82 results about "Flight system" patented technology

The invention discloses an intelligent liquid supplementing and sampling system and method of a microorganism sampler and an unmanned flight system. A control module controls a sampling liquid pump to inject sampling liquid in a sampling liquid bottle into a wet-wall cyclone type sampler by a preset liquid injection amount and suspends the sampling liquid pump; the control module controls the fan to inject air into the wet-wall cyclone sampler for sampling, and adjusts the rotating speed of the fan in real time according to the flow detected by the sampling flow sensor, so that the sampling flow is maintained in a preset flow range; in the sampling process, the temperature sensor is used for detecting the temperature of the current air environment in real time per second, the humidity sensor is used for synchronously detecting the humidity of the current air environment in real time per second, and the control module is used for substituting the current temperature and the current humidity into a one-second sampling liquid evaporation capacity fitting function. And calculating the evaporation capacity of the sampling liquid in one second in the current temperature and humidity environment, controlling the working liquid supplementing time of the sampling liquid pump, and injecting the sampling liquid into the wet-wall cyclone type sampler to realize intelligent real-time liquid supplementing.

The invention belongs to the technical field of flight systems, and particularly relates to a six-rotor unmanned aerial vehicle accurate flight system with positioning and navigation functions, which comprises a multi-source positioning sensing module, a dynamic weight fusion module and a self-adaptive trajectory control module, the multi-source positioning sensing module is integrated with a double-antenna RTK-GNSS unit, a triple-redundancy IMU unit, a laser radar SLAM unit, a visual anchor point identification unit and a pipeline electromagnetic detection unit and can collect air-ground-underground multi-dimensional positioning signals at the same time, and each unit is provided with a signal preprocessing sub-module which can perform noise reduction and abnormal value elimination on original signals; the dynamic weight fusion module is internally provided with a signal confidence evaluation model and a scene pre-judgment sub-module, and the signal confidence evaluation model can calculate the confidence value of each positioning unit in real time. According to the system, through multi-module cooperative linkage, the full-scene positioning precision is greatly improved, and the positioning limitation of a traditional unmanned aerial vehicle is effectively solved.

The invention discloses a laser etching dust extraction flight following system and a control method, and relates to the technical field of thin film solar cell manufacturing. The following system comprises a focusing dust extraction module, a following driving module, a cooperative control unit and a negative pressure dynamic adjusting module. The cooperative control unit comprises a following PLC controller and a motion control card, the following PLC controller synchronously obtains path planning information from a galvanometer flight system of a laser beam and generates a displacement instruction, and the displacement instruction is sent to a following driving module through the motion control card; and the following driving module and a galvanometer scanning module of the galvanometer flight system are synchronously triggered, and the following driving module moves according to the displacement instruction and controls the center of the dust extraction cover body and the etching point of the laser beam to coaxially move in a following manner. The method is low in dust removal efficiency and series resistance, good in parameter stability, low in equipment maintenance cost and suitable for processing large-size thin film batteries such as perovskite and cadmium telluride.

A mode sequencer circuitry for a time-of-flight system, the time-of-flight system including at least an imaging unit and an illumination unit, the imaging unit having a data bus interface for transmitting data to an application processor over a data bus.

The invention relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle and a flight system.The unmanned aerial vehicle comprises a shell, propellers, a heating part, a heat dissipation part and a vehicle arm assembly; one end of the arm assembly is connected to the shell, and the other end of the arm assembly is provided with a propeller; a containing cavity is formed in the machine shell, the heat dissipation piece and the heating piece are arranged in the containing cavity, and the heat dissipation piece is close to or makes contact with the heating piece. An air inlet channel is formed in one end of the machine arm assembly, and an air inlet end opening of the air inlet channel is located below the propeller and located in a rotating area of the propeller; an air outlet end opening of the air inlet channel communicates with the containing cavity, and an air outlet is formed in the containing cavity. According to the unmanned aerial vehicle, the air inlet channel is formed in one end of the vehicle arm assembly, the air inlet port of the air inlet channel is located below the propeller and located in the rotation area of the propeller, the rotation area of the propeller can not be overlapped with the shell, waste of the lift force of the propeller is avoided, and the flight efficiency and the endurance time of the unmanned aerial vehicle can be improved.

