786 results about "Elevator" patented technology

The invention provides an elevator ascending overspeed protection device fault prediction method and system based on big data, and relates to the technical field of elevator safety monitoring, and the method comprises the steps: setting a thermocouple array on the surface of a brake to collect temperature data, constructing a temperature distribution diagram, and extracting a hot spot region; calculating a hotspot migration track and stress distribution by using a big data analysis platform; fitting a damage development curve based on the fatigue damage degree; and space-time correlation analysis is carried out through a multi-point monitoring network, the fault source position and the expansion trend are determined, and fault early warning is realized. Potential faults of the elevator ascending overspeed protection device can be predicted in advance, and the operation safety of the elevator is improved.

A predictive maintenance method based on an elevator operation and maintenance time sequence knowledge graph comprises the steps that firstly, the elevator operation and maintenance time sequence knowledge graph is constructed, predictive maintenance of electromechanical equipment parts is achieved based on elevator part maintenance period optimization, a theoretical distribution model based on Weibull distribution is constructed, and parameters of Weibull distribution are fitted through a least square method. Therefore, the model can accurately reflect the failure rule of the elevator parts; calculating an inference result of the elevator operation and maintenance time sequence knowledge graph through a graph convolution model and a Horkes process model, and carrying out recursive relation calculation of component fault rate functions in N maintenance cycles; an elevator component maintenance comprehensive cost simulation model is constructed, and the optimal maintenance cycle of elevator components is calculated through a continuous time Markov chain method; the fault prediction accuracy is improved.

The invention relates to the technical field of data processing, and discloses an elevator anti-falling self-adaptive protection method and system based on dynamic loads. The method comprises the steps that elevator operation data are collected through a sensor and filtered; calculating steel wire rope tension and load distribution deviation; performing window segmentation processing on the data to identify an abnormal state; evaluating risks in a graded manner based on the abnormality judgment result; executing a corresponding control strategy according to the risk level; the control result is compared with the expected effect, and the mechanical safety device is started when the deviation is too large. According to the method, accurate recognition of the abnormal state of the elevator, scientific quantification of the risk level and dynamic adjustment of the control strategy are achieved, so that unnecessary service interruption is reduced while the operation safety of the elevator is guaranteed, and the accuracy and adaptability of anti-falling protection are improved.

The invention relates to the field of aircraft simulation test, particularly discloses a simulation test device for an aircraft rudder transmission mechanism, and solves the problems that an existing winged unmanned aircraft cannot conveniently perform simulation test on a rudder deflection angle and maximum stress and cannot conveniently perform accurate test on flight control performance. The device comprises a base, a mounting table, an adjusting assembly, a second telescopic part, a disc, a driving motor, a frame body, a front sliding rod, a mounting frame, a clamping frame, a sliding frame and a clamping plate, the driving assembly is arranged on the clamping frame, a limiting assembly is arranged in the frame body and used for limiting the mounting frame on the surface of the front sliding rod, and a supporting assembly is further arranged on the base and used for supporting the mounting frame on the surface of the front sliding rod. The supporting assembly is used for horizontally supporting the clamping frame. The device can perform simulation test on the angle adjustment precision of an elevator or a rudder of the winged unmanned aerial vehicle and the maximum stress of a transmission mechanism of the winged unmanned aerial vehicle, so that the flight control performance of the distance can be known conveniently, and the accurate control of the aerial vehicle is realized.

The invention relates to the field of flight control of aircrafts, and provides a control method and system for high-precision tracking of a landing glide line by an unmanned aerial vehicle, and the unmanned aerial vehicle. The control method comprises the steps that S1, a control structure for controlling the height of the elevator is determined, specifically, a double-ring cascade PID control structure is adopted, a pitch angle ring is a PID control structure, and a height ring is a PID control structure; a lag network is introduced between the pitch angle ring and the height ring; s2, an accelerator channel adopts a control structure that the air speed is controlled by an accelerator; s3, a landing height instruction and an air speed instruction are obtained, and the unmanned aerial vehicle is controlled to land along the designed glide line track through a control structure for controlling the height through an elevator and a control structure for controlling the air speed through an accelerator. The control system comprises a control module for controlling the height of the elevator, an accelerator control module and a landing glide control module. The method has the beneficial effects that the accuracy of tracking the landing glide track height by the unmanned aerial vehicle is effectively improved, and the safety of the unmanned aerial vehicle in the landing process is ensured.

