76 results about "Altimeter" patented technology

The embodiment of the invention provides a method and a system for processing ocean multi-parameter wide-width imaging data of a Beidou interference altimeter, and relates to the technical field of GNSS-R. The method comprises the following steps: constructing a set of complete and strict data processing chain; through precise calculation of a GNSS-R direct signal and reflection signal delay inequality interference geometric model and correction of actual measurement delay inequality errors, systematic errors in the process of converting original signals into geophysical parameters are remarkably reduced, and the precision and reliability of parameters obtained through final inversion are improved. And on the basis of a self-adaptive data collection strategy of parameter space-time transformation characteristics and a spatial interpolation reconstruction process, discrete strip data is intelligently'woven 'into a continuously-covered wide-swath imaging type data product, so that the data format better meets the analysis requirements in the fields of oceanography, climatics and the like, and the intuition and usability of the product are improved.

The invention discloses a low-altitude aircraft accurate positioning method based on Beidou satellite data, and the method comprises the following steps: collecting the multi-source data of Beidou positioning, IMU, barometer and altimeter in the flight process, and generating an original positioning data set; after multi-source data are aligned, a fusion data sequence is constructed; carrying out error modeling by adopting zero offset correction, drift compensation and scale normalization, and outputting a calibrated data sequence; an improved FGO algorithm is input, factors such as Beidou satellite pseudo-range, IMU integration and process prior are processed in a combined mode, track combined optimization is executed, and a preliminary positioning result is output; performing error correction by combining a ground differential base station and satellite-based enhanced data, and outputting a high-precision positioning result sequence; and abnormal point elimination and trajectory smoothing are realized through consistency discrimination and confidence evaluation, and a final positioning result is obtained. The method improves the positioning precision and robustness of the low-altitude aircraft, and is suitable for high-precision positioning application in a complex environment.

The invention discloses a 5G and Beidou fused vehicle positioning navigation system. The system comprises a multi-source heterogeneous positioning module; a high-precision map and a dynamic traffic information base; a self-adaptive multi-layer map matching module; the dynamic path planning module considers steering limitation and real-time position feedback; and a central information fusion and decision unit. According to the invention, multi-source heterogeneous positioning data such as Beidou / GPS, 5G positioning, high-precision IMU, a vehicle-mounted atomic clock and a barometric altimeter are fused, and a tight combination algorithm based on ESKF or a factor graph is adopted, so that the system can realize accurate positioning in an environment with good satellite signals, partial shielding and even serious loss. Continuous, smooth and high-precision vehicle state estimation can be output, particularly when the number of visible satellites is insufficient, double-satellite positioning can be achieved by using the vehicle-mounted atomic clock to predict the clock error and combining the elevation constraint of the barometric altimeter, and the usability and robustness of positioning are improved.

The invention discloses a river water level inversion method taking altimeter footprint heterogeneity into consideration. The method comprises the following steps: acquiring an observation waveform of an SAR altimeter; space geometric parameters are calculated through footprint gridding and observation geometric modeling; constructing a water distribution scene based on the water mask and the river network, and classifying the water into a main river channel, a flood area and an adjacent isolated water body; electromagnetic scattering numerical integration is carried out based on the differentiated surface roughness parameters, and a simulated echo waveform is generated; waveform retracking and parameter inversion are realized through coarse grid search and local optimization solution; calculating an absolute water level and carrying out geophysical correction; performing multi-index quality control based on the interpretation rate of the analog waveform and the residual whitening degree; and finally outputting a water level product. According to the method, the defects of insufficient inversion precision and robustness of an existing method in a complex earth surface mixed scene are overcome, and the accuracy, reliability and physical interpretability of inland river water level monitoring are remarkably improved.

