1413 results about "Elevator" patented technology

An urban air mobility building-top skyport for landing. loading and unloading. servicing. and parking short field takeoff and landing (STOL) aircraft. which includes a rotatable flight deck having at least one runway on which aircraft takeoff and land: a rotatable lower deck immediately below the flight deck and including an aircraft taxiway surrounding an enclosed central terminal with an elevator bank: and first and second aircraft ramps connecting the flight deck and the lower deck on which to taxi aircraft between the flight deck and the lower deck. A battery-swap station robotically replaces depleted batteries with fully charged batteries without the need for aircraft to cease moving at slow taxi speeds at any point during the process.

The invention relates to the technical field of aircrafts, and discloses an aircraft attitude control method, device and equipment and a storage medium, and the method comprises the steps: collecting flight state parameters of an aircraft; the pitch angle data in the flight state parameters are compared with a preset angle threshold value, corresponding flight mode switching is executed, and the attitude deviation value is calculated; power distribution calculation is conducted on the three ducts, and the target rotating speed of each duct paddle is obtained; performing position optimization calculation on the guide plates below the duct to obtain the position control quantity of each guide plate; the three flow guide plates are configured as triangular control points, the position compensation amount of an aileron, a yaw rudder and an elevator is calculated and determined through vector synthesis, and the angle control amount of each control surface is obtained; according to the method, the attitude of the aircraft is converted into an execution signal, execution feedback data is acquired to correct a control instruction in real time, closed-loop attitude control of the aircraft is realized, the attitude control precision of the aircraft is improved, and the stability of the flight process is ensured.

The invention discloses a fault prediction method and device based on the real-time running state of an elevator and a medium, and relates to the technical field of data processing.The method comprises the steps that historical running data of the elevator are obtained, a fault feature database is established according to historical fault features corresponding to the historical running data, and real-time running data of the elevator are obtained; a real-time running track corresponding to the elevator is determined; determining at least one to-be-selected fault feature corresponding to the real-time operation data based on a fault feature database, and determining a target fault feature with a potential risk from the to-be-selected fault features in combination with the real-time operation trajectory; and the target fault features are input into the trained fault prediction model, and the fault type corresponding to the elevator is output in combination with the predetermined elevator operation features, so that the accuracy and the efficiency of elevator fault prediction are improved, and the downtime and the maintenance cost caused by faults are reduced.

The invention provides an elevator risk early warning method based on a time sequence attention and decomposition module, which comprises the following steps of: acquiring discrete data of an Internet of Things elevator, converting the discrete data into multivariable time sequence features by adopting a feature embedding module in a data coding layer, decomposing the multivariable time sequence features by adopting a feature extraction layer, and determining the risk of the elevator according to the decomposed multivariable time sequence features. The learning difficulty of a self-attention mechanism is reduced; based on the decomposed features, a time sequence multi-head self-attention module is adopted to acquire point-to-point feature similarity through multi-head self-attention calculation, feature self-attention calculation and forward calculation so as to realize long-distance time sequence feature extraction; and on the basis of the feature similarity, the elevator fault probability is predicted through the prediction layer, and specific maintenance requirements can be formulated through the prediction probability, so that the fault risk of the elevator is reduced.

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.

The invention discloses a distributed electric propulsion box type wing ground effect aircraft which comprises a main fuselage, the two sides of the main fuselage are connected with one ends of sweepback wing main wings, one ends of two empennages above the tail of the main fuselage are connected with the main fuselage through vertical tails, and the other ends of the two empennages are connected with the other ends of the two main wings through end plates respectively. The empennage is connected with a plurality of high ducted fans directly driven by a motor, an elevator and an aileron are arranged at the rear part of the empennage, a rudder is arranged at the rear part of the vertical fin, and the elevator, the aileron and the rudder are controlled by a flight control system and are mutually independent. The ground-effect aircraft provided by the invention adopts a box-type wing structure formed by combining the sweepback main wing and the sweepforward empennage, has better aerodynamic performance in a take-off and climbing low-speed flight state, and can provide larger lift force and better maneuvering characteristics.

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 discloses an elevator operation fault detection method and system. The method comprises the steps that an operation data set in the elevator operation process is collected; dividing the operation data set into a plurality of operation data blocks according to data types; if the abnormal operation data exists in the operation data set, detecting a corresponding overall fault mode by using the operation data set; searching an operation data block corresponding to the abnormal operation data, and detecting a corresponding local fault mode by using the operation data block; and the fault position of the elevator is detected according to the overall fault mode and the local fault mode. According to the embodiment of the invention, the fault position of the elevator can be accurately identified, so that the timeliness and accuracy of fault detection are improved, and the safe operation of the elevator is ensured.

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.