This application relates to an air control system, an aircraft air control method, an aircraft, and a flight system. The air control system includes an oxygen supply module, an air exchange module, a pressure regulation module, a detection module, and a control module. The oxygen supply module includes an oxygen reservoir, an oxygen electronically controlled valve, and an oxygen pipe. The air exchange module includes an airflow control component for regulating the airflow introduced from outside the cockpit to the indoor air outlet. The pressure regulation module is used to regulate the cabin pressure. The detection module includes an oxygen concentration detector and a cabin pressure detector. The control module is configured to control at least one of the oxygen electronically controlled valve, the pressure regulation module, and the airflow control component based on the oxygen concentration and cabin pressure. The air control system of this application can reduce the complexity of the system and, at the same time, can adaptively adjust in various scenarios, improving the accuracy and comfort of oxygen supply.

The application discloses a microbial sampler intelligent liquid supplementing sampling system and method and an unmanned flight system, a control module controls a sampling liquid pump to inject sampling liquid in a sampling liquid bottle into a wet-wall cyclone sampler by a preset liquid injection amount and pauses the sampling liquid pump; the control module controls an air blower to inject air into the wet-wall cyclone sampler for sampling, and adjusts the rotating speed of the air blower in real time according to the flow detected by a sampling flow sensor, so that the sampling flow is maintained within a preset flow range; during the sampling process, a temperature sensor is used for detecting the temperature of the current air environment in real time every second, a humidity sensor is used for synchronously detecting the humidity of the current air environment in real time every second, and the control module is used for substituting the current temperature and the current humidity into a one-second sampling liquid evaporation amount fitting function, calculating the one-second sampling liquid evaporation amount under the current temperature and humidity environment, and controlling the sampling liquid pump to work for a liquid supplementing time, so that the sampling liquid is injected into the wet-wall cyclone sampler to realize intelligent real-time liquid supplementing.

The invention relates to a wearable flight system, that is, an apparatus for enabling an individual to fly. A wearable flight system (10) for a user comprises a right hand propulsion unit (14), a left hand propulsion unit (16), and a body support structure (18) for being worn on the user's body. The wearable flight system (10) further comprises a right support arm (20) extending from the body support structure (18) to the right hand propulsion unit (14) and connected to the body support structure (18) by a right rotational joint (101) comprising a resilient member; and a left support arm (22) extending from the body support structure (18) to the left hand propulsion unit (16) and connected to the body support structure (18) by a left rotational joint (103) comprising a resilient member.

The utility model discloses an unmanned plane landing anti -thrust device belongs to unmanned plane technical field, the device is in the abdomen of large fixed wing unmanned plane, including anti -thrust board and two groups of drive adjusting mechanism, the anti -thrust board is paddle formula arc structure, and the bottom surface is equipped with longitudinal fairing and is made with carbon fiber composite material, and the angle on the board is equipped with pressure sensor, drive adjusting mechanism contains support, connection hanging cylinder, drive assembly, axle seat, connecting seat and connecting rod assembly, can drive anti -thrust board and realize 0 degree 90 degree angle adjustment, and sensor feedback signal reaches controller, and controller receives unmanned plane flight system landing information and controls motor, forms closed loop control. The device utilizes the airflow to generate the reverse thrust and shortens the brake distance, and the anti -thrust board is horizontal when not working and does not influence the flight, and is light in weight, and the adjustment is accurate, and is convenient to maintain, is applicable to the safe landing of large fixed wing unmanned plane.

The present invention provides an unmanned aerial vehicle (100) comprising: a flight system (4) for producing thrust to manoeuvre the unmanned aerial vehicle (100). The flight system (4) comprises: one or more flight rotors (42) defining a plane passing through each flight rotor and a thrust direction generally perpendicular to the plane; and one or more electric motor (44) for driving the one or more flight rotors (42). The unmanned aerial vehicle (100) further comprises: a cargo area for coupling to or receiving a load (200); and a load system (6) for providing thrust additional to the thrust provided by the flight system (4) to thereby lift a load attached to the connection point. The load system (6) comprises: a first gas turbine propulsion system; and a controller configured to control the flight system (4) and load system (6).

