44results about How to "Enhanced cruise capability" patented technology

The invention provides a multifunctional unmanned aerial vehicle for fishery breeding, belongs to the field of unmanned aerial vehicles, and particularly relates to a fishery breeding unmanned aerial vehicle. The unmanned aerial vehicle comprises a machine body, machine arms, motors, rotors, a cradle head, a camera, fish finders, lighting lamps, a feed delivery machine connecting frame, a feed delivery machine and a landing gear. The fish finders and the lighting lamps are installed on the machine arms. The feed delivery machine connecting frame is arranged below the machine body, and the feed delivery machine can be connected with the feed delivery machine connecting frame through bucket lugs. After the feed delivery machine is removed, the landing gear can be installed. According to the multifunctional unmanned aerial vehicle for fishery breeding, by combining the feed delivery machine with a multi-rotor aircraft, the labor cost can be lowered, the functions of the fish finders and the camera are combined, the fish categories are accurately distinguished, fish school distribution positions are accurately located for feed delivery, in this way, feed waste can be reduced, and the feeding efficiency is improved. In addition, the feed delivery machine can be removed from the unmanned aerial vehicle, and the patrol flexibility and cruising capacity of the unmanned aerial vehicle can be improved.

The invention belongs to the field of design of aviation aircrafts, and relates to a method for designing a fixed-wing aircraft capable of vertically taking off and landing. The method for designing the aircraft is used for a mixed-mode aircraft and can be realized under current technical conditions, and vertical taking-off and landing are achieved on the basis of the fixed-wing aircraft. When the contradiction between vertical flight and wing-borne flight is handled with, design is conducted with the wing-borne flight as the main working point, higher cruise efficiency and higher cruise capacity are pursued to the larger extent under the current technical conditions, and the requirement for efficient long-time cruise is better met. When the contradiction between the vertical flight and the wing-borne flight is handled with, through coordinated optimization design of two working points, part of performance of the vertical flight is considered, the efficiency and other performance of the vertical flight is improved on the premise of satisfying the cruise performance index, and design failure caused by unreasonable performance of the vertical flight is avoided.

The embodiment of the invention provides a task scheduling method, a task scheduling device and a multi-core system. The energy consumption of the multi-core system is minimum through reasonable task scheduling. The method comprises the following steps: computing absolute load of a first to-be-scheduled task; computing a system energy consumption estimation parameter of the multi-core system when P processor cores managed by R clusters are respectively worked under the corresponding running frequencies to run the first to-be-scheduled task; determining a target processor core for running the first to-be-scheduled task and the corresponding target running frequency under the minimum system energy consumption estimation parameter according to the system energy consumption estimation parameter of the multi-core system when P processor cores managed by R clusters are respectively worked under the corresponding running frequencies to run the first to-be-scheduled task; controlling the target processor core to work under the target running frequency, and scheduling the first to-be-scheduled task to run on the target processor core. The method, device and the system provided by the invention are suitable for computer field.

The invention provides a sea-land dual-purpose self-powered unmanned aerial vehicle navigation assurance base station. The sea-land dual-purpose self-powered unmanned aerial vehicle navigation assurance base station comprises a wind-solar hybrid generation layer, an unmanned aerial vehicle supply layer, a core component layer and a support which are arranged in sequence from top to bottom. The wind-solar hybrid generation layer comprises a solar power generation device and a wind power generation device. The unmanned aerial vehicle supply layer comprises a charging platform, a guiding module and a charging module which are located on the charging platform. The core component layer comprises an energy storage unit, a control circuit and an information relay module. The energy storage unit is used for storing electric power generated by the wind-solar hybrid generation layer. The control circuit is used for controlling the opening and closing of a solar panel which is used as a cabin door of the unmanned aerial vehicle supply layer, and performing the electric power supply switching of the solar power generation device, the wind power generation device and the energy storage unit. The information relay module is used for strengthening and relaying signals collected by the unmanned aerial vehicle within a signal range to transfer to a shore-based management center. The design of the sea-land dual-purpose self-powered unmanned aerial vehicle navigation assurance base station prolongs the cruise duration of an unmanned aerial vehicle and expands the cruising range.

