238 results about "Guidance system" patented technology

The invention relates to a dynamic cooperative path planning and autonomous landing control method for an unmanned aerial vehicle and an unmanned ship, and the method comprises the following steps: collecting the state data of the unmanned ship and the unmanned aerial vehicle and the high sea condition environment data, and carrying out the data fusion processing; an improved fast extended random tree algorithm is adopted to plan a safe navigation path for the unmanned ship, the generated path of the unmanned ship is optimized based on an unmanned ship motion model considering environmental interference, and a model prediction control algorithm is adopted to plan a path for the unmanned ship to fly to a predicted landing point of the unmanned ship. Dynamic cooperation between the unmanned ship and the unmanned aerial vehicle is realized through information interaction between the unmanned ship and the unmanned aerial vehicle; the unmanned aerial vehicle recognizes an unmanned ship landing identifier through a visual servo guide system, calculates the position and attitude deviation relative to a landing point, adjusts flight control parameters according to interference conditions by using an adaptive control algorithm, and performs trajectory prediction compensation in combination with an unmanned ship motion model to realize autonomous landing. Compared with the prior art, safe landing of the unmanned aerial vehicle on the unmanned ship under the high sea condition is achieved.

The technology disclosed teaches distributed networks and methods for cloud processing for global navigation satellite system (GNSS) interference data from a plurality of GNSS receivers to alert aircraft personnel to GNSS spoofing of aircraft guidance systems. The technology disclosed includes receiving at a cloud-based server, GNSS interference data from the plurality of GNSS receivers, analyzing the GNSS interference data upon receipt, identifying an interference event from the analyzed GNSS interference data, and in response to an identified interference event, the cloud-based server providing an alert to EFB tablet devices onboard the aircraft thereby causing notification of aircraft personnel of a potential spoofing event.

The invention provides a reusable rocket landing stage starting height prediction method, a guidance system and a processor, and aims to dynamically and accurately determine the ignition time of an engine by constructing a real-time online starting height prediction model based on an energy conservation principle and combining multiple safety thresholds (including an allowable starting height upper limit and a standby starting height lower limit) so as to predict the starting height of the rocket in a landing stage. And the safety and fuel optimality in the whole flight envelope are ensured, so that the reliability, accuracy and economical efficiency of the reusable rocket landing are remarkably improved. The problems that in the prior art, engine starting height prediction precision and robustness are insufficient, online adaptation to uncertainty of a complex flight environment cannot be achieved, and safety margin consideration is insufficient are solved, and potential safety risks are thoroughly eliminated.

The invention discloses a wearable path guiding system based on visual-tactile cross-modal mapping. The wearable path guiding system adopts a three-module architecture, namely a visual environment sensing module, a simplified path planning module and a tactile guiding module. The environment perception module constructs an incremental scene map with semantic annotations based on a depth camera. And the simplified path planning module is used for generating a steering vector containing gait information and a steering angle according to the advancing direction and simplified path pointing and performing real-time iterative optimization to realize real-time matching of the advancing direction of the user and the target direction. And the tactile guidance module is used for realizing synchronization of gait and tactile stimulation, generating priority gradient intensity field tactile feedback with a direction indication characteristic according to path deviation information, correcting the advancing direction, and starting the voice auxiliary module when multiple times of tactile correction do not reach the expectation. The method is suitable for a visual signal limited scene, the visual signal is mapped into the tactile signal to realize self-adaptive synchronization with the motion rhythm, and path guidance is completed.

The invention belongs to the technical field of civil aviation, and particularly relates to a portable visual parking guiding system which comprises a portable image device used for generating an environment reference file when a worker is placed at an entrance of a target parking area; the target locking and contour snapshot acquisition unit is used for generating an integrated contour in three rounds of iteration by adopting an accumulation and superposition strategy after the target enters a preset sensing range; calculating a positioning vector set according to a position relation between the integrated contour and a set ideal parking attitude, and writing the positioning vector set into an instruction buffer queue; and the guide visual output unit is used for reading the instruction buffer queue and synchronously displaying character prompts on an interface of the handheld end. The method can continuously provide high-precision, strong-robustness and low-power-consumption parking guiding capability within millisecond-level time delay under the condition that fixed infrastructures and manual calibration are not needed.

