357 results about "Barometer" patented technology

In a portable biological information monitor apparatus, a pulse wave detection signal obtained by light emission from a green LED and a body motion detection signal obtained by light emission from an infrared LED are detected as biological information. This biological information is analyzed to compute various barometers. In a wake normal mode of a set generation mode, body motion and pulse are calculated as wake evaluation barometers for evaluation of a test subject's status in wake. In a wake steady state motion mode, body motion, pulse, and pitch are calculated as motion evaluation barometers for evaluation of the test subject's status in steady state motion. In a sleep mode, body motion, pulse, and autonomic nervous function are calculated as sleep evaluation barometers for evaluation of the test subject's status in sleep. Necessary barometers are thereby generated regardless of the test subject's action using the portable monitor apparatus alone.

The invention discloses a motion-sensing follow-type flight control system and method. The motion-sensing follow-type flight control system comprises a remote controller and an aircraft. The remote controller comprises a power supply system, an acceleration sensor, a digital-analog converter, a microcontroller and a radio transmission module. The aircraft comprises an information receiving module, an acceleration sensor, a gyroscope sensor, a barometer sensor, a data processing module and a control driving module. The remote controller obtains the acceleration magnitude of the hand through the acceleration sensor, collects motion data of the hand, and processes the motion data through the digital-analog converter. Then, the microcontroller calculates the acceleration change of the aircraft according to the acceleration change of the hand, and transmits a corresponding control instruction to the aircraft through the radio transmission module, so that the aircraft follows motions of the hand to cope and magnify the control motions guided by the hand, the aircraft is guided to fly in various corresponding flight paths by following the motions of the hand, and the immersive feeling is brought to an operator.

Disclosed is a rotor unmanned aircraft independent take-off and landing system based on three-layer triangle multi-color landing ground. The system comprises a small rotor unmanned aircraft (SRUA), an onboard sensor, a data processing unit, a flight control system, an onboard camera, landing ground, a wireless image transmission module, a wireless data transmission module and a ground monitor station, wherein the onboard sensor comprises an inertial measurement unit, a global positioning system (GPS) receiver, a barometer, an ultrasound device and the like, the data processing unit is used for integrating sensor data, the flight control system finishes route planning to achieve high accuracy control over the SRUA, the onboard camera is used for collecting images of the landing ground, the landing ground is a specially designed landing point for an unmanned aircraft, the wireless image transmission module can transmit the images to a ground station, the wireless data transmission module can achieve communication of data and instructions between the unmanned aircraft and the ground station, and the ground station is composed of a visual processing unit and a display terminal. According to the rotor unmanned aircraft independent take-off and landing system based on the three-layer triangle multi-color landing ground, the reliability of SRUA navigation messages is guaranteed, the control accuracy of the SRUA is increased, costs are low, the application is convenient, and important engineering values can be achieved.

A navigation device and a method of calibrating the same are provided. The device includes a barometric pressure sensor and a GPS receiver. A processor calculates barometric and GPS derived altitudes and, based on a difference therebetween, corrects barometer altitude readings that would otherwise include drift errors. The processor uses a filter, such as a state feedback loop, to determine correction factors. The state feedback loop is adjustable to operate with different time constants. An error drift model is empirically determined and used to set the time constant. The time constant may be adjusted during operation based on a relation between the barometer correction quantity and an uncertainty in the vertical component of the GPS derived altitude. The method includes updating and recalibrating an atmospheric pressure model used to derive altitudes from the output of the barometric pressure sensor.

A method for collecting data for a geographic database is disclosed. Altitude data are collected using a vehicle traveling in a geographic region. A barometer associated with the vehicle supplies the altitude data. Road grade data along the roads traveled by the vehicle is derived by analyzing the altitude data. The geographic database is updated to indicate the road grade.