A modular unmanned aerial vehicle (UAV) system comprises a body module, a rotor module, and a wing module. The body module includes a flight controller and a power distribution device. The body module is releasably attachable to the rotor module or the wing module, and the body module is releasably attachable to the rotor module. The rotor module includes one or more motors and electronic speed controllers (ESCs), while the wing module includes a wing having a flap, elevator, aileron, or rudder. Various UAV configurations can be formed from the body module, the rotor module, and the wing module. Each configuration includes different advantages for flight time, distance, battery life, and payload capacity. A UAV can be configured to a particular configuration to optimize parcel delivery.

The invention belongs to the technical field of aerodynamic parameter identification, and relates to an intelligent fitting optimization method for aerodynamic parameters of a fixed-wing aircraft based on direct lift force. According to the invention, a BP network is used to carry out fitting of a lift coefficient and an aerodynamic derivative of the lift coefficient to an attack angle on noiseless data. The input of the BP network comprises an attack angle, an elevator, a flap, a speed and a pitch angle speed, and is input into the BP network to obtain a prediction result when no noise influence exists, a loss function value is calculated, a gradient is calculated according to the loss function value, and then network parameters are updated according to a gradient descent algorithm to reduce the loss function value. When the loss function value is small, the difference between the prediction result of the network and the actual result is small, that is, the lift coefficient identification value output by the network is accurate in the BP network. The aerodynamic derivative obtained through calculation can be applied to a controller and has good control quality.

An aircraft control system includes a longitudinal control module, an engine torque control module, and an actuator control system. The longitudinal control module is configured to generate a desired torque value and a desired elevator position value for an aircraft based on a desired airspeed value, a desired altitude value, an actual airspeed value, and an actual altitude value. The engine torque control module is configured to generate a desired power lever position value based on the desired torque value and a measured engine torque value that indicates a measured engine torque in the aircraft. The actuator control system is configured to generate a power lever position command and an elevator position command for the aircraft based on the desired power lever position value and the desired elevator position value.

The invention discloses a vertical take-off and landing aircraft with improved linked wing tilting ducted fan layout, and belongs to the technical field of pneumatic and power systems of vertical take-off and landing aircrafts. The aircraft comprises an improved joined wing structure layout and a tilting ducted fan system integrally designed with the improved joined wing structure layout. The improved joined wing structure layout comprises a front wing, a rear wing, a vertical connecting wing surface, a vertical stabilizer and a fuselage. The front wing is divided into a front wing inner side wing surface and a front wing outer side wing surface by a vertical connecting wing surface, and adopts a sweepback wing belt dihedral structure; two ends of the rear wing are respectively arranged above the front wing through a vertical connecting wing surface, the middle part of the rear wing is arranged above the tail part of the fuselage through a vertical stabilizer, and the rear wing adopts a forward swept wing structure; the tilting ducted fan system comprises a front wing integrated ducted fan flap 7, a rear wing integrated ducted fan lifting control surface 9 and a tail propelling ducted fan 16. The core problems that pitching of a traditional connected wing is out of control, the weight of a tilting structure is large, and the energy efficiency is low are solved.

A seal assembly (100) for an elevator (200) is disclosed. The seal assembly includes a covering structure (102). The covering structure covers a top portion of the elevator. The covering structure (102) comprises a plurality of pairs of U-shaped slots (102A) integrally formed along a peripheral portion of the covering structure (102), the plurality of pairs of U-shaped slots (102A) being arranged in mutually orthogonal orientations. Further, a plurality of U-shaped plates (104) are disposed along the peripheral portion and a plurality of seal moulds (106), each seal mould (106) is positioned in a respective region bounded by the peripheral portion and a lower surface of the covering structure (102), the pair of outer side walls (104A, 104B), and an elevator cabin (220) of the pneumatic vacuum elevator (200), thereby enhancing sealing performance and reducing vibration transmission to the elevator cabin.