The disclosed invention introduces an advanced Visual Alarm and Guidance System designed to significantly enhance safety in industrial environments. This innovative system integrates state-of-the-art computer vision and light projection technologies, along with trajectory prediction algorithms, to dynamically identify potential hazards and guide workers in real-time out of potential collision pathways. It marks a considerable advancement over traditional safety methods by not only detecting imminent dangers but also providing clear, visual navigation aids. This system is adaptable to various high-risk settings, seamlessly integrates with existing infrastructures, and offers a novel approach to real-time, visual safety management in industrial settings.

An aircraft-based strategic and tactical interactive guidance system for ground operations includes position sensors for determining position information of an aircraft engaged in taxi operations (e.g., gate to takeoff, touchdown to gate) at an airport. The guidance system stores airport database information about runways, taxiways, hazards, gates, and other airport features. The guidance system analyzes and parses verbal taxi instructions from the airport control facility, into a navigation path. The guidance system fuses the navigation path with the airport database information and the aircraft's position information to present, via an interactive display surface, a strategic display, e.g., providing an overhead view of the current aircraft position, its assigned gate or destination, and the navigation path incorporating the prescribed runways and / or taxiways via which the aircraft will reach said destination. The pilot may modify the displayed navigation path via the interactive display surface.

The technology disclosed teaches distributed networks and methods for cloud processing for global navigation satellite system (GNSS) interference data from a plurality of GNSS receivers to alert aircraft personnel to GNSS spoofing of aircraft guidance systems. The technology disclosed includes receiving at a cloud-based server, GNSS interference data from the plurality of GNSS receivers, analyzing the GNSS interference data upon receipt, identifying an interference event from the analyzed GNSS interference data, and in response to an identified interference event, the cloud-based server providing an alert to EFB tablet devices onboard the aircraft thereby causing notification of aircraft personnel of a potential spoofing event.

The invention discloses a multi-missile self-learning differential game cooperative guidance method based on disturbance feed-forward compensation, and the method comprises the steps: providing a finite-time convergence sliding-mode nonlinear expansion state observer for solving the problems of unknown partial parameters and external disturbance in a multi-missile cooperative guidance system; a sliding mode control method is combined with an extended state observer, a novel fixed-time convergence sliding mode surface and a sliding mode reaching law are constructed, and real-time estimation and efficient compensation of unknown disturbance in a system are achieved. Strictly proving the fixed convergence time of the observer by using a Lyapunov function, and analyzing a disturbance estimation error; compared with a traditional ESO, the method has the advantages that the speed and precision of state tracking are remarkably improved, and the anti-interference capability of the multi-missile cluster in a complex interference environment is effectively improved.

An aircraft pylon comprising a box-section primary structure and at least one tank positioned inside the primary structure. To facilitate mounting or demounting the tank, the pylon is equipped with a guide system configured to move the tank from its mounted position toward a through-hole, including a guide rail fastened to the primary structure and positioned above the tank and a guide pin fastened to the tank cooperating with the guide rail so that the tank is supported by the guide rail and is able to slide along the latter. This guide system contributes to simplifying manipulation of the tank when mounting or demounting the tank by at least partly compensating its weight and guiding the tank.

