CN215043670U - Composite wing electric cruise unmanned aerial vehicle - Google Patents

Abstract

The utility model provides a compound wing electric power unmanned aerial vehicle that cruises, through adopting the sweepback wing, the compound wing that vortex wing and vert the rotor combination is connected with the fuselage, the sweepback wing is connected with the fuselage both sides, the vortex wing is close to the fuselage both sides and is connected with the sweepback wing, the rotor that verts is located the aircraft nose both sides and is connected with the sweepback wing, fixed rotor is located the fuselage rear portion, camera equipment is located the fuselage lower part, the picture passes the antenna and is located sweepback wing upper portion, the flight control board is located the fuselage lower part, control unmanned aerial vehicle through remote control system and cruise, flight control system control unmanned aerial vehicle flight gesture is automatic patrols and examines high-voltage power circuit. The utility model overcomes former power line unmanned aerial vehicle that cruises needs the manual work to reach near target point and control, can not independently patrol and examine, and the dead time is short, patrols and examines the problem of inefficiency, has simple structure, need not to reach near target area and lets fly unmanned aerial vehicle, and the dead time is long, and flight stability is good, and the intellectuality is patrolled and examined efficiently, and accurate patrolling and examining, easy operation convenient characteristics.

Description

Composite wing electric cruise unmanned aerial vehicle

Technical Field

The utility model belongs to the technical field of the artificial intelligence aircraft, a compound wing electric power unmanned aerial vehicle that cruises is related to.

Background

Unmanned aerial vehicles in aircrafts are more and more widely applied, wherein the unmanned aerial vehicles cruise power lines are involved, the unmanned aerial vehicles adopt six rotors to patrol the unmanned aerial vehicles, the maximum dead time is 60 minutes (2.5 KG load), the maximum flight speed is 12M/S, the maximum flight range is 10KM, the flight temperature is between minus 20 ℃ and 30 ℃, the detection mode is infrared remote detection, manual operation is needed during patrol, the intelligent degree is low, and a large amount of manpower and material resources are needed for support; the aircraft has short dead time and low detection efficiency, and detection personnel need to arrive near a detection target for flying; rely on artifical visual inspection, it is higher to patrol and examine the mode cost, and it is lower to patrol and examine the precision.

Disclosure of Invention

The utility model aims to solve the technical problem that a composite wing electric power unmanned aerial vehicle that cruises is provided, moreover, the steam generator is simple in structure, adopt the sweepback wing, the vortex wing is connected with the fuselage with the composite wing of the rotor combination that verts, the sweepback wing is connected with the fuselage both sides, the vortex wing is close to the fuselage both sides and is connected with the sweepback wing, the rotor that verts is located the aircraft nose both sides and is connected with the sweepback wing, fixed rotor is located the fuselage rear portion, camera equipment is located the fuselage lower part, the picture passes the antenna and is located sweepback wing upper portion, the flight control board is located the fuselage lower part, remote control system controls unmanned aerial vehicle and cruises, flight control system control unmanned aerial vehicle flight gesture is automatic to patrol and examine high-voltage power circuit, need not to reach near target area and put unmanned aerial vehicle, the dead time is long, flight stability is good, it is intelligent efficient, accurate patrol and examine, and simple operation is convenient.

In order to solve the technical problem, the utility model discloses the technical scheme who adopts is: a composite wing electric cruise unmanned aerial vehicle comprises a fuselage, composite wings, a camera device, a pattern transmission antenna and a flight control panel; the sweepback wings of the composite wing are connected with two sides of the fuselage, the turbulence wings are connected with the sweepback wings close to two sides of the fuselage, the tilting rotor wings are positioned on two sides of the fuselage and connected with the sweepback wings, and the fixed rotor wings are positioned at the rear part of the fuselage and connected with the fixed rotor wings; an AI camera of the camera equipment is positioned at the lower part of the machine body, the image transmission antenna is positioned at the upper part of the sweepback wing, and the flight control panel is positioned at the lower part of the machine body; tilt rotor, fixed rotor, camera equipment, picture pass the antenna and fly the power module electric connection in control panel and the fuselage.