The technology disclosed herein relates to a rooftop platform to facilitate a delivery of a parcel by an aerial vehicle. The rooftop platform may comprise an elevator apparatus at least partially accessible via the rooftop platform. The rooftop platform may also comprise a rotatable turntable mounted to the rooftop platform. The rotatable turntable can be rotated to position the parcel on the elevator apparatus. The rotatable turntable may have tracks for receiving track wheels of a parcel containment unit. In some embodiments, the parcel may be positioned on the elevator apparatus at a top surface of a lift cabin of the elevator apparatus. The rooftop platform may also comprise a landing area for the aerial vehicle to deliver or receive the parcel containment unit via the rotatable turntable.

An aircraft sub-assembly manufacturing system is arranged over multiple floors of a manufacturing facility. A production line of workstations is provided at locations at both a first floor and a second floor of the facility, each of the workstations being arranged for providing manufacturing steps for the aircraft sub-assembly. Elevator apparatus is arranged to transport the assembled aircraft sub-assembly between the first floor and the second floor of the facility.

The invention discloses a supporting and positioning device for elevator installation, relates to the field of lifting and landing platforms, and solves the problems that an existing supporting and positioning device for elevator installation is tedious in operation and poor in adaptability during use, the supporting and positioning device comprises a device box, an adjusting plate, a supporting mechanism, an adjusting mechanism and a positioning mechanism, and the supporting mechanism comprises a supporting rod; the positioning mechanism comprises a positioning plate, by adjusting the inclination angle and length of the supporting rod, the supporting rod supports and fixes the positions of elevator shaft corners of different sizes, the positioning mechanism adjusts the position of the positioning plate to achieve positioning of an elevator chassis, the state of the supporting rod is controlled in a linkage mode in the positioning process, and the positioning accuracy is improved. The position of the supporting rod is limited in an auxiliary mode, the device box is aligned to the relatively middle position, the horizontal degree of the adjusting plate can be adjusted while the relative position of the adjusting plate is kept through the adjusting mechanism, large-amplitude shaking of the adjusting plate is avoided, and the follow-up installation operation of the lift car chassis is more stable and efficient.

Provided in the present application are a vertical take-off and landing aircraft and a control method therefor. The vertical take-off and landing aircraft comprises a fuselage and 2N tilt-rotors. Wings are provided on two sides of the fuselage, and an empennage is provided at the tail of the fuselage, an elevator rudder being provided on the empennage. The 2N tilt-rotors are symmetrically mounted on two sides of the fuselage, and some of the 2N tilt-rotors are located on the empennage, where N is a natural number greater than or equal to 2. In a vertical take-off and landing state, the projections of propellers of the 2N tilt-rotors on the horizontal plane are centrally symmetrical about point B, both the point B and the center of gravity G of the vertical take-off and landing aircraft are located in the symmetrical plane of the fuselage, and the point B is located on the side of the point G close to the empennage. During the transition of the vertical take-off and landing aircraft from the vertical take-off and landing state to a cruising state, both the point G and the point B move along the symmetrical plane towards the side close to the nose, and the point B is always located on the side of the point G close to the empennage. Such a layout enables the vertical take-off and landing aircraft to have a better pitch trim capability.

A seal assembly 100 for an elevator 200 is disclosed. The seal assembly includes a covering structure 102. The covering structure covers a top portion of the elevator. The covering structure includes a plurality of grooves 104 and a seal mould 106. The plurality of pairs of grooves is disposed on a peripheral portion of the covering structure 102. Each plurality of pairs of grooves is positioned diametrically opposite each other. The seal mould operatively coupled with the plurality of pairs of grooves. The seal mould is adapted to position on the peripheral portion of the covering structure at a clearance between a wall 108 of each groove of the plurality of pairs of grooves and a sealing material.

The invention discloses an elevator speed anomaly detection and fault early warning method and device, equipment and a medium. The elevator speed anomaly detection and fault early warning method comprises the steps that elevator speed data and various influence data are obtained; calculating the noise degree of the elevator speed data and determining an initial K value; determining a distance set of data points in the elevator speed data by utilizing a KNN algorithm based on the elevator speed data and the various influence data; calculating the distribution degree of each distance set, and determining an improved K value of each data point based on the distribution degree and the initial K value; based on the elevator speed data, the multiple influence data and the improved K value of each data point, the abnormal elevator speed is determined through a KNN algorithm; and elevator fault early warning is conducted based on the abnormal elevator speed, the elevator speed data and the multiple influence data. The problem that when the KNN algorithm is used for elevator speed anomaly detection, if the K value is set improperly, the situation of over-fitting or under-fitting may be caused, and then the accuracy of anomaly detection is affected is solved.

