A power inspection drone

Abstract

The present invention provides an electric power inspection UAV, which includes: a body, an equipment compartment body, and an inspection camera; wherein the equipment compartment body is arranged on the body, and the inspection camera is arranged in the equipment compartment body in a movable manner; a pair of movable wing panels are provided at the compartment opening of the equipment compartment body; the movable wing panels are connected to the equipment compartment body along the compartment opening wall of the equipment compartment body in a sliding manner; both sides of the equipment compartment body are rotatably connected with a wing panel fixing mechanism. The present invention supports the sliding movable wing panels through the wing panel fixing mechanism, and drives the movable wing panels to rotate to an inclined upward position to form a V-shaped structure, which helps to achieve a wind-breaking and diverting effect during flight, thereby achieving the purpose of reducing wind resistance, reducing energy consumption, and improving inspection endurance.

Description

Technical Field

[0001] The present invention relates to the technical field of intelligent electric power inspection, and in particular to an electric power inspection drone. Background Art

[0002] In a broad sense, drones are various remote-controlled aircraft that do not require a pilot to board. Drones do not have cockpits, but are equipped with equipment such as autopilots and program control devices. Personnel on the ground, on ships, or at the mother aircraft remote control station use radar and other equipment to track, locate, remotely control, telemeter, and transmit digital data to them. Drones are widely used.

[0003] Power inspection drones are very effective in inspecting overhead power lines and equipment, and have been widely used in power companies.

[0004] However, existing power inspection drones still have many shortcomings in their operation. For example, since current drone equipment is powered by batteries to ensure normal inspection work of the equipment, and the battery power supply is limited, the battery often needs to be replaced after flying for a while. Especially when flying under strong wind conditions, the flight resistance of the aircraft equipment itself increases, and the actual sustainable flight distance is further reduced. Summary of the Invention

[0005] In view of this, the present invention proposes a power inspection drone, which aims to solve the problem that the existing power inspection drone has a reduced continuous flight distance due to increased flight resistance during flight under strong wind conditions.

[0006] The present invention proposes an electric power inspection drone, which includes: an aircraft body, an equipment compartment body and an inspection camera; wherein the equipment compartment body is arranged on the aircraft body, and the inspection camera is arranged in the equipment compartment body in a movable manner; a pair of movable wing panels are provided at the compartment opening of the equipment compartment body; the movable wing panels are connected to the equipment compartment body along the compartment opening wall of the equipment compartment body in a sliding manner, and are used to close the compartment opening of the equipment compartment body so that the inspection camera is enclosed inside the equipment compartment body, and the movable wing panels can also open the compartment opening of the equipment compartment body so that the inspection camera can slide from the compartment opening of the equipment compartment body and extend to the outside of the equipment compartment body for image acquisition; both sides of the equipment compartment body are rotatably connected with a wing panel clamping mechanism, which is used to support the slid-out movable wing panels and drive the movable wing panels to rotate to an inclined upward position to form a V-shaped structure, which plays a role in reducing wind resistance during the flight of the drone.

[0007] Furthermore, in the above-mentioned power inspection drone, the wing plate fixing mechanism includes: a rotating support shaft and two lifting and landing support rods; wherein the rotating support shaft is rotatably arranged on the equipment warehouse body; the two lifting and landing support rods are respectively arranged at both ends of the rotating support shaft, and a lifting and landing cross bar is provided between the two lifting and landing support rods, and the lifting and landing cross bar, the two lifting and landing support rods and the rotating support shaft form a quadrilateral structure; auxiliary slots are provided between the side walls on the opposite sides of the two lifting and landing support rods, which are used to support the movable wing plate when the movable wing plate slides out and opens the hatch of the equipment warehouse body, so that the two sides of the movable wing plate can be slidably inserted into the two auxiliary slots respectively, thereby allowing the movable wing plate to rotate with the quadrilateral structure.

[0008] Furthermore, in the above-mentioned power inspection drone, a first driving mechanism is provided on the equipment compartment body, and a power output end of the first driving mechanism is connected to the wing plate fixing mechanism for driving the wing plate fixing mechanism to rotate.

[0009] Furthermore, in the above-mentioned electric inspection drone, the first driving mechanism includes: a first driving motor and a first transmission member; wherein, the power input end of the first transmission member is connected to the first driving motor, and the power output end of the first transmission member is connected to the rotating support shaft of the wing plate fixing mechanism, which is used to drive the rotating support shaft to rotate under the action of the first driving motor, so as to drive the movable wing plate fixed on the wing plate fixing mechanism to rotate.

[0010] Furthermore, in the above-mentioned power inspection drone, the equipment compartment body is also provided with a second driving mechanism for driving the movable wing plate to slide.