Disclosed is a road for charging electric vehicle. The road includes an electrified rail which includes an electrode plate for connecting an electric plate of the electric vehicle, an insulated cover covering on the plate electrode so as to prevent electric leakage and a neutral layer covering on the insulated cover for connecting a neutral electrode plate of the electric vehicle. The electrode plate includes a first electrode plate and a second electrode plate. The first electrode plate is disposed above the second electrode plate and between the first electrode plate and the second electrode plate there is a gap so that the electric plate of the electric vehicle is able to be sandwiched between the first electrode plate and the second electrode plate while charging. According to the present invention, the road surface is provided with electrified rail, thus the electric vehicle can charge while driving.

The invention discloses a light rail robot four-wheel-drive motion control system and a method thereof. A central control unit communicates with a power energy management unit, a motion driving unit and a peripheral sensing auxiliary unit; the central control unit controls the motion driving unit and the peripheral sensing auxiliary unit, and receives feedback information of the peripheral sensing auxiliary unit at the same time to adjust control parameters of the motion driving unit in real time, thus realizing the safe and stable operation of the system; and the central control unit reasonably adjusts the load balance of the motion driving unit according to the electricity quantity control and feedback of the power energy management unit. The light rail robot four-wheel-drive motion control system and the method have the following advantages: the driving of four independent step-servo motors of a light rail robot in an electrical power tunnel is realized; with an optimal energy efficiency ratio, the synchronization of the running of four wheels is realized; and the problems, such as the unstable gravity center of single-wheel-drive on-rail motion, insufficient driving force, the slipping of driving wheels on a slope, great motion noise after the addition of a speed reducer, and the like are solved.

The invention discloses a solid rocket vehicle, and belongs to the field of recyclable rocket design. The solid rocket vehicle specifically comprises a head load compartment, a rocket body, wings, a rudder, horizontal tail rudders, an adjustable gas flow baffle, ad a tilt buffer; the head load compartment is in a lifting-body shape, the wings are located on both sides of the middle of the rocket body, and the horizontal tail rudders are located on both sides of the rear of the rocket body; and the rudder is located on the back of the rocket body, and the adjustable gas flow baffle is mounted on the rocket body and placed at the lower back portion of the outlet of an engine nozzle. The solid rocket vehicle comprehensively applies the lifting-body load compartment, the wing-level full-actingtail rudders and the landing buffer to increase the lifting force of a flight test platform, and the lift-block ratio and the delay time of the flight test platform are improved, so that the cruisingcapability of the flight test platform is improved; and the method of control rolling rotating of the differential horizontal tail rudders is used, the complexity of a control mechanism is simplified, the self-control of the drop point is achieved by using the cruising capability and the tilt strategies of the flight test platform, and landing recovery is easier.

The invention belongs to the technical field of vertical / short-distance take-off and landing aircrafts, and particularly relates to a wing applied to a tilting wing aircraft. The wing mainly comprisesan aerofoil main body, an aerofoil trailing edge pneumatic device and an aerofoil leading edge pneumatic device. Wherein the wing trailing edge pneumatic device is fixed to the trailing edge of the wing body through a rotatable connecting mechanism, the wing leading edge pneumatic device is fixed to the wing leading edge, and the control device located in the aircraft can automatically set the proper angle of the trailing edge pneumatic device according to the attack angle of the wing. By arranging the front and rear edge pneumatic devices for the wing, the influence of the attack angle on the lifting force of the wing is artificially reduced, and the attack angle of the wing caused by stall is greatly delayed, so that the lifting force of the wing is controllable until the engine is erected to reach a high enough angle, and seamless connection from the wing to the engine can be realized through the control of the whole aircraft; and the controllability and the safety of the conversion stage are greatly improved.

The invention discloses a railway inspection unmanned aerial vehicle based on a 5G technology. According to the invention, an unmanned aerial vehicle carries a laser imaging radar to carry out wear detection on a contact line of a contact network, carries a pan-tilt camera to carry out tracking flight, carries a high-definition camera to recognize the fracture and deformation of a steel rail, the current position of the unmanned aerial vehicle is positioned in real time by adopting a Beidou positioning module, a wireless charging station is arranged along a railway, a charging platform is provided when the unmanned aerial vehicle is inspected along the railway, the cruising ability of the unmanned aerial vehicle is improved, and collected data are transmitted to a monitoring center in real time through a 5G communication technology for analysis and storage, or the monitoring center sends an instruction to a 5G module through the 5G communication technology to control the flight of the unmanned aerial vehicle, when a train passes through the inspected railway section, the monitoring center automatically sends information that the train goes to the unmanned aerial vehicle in advance, and a control circuit board controls the unmanned aerial vehicle to change the flight direction and fly to the nearby wireless charging station for waiting.