The utility model discloses a lifter, which relates to the technical field of conveying equipment, and comprises a machine base and two lifting devices arranged at intervals along the height direction of the machine base, and the machine base is provided with a mounting rod; each lifting device comprises a first conveying mechanism, a second conveying mechanism and a lifting mechanism, the first conveying mechanism is arranged on the mounting rod in a sliding mode in the height direction of the machine base and can convey components in the first direction, and the first conveying mechanism is provided with a first conveying face; the second conveying mechanism is arranged on the machine base and can convey the components in the second direction, the second conveying mechanism is provided with a second conveying face, the lifting mechanism is arranged below the first conveying mechanism, and the lifting mechanism can drive the first conveying mechanism to slide in the height direction of the machine base and make the first conveying face higher than or lower than the second conveying face. According to the technical scheme, the conveying direction of the component can be changed, and the technical problem that a conveying track cannot change the conveying direction of the component is solved.

The invention discloses a water-air cross-medium unmanned aerial vehicle and a flight method, and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle comprises a sealed cabin body composed of an upper cabin body and a lower cabin body, symmetrical vehicle arms, a tail steering engine, a rudder, a left steering engine, a right steering engine, an elevator, an underwater propeller and various types of sensors (a binocular camera, a sonar, a water quality sensor and the like). Air flight is achieved in a four-rotor mode, and underwater sneaking is driven in a fixed-wing mode. The control method comprises the stages of takeoff, air flight, air-water transition (a water surface hovering automatic switching mode), underwater navigation, water-air transition and landing, and complete-process autonomous cross-medium conversion is achieved by combining layered rate descent and multi-sensor fusion judgment states. The device has the advantages of being compact in structure, reliable in sealing and accurate in cross-domain control, and is suitable for ocean exploration, environment monitoring, underwater reconnaissance and other scenes.

A flying elevator is characterized by comprising (100) a ducted propeller arrangement. And (200) a flying elevator telescopic car body. And (300) supplying power to the transfer platform truck. And (400) an intelligent control system. And (500) final assembly of the structure. The mechanisms and the systems are combined through final assembly. Therefore, a set of economical and practical elevator type intelligent low-altitude aircraft is formed. The technical problem that a conventional low-altitude aircraft cannot be connected for a long time to continuously work and cannot be increased in capacity due to limitation of self-loading power or electric power is solved. The elevator is widely applied to high-rise buildings, high-altitude construction sites, disaster areas and scenic areas and serves as a temporary elevator or a short-distance aircraft. And the emergency operation and rescue work of personnel transfer and material transportation can be continuously carried out by a single machine for a long time. The flying elevator has the beneficial effects that 1, the flying elevator flies with lines, and electric power is continuously provided by using the mains supply or a vehicle-mounted power generation device, so that the flying elevator can continuously run for a long time; 2, off-line flight: driving the flight elevator to run by utilizing a reserve battery in an area which is not suitable for line-carried flight; and emergency operation and rescue work in different environments are facilitated. And 3, a multi-set mechanical structure design, a power supply device and a control system. And flight safety and operation convenience are guaranteed.

The invention discloses a TOF elevator light curtain passenger elevator taking trend detection method which comprises the steps that a TOF flight time sensor is installed on an elevator safety light curtain, the light curtain continuously reads data of the sensor, and whether a moving object exists in front of an elevator door or not is judged; if the moving object exists, the moving speed of the object relative to the elevator safety light curtain is calculated, and then the moving speed and the moving direction of the passenger relative to the elevator door are converted through the included angle between the detection area of the elevator safety light curtain and the center line of the elevator door. The processing of the method is mainly divided into two parts: a light curtain processor triggers the detection of the elevator taking trend of passengers according to the change of a shielding signal, and the motion trend of the passengers is calculated through a TOF (Time of Flight) sensor. According to the method provided by the invention, the elevator taking intention of the passenger can be judged by acquiring the movement change of the object in the sensing range through the TOF sensor, and the elevator taking experience is improved by properly delaying the closing of the elevator door.