The upper parts of the front end and the rear end of the machine body are respectively connected with the machine head and the vertical tail, and the cover plate is positioned at the upper part of the machine body and is matched with the closed engine room.

The lower part of the sweepback wing is provided with a flap transmission mechanism connected with the flap, and a reinforcing rod is arranged between the two flap transmission mechanisms and connected with the sweepback wing.

The spoiler wing is the arc of variable cross-section, and the broadening and the thickness of arc dwindle gradually to extend to the vertical fin rear portion from sweepback wing junction to fuselage rear end.

The tilting rotor wing comprises a tilting device connected with one end of a wing rod and a propeller connected with the tilting device, the other end of the wing rod is connected with a sweepback wing, and the tilting device drives the propeller to rotate up and down.

The fixed rotor wing comprises a propeller connected with one end of a tail rod, and the other end of the tail rod is connected with the rear end of the aircraft body.

And the sweepback wing is provided with a high-voltage induction electricity taking device connected with the battery pack.

The camera equipment comprises an AI camera and an image transmission camera which are connected with an OSD module; the AI camera is positioned in the groove at the lower part of the machine body; the picture transmission camera is positioned in the windward cavity at the lower part of the machine head, and the wind shielding plate is matched with the windward cavity.

The image transmission antennas are positioned on two sides of the machine body and connected with the sweepback wings, and transmit images shot by the camera equipment out in a digital signal mode; the flight control panel is located the unmanned aerial vehicle barycenter of fuselage lower part department and is connected with it.

A composite wing electric cruise unmanned aerial vehicle comprises a fuselage, composite wings, a camera device, a pattern transmission antenna and a flight control panel; the sweepback wings of the composite wing are connected with both sides of the fuselage, the turbulence wings are connected with the sweepback wings close to both sides of the fuselage, the tilting rotor wings are positioned on both sides of the fuselage and connected with the sweepback wings, and the fixed rotor wings are positioned on the back of the fuselage and connected with the fixed rotor wings; an AI camera of the camera equipment is positioned at the lower part of the machine body, the image transmission antenna is positioned at the upper part of the sweepback wing, and the flight control panel is positioned at the lower part of the machine body; tilt rotor, fixed rotor, camera equipment, picture pass the antenna and fly the power module electric connection in control panel and the fuselage. Simple structure, through adopting the wing of sweeping backward, the spoiler is connected with the fuselage with the composite wing of rotor combination that verts, the wing of sweeping backward is connected with the fuselage both sides, the spoiler is close to the fuselage both sides and is connected with the wing of sweeping backward, the rotor that verts is located the aircraft nose both sides and is connected with the wing of sweeping backward, fixed rotor is located the fuselage rear portion, camera equipment is located the fuselage lower part, the picture passes the antenna and is located the wing upper portion of sweeping backward, it is located the fuselage lower part to fly the control panel, control unmanned aerial vehicle through remote control system and cruise, it patrols and examines high-voltage power circuit to fly control unmanned aerial vehicle flight gesture automation, need not to reach near target area and fly unmanned aerial vehicle, the dead time is long, flight stability is good, it is efficient to intelligently patrol and examine, accurate patrolling and examining, easy operation is convenient.

In a preferred scheme, the upper parts of the front end and the rear end of the machine body are respectively connected with the machine head and the vertical tail, and the cover plate is positioned at the upper part of the machine body and matched with the machine room to seal the machine room. Simple structure, during the use, the aircraft nose is towards the direction of flight, and the vertical fin prevents at the high-speed flight in-process of unmanned aerial vehicle that the aircraft nose upwarps, and the apron prevents inside rainwater and the dust gets into the cabin, avoids the equipment in the cabin to receive the influence.

