270 results about "Takeoff" patented technology

The invention discloses a dual-hangar collaborative operation system for high-frequency inspection. The dual-hangar collaborative operation system comprises a remote server and two hangar subsystems which are adjacently deployed in an electric power inspection base station, the remote server communicates with the main control modules of the two hangar subsystems through the Ethernet and is used for issuing operation instructions and receiving motor state data and meteorological data. And the main control modules of the two hangar subsystems are in communication connection and are used for sharing meteorological data and operation state data and executing collaborative scheduling logic to realize parallel processing of take-off preparation and landing storage of the unmanned aerial vehicle. Depending on a double-hangar collaborative scheduling strategy, parallel processing of takeoff preparation and landing storage is achieved in a daily scene, while a first hangar executes takeoff preparation (cabin door opening, platform ascending and pressing rod loosening), a second hangar synchronously completes landing storage (unmanned aerial vehicle centering, pressing rod fixing and cabin door closing), and the unmanned aerial vehicle is taken off. And the total time consumption of single operation is shortened to be within 120s from 200s of a single-machine library.

A seat unit for a passenger of an aircraft, including a seat and a shell, the seat including a sitting portion and a backrest movable on a base, respectively actuated by a motor-driven mechanism, the unit including a means for detecting the presence of the passenger on the seat, the seat being configured to adopt a takeoff / taxiing / landing position when a presence of the passenger is detected, in which the sitting portion is away from the shell and in which the backrest is reclined in the direction of the shell, and a docking position when a presence of the passenger is not detected, in which the sitting portion is close to the shell, and in which the backrest is substantially parallel to the shell, so as to widen the egress between two seat units.

A craft comprises a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

A method of aligning an aircraft with a landing platform in motion comprises measuring a GPS heading with at least one GPS sensor positioned at a known location relative to the landing platform while the landing platform is in motion, measuring an orientation of the aircraft with an orientation sensor fixed relative to the aircraft, calculating an orientation of the landing platform from the GPS heading, calculating an orientation offset between the measured orientation of the aircraft and the calculated orientation of the landing platform, and changing an orientation of the aircraft or the landing platform to reduce the orientation offset. A system for landing and securing an aircraft in an enclosure, a system for disconnecting a tether from an aircraft, and a system for landing an aircraft in an enclosure are also described.

A craft comprises at least one hull, at least one wing configured to generate upwards acro lift as air flows past the at least one wing to facilitate wing-borne flight of the craft, at least one retractable hydrofoil configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the at least one hydrofoil to facilitate hydrofoil-borne movement of the craft through the water, and a control system that comprises data storage having instruction code stored thereon that causes the control system to during a takeoff operation when the craft is accelerating through the water and is supported by the at least one hydrofoil, control the at least one hydrofoil to generate downwards hydrofoil lift that maintains the at least one hydrofoil submerged at a predetermined hydrofoil depth threshold below the water surface; and when the craft reaches a takeoff condition, cause the least one retractable hydrofoil to release the craft from the water to facilitate wing-borne flight of the craft.

The invention relates to the technical field of low-altitude aircraft operation safety, in particular to a low-altitude aircraft-oriented conflict-free flight path planning method before takeoff, which comprises the following steps of: calculating a basic protection interval and an aerodynamic disturbance range of a low-altitude aircraft and determining a three-dimensional dynamic safety boundary; discretizing the airspace into a regular three-dimensional grid array; constructing preset space-time paths before takeoff of the low-altitude aircrafts, mapping the preset space-time paths to the three-dimensional grid array, and identifying all the preset space-time paths before takeoff with space-time overlapping by analyzing the expected space-time occupation section; constructing a space-time path optimization algorithm, and setting priority decision rules of various types of low-altitude aircrafts; generating a space-time path adjustment instruction with the minimum comprehensive adjustment cost; and integrating all space-time path adjustment instructions to generate a conflict-free track before takeoff. According to the method, the conflict in the preset flight path before the low-altitude aircraft takes off is detected and released, and the method can be used for formulating the conflict-free preset flight path and flight path of the low-altitude aircraft before the low-altitude aircraft takes off.