An urban air mobility building-top skyport for landing, loading and unloading, servicing, and parking short field takeoff and landing (STOL) aircraft, which includes a rotatable flight deck having at least one runway on which aircraft takeoff and land; a rotatable lower deck immediately below the flight deck and including an aircraft taxiway surrounding an enclosed central terminal with an elevator bank; and first and second aircraft ramps connecting the flight deck and the lower deck on which to taxi aircraft between the flight deck and the lower deck. A battery-swap station robotically replaces depleted batteries with fully charged batteries without the need for aircraft to cease moving at slow taxi speeds at any point during the process.

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.

The invention belongs to the technical field of glide control, and relates to a direct lift active disturbance rejection control method suitable for flying wing layout. According to the method, a trailing edge flap is introduced to serve as a main lift control surface, meanwhile, a constant attack angle is kept through a lifting aileron so as to balance part of pitching moment generated by the trailing edge flap, and therefore the attitude of the aircraft is stabilized, and the constant speed is maintained. In the actual flight process, external disturbance is inevitable, so that an original glide control strategy is improved and optimized in combination with an active disturbance rejection control method. Compared with a traditional glide control method, the flying wing layout direct lift active-disturbance-rejection control method provided by the invention has remarkable anti-interference capability and excellent glide control performance, and shows a wide application prospect.

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 provides an automatic turnover device for a cabin section. The automatic turnover device comprises a turnover elevator, a quick change device and a turnover clamp, the turnover lifting machine comprises a rack, a turnover lifting arm and a rotating platform, and the rack completes Y-direction horizontal movement along a ground guide rail; the overturning lifting arm completes Z-direction lifting motion along the rack, the overturning lifting arm completes X-direction horizontal movement at the fixed height of the rack, and a rotating platform at the working end of the overturning lifting arm completes rotating motion around the X axis; the quick-changing device comprises a main side and a tool side, the main side is mounted on the rotating platform, and the tool side is mounted on the overturning clamp; the overturning clamp is clamped on the cabin section, and the overturning elevator is connected with the cabin section through butt joint of the main side and the tool side of the quick-changing device; y-direction movement of an upper rack of the turnover lifting machine and X-direction movement of a turnover lifting arm implement accurate butt joint of the main side and the tool side of the quick change device, Z-direction movement of the turnover lifting arm implements lifting or placing of a cabin section, and a rotary platform of the turnover lifting machine rotates around the X axis to drive the cabin section to turn over.

A system (100) for detecting a position and controlling a speed of an elevator cabin (102) is disclosed. The system includes a plurality of light detection and ranging sensors (LiDAR) (104) and a shaft controller (110). The plurality of LiDAR is positioned at a ceiling (106) and at a floor (108) of the elevator (300), facing towards the elevating cabin. The plurality of LiDAR is configured to read and transmit, the distance of the elevator cabin from at least one of ground and a topmost position of the elevator and the speed of the elevator cabin by reading the distance travelled per unit of time. The shaft controller detects the position of the elevator cabin by receiving the distance from the plurality of LiDAR. The shaft controller also detects an overspeed condition when the speed of the elevator cabin received from the plurality of LiDAR is above safe threshold speed.

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 belongs to the technical field of aircraft simulation, and particularly relates to an aircraft longitudinal maneuvering load simulation method and device. The method comprises the following steps: S1, carrying out 1g level flight balancing on the aircraft, and determining a balancing attack angle of the aircraft and a balancing elevator skewness of the aircraft; s2, determining the aerodynamic force of the aircraft; s3, dynamic response solving is carried out on aerodynamic force of the aircraft, and the aerodynamic attack angle, normal overload, the flight speed and the pitch angle speed are obtained; s4, acquiring a first elevator skewness calculated by the stability augmentation system according to the pneumatic attack angle and the normal overload, and superposing a second elevator skewness given by the elevator instruction to obtain an actually required elevator skewness; and S5, re-determining the aerodynamic force of the aircraft according to the flight speed, the pitch angle speed, the aerodynamic angle of attack and the actually required elevator skewness until the simulation is finished. The effect of the stability augmentation system in the process of determining the longitudinal maneuvering load of the aircraft is considered, the simulation process is simple, and the precision is high.

The invention belongs to the technical field of aircraft simulation, and relates to a flight simulation method and device under gust load considering a downwash effect. The method comprises the following steps: S1, carrying out 1g level flight balancing on the aircraft, and determining a balancing attack angle of the aircraft and a balancing elevator skewness of the aircraft; s2, superposing the aerodynamic coefficient increment brought by the downwash angle of attack to the aerodynamic coefficient of the aircraft body, and determining the aerodynamic force of the aircraft; s3, dynamic response solving is conducted on aerodynamic force of the aircraft, the flight speed is obtained, the corrected speed of the aircraft is determined after the flight speed is superposed with the wind speed of the vertical gust field, and the aerodynamic attack angle and the flight Mach number are determined according to the corrected speed; and S4, re-determining the aerodynamic force of the aircraft according to the flight Mach number, the pitch angle speed, the aerodynamic angle of attack, the given wind speed of the vertical gust field and the elevator skewness, and circulating the steps until the simulation is finished. The method is simple in simulation process and high in precision, and meets the requirements of engineering practice.