Methods, apparatuses, and non-transitory processor-readable media of the present disclosure are presented for efficiently executing applications based on pressure sensor data. In some embodiments, a method includes monitoring pressure, and determining a rate of change in the pressure over time exceeds a predetermined rate-of-pressure-change threshold. The method further includes subsequently determining that the rate of change in the pressure over time no longer exceeds the predetermined rate-of-pressure-change threshold. The method further includes determining a change in pressure has exceeded a predetermined pressure-change threshold, and performing floor disambiguation.

The invention discloses a single person positioning navigator based on multi-sensor fusion and a positioning and navigating method. The single person positioning navigator comprises a global satellite positioning system, a barometer, a three-axis gyroscope, a three-axis accelerometer and three-axis geomagnetic sensors. Attitude angle information obtained through the gyroscope, position information obtained through the accelerometer, human body course information provided by the geomagnetic sensors, height information provided by the barometer, stride frequency information worked out by the accelerometer, and position and speed information provided by the global satellite positioning system are input into a kalman filter together, multi-information fusion is carried out through a kalman filter algorithm, and thus positioning and navigating parameters are output. Even when the global satellite positioning system cannot stably receive information due to shielding, electromagnetic interference and other factors, the single person positioning navigator based on multi-sensor fusion and the positioning and navigating method can achieve effective positioning and navigating and are suitable for various environments such as inside rooms or inside tunnels. By means of the single person positioning navigator based on multi-sensor fusion and the positioning and navigating method, positioning errors accumulated along with time can be reduced, and accurate individual 3D positioning can be achieved.

A state estimation system that utilizes long-range stereo visual odometry that can degrade to a monocular system at high-altitude, and integrates GPS, Barometer and IMU measurements. The system has two main parts: An EKF that is loosely fused and a long-range visual odometry part. For visual odometry, the system takes the EKF information for robust camera pose tracking, and the visual odometry outputs will be the measurement for EKF state update.

The invention relates to a virtual reality technology-based in-building navigation system, which comprises a three-dimensional simulation system, a strapdown inertial navigation system and a virtual reality display system; the strapdown inertial navigation system comprises an electronic compass, a gyroscope accelerometer and a barometer, and is used for acquiring the positioning information of a user, including orientation information and attitude information; the three-dimensional simulation system is used for three-dimensional modeling on a building structure and a scene, for coordinate transformation of the positioning information input by the strapdown inertial navigation system, for adding the positioning information into three-dimensional building information subjected to the three-dimensional modeling, and then outputting a processing result to the virtual reality display system so as display the processing result to the user. The virtual reality display system receives the processing result output by the three-dimensional simulation system, displays to the user, and is used for the display and navigation of a virtual scene.

The present invention discloses a low-cost GPS and INS integrated navigation system for multi-rotor aircrafts. The system includes a data acquisition processor; the data acquisition processor is respectively connected to a gyroscope, an accelerometer, a magnetometer and a barometer via an IIC bus; the data acquisition processor controls the gyroscope, accelerometer, magnetometer, and barometer for data collection, and sends the collected sensor data to a DSP controller; the GPS module sends the positioning data to the DSP controller; and the DSP controller conducts navigation calculation on the sensor data and location data. The invention has the beneficial effects that according to the dynamic characteristics of the multi-rotor aircraft and error characteristics of the low-cost sensor, the navigation system provides accurate attitude, speed and location information for the aircraft.

The invention provides an individual fireman positioning and navigation device. The device comprises a satellite navigation information receiving module, an electronic compass module, a barometer module, an electronic map module, a storage module, an MEMS inertial navigation module, an image information code reading module and a central processing unit module; first positioning information is obtained through the satellite navigation information receiving module; second positioning information is obtained through the electronic compass module; third positioning information is obtained through the barometer module; the electronic map module displays a map and makes comprehensive positioning information transmitted by the central processing unit module be displayed on the map; fourth positioning information is obtained through the MEMS inertial navigation module, the image information code reading module reads preset image information codes to obtain control information; the central processing unit module performs data fusion on the received control information, the first positioning information, the second positioning information, the third positioning information and the fourth positioning information to obtain the comprehensive positioning information. The individual fireman positioning and navigation device is widely applied to the field of fire protection and disaster relief.