The invention discloses a twenty-two-axis vertical take-off and landing aircraft and a control method thereof. The twenty-two-axis vertical take-off and landing aircraft mainly comprises a parachute bag, a cabin and a power device. The twenty-two shafts comprise ten propellers, eight rotating shafts and four movable wings which are powered by independent power devices. The attitude, the position, the speed, the height and the course parameters of the aircraft are set on a computer according to the use requirements, and the attitude, the position, the speed, the height and the course parameters of the aircraft are calculated through sensors installed on twenty-two axes and an inertial reference system / attitude course reference system, an atmospheric data system, a global navigation satellite system, a course assisting and correcting system, a radio altimeter and an atmospheric temperature sensor in a cabin. A computer carries out data fusion and sends instruction signals to a power device for controlling ten propellers, eight rotating shafts and four movable wings, so that state control of the aircraft is realized, flight environment safety is intelligently diagnosed, and risk early warning and active avoidance are provided.

The application discloses a calibrator star-based altimeter calibration system and method, which utilizes a calibrator star carrying a calibrator to correct the system error of a spaceborne radar altimeter, thereby completing the calibration of the altimeter to the earth. The calibrator can modulate and retransmit the pulse emitted by the altimeter, and the calibration factor can be calculated according to the echo of the calibrator without relying on the ground calibration field, and then the calibration task can be completed by substituting into the ground target echo equation. The method utilizes the calibrator star to convert the calibration task from the original single "air-ground" data acquisition to an integrated calibration system of "altimeter-load platform-ground target", and the calibrator is moved from the ground to the space, so that the ground clutter can be reduced or even eliminated, the system error and the atmospheric error can be separated, and the coupling problem of the system error and the atmospheric error can be indirectly completed.

The embodiment of the invention provides an interactive multi-model factor graph integrated navigation method based on tight coupling attitude constraint. In a specific embodiment, the method comprises the following steps: constructing an integrated navigation system; constructing an inertial measurement unit factor pre-integrated by the inertial navigation system; constructing a direct celestial navigation factor and a refraction celestial navigation factor which are respectively and tightly coupled with an inertial measurement unit factor based on the star sensor observation condition of the celestial navigation system; constructing a horizontal radio navigation factor and a vertical radio navigation factor based on the position information of the land-based radio navigation system; acquiring height measurement data of the barometric altimeter to construct barometric altimeter factors; dynamically adjusting the weight ratio of the height measurement data of the vertical radio navigation factor to the height measurement data of the barometric altimeter factor through an interactive multi-model algorithm; and carrying out global state estimation of the integrated navigation system on a factor graph framework formed by the factors.

The utility model discloses an autonomous water taking device based on an altimeter, and relates to the technical field of water taking devices, the autonomous water taking device comprises a temperature-salinity-depth profiler body, the top of the temperature-salinity-depth profiler body is fixedly provided with a cable, and the inner side of the top of the temperature-salinity-depth profiler body is provided with a water taking assembly and a connecting assembly; the water taking assembly comprises a first connector, a second connector, a plurality of water taking tanks, a first electromagnetic valve, a second electromagnetic valve, a manual drain valve and a connecting cable; according to the technical scheme, the water taking assembly is arranged, specifically, according to the fact that the temperature-salinity-depth section plotter body is released to a certain depth of the bottom of the sea level, then the controller of the ship body controls the first electromagnetic valve and the second electromagnetic valve to be opened through the connecting cable, liquid is automatically poured into the water taking tank at the moment, and rapid and automatic water taking is carried out; and a plurality of water taking tanks are adopted, so that different types of seawater can be sampled, and the device is convenient to use.

This invention discloses a method for improving the orbital accuracy of a lunar probe based on reflective prism constraints. The method first utilizes laser ranging data obtained from a known reflective prism on the lunar surface using an onboard laser altimeter, and constructs an error equation set by combining this data with a dynamic orbital model. Next, a high-resolution camera is used to perform multiple imaging operations on the lunar reflective prism from different orbits and perspectives. Using the bundle adjustment principle, the observed image point coordinates are combined with the dynamic model to construct the error equation set. Finally, laser ranging observations from the reflective prism and multi-temporal photogrammetry observations are used as two different types of geometric constraints to construct a joint adjustment model of multi-source observation data. The high-precision orbital parameters are then calculated using a least-squares algorithm. This invention uses laser ranging data and an optical image database to add new constraints to the estimated orbit, ultimately correcting and further improving the orbital accuracy of the lunar probe.

