: obtaining K and He, and the step A5: calculating the Hm; the step B: comprising the following steps executed in order: the step B1, coinciding the rotation of the X axis of an attitude indicator with the X axis of the magnetometer, the step B2: coincidingthe rotation of the Y axis of the attitude indicator with the Y axis of the magnetometer, and the step B3: coinciding the rotation of the Z axis of the attitude indicator with the Z axis of the magnetometer. The underwater dynamic high-precision magnetic force measurement method and device makes the orthogonality of the magnetic axes of the magnetometer itself, maintains consistency of magnetic axes and the axes corresponding to the attitude indicator, and can obtain high-precision magnetic measurement data in a dynamic condition.

The invention discloses a calibration device for an attitude indicator. The calibration device comprises a workbench 1, an attitude indicator 2, a rotary bracket 3, a rotary central spindle 4, a control box 5, a desk frame 6, an adjusting screw 7, an electric cylinder 8, a connecting shaft 9, a bearing 10, a bracket 11, an angular displacement transmitter 12, a shaft coupling 13, a connecting rod 14, a back bearing 15, a rotating shaft 16, a support 17, a cross roller collar 18, a screw 19, a servo motor 20 and an encoder 21, wherein the servo motor and the encoder on the electric cylinder serving as a movable component drive the connecting rod to swing through the connecting shaft and the bearing so as to drive the rotating shaft to rotate; the angular displacement transmitter is coaxial with the shaft coupling and the rotating shaft and is connected with the workbench through the cross roller collar; the workbench rotates under the action of an intelligent combined unit; an attitude angle is formed by the attitude indicator on the workbench; and a control system control the rotating speeds and reciprocating rotational frequencies of the servo motor and the encoder of the electric cylinder so as to control the frequency and the rotation angle amplitude of the calibration device and achieve high calibration accuracy.