The invention discloses a hybrid aerospace positioning method based on a barometer and WiFi. The method comprises the specific steps of S1, collecting data of all users of a whole building in a crowdsourcing mode, wherein the data mainly comprises RSS vectors and baro values of positions at which the users are located; S2, preprocessing data uploaded by all users through a cloud service platform; S3, calibrating the preprocessed data by the cod service platform, thereby obtaining standard data; S4, carrying out data analysis clustering on the calibrated data, thereby obtaining a Baro-RSS fingerprint map of the building; and S5, carrying out real-time positioning on the positions at which the users are located by the users themselves. According to the method, the floor positioning problem is solved through the hierarchical clustering analysis of the baro and the K-Means clustering of the WiFi, and the satisfactory positioning accuracy is achieved in a true environment.

Altimeters correct themselves by analysing pressure data to identify underlying climatic changes and modify sensed pressures accordingly to provide corrected altitude values. The detected underlying climatic changes are used to provide a barometer function independent of altitude changes.

Altitude measuring devices such as barometers typically provide good differential reading yet poor absolute reading, mainly depending on dynamic weather conditions. Placed at the same altitude but on different days, a barometer based altimeter might show different altitude reading. Thus, such altimeters, when used for navigation by pilots and mountaineers, for example, require manual and timely calibration. The present invention discloses a method for automatic calibration of altitude measurement devices, such as barometers, in order to achieve good absolute readings yet avoid the present manual calibration. This method is particularly useful for indoors navigation.

The invention discloses a system for simulating an operating environment of a composite insulator in high altitude localities. An output hole of a powder spraying machine of the system is communicated with an adjustable fan, an output hole of the adjustable fan is communicated with a test tank through an air flue, an output hole of a fog generator is also communicated with the test tank through an air flue; control ends of the powder spraying machine, the adjustable fan, the fog generator, a raining rank, a temperature adjusting device and a pneumatic control unit are connected with a control signal output end of a simulation environment control module through a total control module of an executing mechanism; signal output ends of a temperature sensor, a humidity sensor, a raining amount tester, a barometer, a wind speed and direction sensor and a dust sensor are connected with a signal input end of the simulation environment control module through a data acquiring module. The system is capable of rapidly and accurately simulating the operating environment in the high altitude localities under the condition of low-altitude localities, and is helpful to research the operating environment of the composite insulator in the high altitude localities.

A weather sensor system for gathering and transmitting weather related information. The system integrates information gathered from a barometer, temperature sensor, hygrometer, GPS, tilt sensor, and an anemometer. The anemometer assembly is a combined wind speed and direction sensor and radio antenna. The weather sensor data can be transmitted from a remote location and relay data to central collection point or network location.

The invention discloses a targeted staying and return voyage control system of an unmanned aerial vehicle. The system comprises a GPS positioning module, an electronic compass, a barometer, a memory, and a control chip, and the control chip is connected with the GPS positioning module, the electronic compass, the barometer, and the memory. After the control chip receives coordinate information generated by the GPS positioning module, direction recognition information generated by the electronic compass, and height information generated by the barometer, the information is processed, and a control instruction is generated to control motor driving of the unmanned aerial vehicle so that real-time positioning of any height and position of the unmanned aerial vehicle is realized, and the system is applicable to some special tasks, such as photography and exploration; when the control chip receives a return voyage instruction of a remote controller, the control chip performs comparison treatment according to the position and direction information of the unmanned aerial vehicle fed back in real time and initial coordinate information saved in the memory, and controls the unmanned aerial vehicle to automatically return to the take-off position so that the unmanned aerial vehicle can be rapidly recovered, and the system is more applicable to tasks such as investigation and rescue.