A while-drilling acoustic auto-tracking wellbore tool and a method for using same. The tool comprises: a power generation and communication system (100), which comprises a power generation system and a communication system, wherein the communication system is used for bidirectional transfer of measurement data and a control instruction; a power and measurement and control system (200), which comprises a measurement while drilling system, wherein the measurement while drilling system is used for measuring inclination and azimuth data of a newly drilled borehole, and transmitting the data to the communication system; and an acoustic measurement and guidance system (300), which comprises an acoustic emission and measurement and control system, wherein the acoustic emission and measurement and control system is used for emitting an acoustic signal in the newly drilled borehole, receiving a return signal and transmitting the return signal to the communication system. The solution solves the difficult problems of communicating a newly drilled well and an old borehole, determining the distance between a drill bit and the old borehole in real time, etc. The acoustic emission and measurement and control system emits the acoustic signal in the newly drilled borehole, receives the return signal and transmits the return signal to the communication system, and the position of a wellbore is dynamically scanned and monitored in an acoustic while-drilling manner, thereby achieving the aim of performing measurement while drilling.

The invention discloses a marine ranch cruising task-oriented drum sailboat event triggering optimization control method. The method comprises the following steps of: constructing a three-degree-of-freedom nonlinear mathematical model of a drum sailboat; generating a virtual reference path based on the waypoints by using LVS so as to obtain a guidance law and a position error; improving the guidance law by using a limited boundary circle rule to obtain an improved ILVS guidance law, and further obtaining a heading error; designing a virtual control law based on the actor-commentator neural network; a dynamic surface control technology is introduced to filter the virtual control law and define a dynamic error, and a robust neural damping technology is used to carry out robustness processing on a nonlinear term; designing intermediate control input by combining the actor-commentator neural network, the dynamic error subjected to robust processing and the derivative of the filtered virtual control law; designing an integral dynamic event triggering mechanism, and designing a ship path tracking controller by combining an adaptive compensation technology and intermediate control input; according to the invention, the communication load of a guidance system can be effectively reduced, the practicability of the controller in a dynamic marine environment is effectively improved, and the cruise precision of a marine ranch is guaranteed.

The invention relates to the field of aviation safety, in particular to a low-altitude flight safety co-guidance system, which comprises a flight airspace delimiting module, an image intelligent identification module, a position determination module, a collision risk judgment module, a route planning module and a management database, and is characterized in that an identification model is constructed through a convolutional neural network, and a flight airspace image is acquired; the method comprises the following steps: identifying a moving object and a fixed obstacle in a flight airspace, performing position marking on the moving object and the fixed obstacle in a flight airspace image, predicting a movement track of the moving object in the flight airspace image, further judging whether the aircraft has a collision risk, and determining the collision risk position of the aircraft. A heuristic search algorithm is utilized to output a safe flight path fragment, the whole process from environment perception to risk response is covered, and the possibility of collision accidents of the aircraft is greatly reduced.

The invention discloses an eVTOL take-off and landing management system and method based on a mobile take-off and landing platform. The eVTOL take-off and landing management system comprises a low-altitude flight scheduling system, a take-off and landing platform system, an approach management system, a radio height feedback system, an RTK differential positioning system, a Beidou positioning system, a guiding system, an undercarriage fixing system, a recording system and a process feedback system. By using the take-off and landing management system, an eVTOL flexible take-off and landing application channel is opened, and an important guarantee is provided for the mobile take-off and landing platform to take off and land the eVTOL; by means of the mobile take-off and landing platform, take-off and landing at any suitable position in the eVTOL field are achieved, the problem that take-off and landing can only be conducted at a fixed take-off and landing point is solved, and a foundation is laid for wide application of the eVTOL; various sensing systems and intelligent computing systems are applied, technical support is provided for eVTOL take-off and landing, the take-off and landing difficulty is lowered, and human intervention is reduced.

A system and a method for defining and maintaining slope and cross-slope parameters during construction vehicle operations are provided. Data associated with an attachment positioned at reference points on the terrain and the corresponding location and elevation information from a location sensor are obtained. Based on this data, the processing unit calculates slope and cross-slope parameters by analyzing the differences in elevation and the horizontal distances between the reference points. As a result, guidance information is generated for real-time operator feedback or for the automatic adjustment of the attachment. The system includes a location sensor (e.g., GNSS) and optical sensors (e.g., LiDAR) for calculating the slope and cross-slope values, and for controlling operation of the attachment to ensure that the grading or earthmoving matches defined specifications.