An extended reality (XR) system, comprises a head-mounted display (HMD) configured for displaying virtual content to a user, a first altimeter carried by the HMD, a hand-held control, and a second altimeter carried by the hand-held control. The first altimeter configured for outputting first atmospheric pressure data indicative of an elevation of the HMD, while the second altimeter is configured for outputting second atmospheric pressure data indicative of an elevation of the hand-held control. The XR system further comprises at least one processor configured for determining a relative elevation between the first altimeter and the second altimeter based on the first atmospheric pressure data and the second atmospheric pressure data.

A Lidar-based SkyVoice Alert LHA 500 for a general aviation aircraft provides audible announcements of height above a landing surface (e.g., a runway) when the aircraft that is descending on approach or taking off, reaches a specific height above the ground. It gives repeated Gear warnings until the Gear is down and locked. It audibly announces preset GPS / MSL heights. It also announces various user selectable reminders like CheckList, LC GUMPS, Flaps, Check Oxygen, Check Altimeter, Check Fuel, Switch Tank, Top of Descent. The SkyVoice Alert LHA 500 is contained in a housing that mounts onto a removable access plate in a wing cavity, with the Lidar arranged to provide a vertical downward beam though a window formed in the access plate. A connector cable provides connection and disconnection between the SkyVoice Alert LHA 500 and the plane's audio panel.

This invention relates to the field of aviation navigation and simulation technology, specifically disclosing an airborne scene-terrain matching assisted navigation method and a highly realistic simulation platform. The method involves acquiring measured terrain information via an airborne camera, and collecting SAR image information, altimeter and atmospheric sensor information via radar. A matching algorithm between the camera terrain and radar images is used to match the measured data with pre-stored information, outputting the position correction error for inertial navigation to achieve inertial navigation correction. Even in complex electromagnetic environments without satellites or in electromagnetic silence, combined inertial navigation and matching navigation can still be achieved, ensuring stable flight of the aircraft. Simultaneously, a highly realistic 3D visual simulation platform is constructed, including a digital aircraft, flight control law, inertial navigation, 3D terrain, and various airborne equipment, providing full-process simulation support for the design, implementation, and testing of airborne scene-terrain matching assisted navigation systems. This invention solves the problem of aircraft navigation relying on satellites in complex electromagnetic environments, improves the anti-interference and reliability of navigation, and the simulation platform can effectively reduce the R&D and testing costs of navigation systems and improve R&D efficiency.

The invention belongs to the technical field of radar height measurement, and particularly discloses an inter-pulse phase modulation radar height measurement method based on range ambiguity. The method comprises the following steps: a transmitting branch of a pulse Doppler radar altimeter transmits a pulse signal; a receiving branch of the pulse Doppler radar altimeter receives the echo signal; obtaining an echo signal after the range gate is gated, and determining a demodulation code corresponding to the range gate; and carrying out decoding identification on the echo signal of the target distance received at the distance door according to the demodulation code. According to the scheme, the technical problem of fuzzy ranging of the pulse Doppler system radar altimeter is solved.

The invention belongs to the field of airborne interference imaging altimeter error correction, and particularly relates to a platform and baseline error correction method based on an airborne interference imaging altimeter, which comprises the following steps of: acquiring a height measurement data sequence X1 continuously acquired along a flight path; preprocessing the X1 to obtain a preprocessed data matrix X2; performing empirical orthogonal function decomposition on the X2 along the rail direction, and extracting a spatial mode, a time coefficient and a characteristic value; determining a main characteristic mode according to a variance contribution rate corresponding to the characteristic value; identifying and separating a platform error component, a baseline error component and a real height signal component by combining distribution characteristics of a space mode and a time coefficient; and reconstructing a real height signal based on a separation result to realize comprehensive correction of a platform error and a baseline error. According to the method, the platform error and the baseline error which are different from real signals in space-time characteristics are effectively separated through EOF decomposition, and the height measurement precision of the airborne interference imaging altimeter is remarkably improved.