In a preferred scheme, a flap drive mechanism is arranged at the lower part of the sweepback wing and connected with the flap, and a reinforcing rod is arranged between the two flap drive mechanisms and connected with the sweepback wing. The structure is simple, in the inspection process, when the unmanned aerial vehicle is close to an iron tower, the flap transmission mechanism drives the flap to move downwards, the width of the sweepback wing is increased, the area of the sweepback wing is correspondingly increased, and meanwhile, the bending angle of the sweepback wing is also increased, so that the pressure difference of the upper surface and the lower surface of the sweepback wing is increased, the lift force of the airplane is rapidly improved, the unmanned aerial vehicle can rapidly cross the top of the iron tower within a short distance, and the collision accident is avoided; lie in and set up the stiffener between the wing flap drive mechanism and be connected with the wing of sweeping backward, improve overall structure intensity, when avoiding unmanned aerial vehicle speed to exceed the speed of settlement, put down the wing flap by force and lead to unmanned aerial vehicle to disintegrate.

In a preferred scheme, the spoiler is an arc-shaped plate with a variable cross section, and the widening and the thickness of the arc-shaped plate are gradually reduced from the connecting position of the sweepback wing to the rear end of the fuselage and extend to the rear part of the vertical tail. When the unmanned aerial vehicle fast-flying guide vane is used, airflow passes through the front surface of the nose and then impacts a vertical tail at the rear end of the body of the unmanned aerial vehicle, the airflow is guided to the two sides of the sweepback wing, and impact of the airflow on the vertical tail is weakened; when unmanned aerial vehicle low-speed flight, produce decurrent pressure at the fuselage rear end, increase the anterior load capacity of aircraft nose.

In a preferred scheme, the tilting rotor comprises a tilting device connected with one end of a wing rod and a propeller connected with the tilting device, the other end of the wing rod is connected with the sweepback wing, and the tilting device drives the propeller to rotate up and down. Simple structure, during the use, the screw that device drive wing pole one end of verting is connected upwards or rotates downwards from the horizontal direction, and cooperation flight control system controls unmanned aerial vehicle's flight gesture and flight mode.

In a preferred embodiment, the fixed rotor comprises a propeller connected to one end of a tail rod, the other end of which is connected to the rear end of the fuselage. Simple structure, during the use, fixed rotor and two rotors that vert form the triangle-shaped overall arrangement, are favorable to reducing whole weight, improve whole flight's stability.

In a preferred scheme, the sweepback wing is provided with a high-voltage induction electricity taking device connected with the battery pack. Simple structure, before taking off, unmanned aerial vehicle provides the electric energy by the group battery, patrols and examines the in-process, gets the electric installation by high-pressure induction and gets the back and charge the group battery.

In a preferred scheme, the camera equipment comprises an AI camera and an image transmission camera which are connected with an OSD module; the AI camera is positioned in the groove at the lower part of the machine body; the picture transmission camera is positioned in the windward cavity at the lower part of the machine head, and the wind shielding plate is matched with the windward cavity. Simple structure, during the use, under the high-speed flight state of unmanned aerial vehicle, the board that hides need close, avoids the wind speed too high to lift the board that hides and turns over.

In a preferred scheme, the image transmission antennas are positioned on two sides of the machine body and connected with the sweepback wings, and images shot by the camera equipment are transmitted out in a digital signal mode; the flight control panel is located the unmanned aerial vehicle barycenter of fuselage lower part department and is connected with it. The structure is simple, and when the image transmission antenna is used, the image videos shot by the AI camera and the image transmission camera are converted into digital signals to be transmitted out, so that a receiver receives the digital signals; the flight control panel is installed in the barycenter department of abdomen lower part, measures unmanned aerial vehicle's acceleration.