The invention relates to a corridor elevator and a safety protection device thereof. The corridor elevator comprises a guide device, a driving system, a roller assembly, a carrier platform and a baffle. The guiding device is fixed on the corridor through the upper end plate and the lower end plate on the guiding device, the guiding device is of a truss structure composed of the upper guide rail, the lower guide rail and the supporting piece, the overall rigidity is improved, the middle position of the guide rail is not fixed to the step through a bolt, damage to the corridor step is reduced, and the field installation efficiency is improved. The speed reducer of the driving system is preferably fixed to the lower end plate, the motor is arranged above the speed reducer, the seat plate of the carrier platform is arranged above the guiding device, the transverse width of the corridor elevator is reduced, and the overall arrangement space is saved. A transmission chain connecting plate of the roller assembly is connected with a transmission chain of the driving system, and a roller of the roller assembly rotates in a guide rail roller groove of the guide device. The platform connecting plate of the carrier platform is fixed to the roller fixing plate of the roller assembly and moves up and down along the guide rail roller groove along with the rolling assembly. The speed reducer is preferably a turbine speed reducer, and when accidental power failure occurs, due to the fact that the turbine speed reducer has a self-locking function, the carrier platform cannot move accidentally. The roller assembly is provided with a shoe block locking assembly, when the accelerated speed of accidental descending of the carrier platform exceeds a limit value, the shoe block locking assembly can prevent the carrier platform from accelerating descending, and personnel or objects are prevented from being damaged. The rolling wheel assembly is provided with an anti-toppling plate, when the rolling wheels fall off accidentally, the anti-toppling plate prevents the rolling wheel assembly and the carrier platform from toppling over, and personnel or objects are prevented from being damaged.

The utility model belongs to the technical field of elevators, and discloses a mechanical linkage door mechanism applied to an intelligent elevator, which comprises a mounting frame arranged at the top of a cage door and a push rod sleeve arranged on a landing door, the mounting frame is provided with a fixing hole, an adjusting frame is arranged on the mounting frame, the mounting frame and the adjusting frame are both U-shaped, and the push rod sleeve is arranged on the landing door. A kidney-shaped hole is formed in the position where the adjusting frame and the mounting frame are fixed, a push rod seat is mounted at the top of the adjusting frame, a push rod is slidably mounted on the push rod seat, a mounting seat is mounted at the tail of the push rod seat, an electric push rod is mounted on the mounting seat, and a connecting column is mounted at the end of the electric push rod. By the adoption of the structural design, the electric push rod is controlled to operate, the end of the push rod can be inserted into the push rod sleeve, when the cage door operates, the landing door can be driven to ascend synchronously, and the purpose of intelligently opening the landing door is achieved.

The utility model belongs to the technical field of hydrofoils, and particularly relates to a ship with a telescopic elevator structure, which comprises a ship body, a bow, a stern, a buoyancy structure, a first arc-shaped strut and a second arc-shaped strut. The buoyant structure includes a first buoyant volume disposed near the bow and a second buoyant volume located between the first buoyant volume and the stern. The present application provides a vessel with a retractable elevator structure, a first buoyancy volume pivotably coupled to a second buoyancy volume along a radial axis to achieve precise directional control, first and second arcuate struts having proximal ends movably connected to the buoyancy structure and distal ends supporting a hydrofoil lift surface, the first arcuate strut and the second arcuate strut expand and contract in an arcuate manner along an external common radial axis, allowing seamless transition between a compact storage configuration and an expanded operating state, improving ship maneuverability, portability and safety.

A control system for rotating an airfoil along one axis that is offset from a perpendicular axis that varies the angle of attack (AOA), dihedral, and center of lift based on the position of the attachment to precisely maneuver an aircraft. This technique can eliminate the need for traditional control surfaces such as ailerons, elevators, and rudders. allowing for an aerodynamically advantaged shape.

The elevator waiting time estimation device of the present invention includes: a queuing start measurement unit that measures the situation where the user of the elevator arrives at a set position, a boarding measurement unit that measures the situation where the user of the elevator enters the car, a storage unit that stores the arrival time measured by the queuing start measurement unit and the boarding time measured by the boarding measurement unit, and a waiting time calculation unit that calculates the waiting time required until the user of the elevator enters the car based on the arrival time and the boarding time stored in the storage unit. Thus, the waiting time at the landing can be calculated with simple processing and structure.