The invention discloses an indoor positioning method and an indoor positioning device based on a barometer, wherein the indoor positioning method comprises the steps of performing storey change determination by means of a mobile terminal which is internally provided with the barometer through a WiFi and/or Bluetooth positioning method; if storey change is determined by the mobile terminal, acquiring air pressure change value of a current user by means of the mobile terminal which is internally provided with the barometer, searching a preset storey switching air pressure change threshold, determining whether the air pressure change value is larger than the preset storey switching air pressure change threshold; and if the air pressure change value is larger than the preset storey switching air pressure change threshold, switching the storey in which the user exists. The indoor positioning method and the indoor positioning device improves indoor positioning accuracy by means of the mobile terminal through introducing air pressure detection.

The invention discloses a bridge detecting unmanned aerial vehicle system in a non-satellite navigating and positioning environment. The bridge detecting unmanned aerial vehicle system comprises an unmanned aerial vehicle flight platform, an airborne combined positioning module, an airborne monitoring module and a ground station control system, wherein the unmanned aerial vehicle flight platform comprises an unmanned aerial vehicle body, a power supply, a power module, a flight controller and an airborne wireless communication terminal; the airborne combined positioning module comprises a microinertia measuring unit, an ultra-wideband navigating and positioning module, an optical flow measuring module and a barometer; the airborne monitoring module comprises an airborne environment monitoring sensor, a vision sensor and a radar sensor; and the ground station control system comprises a wireless ground infrastructure, ground station planning control software and ground station data processing software. The bridge detecting unmanned aerial vehicle system adopts an integrated navigating and positioning way based on UWB, MIMU, OF and RAR, improves the positionability and the navigatingand positioning accuracy of an unmanned aerial vehicle in a global satellite navigating and positioning environment, and preforms close-distance obstacle observation in a complex bridge environment through the optical flow module.

A brand-new integral air disappears antivibration attenuator, belongs to the slanting back guy antivibration area . Its characteristic: It is made up of rain shade, the rubber armor coat, the metal inside hub, the metal outside hub, on the coupling, under the coupling, the aerocyst, the air valve, the barometer, the steel pipe support and so on. The slanting back guy's nuisance vibration transmits through the rubber armor coat and the metal inside hub gives to the aerocyst, the aerocyst take the steel pipe support as the support, provides counter- damping force to affect again in the slanting back guy, thus changed the slanting back guy original vibration modality, realizes restrains the slanting back guy vibration; The attenuator damping force's size may act according to the slanting back guy the vibration characteristic to make the extra wide adjustment, its antivibration effect is remarkable, is suitable specially in each kind of great span diagonal cable bridge takes the slanting back guy the antivibration device, simultaneously it also has the service life to be long, easy to make, the installment, the maintenance and affects and so on.

An intelligent system for a bicycle is provided with a control assembly including a seat bag control device, a sensor device, a digital camera, a lighting device, a warning device, and a power supply for supplying DC power to above components; and a display assembly including an LCD screen, a processing module, a communications module, and a power module for electrically interconnecting the LCD screen, the processing module, and the communications module. The seat bag control device includes a microprocessor, a memory, and a wireless communications module. The sensor device includes an optical sensor, a thermometer, an acceleration sensor, a barometer, a gyroscope, an electronic compass, a radar, and a GPS. The digital camera includes a rear camera. The lighting device includes an auxiliary light, a rear light, a directional light, and a decoration light. The warning device includes a loudspeaker and a vibration module.

The invention discloses an environmental parameter acquisition method based on vehicle networking and a device. The device comprises an OBD communication module which communicates with a vehicle bus to read the data of a vehicle outdoor air temperature sensor, a barometer which acquires atmospheric pressure, a temperature sensor which acquires air temperature data, a humidity sensor which acquires air humidity data, a PM2.5 dust particle sensor which acquires PM2.5 dust particle concentration, a GPS positioning module which is used for acquiring vehicle position data in real time, a microcontroller which is used for carrying out uniform coding on the acquired data, a 4G network communication module which is used for data transmission, and a cloud platform which is used for carrying out uniform processing on the coded data information. According to the invention, environmental parameter measurement and statistical results rely on a large number of terminal devices; the uploaded data are analyzed and processed on a platform end; large error factors are screened and removed; and a measurement result is more accurate than a measurement result of a single sensor.