The utility model provides a compound wing electric power unmanned aerial vehicle that cruises, it includes the fuselage, compound wing, camera equipment, the picture passes the antenna and flies the control panel, through adopting the sweepback wing, the compound wing of vortex wing and the rotor combination that verts is connected with the fuselage, the sweepback wing is connected with the fuselage both sides, the vortex wing is close to the fuselage both sides and is connected with the sweepback wing, the rotor that verts is located the aircraft nose both sides and is connected with the sweepback wing, fixed rotor is located the fuselage rear portion, camera equipment is located the fuselage lower part, the picture passes the antenna and is located sweepback wing upper portion, it is located the fuselage lower part to fly the control panel, control unmanned aerial vehicle through remote control system and cruise, flight control system control unmanned aerial vehicle flight gesture automatic high voltage power line that patrols and examines. The utility model overcomes former power line unmanned aerial vehicle that cruises needs the manual work to reach near target point and control, can not independently patrol and examine, and the dead time is short, patrols and examines the problem of inefficiency, has simple structure, need not to reach near target area and lets fly unmanned aerial vehicle, and the dead time is long, and flight stability is good, and the intellectuality is patrolled and examined efficiently, and accurate patrolling and examining, easy operation convenient characteristics.

Drawings

The invention will be further explained with reference to the following figures and examples:

fig. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a front view of fig. 1.

Fig. 3 is a schematic sectional view at a-a of fig. 2.

Fig. 4 is a schematic top view of fig. 2.

Fig. 5 is a schematic bottom view of fig. 2.

Fig. 6 is the utility model discloses tilt rotor's schematic structure diagram.

In the figure: fuselage 1, aircraft nose 11, vertical fin 12, apron 13, composite wing 2, sweepback wing 21, spoiler 22, tilt rotor 23, fixed rotor 24, stiffener 25, high-voltage induction electricity-taking device 26, camera equipment 3, OSD module 31, AI camera 32, picture biography camera 33, shield board 34, picture biography antenna 4, flight control panel 5.

Detailed Description

As shown in fig. 1 to 6, a compound wing electric cruise unmanned aerial vehicle comprises a fuselage 1, a compound wing 2, a camera device 3, a pattern transmission antenna 4 and a flight control panel 5; the sweepback wing 21 of the composite wing 2 is connected with two sides of the fuselage 1, the spoiler wing 22 is connected with the sweepback wing 21 near two sides of the fuselage 1, the tilt rotor 23 is positioned at two sides of the nose 11 and connected with the sweepback wing 21, and the fixed rotor 24 is positioned at the back of the fuselage 1 and connected with the fixed rotor; the AI camera 32 of the camera device 3 is positioned at the lower part of the machine body 1, the image transmission antenna 4 is positioned at the upper part of the sweepback wing 21, and the flight control panel 5 is positioned at the lower part of the machine body 1; tilt rotor 23, fixed rotor 24, camera equipment 3, picture pass antenna 4 and fly control panel 5 and the power module electric connection in the fuselage 1. Simple structure, compound wing through adopting sweepback wing 21, turbolator wing 22 and the rotor 23 combination that verts is connected with fuselage 1, sweepback wing 21 is connected with fuselage 1 both sides, turbolator wing 22 is close to fuselage 1 both sides and is connected with sweepback wing 21, tilt rotor 23 is located aircraft nose 11 both sides and is connected with sweepback wing 21, fixed rotor 24 is located fuselage 1 rear portion, camera equipment 3 is located fuselage 1 lower part, picture transmission antenna 4 is located sweepback wing 21 upper portion, it is located fuselage 1 lower part to fly control panel 5, control unmanned aerial vehicle through remote control system and cruise, flight control system control unmanned aerial vehicle flight gesture is automatic to patrol and examine high-voltage power circuit, need not to reach near target area and put the unmanned aerial vehicle, the dead time is long, flight stability is good, the intellectuality is patrolled and examined efficiently, accurate patrol and examine, easy operation is convenient.

In a preferred scheme, the upper parts of the front end and the rear end of the machine body 1 are respectively connected with a machine head 11 and a vertical tail 12, and a cover plate 13 is positioned at the upper part of the machine body 1 and is matched with and used for closing a cabin. Simple structure, during the use, aircraft nose 11 is towards the direction of flight, and vertical fin 12 prevents aircraft nose 11 upwarping at the high-speed flight in-process of unmanned aerial vehicle, and apron 13 prevents inside rainwater and the dust entering cabin, avoids the equipment in the cabin to receive the influence.