An uncrewed aerial system (UAS) is configured to measure one or more atmospheric conditions in a stationary position or during vertical movement through the Earth's lower atmosphere. The UAS has a fuselage with a longitudinal fuselage axis that intersects a vertical reference axis in a non-orthogonal relationship, a plurality of arms, a plurality of motorized rotors supported by a corresponding one of the plurality of arms, and an air sampling module. The air sampling module includes an air scoop with an intake having an intake opening and a longitudinal intake axis that extends through the intake, and a sensor chamber connected to the intake on a first end and having a discharge on a second end. The sensor chamber has a longitudinal sensor chamber axis that extends from the first end to the second end. The longitudinal sensor chamber axis is angularly offset from the longitudinal intake axis by a scoop intake angle. The air sampling module further includes one or more sensors located in the sensor chamber and a fan located in the sensor chamber proximate the discharge.

1.The name of the design product: the unmanned aerial vehicle automatic flight system graphical user interface of electronic equipment. 2.The use of the design product: the design product is an electronic device. 3.The design points of the design product: the interface content of the graphical user interface in the screen. 4.The picture or photo that best indicates the design points: the front view. 5.The design contains colors. 6.The electronic equipment is of conventional design, and the rear view, left view, right view, top view and bottom view are omitted. 7.The use of the graphical user interface: the design product is used to display various data of the unmanned aerial vehicle automatic flight system. 8.The human-computer interaction mode of the graphical user interface: in the front view, after clicking the “aircraft control” button, the interface change state diagram is displayed; the gray block coverage area in the front view and the interface change state diagram is a variable part, and XX in the interface is replaceable text.

The invention relates to the field of unmanned aerial vehicle anomaly diagnosis, in particular to an unmanned aerial vehicle anomaly diagnosis method and system based on multi-modal data fusion. The method comprises the following steps: acquiring multi-modal sensor data of an unmanned aerial vehicle, analyzing dust characteristics in a current environment in real time according to the multi-modal sensor data of the unmanned aerial vehicle, and generating a basic dust risk parameter set; flight state parameters of the unmanned aerial vehicle are obtained, the flight state parameters of the unmanned aerial vehicle serve as dynamic correction factors and are dynamically fused with the basic dust risk parameter set, and a dynamic dust risk influence parameter set is generated; based on this, analyzing the influence degree of dynamic dust on the flight safety of the unmanned aerial vehicle, and generating a comprehensive dynamic risk level of the unmanned aerial vehicle; on the basis, the current dust risk composition condition is diagnosed, and an unmanned aerial vehicle abnormity diagnosis report is generated. In the unmanned aerial vehicle abnormity diagnosis process, the flight system can be effectively supported to carry out prospective self-adaptive decision making, and serious potential safety hazards are avoided.

An apparatus and method for mounting a payload to a flight system. The apparatus includes a first arm, a second arm, a first member, a second member, and at least four attachment interfaces, attached to at least the payload and the flight system.

The utility model relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle and a flight system, and the unmanned aerial vehicle comprises a vehicle body, a first camera module, a second camera module and a third camera module. The vehicle body is provided with a first part and a second part in the first direction, the first direction is the flight advancing direction of the unmanned aerial vehicle, and the first part is located in front of the second part; the first camera module is arranged on the first part of the machine body and located on the first side. The second camera module is arranged on the first part of the machine body and located on the second side, the first side and the second side are oppositely arranged in the second direction, and the second direction is perpendicular to the first direction; the third camera module is arranged on the first part of the machine body and located between the first side and the second side, and the first camera module, the second camera module and the third camera module are distributed in a triangular mode. Through the above structure, the unmanned aerial vehicle can reduce stereo matching ambiguity, improve depth measurement precision, solve the disadvantage of failure of a binocular method in a specific scene, and realize omnibearing multi-view perception coverage.