The invention relates to the technical field of port wharf construction equipment, and discloses a hoisting device for port wharf construction. The hoisting device comprises horizontal frames which are symmetrically arranged on the left and right sides. Rotating shafts are fixedly mounted on the lower surface of each horizontal frame at intervals, wheel forks are fixed to the lower surfaces of therotating shafts, and wheels are fixedly connected with the left and right sides of each wheel fork. Mounting grooves are formed in the horizontal frames, vacuum pumps are fixedly mounted in the mounting grooves, two groups of hydraulic telescopic rods are fixedly mounted on the lower surface of each horizontal frame, and vacuum chucks are fixedly mounted on piston rods of the hydraulic telescopicrods. A crane is not restrained by a rail through the wheels, the crane can freely move, the operating range of the crane is greatly expanded, and flexibility of the crane is greatly improved; the crane is firmly fixed to the ground through the vacuum chucks, and the crane is prevented from toppling or shaking during hoisting or in typhoons; and the maritime affair monitoring capacity of the crane is added through a watchtower, so that practicability of the crane is improved.

The invention relates to the technical field of urban air traffic, and discloses an electric vertical take-off and landing aircraft structure and a working method thereof. The electric vertical take-off and landing aircraft structure comprises a fuselage component, wing components (2) connected to the left side and the right side of the middle-upper portion of the fuselage component and flat tail components connected to the left side and the right side of the tail of the fuselage component, wherein tilting propellers are arranged at the end parts of the left and right wing components and the end parts of the left and right flat tail components; and nacelle components are respectively connected to the middle parts of the left and right wing parts, and foldable propellers are arranged on the nacelle components. The tilting power system has higher take-off and cruise performance, and the operation efficiency of the aircraft is obviously improved by increasing the cruise flight speed; a propeller tilting mechanism is designed, so that the vertical take-off and landing function is met, and course thrust can be provided for cruising; and a pitch changing mechanism is designed to change the pitch of the propeller, so that the propeller works in a high-efficiency interval under two working conditions of low-speed incoming flow during vertical take-off and landing and high-speed incoming flow during a cruising stage, and the endurance performance of the whole machine is improved.

The invention discloses a quad-rotor unmanned helicopter with a remote control system and a flight control system and relates to the technical field of agricultural moth trapping. The quad-rotor unmanned helicopter comprises a shell, rotors, rotor brackets, brushless motors, a lithium battery, a screwed base, a broad-spectrum moth trapping lamp, a spiral support, a conductive web clothed cylinder, a circuit system and a flight control system, wherein the central part of the upper end surface of the shell is provided with the lithium battery, the rotor brackets are uniformly arranged at four corner parts of the upper end surface of the shell; the other ends of the rotor brackets are connected with the brushless motors which are vertical to the shell and face upwards by virtue of the circuit system; the upper ends of the brushless motors are provided with the rotors; the central part of the lower bottom surface of the shell is provided with the spiral support; the spiral support is internally provided with the broad-spectrum moth trapping lamp which is in threaded connection with the shell by virtue of the screwed base; the broad-spectrum moth trapping lamp is covered by the conductive web clothed cylinder which is in sleeving joint with the screwed base; the circuit system is connected with the flight control system. The quad-rotor unmanned helicopter has the beneficial effects that the bottom of the shell is provided with the broad-spectrum moth trapping lamp and the conductive web clothed cylinder, so that moth pests are killed in a flying process, and the quad-rotor unmanned helicopter is scientific and reasonable in design, environmentally friendly, efficient and easy to operate.