Preferably, the aircraft back on fuselage 1 upper portion is streamlined arc protruding to fuselage 1 rear end from aircraft nose 11, and vertical fin 12 is triangular arc piece, connects in aircraft back rear end, and under high speed state, the high-speed air current that produces around the aircraft back flows to fuselage 1 rear end lower part along vertical fin 12 both sides, is favorable to avoiding aircraft nose 11 to upwarp, improves the stability under the high-speed flight state of unmanned aerial vehicle.

Preferably, the flight control system and the power supply module are arranged in the cabin, and the flight control system is connected with the flight control panel 5; the flight control system mainly comprises a main control module, a signal conditioning and interface module, a data acquisition module and a steering engine driving module, and controls the flight attitude by controlling the tilting rotor 23 and the fixed rotor 24.

Preferably, the remote control system employs a MC7RB receiver.

Preferably, fly to control and adopt the flying of spraying f3 accuse, be favorable to adjusting this unmanned aerial vehicle's automatic balance performance.

Preferably, the fuselage 1 is made of carbon steel material to ensure sufficient toughness and strength.

In a preferred scheme, a flap drive mechanism is arranged at the lower part of the sweepback wing 21 and connected with the flap, and a reinforcing rod 25 is arranged between the two flap drive mechanisms and connected with the sweepback wing 21. The structure is simple, in the inspection process, when the unmanned aerial vehicle is close to an iron tower, the flap transmission mechanism drives the flap to move downwards, the width of the sweepback wing 21 is increased, the area of the sweepback wing 21 is correspondingly increased, and meanwhile, the bending angle of the sweepback wing 21 is also increased, so that the pressure difference of the upper surface and the lower surface of the sweepback wing 21 is increased, the lift force of the aircraft is rapidly improved, the unmanned aerial vehicle can rapidly cross the top of the iron tower within a short distance, and the collision accident is avoided; lie in and set up stiffener 25 and be connected with sweepback wing 21 between the wing flap drive mechanism, improve overall structure intensity, when avoiding unmanned aerial vehicle speed to exceed the speed of setting for, put down the wing flap by force and lead to unmanned aerial vehicle to disintegrate.

Preferably, the swept-back wings 21 are arranged in a triangular pattern with respect to the fuselage 1, which is advantageous for minimizing air resistance during high-speed flight conditions.

In a preferred scheme, the spoiler 22 is an arc-shaped plate with a variable cross section, and the widening and thickness of the arc-shaped plate gradually decrease from the connection position of the sweepback wing 21 to the rear end of the fuselage 1 and extend to the rear part of the vertical tail 12. When the unmanned aerial vehicle fast-flying aircraft is used, airflow passes through the front surface of the aircraft nose 11 and then impacts the vertical tail 12 at the rear end of the aircraft body 1, the airflow is guided to the two sides of the sweepback wing 21, and the impact of the airflow on the vertical tail 12 is weakened; when unmanned aerial vehicle low-speed flight, produce decurrent pressure at fuselage 1 rear end, increase the anterior load capacity of aircraft nose 11.

Preferably, the spoiler wings 22 are gradually widened and reduced in thickness from the junction of the swept-back wings 21 toward the rear end of the fuselage 1, which facilitates the direction of the air flow.

In a preferred embodiment, the tilt rotor 23 includes a tilt device connected to one end of a wing rod, and a propeller connected to the tilt device, the other end of the wing rod is connected to the sweepback wing 21, and the tilt device drives the propeller to rotate up and down. Simple structure, during the use, the screw that device drive wing pole one end of verting is connected upwards or rotates downwards from the horizontal direction, and cooperation flight control system controls unmanned aerial vehicle's flight gesture and flight mode.

Preferably, tilt rotors 23 located on both sides of fuselage 1 are vertically centered on the propellers of tilt rotors 23, and are controlled in heading by differential motion of the tilt devices.

Preferably, when the tilt rotor 23 is in a vertical state, the unmanned aerial vehicle can fly vertically; when rotor 23 is in the horizontality verts, the unmanned aerial vehicle transform is the fixed wing flight.