[0011] Furthermore, in the above-mentioned electric inspection drone, the second driving mechanism includes: a second driving motor and a second transmission member; wherein the power input end of the second transmission member is connected to the second driving motor, and the power output end of the second transmission member is connected to the movable wing plate, which is used to convert the rotation of the second driving motor into the reciprocating linear motion of the movable wing plate.

[0012] Furthermore, in the above-mentioned electric inspection drone, the second transmission component includes: a meshing drive gear and a transmission rack; wherein, the drive gear is arranged on the output shaft of the second drive motor, and the transmission rack is arranged on the movable wing plate, which is used to drive the movable wing plate to perform reciprocating linear motion under the driving action of the two drive motors.

[0013] Furthermore, in the above-mentioned power inspection drone, the equipment compartment body is also provided with a support block for supporting the inspection camera, and the support block is slidably connected to the inner wall of the equipment compartment body, and the support block is connected to a third driving mechanism for driving the support block to slide so that the inspection camera on the support block extends out of the equipment compartment body or retracts into the interior of the equipment compartment body.

[0014] Furthermore, in the above-mentioned power inspection drone, the bottom of the support block is an inverted trapezoidal structure, which is used to enable the inverted trapezoidal structure to protrude outside the equipment compartment body to break the wind and divert the flow; the side wall of the equipment compartment body is provided with a guide groove, and the side wall of the support block is provided with a guide groove block adapted to the guide groove, and a shock-absorbing spring is also provided in the guide groove.

[0015] Furthermore, in the above-mentioned power inspection drone, the hatch wall of the equipment hatch is provided with a sliding groove block for guiding and supporting the sliding of the movable wing plate; the four corners of the body are provided with a propeller drive support rod and a propeller drive block, and each of the propeller drive blocks is provided with a positioning groove for clamping the wing plate clamping mechanism when the wing plate clamping mechanism is rotated to an inclined upward position, so that the end of the wing plate clamping mechanism can be clamped in the positioning groove; the movable wing plate is also provided with a drainage groove.

[0016] The electric power inspection UAV provided by the present invention closes the hatch of the equipment compartment body by means of a movable wing panel, so that the inspection camera is enclosed inside the equipment compartment body. The movable wing panel can also open the hatch of the equipment compartment body, so that the inspection camera can slide from the hatch of the equipment compartment body and extend to the outside of the equipment compartment body for image acquisition; the slid-out movable wing panel is supported by a wing panel clamping mechanism, and the movable wing panel is driven to rotate to an inclined upward position to form a V-shaped structure, which helps to achieve a wind-breaking and airflow-diverting effect during flight, achieves the purpose of reducing wind resistance, and reduces the influence of the existing unmanned aerial vehicle landing gear mounting on the inspection camera image acquisition. It can also avoid the risk of friction between the landing gear and power cables that may occur in blind spots of monitoring. That is, by improving the structure of the bottom of the power inspection UAV, the aerodynamic performance of the UAV is optimized, which helps to achieve the wind-breaking and diverting effect during flight, thereby achieving the purpose of reducing wind resistance, reducing energy consumption, and improving inspection endurance. At the same time, it reduces the impact of the landing gear mounting of existing unmanned aerial equipment on the image acquisition of the inspection camera, and can also avoid the risk of friction between the landing gear and power cables that may occur in blind spots of monitoring, solving the problem of reduced continuous flight distance of existing power inspection UAVs due to increased flight resistance during flight under strong wind conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiment below. The accompanying drawings are for illustration purposes only and are not to be considered as limiting the present invention. The same reference symbols are used throughout the drawings to represent the same components. In the drawings:

[0018] Figure 1 A schematic diagram of the structure of a power inspection drone provided by an embodiment of the present invention;

[0019] Figure 2 for Figure 1 A partial enlarged view of point A in the middle. DETAILED DESCRIPTION

[0020] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, unless there is a conflict, the embodiments of the present disclosure and the features described in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0021] See also Figures 1 to 2 , which shows the preferred structure of the power inspection drone provided by the embodiment of the present invention. As shown in the figure, the power inspection drone includes: a body 1, an equipment compartment 2 and an inspection camera 3; wherein,

[0022] The equipment compartment body 2 is arranged on the machine body 1, and the inspection camera 3 is arranged in the equipment compartment body 2 in a movable manner. A pair of movable wing plates 4 are provided at the compartment opening of the equipment compartment body 2; the movable wing plates 4 and the equipment compartment body 2 are connected along the compartment opening wall of the equipment compartment body 2 (such as Figure 1 The horizontal direction shown in the figure) is connected in a sliding manner to close the hatch of the equipment warehouse body 2, so that the inspection camera 3 is enclosed inside the equipment warehouse body 2, and the movable wing panel 4 can also open the hatch of the equipment warehouse body 2, so that the inspection camera 3 can slide from the hatch of the equipment warehouse body 2 and extend to the outside of the equipment warehouse body 2 for image acquisition; both sides of the equipment warehouse body 2 are rotatably connected with a wing panel fixing mechanism 5, which is used to support the sliding movable wing panel 4 and drive the movable wing panel 4 to rotate to an inclined upward position to form a V-shaped structure, thereby reducing the wind resistance during the flight of the UAV.