The invention discloses a GPS (global positioning system), IMU (inertial measurement unit), magnetometer and barometer combinational navigation system device, which is structurally characterized in that a low-noise power supply output by a power supply conversion module is respectively connected with a main control unit, an accelerometer, a magnetometer, a gyroscope, a barometer, a GPS module and a ZigBee module, a high-efficient power supply output by the power supply conversion module is respectively connected with an RS-232 chip and a USART transmitting and receiving module, the main control unit is respectively connected with a USART bus, an I2C (inter-integrated circuit) bus, an SPI (serial peripheral interface) bus and the USART transmitting and receiving module through a main controller, the USART bus is respectively connected with the accelerometer and the magnetometer, the I2C bus is respectively connected with the gyroscope and the barometer, the SPI bus is respectively connected with the GPS module and the ZigBee module, and the USART transmitting and receiving module is connected with the RS-232 chip. The device has a compact structure, the overall size is small-scaled, the power consumption is low, a data processing speed is fast, various kinds of sensors are adopted for united positioning, so that the limitation on geographical application of a single positioning mode is overcome, and the precision and the accuracy of positioning are further improved.

An apparatus and a method for measuring an altitude of a terminal which can correct an altitude error according to temporal and spatial changes are provided. The apparatus includes an atmospheric pressure measuring unit for measuring an atmospheric pressure from a barometer included in the terminal, a position determiner for measuring position information of the terminal, and a controller for, when a reference atmospheric pressure reception period is not generated, predicting a current reference atmospheric pressure by using previously received reference atmospheric pressures and measuring a current altitude by using the predicted reference atmospheric pressure and the measured atmospheric pressure.

The invention relates to a controllable control surface-based rocket and attitude self-correction control method thereof, belongs to the technical field of spaceflight, and aims to solve the problem of instable attitude when a rocket takes off and the problem of spinning of the rocket in the process of operating in air. The rocket includes controllable control surfaces and an electronic control board used for controlling the controllable control surfaces; each controllable control surface is connected with a rocket body through a corresponding steering engine; and the electronic control boardincludes a gyroscope used for measuring the triaxial angular velocity and attitude angle of the rocket, a barometer used for measuring rocket flight height and a processor. The gyroscope and the barometer are utilized to obtain current actual measurement attitude data, Kalman filtering is utilized to filter triaxial angular velocity input to a PID controller; the eventually obtained flight height,triaxial angular velocity and attitude angle are input to the PID controller; the PID controller compares the read actual measurement attitude data with ideal attitude data, and provides a reasonablePID controlled quantity through operation of the processor; and the PID controlled quantity drives a rocker arm of the steering engine to act, thereby achieving the purpose of controlling the attitude of the rocket eventually.

The invention discloses a detection method and device for unmanned aerial vehicle flight height, and an unmanned aerial vehicle, and relates to the technical field of the unmanned aerial vehicles. The method comprises the following steps: on the basis of second flight height detected by an ultrasonic wave height measurement device, determining a confidence coefficient of detection performed by the ultrasonic wave height measurement device; according to the confidence coefficient and first flight height and the second flight height detected by an air pressure height measurement device, determining the flight height. According to the detection method and device and the unmanned aerial vehicle provided by the invention, through the flight height detected by the ultrasonic wave height measurement device, the confidence coefficient of the detection performed by the ultrasonic wave height measurement device is obtained, a confidence coefficient value and the flight height detected by the air pressure height measurement device and the ultrasonic wave height measurement device are subjected to fusion calculation to generate a smooth fusion height value, the advantages of ultrasonic wave height measurement and barometer height measurement can be fully utilized, the problem of discontinuous flight height detection values in traditional fusion calculation can be solved, a phenomenon of sudden change of the flight height detection value is avoided, the accuracy of flight height measurement is improved, and unmanned aerial vehicle control stability is improved.