Preferably, the tilting device comprises a rotating plate connected with the output end of the tilting motor, the steering engine connected with the propeller is connected with the rotating plate, and the tilting motor is connected with the wing rod.

Preferably, the steering engine adopts a SUNNYSKY Langyu X2820KV570 motor, and under the voltage of 24V, a single motor is matched with an 8038 carbon fiber nylon blade to be favorable for generating 10KG pulling force.

Preferably, the electric regulator connected with the steering engine and the flight control system adopts a four-in-one 60A electric regulator, and the maximum instantaneous current reaches 65A.

Preferably, the rotating plate is made of a photosensitive resin composite material and is formed by compounding through 3D printing, and can bear the load of 20 KG.

Preferably, the wing rod is made of 3K carbon fiber and has the characteristics of light weight, high strength and corrosion resistance.

In a preferred embodiment, the fixed rotor 24 includes a propeller connected to one end of a tail rod, and the other end of the tail rod is connected to the rear end of the fuselage 1. Simple structure, during the use, fixed rotor 24 and two rotors that vert 23 form the triangle-shaped overall arrangement, are favorable to reducing whole weight, improve the stability of whole flight.

Preferably, in the fixed-wing flight state, the two tilt rotors 23 are in the horizontal state, and the fixed rotor 24 is stopped; in a pendulous flight condition, fixed rotor 24 and two tiltrotors 23 are simultaneously activated.

In a preferable scheme, a high-voltage induction power taking device 26 is arranged on the sweepback wing 21 and connected with the battery pack. Simple structure, before taking off, unmanned aerial vehicle provides the electric energy by the group battery, patrols and examines the in-process, gets the electric installation 26 by high-pressure induction and gets the back and charge the group battery.

Preferably, when the unmanned aerial vehicle flies to the patrol and examine the set height, high-voltage induction gets electric installation 26 and is located the high-voltage electric field scope, and high-voltage induction gets electric installation 26 and converts the electromagnetic energy around the high-voltage line into the electric energy.

Preferably, the battery pack adopts 217000 battery node groups, single 5000mah battery nodes, and 12 battery nodes are connected into one group.

In a preferred embodiment, the image capturing device 3 includes an AI camera 32 and an image transmission camera 33 connected to an OSD module 31; the AI camera 32 is positioned in a groove at the lower part of the machine body 1; the image-sensing camera 33 is positioned in the windward cavity at the lower part of the machine head 11, and the wind shielding plate 34 is matched with the windward cavity. Simple structure, during the use, under the high-speed flight state of unmanned aerial vehicle, the board 34 that hides need close, avoids the wind speed too high to lift the board that hides and turns over.

Preferably, the OSD module 31 is a video overlay system, which mainly integrates an anemoscope, an altimeter, and a quantitative monitoring device, and returns the monitored data to the terminal to be overlaid on the image transmitted by the image.

Preferably, the AI camera 32 mainly identifies the high-voltage wires under the belly, and cooperates with the map-transmission camera 33 to jointly identify the iron tower.

Preferably, the AI identification camera adopts an openmv 7H 7 PLUS camera, and the resolution reaches 1080 p; using NMS to obtain about 300 propofol, pooling to obtain bbox, the whole process is called RPN, yolov3 is to divide the picture into 7 × 7 grids for prediction, so the speed is much faster than that of RCNN; yolo divides the picture into 7 × 7 cells, each cell can process one category, and the processing accuracy of the image is higher by using a neural source depth optimization algorithm.

Preferably, an electric push rod is arranged in the windward cavity and connected with the wind shielding plate 34, one end of the wind shielding plate 34 is matched with a shaft head in the wind cavity, and the electric push rod pushes the wind shielding plate 34 to rotate around the shaft head, so that the same windward cavity of the wind shielding plate 34 is matched and sealed.