This invention discloses a space-ground coordinated radiometric characteristic calibration method for spaceborne active microwave sensors in the field of radar Earth observation technology. It constructs a space-ground coordinated calibration system consisting of a radiation reference source satellite and a ground calibration processing station. The method includes: determining the orbital parameters of the radiation reference source satellite; the satellite transmitting signals to the ground station in Earth observation mode, using a known RCS target on the ground to calibrate its own antenna gain and link gain; receiving signals from the satellite to be calibrated in Earth observation mode, accurately calculating and transmitting echo signals based on the calibrated parameters; and the satellite to be calibrated calibrating its own transmit / receive link gain based on the received echo signals. This invention can be widely applied to the on-orbit radiometric calibration of active microwave sensors such as synthetic aperture radar, altimeters, and microwave scatterometers, significantly improving calibration frequency and accuracy, supporting multi-band, high-stability quantitative remote sensing tasks, and providing reliable technical support for precise observation in fields such as ocean monitoring, weather forecasting, and topographic mapping.

This invention discloses an automatic frequency-elevation map measurement method and system based on residual networks, enabling rapid and automatic extraction of key ionospheric parameters from frequency-elevation maps acquired by digital altimeters. The method first parses the header information and echo intensity data from the original binary file of the altimeter to generate a frequency-elevation map image. Then, a small number of samples are manually labeled to establish a training set with critical frequencies such as foF2 and h'F2 as ground truth. Based on this, an end-to-end model including a backbone residual network, pooling layers, and a feature extraction head is built. This model is trained to convergence through backpropagation and further fine-tuned using expanded sample data to obtain an engineering-deployable model. Finally, the frequency-elevation map to be processed is input into the model, and the predicted values ​​of the target parameters are output and written to the results file. This method reduces the workload of manual interpretation and verification and improves the measurement accuracy of irregular and disturbed frequency-elevation maps.

A system for geographically context-related crater detection, consisting of: a camera configured to capture raw images of the descent route; one or more integrated sensors configured to provide terrain context data, including altimeter, inertial measurement, or geological mapping information; a context-based super-resolution module (CISR) configured to produce a super-resolution image based on terrain context data; a crater detection network configured to detect one or more craters from the high-resolution image; a graph-based relational matching module configured to match the detected craters with a pre-calculated crater database; and an adaptive state estimation module configured to generate a spacecraft state output based on the matched crater pattern

The invention relates to a ducted water-air amphibious cross-medium aircraft. The aircraft is characterized in that the rear end of a nose is fixedly connected with the front end of a front fuselage, two turnover wings are fixedly connected to the left side and the right side of the front fuselage respectively, the rear end of the front fuselage is fixedly connected with the front end of a rear fuselage, and the front end of the rear fuselage is fixedly connected with the front end of an empennage; real-time data of an altimeter, a water pressure gauge and a gyroscope are integrated, a medium environment is automatically recognized through real-time data feedback, control modes are dynamically switched to adapt to different media, folding and unfolding of a turnover type wing can be controlled according to the requirements of air flight or underwater navigation, and an empennage control surface is driven to achieve attitude control. The folding type wings, the control surfaces and power output are coordinated according to task requirements, and seamless conversion and stable movement between the air environment and the water environment are achieved. Therefore, the medium limitation of a traditional platform can be broken through, and the adaptability and task ability of the aircraft in a complex environment are improved.