The invention discloses a household intelligent, light, safe and folding type small manned aircraft which comprises a ground walking system, a rotor wing flight system, a cabin, a fixed wing flight system and the like, and the ground walking system comprises tire supporting legs, stress spring sensors and driving motors; the rotor wing flight system comprises a foldable machine arm, a motor, a rotor wing and an anti-collision radar; the fixed wing flight system comprises a foldable fixed wing, a motor and a rotor wing. The aircraft top adopts the inflatable low-cost parachute, the aircraft bottom adopts the anti-falling safety airbag, the wings are provided with the anti-collision radars, and the micro laser ranging radar is arranged in front, so that the aircraft is safe and reliable to use. The structural part is made of the carbon fiber material, so that the weight is light. The foldable electric vehicle has the advantages of being reasonable in structure, high in practicability, small in size, light in weight, foldable, high in controllability, low in cost, safe, reliable and high in intelligent degree.

The utility model relates to the technical field of communication equipment, and discloses communication control equipment and a flight system, and the communication control equipment comprises a housing, a circuit board, an antenna and a reflection part. The shell is provided with a containing cavity and comprises a first side wall defining the local boundary of the containing cavity. The circuit board is arranged in the accommodating cavity; the antenna is arranged in the accommodating cavity and is electrically connected with the circuit board; the reflection part is arranged in the containing cavity, located on the side, away from the first side wall, of the antenna and configured to reflect signals of the antenna to the first side wall. According to the embodiment of the invention, the reflection part is additionally arranged in the shell, and the reflection part is arranged on the side, away from the first side wall, of the antenna, so that the reflection part can reflect the signal sent by the antenna to the first side wall, and the intensity of the signal directionally sent along the first side wall is enhanced; and the communication stability between the communication control equipment and the unmanned aerial vehicle is improved.

An image processing circuitry for a time-of-flight system configured to: generate, based on obtained image data of a plurality of pixels representing a time-of-flight measurement of light reflected from a scene that is illuminated with spotted light, corresponding component data including component values of the plurality of pixels; calculate, based on the generated component data, corresponding phase amplitude image data including phase amplitude values of the plurality of pixels; determine, based on the calculated phase amplitude image data, spot pixel regions and a valley pixel region among the plurality of pixels; and calculate a depth value for each of the spot pixel regions in the first set of spot pixel regions.

This invention discloses a control method, device, aircraft, flight system, and storage medium for a lens module. The control method is applied to an aircraft equipped with a gimbal for mounting the lens module. The control method includes: acquiring the model data of the lens module when it is compatible with the aircraft; determining the lens model of the lens module based on the model data; and identifying the corresponding lens module based on the lens model to control the lens module. The control method provided by this invention acquires the model data of the lens module, thereby identifying the corresponding lens module compatible with the aircraft. This allows the control program for the corresponding lens module to be invoked to control the lens module, enabling the aircraft to automatically identify and drive the replaced lens module during disassembly and replacement.

The present invention provides an unmanned aerial vehicle (100) comprising: a flight system (4) for producing thrust to manoeuvre the unmanned aerial vehicle (100). The flight system (4) comprises: one or more flight rotors (42) defining a plane passing through each flight rotor and a thrust direction generally perpendicular to the plane; and one or more electric motor (44) for driving the one or more flight rotors (42). The unmanned aerial vehicle (100) further comprises: a cargo area for coupling to or receiving a load (200); and a load system (6) for providing thrust additional to the thrust provided by the flight system (4) to thereby lift a load attached to the connection point. The load system (6) comprises: a first gas turbine propulsion system; and a controller configured to control the flight system (4) and load system (6).

The technology described herein relates to, among other topics, an aircraft flight system (or any vehicle system) for balancing loads across different distributed power units (e.g., batteries). In particular, the technology is directed to balancing battery systems (e.g., in aircraft with multiple isolated battery systems used for electric propulsion) using electric propulsion unit commands.