The invention discloses a guiding system and method for penetrating through a special site through horizontal directional drilling, and relates to the technical field of horizontal directional drilling. Comprising a control system, a sensor arranged at the end of a drill rod or a drill bit and used for collecting position signals of the end of the drill rod or the drill bit, a guiding instrument used for receiving signals of the sensor and a carrying device used for carrying the guiding instrument, and the guiding instrument is used for transmitting the received signals of the sensor to the control system. And data analysis and processing are carried out through the control system. By arranging the carrying device, the guiding instrument synchronously moves along with the drill rod, the problems that the guiding instrument cannot be held by a person to reach a special site in a long distance or the guiding positioning is unstable and the precision is reduced when the guiding instrument is carried by a ship are solved, the personnel safety is ensured, and the position of a drill bit is corrected in real time through the control system; the drill bit is kept at the preset position all the time, and it is guaranteed that an actual guide hole is consistent with a penetrating design curve track.

A system and method for providing airport docking guidance for an aircraft includes supplying, from an airport gate database, airport gate data parking data indicative of gate position points and a gate aircraft parking headings. Aircraft data is supplied from an aircraft data source. Position error data is supplied from a position error receiving system. Airport gate data for one airport gate is retrieved. A processing system processes the aircraft data and the position error data to determine, for the one airport gate, an aircraft position point, an aircraft position deviation, and an aircraft heading deviation. The position error data may be supplied from a ground-based position error transmission system that at least selectively determines, from airport gate data and a ground-based position measurement system, the position error data and transmits the position error data.

The invention relates to the technical field of telescope control, in particular to a closed-loop tracking guiding method and guiding system for a telescope, and the method comprises the steps: setting a triggering frequency as an integral multiple of a frequency for receiving an actual guiding direction, and determining whether to trigger the telescope guiding or not according to the multiple. And according to a target miss distance and encoder pointing fitting trajectory formula, calculating a target reference guide pointing direction, superposing the target reference guide pointing direction and the target miss distance, obtaining an actual guide pointing direction for guiding the telescope to rotate, and guiding the telescope to rotate to track the target. The method does not need to consider the time alignment problem of each module, effectively reduces the jitter degree of the target in the visual field, and improves the tracking precision.

The application relates to a vertical five-axis simulation turntable with a coaxial sleeve structure and belongs to the technical field of semi-physical simulation equipment of inertial navigation and optical guidance systems. The turntable adopts a vertical structure and comprises a base, a two-axis table and a three-axis table. The azimuth, pitch and roll frame assemblies of the three-axis table constitute a frame assembly of three rotary degrees of freedom, so that three-dimensional attitude motion simulation of an aircraft is realized. The pitch and azimuth frame assemblies of the two-axis table constitute a frame assembly of two rotary degrees of freedom, so that starry sky simulation, target vision simulation or infrared target motion simulation on a spherical screen is realized. The external two-axis table is independently sleeved outside the internal three-axis table. The turntable has the characteristics of compact structure, high precision, large azimuth angle range of target motion simulation, large load size, wide bearing range and the like.

The application discloses a kind of anti-UAV guidance information extraction methods, comprising the following steps: S1, establish anti-UAV guidance system, set system state model, system observation model, the system state model includes acceleration submodel, Singer submodel and sinusoidal submodel;S2, by total strapdown seeker measurement target, obtain line-of-sight angle information, relative distance information, by airborne sensor obtains unmanned plane acceleration information, above-mentioned information is as the observation value of system observation model;S3, by filter to anti-UAV guidance system is filtered, respectively obtains acceleration submodel, Singer submodel and sinusoidal submodel filter result;S4, the filter result of submodel is fused and estimated, obtains final guidance information.The anti-UAV guidance information extraction method disclosed in the application obtains unmanned plane guidance information error, and accuracy is high.