In a preferred scheme, the image transmission antenna 4 is positioned on two sides of the body 1 and connected with the sweepback wing 21, and transmits an image shot by the camera device 3 as a digital signal; the flight control panel 5 is located the unmanned aerial vehicle barycenter of fuselage 1 lower part and is connected with it. The structure is simple, when in use, the image transmission antenna 4 is used for converting image videos shot by the AI camera 32 and the image transmission camera 33 into digital signals to be transmitted out, so that a receiver can receive the digital signals; the flight control panel 5 is installed in the centroid of the lower portion of the belly, and the acceleration of the unmanned aerial vehicle is measured.

Preferably, the panda 1W map is adopted for map transmission, and a 20DBI maple leaf panel antenna is matched, so that the flying distance of the unmanned aerial vehicle can reach more than 50KM, and the maximum takeoff weight is as follows: 20KG, the maximum landing weight of 27KG, the maximum climbing rate of more than or equal to 5 m/s, the flight distance under the no-high-voltage charging mode of 302KM, the high-voltage charging mode determined according to the length of the line patrol line, the cruising speed of 100 KM/h, the conversion time between the fixed wing mode and the vertical mode of less than or equal to 20 milliseconds, the maximum lifting limit height of less than or equal to 6000 m, the no-alternating current charging endurance time of 180 minutes, the maximum overload of 7G, and the fixed-point hovering error of less than or equal to 0.1m,

as above a compound wing electric power unmanned aerial vehicle that cruises, when installing and using, adopt sweepback wing 21, the compound wing that vortex wing 22 and vert rotor 23 combination is connected with fuselage 1, sweepback wing 21 is connected with fuselage 1 both sides, vortex wing 22 is close to fuselage 1 both sides and is connected with sweepback wing 21, vert rotor 23 is located aircraft nose 11 both sides and is connected with sweepback wing 21, fixed rotor 24 is located fuselage 1 rear portion, camera device 3 is located fuselage 1 lower part, picture transmission antenna 4 is located sweepback wing 21 upper portion, flight control board 5 is located fuselage 1 lower part, remote control system controls unmanned aerial vehicle and cruises, flight control system control unmanned aerial vehicle flight gesture is automatic patrols and examines high voltage power circuit, need not to reach near target area and put the unmanned aerial vehicle that flies, the dead time is long, flight stability is good, intelligent patrol and examine efficiently, it patrols and accurately patrols and examines, easy operation is convenient.

During the use, aircraft nose 11 is towards the direction of flight, and vertical fin 12 prevents aircraft nose 11 upwarping at the high-speed flight in-process of unmanned aerial vehicle, and apron 13 prevents inside rainwater and the dust entering cabin, avoids the equipment in the cabin to receive the influence.

In the inspection process, when the unmanned aerial vehicle approaches the iron tower, the flap transmission mechanism drives the flap to move downwards, the width of the sweepback wing 21 is increased, the area of the sweepback wing 21 is correspondingly increased, and meanwhile, the bending angle of the sweepback wing 21 is also increased, so that the pressure difference of the upper surface and the lower surface of the sweepback wing 21 is increased, the lift force of the airplane is rapidly improved, the unmanned aerial vehicle can rapidly cross the top of the iron tower within a short distance, and the collision accident is avoided; lie in and set up stiffener 25 and be connected with sweepback wing 21 between the wing flap drive mechanism, improve overall structure intensity, when avoiding unmanned aerial vehicle speed to exceed the speed of setting for, put down the wing flap by force and lead to unmanned aerial vehicle to disintegrate.

When the unmanned aerial vehicle fast-flying aircraft is used, in the process of fast flying of the unmanned aerial vehicle, airflow passes through the front surface of the aircraft nose 11 and then impacts the vertical tail 12 at the rear end of the aircraft body 1, the airflow is guided to the two sides of the sweepback wing 21, and the impact of the airflow on the vertical tail 12 is weakened; when unmanned aerial vehicle low-speed flight, produce decurrent pressure at fuselage 1 rear end, increase the anterior load capacity of aircraft nose 11.

