167 results about "Guidance system" patented technology

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.

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.

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.

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 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 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.

In this invention, a travel route acquisition unit acquires a travel route for an electric vehicle. A weather information acquisition unit acquires information about the weather on the travel route. A route guidance information generation unit generates route guidance information on the basis of the acquired travel route and weather information. If there is a low-temperature area on the travel route, the travel route acquisition unit additionally acquires a separate travel route, and the route guidance information generation unit generates route guidance information recommending the travel route with the smaller low-temperature area.

This invention discloses an angle-constrained guidance and control method for an aircraft, comprising the following steps: establishing a guidance system based on the relative motion equations between the aircraft and the target; setting up a timing disturbance observer for sub-estimation and feedforward compensation of the target's flight state; obtaining a timing sliding mode guidance law based on the timing disturbance observer and the guidance system; and controlling the aircraft's flight attitude through the timing guidance law. The angle-constrained guidance and control method disclosed in this invention can estimate and compensate for the target even without prior information, accurately acquiring target maneuvers and improving target strike accuracy.

The utility model provides a fuze device with a miniaturized proximity detector and a projectile body, and the fuze device comprises an air cap with a hollow structure, a detachably connected base, and a proximity detector which is located in the hollow structure of the air cap and is fixedly connected to the upper part of the base, according to the proximity detector, the encapsulation shell used for fixedly placing the circuit board device is arranged, the circuit board device is fixed by pouring the encapsulation glue, and the maximum radial diameter of the encapsulation shell is matched with the radial inner diameter of the upper end part of the hollow structure of the hood, so that the miniaturization of the proximity detector is realized, and the reliability of the proximity detector is improved. The geomagnetic satellite navigation system is adaptively installed at the front position of the front end of a projectile body, more layout space is provided for high-performance design of a guide cabin where a detector is located and a rear cabin section, the power of the detector and the geomagnetic satellite navigation system is increased, and the detection distance, the anti-interference capability, the positioning precision and the signal strength are all greatly improved.

This disclosure relates to improved techniques for upgrading legacy flight management systems (FMSs) installed in an aircraft. In certain embodiments, an integrated guidance system (IGS) can be installed in an aircraft having a legacy FMS to provide enhance flight functionalities, such as required navigation performance (RNP), localizer performance with vertical guidance (LPV), and automatic dependent surveillance-broadcast (ADS-B), capabilities. Additionally, the IGS described can include, inter alia, a navigator system that receives and processes information from an ADS-B system to implement a variety of automated following options, each of which can provide an automated mechanism for controlling a flight path of the aircraft relative to another aircraft that is being tracked by an ADS-B system.

A boom control system includes sensors that output sensor data indicative of a three-dimensional (3D) position of a receiver aircraft and a refueling boom in respective reference frames. An electronic control unit (ECU) reads a 3D model of the receiver from memory. The sensor data includes a 3D position of the receiver and boom in respective reference frames. The ECU maps points in the receiver reference frame to the boom reference frame as mapped points using the 3D model of the receiver and a linear model of the boom. The ECU computes Euclidian distances between each of the mapped points and each respective point on the boom, determines a minimum Euclidian distance, and executes a flight control operation of the boom in response to the minimum Euclidian radial distance being less than a threshold minimum distance.

This disclosure relates to improved techniques for upgrading legacy flight management systems (FMSs) installed in an aircraft. In certain embodiments, an integrated guidance system (IGS) can be installed in an aircraft having a legacy FMS to provide enhance flight functionalities, such as required navigation performance (RNP), localizer performance with vertical guidance (LPV), and automatic dependent surveillance-broadcast (ADS-B), capabilities. Additionally, the IGS described can include, inter alia, a navigator system that receives and processes information from an ADS-B system to implement a variety of automated following options, each of which can provide an automated mechanism for controlling a flight path of the aircraft relative to another aircraft that is being tracked by an ADS-B system.

The invention discloses an all-weather landing guidance system and method for an unmanned aerial vehicle based on dynamic encrypted light streaks, and relates to the technical field of unmanned aerial vehicles, and the system comprises a ground light streak projection device which is used for generating and projecting encrypted and coded dynamic light streaks; the unmanned aerial vehicle end processing module is used for capturing the dynamic light streaks projected on the ground through an airborne visual sensor, performing image processing, decryption verification and relative pose calculation on the dynamic light streaks, and finally sending pose data to a flight control system of the unmanned aerial vehicle end to execute a landing instruction; and the control instruction issuing equipment comprises a cloud service platform and a mobile terminal Bluetooth direct connection unit and is used for issuing a user instruction. According to the invention, through combination of dynamic encryption light streak and verification positioning, the defects of the existing unmanned aerial vehicle landing technology in the aspects of safety and environmental adaptability are effectively solved, accurate and safe landing in a complex environment is realized, a dynamic encryption and verification mechanism is adopted, instruction counterfeiting and replay attack are effectively prevented, and it is ensured that only an authorized unmanned aerial vehicle can land.

The invention provides an elevator guide system full life cycle performance evaluation method. The method comprises the steps that S1, a single guide rail with an initial deflection limit value and a fitting three-dimensional model are prepared; s2, designing a guiding system structure according to the elevator design parameters; s3, constructing a three-dimensional model of an actual lifting height guiding system assembly according to the installation error limit; s4, importing a finite element analysis model and carrying out grid division; s5, setting bolt pre-tightening, gravity, safety tongs action load and building contraction load; s6, carrying out multi-step load finite element analysis calculation and obtaining a convergence result; s7, judging whether the guide rail strength and the deformation limit value are met or not and whether other parts meet the strength requirement or not; if yes, determining that the guide system design is qualified; if not, returning to the step S2, and repeating the steps S2 to S7 until the design of the guidance system is judged to be qualified; according to the invention, the strength performance and the comfort performance are comprehensively evaluated; and comprehensive evaluation of the guiding system is realized.

