117 results about "Altimeter" patented technology

The invention relates to the field of radio measurement, in particular to a radio height simulation device and method. The radio height simulation device comprises a fixed attenuator, a photoelectric conversion module Tx, a first optical path control member, a second optical path control member, a photoelectric conversion module Rx, a numerical control attenuator and a host. One end of the fixed attenuator is connected with the radio altimeter, one end of the photoelectric conversion module Tx is connected with the fixed attenuator, the other end of the photoelectric conversion module Tx is connected with the first optical path control element, the first optical path control element is externally connected with at least one optical fiber, and the optical fiber is connected with the second optical path control element; according to the invention, the dependence on a digital signal processor and a long-distance radio frequency cable is reduced, the hardware cost is reduced, the radio altimeter can be tested according to the radio height simulation device, the device can be calibrated by using a vector network analyzer, and the accuracy of height simulation is further ensured.

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.

A method includes generating an output radio frequency (RF) signal. The method includes communicating the output RF signal to an antenna module. The method includes receiving a bit stream from the antenna module. The bit stream includes data representing the output RF signal prior to transmission of an output RF waveform associated with the output RF signal at the antenna module and data representing a return RF signal associated with a return RF waveform received at the antenna module following transmission of the output RF waveform as part of a sensing operation. The method includes analyzing one or more values of the data representing the return RF signal to generate an altitude indication for a vehicle, a ground speed indication for the vehicle, or a combination thereof.

The present disclosure relates to the technical field of model construction, and provides a river water dynamics model construction method based on multi-source remote sensing, which comprises the following steps: acquiring a river remote sensing image to obtain a water edge line, acquiring water level data by means of an altimeter satellite, and giving an elevation value to a water edge line corresponding point according to the water edge line and the water level data; for a straight river section, a value is taken according to a specific rule, and for a curved river section, the value is determined according to linear fitting of multiple elevation measuring point values on a river section; based on the elevation values of the water edge lines of the straight and curved river sections, a river terrain digital raster model is further constructed by interpolation along the water edge line, the river water dynamics model is constructed by using the river terrain digital raster model, the simulation effect of the water dynamics model is determined by comparing the water level consistency or the water surface vector form consistency, and the calibration and verification of the river water dynamics model are realized. The present disclosure realizes accurate simulation of the river water dynamics process. The present disclosure can reduce the cost of model parameter acquisition.

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 an unmanned aerial vehicle height estimation method, and belongs to the technical field, and the method comprises the steps: S1, data collection: controlling an unmanned aerial vehicle to vertically climb or descend by H meters in situ, and continuously collecting images and air pressure height data during the period; s1-1, collecting a first group of data; s1-2, collecting a second group of data; s1-3, carrying out data pairing; s2, calculating the height of each image to the ground at the acquisition moment; s3, calculating the relation between the air pressure height and the height to the ground; and S4, calculating the relation. The unmanned aerial vehicle height estimation method is low in cost, does not need to additionally add a sensor, can realize ground height estimation by using an existing visual system and a barometer of the unmanned aerial vehicle, greatly reduces hardware cost, is suitable for vertical motion scenes of the unmanned aerial vehicle, especially has good performance in low-speed scenes such as landing, makes up for the dependence on horizontal displacement speed in the prior art, and has good application prospects. Through multi-group data acquisition, feature matching and linear fitting, the accuracy and reliability of ground height estimation are 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.

A method includes receiving an output radio frequency (RF) signal. The method includes generating a digitized output RF signal representing the output RF signal. The method includes transmitting an output RF waveform associated with the output RF signal. The method includes receiving a return RF waveform based on transmission of the output RF waveform. The method includes generating a digitized return RF signal representing a return RF signal associated with the return RF waveform. The method includes serializing the digitized output RF signal and the digitized return RF signal to generate a serialized baseband signal. The method includes communicating a bit stream based on the serialized baseband signal to an RF unit. The RF unit is configured to generate an altitude measurement, a ground speed measurement, or both for a vehicle based on the serialized baseband signal.

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.

1. The name of this design product: altimeter body. 2. Purpose of the product of this design: The whole product is an altimeter used to measure height; the part of the product is the main body of the altimeter. 3. The key design point of this design product lies in the shape of the solid line part in the figure. 4. The picture or photo that best illustrates the design points: Stereoscopic drawing 1. 5. Other situations that need to be explained Other explanations: The dotted part in the figure is the content that is not requested to be protected.

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.

The invention relates to a radio altimetry system capable of being loaded on board an aircraft. The invention relates to a radio altimetry system (101) capable of being loaded on an aircraft and capable of providing a height of the aircraft from the ground level, the radio altimetry system comprising: a first subsystem (201) based on FMCW technology and providing a first height value (V1); a second subsystem (202) based on UWB technology and providing a second altitude value (V2); and merging electronic circuitry (203) (configured to: compare the second value with a predetermined threshold; if the second value is less than or equal to the threshold, determining a merge value (VC) based on the first value and the second value; and if the second value is greater than the threshold, determining a merge value (VC) based on the first value irrespective of the second value. In this way, the proposed radio altimetry system is resistant to various interferences.

