108 results about "Guidance system" patented technology

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 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 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 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 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.

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.

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.

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.

The application discloses a kind of polar coordinate space light field azimuth guiding device and method based on timing, including laser, reflector, radial swing mechanism and circumferential stepping rotation mechanism, laser is erected on the upper portion of circumferential stepping rotation mechanism, light emitting position is fixed relative to radial swing mechanism, by radial swing and circumferential rotation combined drive, make reflector do spatial periodic swing, and laser beam forms circular light field;From the timing angle, it is guaranteed that laser is always scanned from the center to the circumference;Solution module only needs to identify the spot time arriving at detector, and distributes weight according to timing, and synthesizes guide vector, and there is no information interaction with launch carrier;The method greatly reduces the system complexity and device cost of the existing laser pilot guidance system, without complex laser spatial polarization, light intensity, frequency modulation, etc., and the hardware solution circuit is simple and reliable.

This invention discloses an angle-constrained guidance method for aircraft considering the dynamic characteristics of an autopilot, comprising the following steps: establishing the relative motion equations between the aircraft and the target; setting autopilot equations to characterize the autopilot with dynamic delays; setting aircraft angle constraints; establishing a guidance system model based on the relative motion equations and the autopilot equations; and obtaining the guidance law based on the guidance system model. The angle-constrained guidance method for aircraft considering the dynamic characteristics of an autopilot disclosed in this invention can control an aircraft to intercept maneuvering aerial targets in a shorter time, improving the guidance accuracy of the aircraft when attacking maneuvering aerial targets.

Systems and methods for use in automatic alignment of prefabricated building modules. Mating alignment structures on a new module and one more placed modules or mounted pilots interact as the new module is lowered to align edges of the new module relative to the placed components. Different alignment structure types are used to provide different degrees of positional alignment for different edges of a module during installation. When two edges of a module are simultaneously constrained, a horizontal position of one edge is constrained to a greater degree than the second edge. Alignment structures also can be configured so the degree of position constraint on a particular edge varies and to change which module edges are constrained as a module is lowered into position. The system and methods are suitable for use with prefabricated modules having preinstalled interlocking façade panels.

A processing system including at least one processor executing a traffic management application may detect a proximity to a traffic zone for vehicular traffic, the dual-mode vehicle having two modes of operation, the two modes of operation comprising a surface mode of operation and an aerial mode of operation, and may verify a rule set for vehicular operations within the traffic zone. The processing system may then identify a leader traffic management application from among a plurality of traffic management applications of a plurality of dual-mode vehicles within or near the traffic zone, obtain at least one navigation instruction from the leader traffic management application, and perform at least one of: executing a navigation action in accordance with the at least one navigation instruction, or displaying at least a portion of a permitted route that is in conformance with the at least one navigation instruction.

The invention relates to the technical field of traffic control systems, and discloses an anti-collision early warning and safety guiding system for inspection equipment in a tunnel traffic environment, which comprises a coordinate mapping module for converting social vehicle image coordinates into tunnel mileage positions by using a mapping matrix; the parameter self-calibration module corrects mapping matrix parameters on line by using self-positioning data of inspection equipment, and eliminates parameter drift caused by tunnel environment interference; the collision risk calculation module calculates residual collision time; the risk avoiding decision module generates a forced rail switching instruction when the residual collision time is smaller than a safety threshold value; according to the invention, a closed-loop mechanism for reversely calibrating the monitoring end by using the controlled object is established, so that the problem of precision attenuation of a sensing system caused by vibration of a tunnel environment is solved, a downstream operation gap is actively constructed by using upstream speed limit, and safety cooperation of inspection operation and traffic passage is realized.

The head-up guidance system for aircraft takeoff of the present invention includes: a display panel for mode selection and notification, a sensor group, a flight management system, a takeoff guidance calculation module, a symbol image generation module, and a head-up display device. The head-up guidance system and mode switching logic for aircraft takeoff are suitable for various large transport aircraft and have versatility.

The invention discloses a Mars entering section trajectory tracking self-adaptive guidance method and a Mars entering section trajectory tracking self-adaptive guidance system. The method comprises the steps that a current state vector entering an aircraft and a pre-stored reference trajectory are obtained, and the current state vector at least comprises the position, the speed, the flight path angle and the course angle; calculating a longitudinal height error state variable based on the current state vector and the reference trajectory, the longitudinal height error state variable comprising a height error and a height error change rate; and based on the height error state variable, constructing a terminal sliding mode surface, and based on the terminal sliding mode surface and the current state vector, generating a first guidance instruction for controlling the cosine of the heeling angle of the entering aircraft, so that the state of the entering aircraft converges to the reference trajectory within finite time. The method solves the technical problem that the Mars probe is inaccurate in guidance under the uncertain conditions of atmospheric density, lift-drag ratio and the like.

This invention relates to the field of antenna technology, specifically to a compact dual-band monopulse feeding system and method, comprising a Ku-band monopulse feeding system and a Ka-band monopulse feeding system. The two monopulse systems are spatially layered. The Ku-band monopulse feeding system includes a waveguide slot array antenna and a waveguide sum-difference network. The Ka-band monopulse feeding system includes a microstrip patch array antenna and a microstrip sum-difference network. The sum-difference networks of the two monopulse feeding systems are connected to the array antenna to radiate the monopulse signal in the form of sum beams, elevation difference beams, and azimuth difference beams for target detection and tracking. The monopulse feeding system adopted in this invention, through its compact and miniaturized structural design, can be applied to the feeding and transmission of dual-band monopulse signals in multi-frequency composite precision guidance systems on missile platforms.

A boom guidance system for use during an automated air-to-air refueling (A3R) mission. The boom guidance system includes sensors configured to output sensor data indicative of a three-dimensional (3D) position of a fuel-receiving aircraft (receiver) and a refueling boom of a fuel-supplying aircraft (tanker) in a tanker reference frame and a boom reference frame, respectively. An electronic control unit (“ECU”) is in communication with the sensors. The ECU is programmed to receive the sensor data and determine coordinates for a receptacle on the receiver in a tanker reference frame. The ECU is also programmed to transform the coordinates for the receptacle in the tanker reference frame into boom parameters, determine a receiver status for the receiver based on the boom parameters, and initiate an automatic breakaway of the refueling boom from the receiver when the receiver status satisfies a corresponding automatic breakaway condition.