This invention discloses an aircraft flight status identification method and system based on ADS-B, comprising: acquiring ADS-B data of the aircraft in real time and caching the ADS-B data in a high-speed cache database; extracting the latest ADS-B data points of the aircraft from the high-speed cache database at set time intervals, and storing multiple consecutively extracted latest ADS-B data points into a fixed-length queue of a preset length to form a temporal ADS-B data sequence; calculating estimated parameters for status determination by combining the aircraft's flight dynamic data with preset geospatial information; and identifying the current flight stage of the aircraft through a state machine model based on the temporal ADS-B data sequence and the estimated parameters, wherein the current flight stage includes one of taxiing, takeoff, climb, cruise, descent, approach, and landing. The method and system of this application improve the accuracy, continuity, and real-time performance of flight status identification.

A final approach and takeoff (FATO) surface for a VTOL aircraft redirects downwash as outwash and may capture outwash from the VTOL aircraft to generate electricity. The FATO surface system may include a central solid plateau configured to capture downwash from the VTOL aircraft to enhance a ground effect for optimal stabilization during takeoff and landing. A floor grate surrounding the plateau may allow outwash to pass through to a subsurface where the outwash is channeled to exhausts or at least one turbine for generating electricity from the outwash. Redirecting the downwash to outwash reduces undesirable effects such as noise and airspeed associated with the VTOL aircraft. The electricity may be used to recharge the VTOL, electric vehicles parked at a vertiport of the FATO surface system, may be used by a building at the vertiport, or may be delivered to a local power grid.

An operational safety region generation method, comprising: generating an initial safety region on the basis of an operational plot and takeoff / landing position information of an unmanned device (S110); determining an editable boundary line of the initial safety region (10) (S120); receiving an editing operation for the editable boundary line, and adjusting the editable boundary line on the basis of the editing operation (S130); and generating a target safety region on the basis of the adjusted editable boundary line (S140). By means of the method, an editable boundary line can be determined in a preliminarily planned safety region, and a user edits the editable boundary line such that the adjusted safety region does not contain obstacles and retains part of the region in which an unmanned device can fly, thereby ensuring that a safe and efficient flight route is directly planned within the adjusted safety region, and meeting the efficient-operation requirements of the unmanned device.

The utility model relates to the technical field of takeoff and landing protection equipment, and discloses takeoff and landing protection equipment for an unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, and a display connection signal screen is fixedly mounted on the outer wall of the unmanned aerial vehicle body. The foldable light and thin mounting plate is rapidly folded and unfolded through the rotating hinge and the small hydraulic push rod, in the flight state, the mounting plate is folded and tightly attached to the fuselage, air resistance is effectively reduced, the flight efficiency is improved, before landing, the hydraulic push rod rapidly pushes the mounting plate to be unfolded to the horizontal position, and the supporting area is enlarged; the unmanned aerial vehicle is in direct contact with the ground in cooperation with an anti-skid balancing weight, the friction force between the unmanned aerial vehicle and the ground is increased, the unmanned aerial vehicle is effectively prevented from sliding or rollover after landing, meanwhile, an inflation pump is arranged in an inflation box to inflate a buffering air bag, a flexible protection layer surrounding the unmanned aerial vehicle is formed, falling impact is effectively relieved, and the unmanned aerial vehicle is protected from falling. And the effect of improving the protection safety is achieved.