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 invention discloses an elevator accident prediction method and device, a medium and a product, and relates to the field of elevator accident prediction.The method comprises the steps that working parameters of a to-be-detected elevator are obtained; the working parameters comprise an operation parameter, a management parameter and a riding parameter; inputting the working parameters into an elevator accident prediction model to obtain a fault occurrence probability corresponding to the to-be-detected elevator; the elevator accident prediction model is a deep learning network; when the fault occurrence probability exceeds a preset threshold value, the elevator accident type is determined according to the fault occurrence probability; the elevator accident type serves as a target variable, and each working parameter serves as a characteristic variable; respectively calculating standardized mutual information values of the target variable and each characteristic variable, and determining a maximum standardized mutual information value; and determining a to-be-optimized fault combination according to the maximum standardized mutual information value. According to the invention, the elevator accident can be accurately predicted.

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.

The invention belongs to the technical field of aircraft simulation, and particularly relates to an aircraft maneuvering load simulation method and device considering a downwash effect. The method comprises the following steps: S1, carrying out 1g level flight balancing on the aircraft, and determining a balancing attack angle of the aircraft and a balancing elevator skewness of the aircraft; s2, superposing the aerodynamic coefficient increment brought by the downwash angle of attack to the aerodynamic coefficient of the aircraft body, and determining the aerodynamic force of the aircraft; s3, dynamic response solving is carried out on aerodynamic force of the aircraft, and the aerodynamic attack angle, the flight speed and the pitch angle speed are obtained; s4, calculating elevator skewness at the current moment according to elevator instruction input; and S5, re-determining the aerodynamic force of the aircraft according to the flight speed, the pitch angle speed, the aerodynamic angle of attack and the elevator skewness until the simulation is finished. According to the method, the effect of the downwash influence in the aircraft maneuvering load determination process is reasonably considered, the simulation process is simple, the precision is high, and the engineering practice requirement is met.

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 present disclosure provides systems and methods for delivery using unmanned aerial vehicles (UAVs). In an aspect, the present disclosure provides an unmanned aircraft system, comprising: a communications unit; and a UAV comprising: a non-transitory computer-readable medium; a lift system comprising lift mechanisms to propel the UAV; a sensor system to obtain sensor information related to the UAVs environment; a processor to control operation of the lift system and the sensor system; an object detection module to detect potential mobile landing structures within the UAVs environment based on the sensor information; a mobile landing area recognition module to identify a mobile landing area on a mobile landing structure based on the sensor information; and a navigation module to estimate a real-time state of the mobile landing area based on the sensor information or the mobile landing area and to land the UAV onto the mobile landing area.

The invention discloses an elevator air pressure height self-correction method and device, relates to the field of data processing, and can effectively improve the detection precision of the elevator height, and the method comprises the following steps: through a Kalman filter, utilizing an elevator state estimation parameter updated at a k-1 moment to predict an elevator state estimation parameter at a k moment; correcting the elevator state estimation parameter at the moment k through the air pressure detection value at the moment k to obtain the updated elevator state estimation parameter at the moment k; based on the relationship between the air pressure and the height, the height change gradient value of the elevator from the air pressure k-1 moment to the air pressure k moment is calculated through the air pressure estimated value updated at the k-1 moment, the air pressure change rate estimated value updated at the k-1 moment and the air pressure estimated value updated at the k moment; and the air pressure height value of the elevator at the moment k is calculated according to the height change gradient value of the elevator from the moment k-1 to the moment k, so that the height detection precision of the elevator can be effectively improved.

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.

The utility model is applicable to the technical field of elevators, and provides an anti-fall buffer mechanism of an intelligent elevator, comprising an elevator box, wherein the lower surface of the elevator box is fixedly connected with a speed sensor, and the inner wall of the elevator box is fixedly connected with a controller. The utility model detects the running speed of the elevator box through the speed sensor. When the elevator box falls, the speed sensor detects that the running speed of the elevator box exceeds a set value, and the speed sensor sends a signal to the controller. The controller receives the signal of the speed sensor, and the controller controls the operation of an electric hydraulic rod. Through the extension of the telescopic end of the electric hydraulic rod, the support rod is expanded to the surroundings, so that the abutment plate contacts the inner wall of the elevator shaft, thereby increasing the friction between the elevator box and the elevator shaft, slowing down the falling speed of the elevator box, and absorbing and weakening the impact force on the elevator box through the first damper and the first spring, so as to provide buffer protection for passengers in the elevator box when the elevator box falls.