The invention discloses a broad-spectrum moth attractant unmanned plane, and relates to the agricultural moth attractant technical field. The broad-spectrum moth attractant unmanned plane includes a machine casing, rotor wings, rotor wing brackets, brushless motors, a lithium battery, a screw-port seat, a broad-spectrum moth attractant light, a spiral supporting frame, a conductive net cylinder, a circuit system and a flight control system; the center position of the upper end face of the machine casing is provided with the lithium battery, and the rotor wing brackets are uniformly distributed at four corners; the other end of each rotor wing bracket is connected with the brushless motor upwards perpendicular to the machine chasing face through the circuit system; the upper end of each brushless motor is provided with the rotor wing; the center position of the lower bottom surface of the machine chasing is provided with the spiral supporting frame; the interior of the spiral supporting frame is provided with the broad-spectrum moth attractant light in threaded connection with the machine chasing through the screw-port seat; the broad-spectrum moth attractant light is externally covered with the conductive net cylinder, and the conductive net cylinder is connected with the screw-port seat in a sleeved mode; the circuit system is connected with the flight control system. The broad-spectrum moth attractant unmanned plane has the beneficial effects that the broad-spectrum moth attractant light and the conductive net cylinder are mounted at the bottom of the machine casing, during the flight, moths and insect pests are killed, and the broad-spectrum moth attractant unmanned plane has the advantages of scientific and reasonable design, environmental protection, high efficiency, and easy operation.

The invention discloses an unmanned aerial vehicle and unmanned ship cooperative lake surface garbage cleaning device. The system comprises an unmanned aerial vehicle and an unmanned ship. The unmanned ship is provided with a cleaning mechanism, a garbage storage mechanism, a parking platform, an unmanned ship wireless communication module, an unmanned ship positioning module, a double-source driving mechanism and an unmanned ship controller. The unmanned aerial vehicle is provided with an unmanned aerial vehicle controller, an image acquisition module, an unmanned aerial vehicle positioning module, an unmanned aerial vehicle battery, an unmanned aerial vehicle wireless communication module and a charging and discharging module; and the unmanned aerial vehicle wireless communication module communicates with the unmanned ship wireless communication module. According to the lake surface garbage cleaning device based on cooperation of the unmanned aerial vehicle and the unmanned ship, the unmanned aerial vehicle and the unmanned ship conduct garbage cleaning in a cooperation mode, wherein a double-source driving mechanism and a two-way charging mode are adopted, so that the situation that the endurance time of the unmanned aerial vehicle and the unmanned ship influences the garbage cleaning efficiency is avoided.

The invention discloses a four-rotor-wing unmanned aerial vehicle with a flight control system and relates to the technical field of agricultural moth attraction. The four-rotor-wing unmanned aerial vehicle comprises an enclosure, rotor wings, rotor wing brackets, a brushless motor, a lithium battery, a screw opening base, a broad-spectrum moth attraction lamp, a spiral supporting frame, a conductive net barrel, a circuit system and the flight control system, wherein the lithium battery is mounted at the central position of the upper end face of the enclosure, and the rotor wing brackets are uniformly distributed at four corners; the other ends of the rotor wing brackets are connected with the brushless motor, which is vertical to the enclosure and is arranged upwards, through the circuit system; the rotor wings are mounted at the upper end of the brushless motor; the spiral supporting frame is mounted at the central position of the lower bottom surface of the enclosure; the spiral supporting frame is internally provided with the broad-spectrum moth attraction lamp which is in threaded connection with the enclosure through the screw opening base; the conductive net barrel covers the broad-spectrum moth attraction lamp and is in sleeving joint with the conductive net barrel and the screw opening base; and the circuit system is connected with the flight control system. The four-rotor-wing unmanned aerial vehicle with the flight control system, disclosed by the invention, has the beneficial effects that the broad-spectrum moth attraction lamp and the conductive net barrel are mounted at the bottom of the enclosure, and thus moth insects can be killed in a flight process; and the four-rotor-wing unmanned aerial vehicle is scientific and reasonable in design, environment-friendly and efficient, and easy to operate.

The invention provides a wing assembly, and relates to the technical field of aircraft wings. The wing assembly comprises a driving shaft used for driving a wing to rotate, the middle of a wing mounting support is connected with the end of the driving shaft, a first paddle is arranged on the wing mounting support and rotationally connected with the wing mounting support, a second paddle is arranged on the wing mounting support, a transmission mechanism is mounted on the wing mounting support, and the transmission mechanism drives the first paddle to rotate. The wings with different wing section types are installed, a steering mechanism is installed in a first blade, the relative direction between the first blade and a second blade can be changed online, the front edge and the rear edge of the two blades are in axial symmetry in the vertical lifting process, and the wings become rotor wings; during horizontal flight, the front and rear edges of the two blades are in plane symmetry, and the wings are changed into fixed wings. The vertical take-off and landing of an aircraft can be realized, and the cruising performance of the aircraft can be improved.