This invention discloses a plug-in independent power supply hybrid power system for aircraft, which can be installed in situ without altering the original aircraft's core structure. The system employs an external independent power battery module, a small-power engine generator, and a small battery module to form a "three-level independent redundant power architecture," with each unit's power supply circuit electrically isolated from the others. The external independent power battery only charges on the ground and discharges unidirectionally during flight, without energy recovery or reverse charging. It only replaces all functions of the flight control system and electronic control system when the engine and small battery fail. The small-power engine does not participate in takeoff and climb, but is dedicated to cruise power supply. The small battery is responsible for powering the flight control system, electronic control system, and engine starter, sharing a high-voltage DC bus with the generator to achieve bus voltage stabilization and short-term power compensation. Ground charging simultaneously performs a full system self-check. When the battery power is insufficient or the test fails, there is no manual bypass, and the electronic control system is forcibly locked, prohibiting engine starting and ensuring absolute flight safety.

The invention provides a fire fighting truck integrated with double unmanned aerial vehicle sequential take-off systems and a control method thereof.The fire fighting truck comprises a chassis truck and a fire fighting carriage, a unit and a control system are installed in a cabin, a first unmanned aerial vehicle UAV1, a second unmanned aerial vehicle UAV2 and two lifting mechanisms are arranged, and sequential take-off of the unmanned aerial vehicles is controlled through logic of the control system; the unmanned aerial vehicle is provided with a spray pipe connected with a water hose, and the water hose is connected with the compressed air foam fire extinguishing system. According to the method, the collision risk among people, aircrafts and vehicles is fundamentally avoided through logic control, an environment pre-judgment mechanism is introduced, and initial condition safety of takeoff is ensured. And meanwhile, double independent lifting systems, high-capacity feeding, special power supply and cooperative flight control are deeply integrated, so that the fire fighting truck is transformed into a mobile operation base station with quick response, continuous combat and cluster control capabilities from a transportation platform, and machine-vehicle deep fusion and efficiency multiplication of the platform and equipment are realized.

An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

The application discloses a kind of vehicle-mounted mechanical arm auxiliary aircraft take-off system, belong to aviation equipment technical field.System includes aircraft, vehicle-mounted mechanical arm device, vehicle-mounted power battery pack and carrying truck;The vehicle-mounted mechanical arm device is fixedly installed on truck frame, and the end of mechanical arm can be separated with the bottom of aircraft It realizes detachable docking, relies on vehicle-mounted power battery pack to provide power drive mechanical arm to stretch and lift up.In the aircraft take-off stage, mechanical arm exerts upward and forward boost force to aircraft, and the maximum energy consumption of vertical take-off is transferred to ground vehicle system in the flat flight stage, which greatly reduces the battery consumption of aircraft itself.The system is suitable for various types of vertical take-off and landing aircraft, especially for logistics distribution unmanned aerial vehicle, manned aircraft and other scenarios, effectively prolongs the aircraft range, improves the effective payload, the overall structure is flexible and convenient to deploy, with high engineering application value.

The invention relates to the technical field of aerospace, in particular to a method for calculating the sea-launch take-off drift distance of a carrier rocket. The method comprises the steps that a launching platform shaking model is established under a launching platform body coordinate system, and a launching platform rolling angle and a launching platform pitching angle are obtained; establishing a carrier rocket vector form dynamical model under a carrier rocket body coordinate system to obtain the attitude angular velocity of the carrier rocket and the displacement of the carrier rocket mass center; obtaining relative displacement of a launch vehicle tail observation point and a launch platform motion reference point under a launch point gravity coordinate system according to the launch platform rolling angle, the launch platform pitching angle, the attitude angular velocity of the launch vehicle and the displacement of the launch vehicle mass center; and according to the relative displacement, obtaining the synthetic drift distance of the carrier rocket tail observation point relative to the launching platform under the body coordinate system of the launching platform. The method can reduce the prediction error of the sea-launch take-off drift distance of the carrier rocket, and meets the sea-launch high safety margin requirement.