The invention relates to a radio altimetry system (101) suitable for installation in an aircraft and for providing the aircraft's altitude above the ground, comprising: a first subsystem (201) based on FMCW technology and providing a first altitude value (V1); a second subsystem (202) based on UWB technology and providing a second altitude value (V2); and electronic consolidation circuitry (203) (configured to: compare the second value to a predetermined threshold; if the second value is less than or equal to the threshold, determine a consolidated value (VC) based on the first and second values; and if the second value is greater than the threshold, determine a consolidated value (VC) based on the first value and disregarding the second value). In this way, the proposed radio altimetry system offers resilience to various interferences. Figure to be published with the abstract: Fig. 2

The utility model relates to a parachuting altimeter, and relates to the technical field of parachuting equipment. The upper meter cover covers and is fixedly arranged on the lower shell; the dial plate is fixedly installed in the lower shell, and the dial plate is divided into a first area, a second area and a third area; the fixed end of the stepping motor is fixedly mounted on the lower shell; the circuit board is fixedly installed in the lower shell and electrically connected with the stepping motor, and a sensor is fixedly installed in the lower shell and electrically connected with the circuit board; the rotating wheel is coaxially and fixedly installed at the output end of the stepping motor. The pointer is fixedly connected with the rotating wheel, the rotating wheel is used for driving the pointer to rotate, and the pointer is arranged above the dial. The method has the effect of improving the observation efficiency of the parachutist.

This invention discloses a multi-functional altimeter for terrain-matching navigation, compatible with both high-resolution altimetry and high-mobility altimetry functions. Differentiated designs are required in antenna beamforming and signal processing to meet these requirements. To ensure hardware compatibility, altimetry mode switching is achieved through software switching, employing compatibility design measures. Specifically, the receiving antenna integrates a wide-beam antenna and a narrow-beam antenna on the same substrate. The signal processing group and hardware are designed for compatibility, using different signal processing flows for the signal characteristics of high-resolution altimetry and high-mobility altimetry, ensuring that both altimetry functions and performance meet the requirements.

This invention provides a viewing area survey system that facilitates the measurement of received electric field strength to determine the viewing area for a given radio wave. [Solution] The viewing area survey system 1 comprises a measuring device 3 mounted on a drone and having a GNSS device 31 for detecting its position information, an altimeter 32 for measuring the drone's altitude, and a receiving field strength measuring unit 33 for measuring the received field strength of broadcast waves, and a management server having a viewing area determination unit 46 for determining the viewing area of ​​broadcast wave A. The GNSS device, altimeter, and receiving field strength measuring unit are connected to the viewing area determination unit so as to be able to communicate with each other. The drone flies based on a predicted viewing area where the received field strength of the broadcast wave is predicted to be equal to or greater than the minimum received field strength required to view the broadcast wave. The receiving field strength measuring unit acquires the point where the received field strength of the broadcast wave becomes the minimum received field strength, and the viewing area determination unit determines the area inside the area formed by connecting the acquired points as the viewing area.

The aircraft's altitude is acquired with high precision, even during takeoff and landing. [Solution] The aircraft is equipped with a flight altimeter which includes at least one of a barometric altimeter and a GPS altimeter, a laser altimeter which is equipped with the aircraft, and a control unit which switches which of the measured values ​​of the flight altimeter and the measured value of the laser altimeter to use when the aircraft is descending, based on the operating conditions.

An extended reality (XR) system, comprises a head-mounted display (HMD) configured for displaying virtual content to a user, a first altimeter carried by the HMD, a hand-held control, and a second altimeter carried by the hand-held control. The first altimeter configured for outputting first atmospheric pressure data indicative of an elevation of the HMD, while the second altimeter is configured for outputting second atmospheric pressure data indicative of an elevation of the hand-held control. The XR system further comprises at least one processor configured for determining a relative elevation between the first altimeter and the second altimeter based on the first atmospheric pressure data and the second atmospheric pressure data.

The invention relates to the technical field of engineering machinery, and discloses a suspension arm deflection monitoring and early warning method, which comprises the following steps of: S1, respectively arranging a laser altimeter at each section of arm head position of a main arm of a suspension arm; s2, acquiring the extension length of an arm support through a length sensor mounted in the middle of the basic arm, acquiring elevation data through an angle sensor mounted at a root joint of the suspension arm, cooperatively calculating the working amplitude, and acquiring actual height data of each section of main arm at the sampling frequency of 1-10 times per second; s3, calculating the theoretical height of each section of main arm according to the extension length and the working amplitude of the arm support; and S4, comparing the actual height data with the theoretical height to obtain the deformation deflection. According to the method, the laser altimeters are arranged on the arm heads of all the sections of the main arm respectively, and actual height data are collected in real time, so that the problem that the detection and positioning precision is poor due to the fact that most traditional suspension arm deflection monitoring methods only conduct early warning for overall deformation and cannot accurately position local deformation of specific arm sections is solved.