The application discloses a kind of based on real-time positioning and physiological data's cruise ship emergency evacuation guiding system and method, including bracelet terminal, monitoring subsystem, server platform and client;Bracelet terminal is worn in passenger or crew hand, including heart rate sensor, navigation display and prompt unit, wireless communication module and control circuit etc..Heart rate sensor is used to collect the heart rate information of wearer, navigation display and prompt unit are used to display route guide and provide vibration or voice prompt.By constructing dynamic electronic fence based on computer vision, combined with real-time personnel position and channel topological information to carry out evacuation simulation, generate and dynamically adjust the optimal evacuation path, and use physiological data such as heart rate to optimize the evacuation guiding strategy, trigger nearby rescue dispatch for people with abnormal vital signs, so as to improve the efficiency and safety of cruise ship emergency evacuation.

This invention discloses a surgical instrument guidance system, comprising a robotic arm, a clamping device, and a navigation marker assembly. The clamping device includes a body, a receiving portion, a sleeve, a first pressing member, and a multi-link mechanism. The receiving portion has a receiving hole. The sleeve is detachably disposed in the receiving hole. The sleeve has a through hole for inserting a surgical instrument. One side of the sleeve has a notch along the axial direction of the through hole, the notch communicating with the through hole. The sleeve also has a limiting portion at the edge of the notch. The first pressing member is disposed in the body. The multi-link mechanism is disposed in the body and the receiving portion, and connected to the first pressing member and the sleeve. The first pressing member is pressed, causing the multi-link mechanism to push against the limiting portion to reduce the notch, causing the sleeve to deform and clamp the surgical instrument. The surgical instrument guidance system provided by this invention allows the robotic arm and surgical instrument to share a single navigation marker assembly, simplifying the robotic arm calibration process and reducing time.

The technology disclosed teaches distributed networks and methods for cloud processing for global navigation satellite system (GNSS) interference data from a plurality of GNSS receivers to alert aircraft personnel to GNSS spoofing of aircraft guidance systems. The technology disclosed includes receiving at a cloud-based server, GNSS interference data from the plurality of GNSS receivers, analyzing the GNSS interference data upon receipt, identifying an interference event from the analyzed GNSS interference data, and in response to an identified interference event, the cloud-based server providing an alert to EFB tablet devices onboard the aircraft thereby causing notification of aircraft personnel of a potential spoofing event.

The application provides a master-slave cooperative guidance system fault positioning and fault-tolerant method in a communication interference environment. The method can effectively position and tolerate the fault of the communication link error information injection in the cooperative guidance system. First, a distributed observer is constructed according to the cooperative variable of the master-slave cooperative guidance system. Second, the consistency error and the absolute error based on the state output of the observer are calculated. Third, the self-confidence coefficient of each node of the cooperative guidance system and the trust coefficient of each node to the communication link of the neighbor node are evaluated. Finally, the fault-tolerant cooperative guidance law is given. Thus, the node fault or the communication link fault of the master-slave multi-aircraft cooperative guidance system in the communication interference environment can be effectively positioned and tolerated.

The invention relates to the technical field of airport epidemic prevention facilities, and discloses an airport gallery bridge epidemic prevention conversion isolation protection method and system, and the method comprises the steps: obtaining real-time flight information data, carrying out the comprehensive judgment of risks, and carrying out the mode switching decision judgment; carrying out sealing treatment on the gallery bridge channel and detecting the sealing performance by adopting a pressure attenuation method; the sealed isolation channel is partitioned, and the air supply and exhaust rate ratio of each region is accurately controlled; supplied air and exhausted air are purified by adopting a tandem type multi-stage purification device; the sealed isolation channel is monitored in real time by adopting a multi-sensor fusion monitoring network; system operation parameters are adjusted in real time; a multimedia interaction guiding system is adopted to guide passengers, and passenger behaviors are monitored through a computer vision technology; by integrating an intelligent risk assessment mechanism and an electric telescopic isolation barrier system, rapid switching of the gallery bridge between a usual operation mode and an epidemic isolation mode is realized.