According to the high-rotation transient turbulent flow actuating mechanism control device and the simulated flight test method provided by the invention, the aerodynamic configuration of a flight body and the air flow field around the flight body are changed by accurately controlling the extension and retraction of the spoiler, so that the aerodynamic force and the aerodynamic moment suffered by the flight body are controlled, and the control effect is realized; that is, the spoiler actuating mechanism drives the spoiler to stretch out and retract through the high-frequency response motor so as to realize continuous, repeated and high-frequency super-agile continuous control, and the high-overload resistance of the actuating mechanism is ensured through the high-overload resistance design and the potting process of a mechanical structure; in addition, a simulated flight test device is also established, and the actuation performance of the turbulent flow actuation mechanism is tested in the simulated flight process. According to the invention, continuous, repeated and high-frequency continuous control can be carried out while high overload can be borne, and a control / actuation mechanism implementation way is provided for realizing guided transformation of a high-rotation flight system.

The present application relates to the technical field of manned aircrafts, and in particular to an aircraft, a control method and system, a storage system, a flight system, and a facility. The manned aircraft is configured to enable manned flight within a first constraint space defined by a mechanical constraint facility, and the mechanical constraint facility comprises at least one of a rail assembly and a utility tunnel assembly; the rail assembly comprises a suspended rail and a safety connection component assembly, and the rail and the safety connection assembly are used for defining the first constraint space; the upper, lower, left, and right sides of the internal passage of the utility tunnel assembly are all provided with blocking members to define the first constraint space; the manned aircraft comprises a safety processing assembly, and the safety processing assembly comprises at least one of a first safety processing unit, a second safety processing unit and a third safety processing unit. The present application can improve the flight safety of aircrafts.

The application relates to the field of unmanned aerial vehicle (UAV) anomaly diagnosis, and in particular to a multi-modal data fusion UAV anomaly diagnosis method and system. The method comprises the following steps: acquiring multi-modal sensor data of the UAV, analyzing dust characteristics in a current environment in real time according to the multi-modal sensor data of the UAV, and generating a basic dust risk parameter set; acquiring UAV flight state parameters, taking the UAV flight state parameters as a dynamic correction factor, dynamically fusing the dynamic correction factor with the basic dust risk parameter set, and generating a dynamic dust risk influence parameter set; based on this, analyzing the influence degree of the dynamic dust on the flight safety of the UAV, and generating a UAV comprehensive dynamic risk level; based on this, diagnosing a current dust risk composition situation, and generating a UAV anomaly diagnosis report. In the UAV anomaly diagnosis process, the application can effectively support the flight system to make a forward-looking adaptive decision, and avoid serious safety hazards.

The invention, which relates to the technical field of flight path prediction and control, discloses a power transmission line-oriented guide and ground wire edge end dynamic fitting line-imitating flight system, the system firstly fuses an inspection basic data set, and creatively constructs multi-dimensional asymmetric risk characteristics such as thermal relaxation and line spacing deviation around the physical characteristic difference of a guide and ground wire; thirdly, constructing a risk level prediction model to perform time sequence modeling on the risk features so as to predict a flight risk score value in a future time period; then, a dynamic three-dimensional risk map is generated based on a prediction result, and preliminary path planning is guided; and finally, through path margin conformity evaluation and iterative correction of a closed loop, resolving and ensuring that the minimum clearance distance between the final path and the dynamic no-fly envelope meets the safety requirement. According to the invention, the technical problem that the traditional line-imitating flight is difficult to deal with the dynamic concealment risk of the lead is solved, and the safety, autonomy and environmental adaptability of the inspection flight are improved.

A disclosed device allows a person to fly. A disclosed wearable flight system includes a plurality of propulsion assemblies including a left-hand propulsion assembly configured to be worn on a user's left hand and / or forearm and a right-hand propulsion assembly configured to be worn on a user's right hand and / or forearm. A further embodiment includes a body propulsion device that is configured to provide a net force along an axis defining a net body propulsion vector and a support device configured to support a user's waist or torso. The support device is configured to hold a user's body relative to the body propulsion device such that a line extending between center the of the user's head and the center of the user's waist extends, relative to the orientation of the net body propulsion vector during use, by a body propulsion elevation angle that is greater than zero.