The invention discloses a height integrated navigation method and system for a low-altitude sea-skimming aircraft. The height integrated navigation system for the low-altitude sea-skimming aircraft comprises a radio altimeter, a vertical accelerometer and a combined height filtering processor, the radio altimeter is used for measuring the actual radio altitude of the aircraft; the vertical accelerometer is used for measuring the vertical acceleration of the aircraft; and the combined height filtering processor is used for outputting a combined height, a combined vertical speed and a combined vertical acceleration according to the actual radio height of the aircraft and the vertical acceleration of the aircraft. According to the height integrated navigation system for the low-altitude sea-skimming aircraft, aiming at the height control problem of low-altitude sea-skimming of the aircraft, data of a radio altimeter and an accelerometer are fused, a third-order height filtering system is designed, and height divergence of an inertial system is damped by radio height signals, so that the navigation precision is improved. Complementary advantages of short-term high precision of the accelerometer and long-term stability of the altimeter are fused.

The present invention comprises: a flight altimeter that is provided to an aircraft and includes at least one of a pressure altimeter and a GPS altimeter; a laser altimeter that is provided to the aircraft; and a control unit that, when the aircraft descends, switches a measurement value to be used between a measurement value of the flight altimeter and a measurement value of the laser altimeter on the basis of use conditions.

The application provides an inertial platform fault injection and testing method based on redundancy technology, aiming at an inertial platform accelerometer height measurement and altimeter combined error feedback compensation height measurement system adopting redundancy technology, four faults of platform noise interference fault, platform large interference torque fault signal, altimeter noise fault and altitude redundancy error feedback fault, adopting a time injection function mode, combining an inertial platform mechanical motion model, a direct current torque motor model and a gyroscope measurement model established by a transfer function method, organically combining the above faults and signals into a closed loop closed system, effectively simulating the altitude measurement output signal of the redundancy technology based on the fault state, thereby realizing the fault injection simulation of the inertial platform system and realizing the equivalent function of the testing system.

This invention discloses a high-isolation radio altimeter microstrip antenna, mainly addressing the problem of low isolation in existing antennas. From top to bottom, it includes a radiator (1), an adjustment structure (2), and a ground plane (3). The adjustment structure (2) includes a frame (21), metal stubs (22), shorting pins (23), and a dielectric (24). The metal stubs consist of three parts, with the first part located at the antenna's central axis AA, and the second and third parts symmetrical about the antenna's central axis AA. The shorting pins consist of three groups, with the first group located at the antenna's central axis AA, and the second and third groups symmetrical about the central axis AA. The frame and metal stubs are located on the upper surface of the dielectric, while the shorting pins are located inside the dielectric. This invention uses a split design to form a transmitting antenna and a receiving antenna, which can be flexibly installed in different positions on the device, effectively improving the isolation between the transmitting and receiving antennas. It can be used in radio altimeters or ranging / altitude radars.

A system comprises a RF antenna connected to a vehicle, a primary radio altimeter connected to the antenna, a secondary radio altimeter comprising a millimeter wave radar sensor, and a processor coupled to the primary and secondary radio altimeters. The processor determines whether an altitude detected by the primary radio altimeter is greater than a threshold altitude. If the altitude is greater than the threshold altitude, the altitude detected is used and signals from the secondary radio altimeter are discarded. If the altitude is not greater than the threshold altitude, the processor identifies whether signal interference from a cellular network source is present based on any abnormal signals from the primary radio altimeter. If abnormal signals are not present, altitude estimates detected by the primary and secondary radio altimeters are correlated. If abnormal signals are present, signals from the secondary radio altimeter are processed to detect a vehicle altitude.