The invention relates to the technical field of spacecraft autonomous orbit determination, in particular to an HEO constellation enhanced earth-moon spacecraft satellite-borne GNSS autonomous orbit determination method and system, and the method comprises the steps: determining the weight of GNSS / HEO data; calculating a single-point positioning and speed measurement result by using GNSS / HEO data and HEO enhancement information, and initializing a state quantity and a covariance of a Kalman filter; forecasting the position and speed of the spacecraft by adopting a simplified kinetic model, and updating a state equation; calculating a GNSS / HEO innovation residual error sequence based on a forecast result, and detecting and marking gross errors according to a clock error consistency rule; sequentially carrying out Kalman measurement updating on the observation data without gross error according to the weight, and finishing the correction of the state quantity and the covariance; finally, the position and speed information of the spacecraft is output to a navigation guidance system, and autonomous orbit determination and time service are achieved. Therefore, the problems of low positioning precision, poor orbit determination and autonomous time maintenance capability and the like due to the fact that the earth-moon spacecraft cannot adapt to earth-moon space dynamic and observation conditions in the related technology are solved.

The invention discloses an aircraft view field limited terminal guidance method with specified flight time, and relates to the field of aircraft guidance system design, and the method comprises the following steps: building a mathematical model of intersection of an aircraft and a stationary target in a two-dimensional plane; obtaining a relative motion differential equation by using the mathematical model, and designing a polynomial of an auxiliary variable based on a field angle as a relative distance profile; combining the mathematical model, the relative motion differential equation and the relative distance profile to obtain an analytical guidance law; and by limiting the field angle in the step S2 to monotonically decrease to 0 along with time, the field angle constraint of the aircraft is realized, and a flight time reachable domain is obtained. The design method is an analytical method based on relative distance profile shaping, does not need to linearize the model, does not depend on remaining time estimation, is suitable for guidance tasks with flight time constraints and limited aircraft view fields, and has the advantages of being easy to design and use, high in applicability and the like.

The present invention relates to a travel management system (100), comprising a unified fare comparison module, a memory, a multi-modal transportation integration module, an user interface, an input receiving module and a route optimization module. The unified fare comparison module receiving one or more information including a number of transportation modes and a fare of the transportation in a region. The memory to hold one or more information. The multi-modal transportation integration module configured to combines data from the number of transport modes, allowing users to compare and select the suitable transportation for the journey. The user interface to receive one or more inputs and compared result to the user. The input receiving module to receive one or more inputs from the user based on the displayed one or more information. The route optimization module analyzes pre-specified journey points to present cost-efficient options for a preselected route.

The present invention belongs to the field of cruise ship accident evacuation guidance and discloses a cruise ship passenger dynamic evacuation guidance system. The system comprises three modules: monitoring and alarming, route planning, and dynamic identification. When a disaster occurs on a cruise ship or an abnormal ship posture triggers an alarm, the monitoring and alarming module collects relevant data and transmits it in real time. The route planning module reconstructs the route network and assigns path weights based on this data, using the Dijkstra algorithm with an improved search strategy to search for the global optimal route. The dynamic identification module maps route data to the directions indicated by the signs. The dynamic identification layout is optimized based on passenger perception during system deployment. During the evacuation process, the monitoring and alarming module monitors the crowd gathering situation on each road section in real time, and the relevant data is fed back to the route planning module for a new round of search. The present invention can plan the optimal route in real time based on the cruise ship accident scenario and dynamically adjust the directions indicated by the evacuation signs, thereby achieving dynamic guidance for crowd evacuation.