The invention provides a method and a device for calculating the speed of lifting a front wheel during takeoff in consideration of dynamic influence, and belongs to the technical field of aircraft pneumatic and operation stability design. The method comprises the following steps: calculating the speed of lifting the front wheel during takeoff according to the influence of a propulsion system on flow characteristics and pressure distribution outside and inside a runner during takeoff and taxiing of an aircraft; determining an external flow power influence quantity and an internal flow power influence quantity; constructing a pneumatic pitching force and torque expression including the external flow power influence quantity and the internal flow power influence quantity; an aircraft taxiing kinetic equation is constructed based on pitching moment force and moment borne by the aircraft during taxiing and taxiing; a compressed attack angle is obtained based on the compression amount of a main undercarriage strut and tires when a front wheel is lifted during takeoff, and the pneumatic pitching moment of the center of gravity of the aircraft is solved based on the compressed attack angle, a taxiing kinetic equation and the stress condition of the front wheel; based on the pneumatic pitching moment under the gravity center of the aircraft, obtaining the total pneumatic moment acting on the pneumatic reference point, and based on the total pneumatic moment, obtaining the front wheel lifting speed.

This disclosure provides system and method for performing an autonomous aircraft visual inspection task using an unmanned aerial vehicle (UAV). The UAV is equipped with a front-facing RGB-D camera, one Velodyne three dimensional Light Detection and Ranging with 64 channels, and one Inertial Measurement Unit. In the method of the present disclosure, the UAV takeoff from any nearby location of the aircraft and face the RGB-D camera towards the aircraft. The UAV find the nearest landmark using a template matching approach and register with the aircraft coordinate system. The UAV navigate using LiDAR and IMU measurements, whereas the inspection process uses measurements from the RGB-D camera. The UAV navigate using a proposed safe navigation around the aircraft by avoiding obstacles. The system identifies the objects of interest using a deep-learning based object detection tool and then performs the inspection. A simple measuring algorithm for simulated objects of interest is implemented.

This application discloses a fatigue design method for high-strength bolts used in aircraft wheels, specifically relating to the field of aircraft components. The method includes: determining the bolt preload and preload torque based on the bolt's nominal diameter, the bolt material's yield strength, and a first preset relationship, combined with the bolt's application environment; determining the minimum and maximum stresses on a single bolt; determining the stress cycle ratio of a single bolt; when the stress cycle ratio reaches a preset value, determining the equivalent stress based on the minimum and maximum stresses on a single bolt; determining the bolt's cycle life based on the equivalent stress, and combining the product of the tire's rolling circumference and the aircraft's takeoff and landing distance to determine the bolt's takeoff and landing life. Based on the above method, the service life of high-strength bolts under fatigue cyclic loading can be improved.

This invention discloses a buffer device and its usage method for horizontal impact testing of unmanned aerial vehicles (UAVs). The buffer device includes an aluminum alloy box structure, a hydraulic telescopic rod, and a combined buffer block. The hydraulic telescopic rod and the combined buffer block are both built into the aluminum alloy box structure. A main control panel is installed on the front of the aluminum alloy box structure, including a touch screen and an emergency stop / reset button. Ventilation and observation slots are provided on the left and right sides of the aluminum alloy box structure. This invention discloses a buffer device and its usage method for horizontal impact testing of UAVs capable of intercepting loading slides carrying UAVs with different takeoff weights and maximum level flight speeds. After impact from the loading slide, the buffer device can promptly activate a locking mechanism to effectively prevent the deformed buffer layer from pushing back against the loading slide.

The application discloses a kind of based on flight flow control restriction information autonomous release sequencing method and system, method includes: flow control restriction information is structured as including time, waypoint and digitalization constraint of traffic capacity and storage;According to the constraint screening affected flight, and it is divided into A class flight with fixed calculation takeoff time and B class flight without fixed time;With A class flight time as reference, under multiple constraints such as meeting calculation wheel block time and flow control capacity, dynamically calculate distribution suggestion takeoff time slot for B class flight;Finally, generate flight autonomous release sequencing sequence and output are integrated.This application method and system realize the change from artificial experience decision to intelligent automatic calculation in release sequencing, while guaranteeing instruction compliance, significantly improve sequencing efficiency, rationality and system response dynamic change robustness.