The invention provides a trailing edge with adjustable degrees of curvature for an aircraft wing. The aircraft wing comprises a middle wing part with the fixed degree of curvature. The middle wing part comprises a main beam. The trailing edge with the adjustable degrees of curvature comprises a rear beam, a plurality of trailing edge pole group structures and a trailing edge driving mechanism, wherein the trailing edge pole group structures are arranged in parallel. The rear beam is connected with the rear end of the main beam. The trailing edge driving mechanism comprises rockers driven by a driving device. One ends of the rockers are connected with the rear beam in a rotatable mode, and the other ends of the rockers are connected with the trailing edge pole group structures in a rotatable mode. The trailing edge pole group structures are plane pole group structures based on 5R closed-loop units and respectively have one degree of freedom. Each trailing edge pole group structure comprises a plurality of pairs of 5R closed-loop units, a plurality of networking triangular units, a tail-end 4R closed-loop unit and a tail-end triangular unit. Each pair of 5R closed-loop units comprises the upper 5R closed-loop unit and the lower 5R closed-loop unit. Meanwhile, the invention provides a leading edge with adjustable degrees of curvature for the aircraft wing.

A split winglet configured for attachment to a wing of an airplane. The split winglet may include an upper winglet smoothly extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane from a lower surface of the upper winglet. The upper winglet may include a transition section which curves upward from the wing tip into a substantially planar section. Upper and lower surfaces of the upper winglet may be bounded by leading and trailing edges which are swept toward an airstream direction, parallel with the chord plane, and curve toward the airstream direction before terminating at a point distal of the wing tip. Similarly, upper and lower surfaces of the ventral fin may be bounded by leading and trailing edges which curve toward the airstream direction and terminate at a point distal of the wing tip.

The invention discloses an unfolding mechanism and a folding wing flight device. The unfolding mechanism comprises a gear, a lower sleeve, an upper sleeve and a base. The base, the upper sleeve and the lower sleeve are of cylindrical structures which are coaxially arranged; the lower sleeve is rotatably arranged on the base in a sleeving manner, and the base is fixedly mounted; the lower sleeve sequentially comprises a sleeving section, a gear mounting section and a to-be-unfolded mechanism mounting section from top to bottom; the to-be-unfolded mechanism mounting section is provided with a lower inner rocker arm for mounting a first to-be-unfolded mechanism; the upper sleeve is arranged on the sleeving section in a sleeving mode and provided with an upper inner rocker arm used for installing a second to-be-unfolded mechanism; an upper gear ring is arranged on the lower end face of the upper sleeve; a lower gear ring is arranged on the upper end surface of the outer side of the to-be-unfolded mechanism mounting section; at least one gear mounting shaft is fixed in the same horizontal plane on the base along the circumference, the gear mounting shafts penetrate through horizontal groove bodies correspondingly formed in the gear mounting sections, and the gears are meshed with the lower gear ring and the upper gear ring respectively. The problem that in the prior art, an unfolding mechanism is complex in structure is solved.

The present invention discloses an unmanned aerial vehicle possessing a flight control system, and relates to the agricultural moth trapping technology field. The unmanned aerial vehicle possessing the flight control system comprises a chassis, a rotor, rotor supports, a brushless motor, a lithium battery, a screw socket, a broad spectrum moth trapping light, a spiral supporting rack, a conductive web clothed cylinder, a circuit system and the flight control system. The lithium battery is arranged in the center of the upper end face of the chassis, the rotor supports are distributed at the four corners of the chassis evenly, and the other ends of the rotor supports are connected with the brushless motor which is vertical with the chassis and faces upwards via the circuit system. The upper end of the brushless motor is equipped with the rotor, the spiral supporting rack is arranged in the center of the lower bottom surface of the chassis, and the broad spectrum moth trapping light which is in threaded connection with the chassis via the screw socket is arranged inside the spiral supporting rack and is covered by the conductive web clothed cylinder. The conductive web clothed cylinder is in cup joint with the screw socket, and the circuit system is connected with the flight control system. The beneficial effects of the present invention are that: the broad spectrum moth trapping light and the conductive web clothed cylinder are arranged at the bottom of the chassis and can kill moth pests during the flight process, and the unmanned aerial vehicle possessing the flight control system is scientific and reasonable in design, is environment friendly and efficient, and is easy to operate.