The invention belongs to the technical field of elevator measuring equipment, and particularly relates to an elevator landing door force application gap detection device which comprises a base and a mounting seat fixed above the base. A sliding rail is arranged at the upper end of the mounting seat, a left sliding block and a right sliding block are slidably connected to the sliding rail, a left measuring claw is fixed to the front end of the left sliding block, a right measuring claw is fixed to the front end of the right sliding block, and a left constant-force coil spring and a right constant-force coil spring are hinged to the left side and the right side in the mounting seat respectively. One end of the right constant-force coil spring is fixedly connected with the right measuring claw; the left sliding block and the right sliding block are provided with elevator gap measuring assemblies, a visual identification module is fixed below the left side of the mounting seat, and a central processing module is fixed at the rear end of the base. The left sliding block and the right sliding block are controlled to be in a closed state or a detection state by a driving device; the base is driven by a sliding mechanism to slide back and forth; according to the invention, the force application gap of the elevator landing door can be automatically detected, and the accuracy of a measurement result can be ensured.

Provided are a method and a system for cooperative airborne meteorological perception with multiple aircraft. The method includes: determining a training set based on a spatial position, motion data, weather, an observation image, and static information of each of multiple aircraft; determining a fusion performance function based on an objective of a cooperative perception network; generating a fusion model based on the training set and the fusion performance function; generating a perception result image based on the fusion model; determining flight risk information based on the perception result image; determining a route alarm command and sending the route alarm command to a management user interface and an interactive device of a target aircraft; after receiving the route alarm command, generating, by the management user interface, a route adjustment parameter; in response to obtaining the route adjustment parameter, performing at least one of the following operations: adjusting an engine velocity, adjusting an aileron pressure, adjusting an elevator deflection, and adjusting a rudder deflection.

The invention provides a method, device, equipment and medium for carrying out offset calibration on a scale based on elevator current, and the method comprises the steps: collecting a current signal, a vibration acceleration signal and an environment temperature and humidity signal of an elevator motor and a weight signal of a scale body in real time, and carrying out the preprocessing to form a data set; a prediction model based on multi-modal adversarial learning is constructed, the prediction model comprises a physical constraint flow and a process knowledge flow, and feature extraction irrelevant to working conditions is achieved through a gradient inversion layer; comparing the weight predicted by the prediction model with the weight signal of the scale body in real time, and when the continuous multiple deviations exceed a first preset value and the confidence coefficient is greater than a second preset value, determining that the scale body deviates; the zero point or range parameter of the scale body is automatically calibrated through a progressive parameter adjustment strategy according to the scale body offset type, and a calibration log is recorded, so that the problems that when manual equipment calibration is carried out, operation is tedious, consumed time is long, shutdown operation is needed, and equipment offset cannot be monitored in real time are solved.

An electric vertical take-off and landing aircraft comprises a fuselage and a tilt wing. The tilt wing is tiltable relative to the fuselage in a range of tilt wing angles. Control surfaces are arranged at the tilt wings. The aircraft comprises a horizontal stabilizer with an elevator, in particular a stabilator, a vertical stabilizer with a rudder, in particular a fully movable stabilizer, at least one electric engine for powering main propellers arranged at the tilt wing and at least one software control device. The control device is configured to control at least the control surfaces , the main propellers and the tilt wing angle during hover and transition between hover and cruise flight.

The present invention relates to the technical field of elevator safety gear, specifically a progressive elevator safety gear; it includes side plates, and a top plate and a bottom plate respectively fixed at the upper and lower ends of the side plates; two guiding seats are arranged inside the two side plates; a wedge-shaped clamping block is slidably connected through a guiding groove on one side where the two guiding seats are close to each other; a bracket with a supporting groove is arranged at the rear side of the guiding seat; two supporting pins connecting with the clamping block pass through the two supporting grooves from front to back; a pull rod is arranged at the upper end of the bracket and penetrates upward through the top plate; adjusting ears are arranged at the edges where the two guiding seats are far away from each other and face backward; by adjusting the distance between the two guiding seats, the initial distance between the two clamping blocks is changed, so that the safety gear can meet the installation requirements of guide rails with different widths while maintaining a certain safety gap with the guide rail, improving the application range of the safety gear, and the adjustment method is more convenient and fast.