This application discloses a simulation method and system for a launch vehicle attitude control system. The simulation method specifically includes the following steps: a host computer compiles a simulation model and generates an executable program, which is then downloaded to a simulation computer; the host computer runs the simulation model and selects a simulation mode; an industrial control computer simulates the flight test process, uploads the flight control software to the flight control assembly, and starts the process; the host computer controls the simulation computer to send ignition and takeoff command signals to the flight control assembly; the simulation computer calculates and obtains attitude angle and attitude angular velocity measurement information and sends it to the flight control assembly; the flight control assembly operates after receiving the ignition and takeoff command signals, issuing actuator control commands based on the received measurement information. This application achieves step-by-step, layered verification of the theoretical controller, flight control software algorithm, flight control assembly, and servo mechanism, facilitating problem localization and analysis, and ensuring the safety and reliability of the experimental process.

To more reliably land a flying body at a desired point, a flying body includes a determiner that determines whether the flying body is taking off and ascending from a takeoff point or descending to land, a camera mounted in the flying body, a recorder that records a lower image captured by the camera if it is determined that the flying body is taking off and ascending and a guider that, if it is determined that the flying body is descending to land, guides the flying body to the takeoff point while descending using a lower image recorded in the recorder during takeoff / ascent and a lower image captured during the descent.

This automatic takeoff / landing system for a vertical takeoff / landing aircraft comprises: a relative wind information acquisition unit that acquires the direction of relative wind at a moving object; and a control unit that executes takeoff / landing control to cause the vertical takeoff / landing aircraft to takeoff / land at a landing target point provided on the moving object. The control unit, during takeoff / landing of the vertical takeoff / landing aircraft, executes the takeoff / landing control on the basis of the direction of the relative wind acquired by the relative wind information acquisition unit, in a state in which the aircraft heading of the vertical takeoff / landing aircraft is caused to face the direction of the relative wind.

The invention relates to the technical field of aircraft power control, and discloses an artificial intelligence optimized vertical fixed wing power control method and system, and the method comprises the steps: obtaining the original airspeed data of an airspeed sensor, the ground speed data of a global positioning system and the acceleration data of an inertial measurement unit, and generating the ground speed of an aircraft based on the data fusion. Under the low-wind-speed condition, the ground speed of the aircraft is used as the reference airspeed, the difference between the original airspeed data of the airspeed sensor and the reference airspeed is continuously compared, and the sliding average value of the difference is calculated. When the sliding average value continuously exceeds the preset tolerance range, the method can identify that the airspeed sensor has continuous calibration drift. And then, according to the identified continuous calibration drift, performing real-time compensation on original airspeed data of an airspeed sensor to obtain calibrated airspeed data, and inputting the calibrated airspeed data into flight mode switching judgment logic to trigger an action instruction of a tilting mechanism.

The invention discloses a low-altitude target intelligent identification method and system based on large model fusion, and relates to the field of image identification, and the method comprises a capturing module which is used for shooting preset multi-spectral image data of an airplane takeoff and landing low-altitude flight region, and synchronously capturing the environment illumination, atmospheric visibility and fog concentration parameters of the airplane takeoff and landing low-altitude flight region; the preprocessing module is used for receiving the multispectral image and the environmental parameters shot and captured by the capturing module, and forwarding the multispectral image and the environmental parameters to the extraction module after performing registration fusion and adaptive denoising enhancement processing; the method combines multispectral image accurate registration fusion and adaptive denoising enhancement, effectively improves the image quality in a complex environment, deeply excavates and strengthens target key features and improves the feature discrimination by means of double-attention fusion and multi-scale feature level interaction, and improves the image quality through multi-dimensional feature matching and accurate coordinate solution reasoning. And target category rapid identification and space coordinate accurate locking are realized.