During the use, the screw that tilting device drive wing pole one end is connected upwards or rotates downwards from the horizontal direction, cooperates flight control system control unmanned aerial vehicle's flight gesture and flight mode.

During the use, fixed rotor 24 and two rotors that vert 23 form the triangle-shaped overall arrangement, are favorable to reducing whole weight, improve whole flight's stability.

Before taking off, the unmanned aerial vehicle is provided with the electric energy by the group battery, patrols and examines the in-process, gets the electric back by high-voltage induction electricity-taking device 26 and charges the group battery.

During the use, under the high-speed flight state of unmanned aerial vehicle, shelter from wind board 34 and need close, avoid the wind speed too high to turn over the board that hides.

When in use, the image transmission antenna 4 is used for converting image videos shot by the AI camera 32 and the image transmission camera 33 into digital signals to be transmitted out, so that a receiver can receive the digital signals; the flight control panel 5 is installed in the centroid of the lower portion of the belly, and the acceleration of the unmanned aerial vehicle is measured.

The above embodiments are merely preferred technical solutions of the present invention, and should not be considered as limitations of the present invention, and the features in the embodiments and the examples in the present application may be arbitrarily combined with each other without conflict. The protection scope of the present invention shall be defined by the claims and the technical solutions described in the claims, including the technical features of the equivalent alternatives as the protection scope. Namely, equivalent alterations and modifications within the scope of the invention are also within the scope of the invention.

Claims (8)

1. The utility model provides a compound wing electric power unmanned aerial vehicle that cruises, characterized by: the aircraft comprises an airframe (1), a composite wing (2) and a camera device (3); the sweepback wing (21) of the composite wing (2) is connected with two sides of the fuselage (1), the spoiler wing (22) is connected with the sweepback wing (21) close to two sides of the fuselage (1), the tilt rotor wing (23) is positioned on two sides of the nose (11) and connected with the sweepback wing (21), and the fixed rotor wing (24) is positioned at the rear part of the fuselage (1) and connected with the fixed rotor wing; an AI camera (32) of the image pickup apparatus (3) is located at a lower portion of the body (1).

2. The compound wing electric cruise drone according to claim 1, characterized in that: the upper parts of the front end and the rear end of the machine body (1) are respectively connected with the machine head (11) and the vertical tail (12), and the cover plate (13) is positioned at the upper part of the machine body (1) and is matched with the closed cabin.

3. The compound wing electric cruise drone according to claim 1, characterized in that: the lower part of the sweepback wing (21) is provided with a flap drive mechanism connected with the flap, and a reinforcing rod (25) is arranged between the two flap drive mechanisms and connected with the sweepback wing (21).

4. The compound wing electric cruise drone according to claim 1, characterized in that: the spoiler wings (22) are arc-shaped plates with variable cross sections, the width and the thickness of the arc-shaped plates are gradually reduced from the connecting part of the sweepback wings (21) to the rear end of the fuselage (1) and extend to the rear parts of the vertical tails (12).

5. The compound wing electric cruise drone according to claim 1, characterized in that: the tilting rotor (23) comprises a tilting device connected with one end of a wing rod and a propeller connected with the tilting device, the other end of the wing rod is connected with a sweepback wing (21), and the tilting device drives the propeller to rotate up and down.

6. The compound wing electric cruise drone according to claim 1, characterized in that: the fixed rotor wing (24) comprises a propeller connected with one end of a tail rod, and the other end of the tail rod is connected with the rear end of the aircraft body (1).

7. The compound wing electric cruise drone according to claim 1, characterized in that: the sweepback wing (21) is provided with a high-voltage induction electricity-taking device (26) connected with the battery pack.

8. The compound wing electric cruise drone according to claim 1, characterized in that: the camera equipment (3) comprises an AI camera (32) and an image transmission camera (33) which are connected through an OSD module (31); the AI camera (32) is positioned in a groove at the lower part of the machine body (1); the picture transmission camera (33) is positioned in the windward cavity at the lower part of the machine head (11), and the wind shielding plate (34) is matched with the windward cavity.

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