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 relates to a hybrid altitude measurement method employing dynamic integral Kalman filtering. First, a SiA200 MEMS accelerometer is used to measure the carrier's acceleration, and the acceleration is integrated twice to obtain inertial altitude information. An FYC-LG24-800 radio altimeter is used to measure the carrier's radio altitude information. A GPS device is used to measure the GPS altitude information of the carrier. A second-order square root nonlinear smoothing filter is designed to obtain smoothed signals from the three measured altitude signals. Then, a dynamic integral Kalman filter is designed based on the altitude error after the combined Kalman filtering and the nonlinear integral to adjust the variance information, thereby solving for the pairwise Kalman filtered signals of the three altitude smoothing signals. Finally, the error signal is superimposed with its nonlinear integral signal to generate a dynamic combined weighting factor in real time. The three Kalman filtered altitudes are then optimized and combined to obtain the final total altitude output signal.

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

Aircraft (200), preferably eVTOL aircraft (200), said aircraft (200) comprising: an inertial measurement device (1) configured to provide a first indicator signal (102a) corresponding to the kinematics of the VTOL aircraft (200), an indication device (4) which is different from the inertial measuring device (1) and in particular independent of the inertial measuring device (1), and which is configured to provide a second indicator signal (4b, 5b, 6a, 7a) which is different from the first indicator signal (102a), and a determination device (101) which is configured to process the first indicator signal (102a) and the second indicator signal (4b, 5b, 6a, 7a), in particular to combine them logically, in order to provide a status signal (101a) which correlates with a take-off / landing state of the VTOL aircraft (200), wherein the indication device (4) is a Baro-Altimeter (4) and the Baro-Altimeter (4) is configured to provide the second indicator signal (4b) indicating a take-off state of the VTOL aircraft (200) when the ambient air pressure measured by the Baro-Altimeter (4) increases or the altitude measured by the Baro-Altimeter (4) decreases.

The application provides a significant wave height extraction method based on a synthetic aperture radar image, step 1: data acquisition, matching the altimeter significant wave height with the synthetic aperture radar interferometric imaging mode data to obtain a sample data set. Step 2: the data amount of the altimeter significant wave height in different incidence angle ranges is counted to obtain the numerical distribution of the altimeter significant wave height in the global near-shore range. Step 3: the normalized variance of the backscattering coefficient of the synthetic aperture radar and the altimeter significant wave height are subjected to quality control to obtain the significant wave height and normalized variance data. Step 4: a linear relationship between the significant wave height and the normalized variance is established. Step 5: the estimated value of the synthetic aperture radar significant wave height is evaluated and verified, and the significant wave height can be obtained by inputting only a single image parameter, the normalized variance. The application not only considers the synthetic aperture radar open ocean wave mode, but also relates to the near-shore research, and provides technical support for the development of related topics in the coastal area.

The present application discloses a satellite collision avoidance method, apparatus, and computer-readable storage medium. The method relates to the field of satellite technology. The method comprises: obtaining obstacle information of obstacles within the movable range of a target satellite; calculating the probability that the target satellite will not collide with the obstacle based on the obstacle information and target satellite information of the target satellite; calculating the energy consumed by the target satellite based on the altitude adjusted to avoid collision; constructing a consumption calculation model based on the probability that the target satellite will not collide with the obstacle and the energy consumed by the target satellite; and solving the consumption calculation model using a genetic algorithm with the goal of minimizing consumption to determine the adjusted altitude of the target satellite. This solves the technical problem of excessive fuel consumption when satellites avoid obstacles.

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.

This invention discloses a target drone flight trajectory correction method based on multi-source fusion navigation, belonging to the field of trajectory correction technology. This invention can fully integrate multi-source navigation information such as AI visual navigation, inertial measurement, and barometric altimeter. Through joint analysis of short-term and trend envelopes, it effectively distinguishes between short-term disturbances and long-term deviations, significantly improving the sensitivity and reliability of trajectory anomaly detection. By setting a direction consistency screening and hierarchical weight suppression mechanism, it can suppress false alarms caused by barometric pressure fluctuations or instantaneous noise in low-altitude flight, thereby reducing the false alarm rate. Furthermore, by utilizing envelope difference accumulation evidence and threshold linkage triggering mechanisms, it achieves early warning of trajectory deviations, improving the timeliness of anomaly response in flight missions. Moreover, it can dynamically generate stable and accurate trajectory correction values ​​in a variable flight environment, ensuring the robustness and convergence of the correction process.