The application discloses a cooperative flight system based on magnetic attraction grabbing and collision butt joint of spherical unmanned aerial vehicles, and belongs to the technical field of unmanned aerial vehicles. The system comprises an unmanned aerial vehicle, a connecting arm arranged on the unmanned aerial vehicle, and a control module of the unmanned aerial vehicle. External force is perceived through collision detection, so that the attitude of the unmanned aerial vehicle is adjusted for butt joint of the connecting arm. A threaded connecting piece arranged in cooperation with another unmanned aerial vehicle is arranged on the connecting arm. The control module controls the unmanned aerial vehicle to rotate axially with the connecting arm as the axis, so that fixed connection between the unmanned aerial vehicles is completed. The unmanned aerial vehicle is provided with a spherical shell. A through hole is arranged on the shell. A magnetic attraction assembly is arranged on the spherical shell outside the through hole. The preliminary butt joint of the unmanned aerial vehicle is completed through magnetic attraction. The connecting arm is a telescopic and bendable L-shaped cantilever. After the threaded connection of the cantilever in the vertical state is completed, the cantilever is continuously stretched, so that the preliminary butt joint of the magnetic attraction assembly is peeled off, and another unmanned aerial vehicle is horizontally rolled to form two unmanned aerial vehicles in parallel, and the bottom is connected through the L-shaped cantilever.

The invention provides an electric flight rail flight system, which relates to the field of traffic transportation and is characterized by comprising a rail contact net system, a flight accompanying device power receiving and transmitting system, a main aircraft system and an electric flight operation command and control system. The rail contact network system comprises a supporting structure, an overhead guide rail and a rigid contact network, wherein the rigid contact network is used for external electric energy transmission; the accompanying device system comprises an accompanying device and a power receiving and transmitting device, and a roller power receiving barrel structure is arranged at the lower end of the power receiving and transmitting device and used for electric transmission connection; the main aircraft system comprises a main aircraft body and a power receiving docking device or an integrated power receiving device and is used for continuous power receiving during flight. The system has the advantages that accompanying or integrated wired power supply can be realized in the flying process of the electric aircraft, long-time wire direct connection power supply and energy charging of the aircraft are met, continuous and stable wired power supply is provided for the aircraft, and the flying time, the efficiency and the load are effectively improved.

This invention discloses a UAV contouring flight system and method based on multi-sensor fusion and adaptive planning. The system includes a multi-sensor module for simultaneously acquiring 3D point cloud data, image data, and UAV inertial measurement data of the environment; a localization and mapping module for processing the acquired data through a tightly coupled fusion algorithm to output the UAV's real-time pose and a 3D map of the environment; an adaptive path planning module for identifying target objects based on the 3D environmental map and adaptively selecting and executing a matching path generation strategy to generate a contouring flight path that conforms to the target object's surface; and a flight control module for controlling the UAV according to the contouring flight path. This invention solves the problems of low positioning accuracy, inaccurate environmental modeling, and inability to generate high-precision 3D contouring paths for UAVs in environments lacking GPS signals, achieving efficient contouring for regular targets and high-precision contouring flight for complex targets.

This application relates to the field of aircraft technology, and more particularly to an unmanned aerial vehicle (UAV) and an unmanned flight system. The UAV includes: a fuselage, arms, and legs; multiple arms are spaced circumferentially along the fuselage, one end of each arm connected to the fuselage, and the other end used to mount a rotor; the legs are located at the bottom of the fuselage; at least one of the arms and legs includes: a base and an antenna array; multiple antenna arrays are arranged circumferentially along the base, each antenna array including multiple antenna devices arranged along the length of the base, at least a portion of the antenna device structure being embedded in the base. In this UAV, the base serves as both the supporting frame for the arms and legs and the medium for the antenna devices. Integrating the antenna devices as part of the arms or legs helps reduce the UAV's payload weight and improve its endurance.