Disclosed is a road for charging electric vehicle. The road includes an electrified rail which includes an electrode plate for connecting an electric plate of the electric vehicle, an insulated cover covering on the plate electrode so as to prevent electric leakage and a neutral layer covering on the insulated cover for connecting a neutral electrode plate of the electric vehicle. The electrode plate includes a first electrode plate and a second electrode plate. The first electrode plate is disposed above the second electrode plate and between the first electrode plate and the second electrode plate there is a gap so that the electric plate of the electric vehicle is able to be sandwiched between the first electrode plate and the second electrode plate while charging. According to the present invention, the road surface is provided with electrified rail, thus the electric vehicle can charge while driving.

The invention discloses a solid rocket vehicle, and belongs to the field of recyclable rocket design. The solid rocket vehicle specifically comprises a head load compartment, a rocket body, wings, a rudder, horizontal tail rudders, an adjustable gas flow baffle, ad a tilt buffer; the head load compartment is in a lifting-body shape, the wings are located on both sides of the middle of the rocket body, and the horizontal tail rudders are located on both sides of the rear of the rocket body; and the rudder is located on the back of the rocket body, and the adjustable gas flow baffle is mounted on the rocket body and placed at the lower back portion of the outlet of an engine nozzle. The solid rocket vehicle comprehensively applies the lifting-body load compartment, the wing-level full-actingtail rudders and the landing buffer to increase the lifting force of a flight test platform, and the lift-block ratio and the delay time of the flight test platform are improved, so that the cruisingcapability of the flight test platform is improved; and the method of control rolling rotating of the differential horizontal tail rudders is used, the complexity of a control mechanism is simplified, the self-control of the drop point is achieved by using the cruising capability and the tilt strategies of the flight test platform, and landing recovery is easier.

The present invention discloses a quadrotor unmanned aerial vehicle possessing a remote control system, and relates to the agricultural moth trapping technology field. The quadrotor unmanned aerial vehicle possessing the remote control system comprises a chassis, a rotor, rotor supports, a brushless motor, a lithium battery, a screw socket, a broad spectrum moth trapping light, a spiral supporting rack, a conductive web clothed cylinder, a circuit system and a flight control system. The lithium battery is arranged in the center of the upper end face of the chassis, the rotor supports are distributed at the four corners of the chassis evenly, and the other ends of the rotor supports are connected with the brushless motor which is vertical with the chassis and faces upwards via the circuit system. The upper end of the brushless motor is equipped with the rotor, the spiral supporting rack is arranged in the center of the lower bottom surface of the chassis, and the broad spectrum moth trapping light which is in threaded connection with the chassis via the screw socket is arranged inside the spiral supporting rack and is covered by the conductive web clothed cylinder. The conductive web clothed cylinder is in cup joint with the screw socket, and the circuit system is connected with the flight control system. The beneficial effects of the present invention are that: the broad spectrum moth trapping light and the conductive web clothed cylinder are arranged at the bottom of the chassis and can kill moth pests during the flight process, and the quadrotor unmanned aerial vehicle possessing the remote control system is scientific and reasonable in design, is environment friendly and efficient, and is easy to operate.

The present invention discloses an unmanned aerial vehicle possessing a flight control system, and relates to the agricultural moth trapping technology field. The unmanned aerial vehicle possessing the flight control system comprises a chassis, a rotor, rotor supports, a brushless motor, a lithium battery, a screw socket, a broad spectrum moth trapping light, a spiral supporting rack, a conductive web clothed cylinder, a circuit system and the flight control system. The lithium battery is arranged in the center of the upper end face of the chassis, the rotor supports are distributed at the four corners of the chassis evenly, and the other ends of the rotor supports are connected with the brushless motor which is vertical with the chassis and faces upwards via the circuit system. The upper end of the brushless motor is equipped with the rotor, the spiral supporting rack is arranged in the center of the lower bottom surface of the chassis, and the broad spectrum moth trapping light which is in threaded connection with the chassis via the screw socket is arranged inside the spiral supporting rack and is covered by the conductive web clothed cylinder. The conductive web clothed cylinder is in cup joint with the screw socket, and the circuit system is connected with the flight control system. The beneficial effects of the present invention are that: the broad spectrum moth trapping light and the conductive web clothed cylinder are arranged at the bottom of the chassis and can kill moth pests during the flight process, and the unmanned aerial vehicle possessing the flight control system is scientific and reasonable in design, is environment friendly and efficient, and is easy to operate.