A user's departure from a first airport and landing at a second airport can be detected using tracking device functionality. A user's location (determined using a tracking device) is compared to known airport locations to determine that the user is at a first airport, and an aircraft takeoff event can be identified using tracking device movement information (such as speed and acceleration). In response to the detected aircraft takeoff event, a notification is sent to a set of users associated with the user indicating that the user has taken off from the first airport. A user's second location is compared to known airport locations to determine that the user is subsequently at a second airport. An aircraft landing event can be detected using tracking device movement information, and a second notification is sent to the set of users indicating that the user has landed at the second airport.

The embodiment of the invention relates to the technical field of flight management, and provides a flight plan management method and device for a flight management system, and the method comprises the steps: analyzing a navigation database file of a target protocol, and writing the analyzed navigation data into a target database, the navigation data including airports, waypoints, routes and flight program data; a flight plan creating instruction input by a target user is received through CDU simulation unit software, and the flight plan creating instruction at least comprises a takeoff airport, a target airport and waypoint numbers or route names; based on the flight plan creation instruction, extracting target data from a target database, and generating a flight plan; receiving and responding to an activation instruction input by the target user, and activating the flight plan; and controlling the target flight trainer to execute the activated flight plan based on the activated flight plan. The creation, editing, activation and dynamic over-point calculation of the flight plan can be completely reproduced in the trainer through simulation software, and the cost is reduced.

This invention discloses an airport photovoltaic design method and system based on three-dimensional airspace constraints, which relates to the field of airport photovoltaic engineering technology. S1: Collect legal airspace control data of the target airport, site topography data, flight parameters, and regional annual meteorological and solar radiation data. Based on the collected multi-source data, construct a three-dimensional airspace constraint surface model of the airport, fully integrating four types of core airspace constraint boundaries within the airport: horizontal plane, conical surface, approach surface, and takeoff / climb surface, achieving a three-dimensional quantitative definition of the airspace constraint range. This airport photovoltaic design method and system based on three-dimensional airspace constraints is the first to deeply couple the airport's three-dimensional airspace constraint surface with photovoltaic design, abandoning the traditional two-dimensional uniform height restriction model. It constructs a full-space quantitative model based on the four types of core airspace constraint surfaces, representing a novel technical solution not disclosed in existing technologies, with significant design characteristics specific to airport scenarios.

The present invention makes it possible for various flying devices to land.　A takeoff / landing device (91) for a flying device (3) comprises a first support part (92A) that can support at least a portion of the flying device (3) and a second support part (92B) that can support at least a portion of the flying device (3) and, with the first support part (92A), is to support the flying device (3) to allow the flying device (3) to take off and land. The first support part (92A) and the second support part (92B) are separated in the horizontal direction, and the space between the first support part (92A) and the second support part (92B) is unobstructed in the vertical direction.

This invention provides a control architecture for aerospace permanent magnet synchronous motors based on master-slave redundancy and model prediction, belonging to the field of aerospace electric propulsion control systems. It aims to solve problems in existing systems such as extreme environment parameter drift, single-fault shutdown, multi-objective control conflicts, and fault diagnosis lag. The control architecture includes a master-slave dual-redundant control unit, a wide-temperature-range adaptive model prediction control unit, an electromagnetic interference adaptive suppression unit, and a multi-dimensional fault-tolerant unit. This invention employs a DSP+FPGA heterogeneous redundancy architecture combined with a 3-out-of-2 voting logic to achieve seamless fault switching; it embeds an extended Kalman filter observer to update motor parameters online, preset takeoff / cruise / landing three modes; it suppresses interference in the 100kHz~10MHz frequency band through adaptive notch filtering and sliding mode variable structure control; and it integrates a long short-term memory network to achieve accurate early fault diagnosis, adapting to aerospace scenarios such as electric general aviation aircraft and drones.