Systems and methods are provided for closed-loop, non-contact respiratory guidance that provide quantified alignment feedback data in real time. In one embodiment, the computer-implemented method may include receiving, by a computing system operably coupled to one or more processors, input data including respiratory data indicative of an entity's respiration. The computer-implemented method may include converting, by the computing system, the respiratory data to an entity respiratory signal such that the entity respiratory signal tracks the entity's respiration in real time. The computer-implemented method may include comparing, by the computing system, the entity respiratory signal to a suggested respiratory signal indicative of a suggested respiration. The computer-implemented method may include providing, by the computing system, alignment feedback data to the entity in real time based at least in part on the entity's respiration. The alignment feedback data may be indicative of an alignment between the entity respiratory signal and the suggested respiratory signal.

The application provides a kind of push-pull synchronization mode under the shield propulsion system propulsion force redistribution calculation method, comprising the following steps: S1: according to the shield guidance system obtains historical shield pose information;S2: determine the shield pose change matrix;S3: determine the shield propulsion system structure parameters and segment structure parameters;S4: obtain all the cylinder thrust under push-pull alternation mode;S5: establish the force transmission equation of shield propulsion system;S6: establish the partition thrust redistribution equation under push-pull synchronization mode;S7: according to the thrust redistribution optimization principle, the partition thrust is optimized and solved, so as to obtain the redistribution thrust of the remaining cylinder when some cylinder group is missing. Realize the shield push-pull synchronization mode under the shield propulsion force redistribution, which can consider the shield tunneling pose, the shield propulsion system different partition mode and different missing cylinder group, ensure the equivalent driving force unchanged before and after thrust redistribution, and ensure that the shield machine can continue to advance along the established trajectory under push-pull synchronization mode.

Providing technology that increases the possibility of rapidly performing the process of identifying reachable areas by tracing paths in any direction. [Solution] The reachable range guidance system comprises: a map information acquisition unit that acquires map information representing a road network expressed by links and nodes which are the endpoints of the links; a division unit that divides a predetermined area in which a plurality of the nodes exist into a plurality of cells which are areas with continuous links as boundary lines; a reachable node acquisition unit that acquires as reachable nodes the nodes that can be reached by following the links on the boundary lines from the current position using the remaining energy of the vehicle, and the nodes within the cells that can be reached by following the links on the boundary lines; and a guidance control unit that causes a guidance unit to guide the reachable range indicated by the reachable nodes.

The invention discloses a route guidance system based on a digital twin technology. The route guidance system comprises a data acquisition module; a model management module; a path planning module; the route indicating module is used for controlling a dynamic indicator to rotate to indicate the direction according to the evacuation route planned by the route planning module; the dynamic indicator comprises an outer ring body and an indicating arrow shell, the driver is used for receiving a control instruction of the route indicating module and controlling the rotating shaft to rotate, a first green lamp panel is arranged on the opposite side of the indicating arrow shell, and a red lamp panel is arranged on the arrow side end face of the indicating arrow shell. A second green lamp panel is arranged on the end face of the other side of the indicating arrow shell. A red annular lamp body is arranged on the surface of an outer ring body on the arrow side of the indicating arrow shell, and a green annular lamp body is arranged on the surface of the other side of the outer ring body. Compared with the prior art, the problem that an emergency evacuation scheme of a public building simulation system lacks a reliable guidance system combined with the emergency evacuation scheme is solved.

A boom control system includes sensors that output sensor data indicative of a three-dimensional (3D) position of a receiver aircraft and a refueling boom in respective reference frames. An electronic control unit (ECU) reads a 3D model of the receiver from memory. The sensor data includes a 3D position of the receiver and boom in respective reference frames. The ECU maps points in the receiver reference frame to the boom reference frame as mapped points using the 3D model of the receiver and a linear model of the boom. The ECU computes Euclidian distances between each of the mapped points and each respective point on the boom, determines a minimum Euclidian distance, and executes a flight control operation of the boom in response to the minimum Euclidian radial distance being less than a threshold minimum distance.

The application discloses a positioning and guiding system and a flying vehicle, and relates to the technical field of transportation. The flying vehicle comprises a land vehicle and an aircraft. The aircraft is moved into the land vehicle under the action of driving force along a first path. The positioning and guiding system comprises a guiding channel and a guiding element. The guiding channel is arranged on the land vehicle and extends along the first path. The guiding element is limitedly matched in the guiding channel along with the movement of the aircraft. The guiding channel forms at least two guiding sections with a limiting distance on a second path on the first path. The second path is perpendicular to the first path. The limiting distance of the at least two guiding sections decreases in turn along the first path, so as to drive the guiding element to gradually approach a preset position on the second path. The scheme controls the position deviation of the aircraft and the land vehicle in a lower order of magnitude range in the process of combination of the aircraft and the land vehicle in a step-by-step guiding and hierarchical positioning manner, and realizes the accurate positioning of the aircraft and the land vehicle.

1. Name of the product in this design: Aircraft parking guidance system. 2. Purpose of this design: To provide guidance for the aircraft parking process. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.