[0023] Specifically, an equipment compartment body 2 may be provided below the fuselage 1. The equipment compartment body 2 may be a compartment structure with an open end, and the opening of the open end is arranged downward. The fuselage 1 may also be provided with a movable landing gear, which is used to be lowered to support the fuselage 1 when the fuselage 1 lands. A propeller drive support rod 6 and a propeller drive block 7 may be provided at the four corners of the fuselage 1. An inspection camera 3 is provided in the equipment compartment body 2 for image acquisition; wherein the inspection camera 3 is movably connected to the equipment compartment body 2 and can be extended and retracted to retract into the interior of the equipment compartment body 2 when not in operation. The inspection camera 3 is not in operation. After takeoff, the inspection camera 3 can be extended to the outside of the equipment compartment body 2 to acquire images to achieve inspection.

[0024] The opening of the equipment compartment body 2 is an open end, and a pair of movable wing plates 4 are provided at the opening. Figure 2 As shown, the opening wall of the equipment warehouse body 2 is provided with a sliding groove block 21 for guiding and supporting the sliding of the movable wing plate 4 so that the movable wing plate 4 can slide horizontally. In this embodiment, the two front and rear opening walls of the equipment warehouse body 2 are provided with a sliding groove block 21 along the length direction (such as Figure 1 The two sliding groove blocks 21 are provided on the front and rear ends of the movable wing plate 4 to provide sliding support to ensure the stability of the horizontal sliding of the movable wing plate 4. Two wing plate fixing mechanisms 5 are symmetrically provided on both sides of the equipment warehouse 2. The wing plate fixing mechanisms 5 can be provided below the propeller drive support rod 6 and the propeller drive block 7. The first end of the propeller plate fixing mechanism 5 (as shown in FIG. Figure 1 The left end of the right wing panel fixing mechanism 5 and the right end of the left wing panel fixing mechanism 5 are rotatably arranged on the left and right side walls of the equipment compartment 2 to adjust the position and thereby support the sliding movable wing panel 4. After takeoff, the two wing panel fixing mechanisms 5 are rotated to a horizontal state, and a pair of movable wing panels 4 are moved to both sides (such as Figure 1 The movable wing panel 4 can slide and slide onto the two wing panel fixing mechanisms 5 respectively fixed on both sides. After the movable wing panel 4 completely slides out of the sliding groove block 21, it is supported only on the wing panel fixing mechanism 5. The wing panel fixing mechanism 5 can be rotated so that the wing panel fixing mechanism 5 drives the movable wing panel 4 to rotate. It can be rotated to an inclined upward position, that is, rotated toward a position close to the propeller drive block 7, so that the two sets of wing panel fixing mechanisms 5 form a V-shaped structure, which helps to achieve a wind-breaking and diverting effect during flight, achieve the purpose of reducing wind resistance, and reduce the impact of the existing unmanned aerial vehicle landing gear mounting on the inspection camera image acquisition. It can also avoid the risk of collision between the landing gear and the power cable that may occur in the monitoring blind spot. Among them, the movable wing panel 4 can slide and be supported below the wing panel fixing mechanism 5. Preferably, the movable wing panel 4 is provided with a drainage groove, which can be set on the lower surface of the movable wing panel to ensure good air diversion.

[0025] In order to ensure the stability of the tilted arrangement of the wing plate fixing mechanism 5 during the flight of the aircraft 1, preferably, each spiral wing driving block 7 is provided with a positioning groove 71, which is used to fix the wing plate fixing mechanism 5 when the wing plate fixing mechanism 5 is rotated to the tilted upward position, so that the end of the wing plate fixing mechanism 5 can be clamped in the positioning groove 71. Specifically, the positioning groove 71 is provided on each of the four spiral wing driving blocks 7. After the wing plate fixing mechanism 5 is rotated to the tilted upward position, the second end (such as Figure 1 The front and rear sides of the right end of the right wing panel clamping mechanism 5 and the left end of the left wing panel clamping mechanism 5 are respectively clamped in the positioning grooves 71 on the front and rear rotor drive blocks 7, thereby realizing the engagement between the wing panel clamping mechanism 5 and the positioning grooves 71, which can ensure the stability during flight after the wing panel clamping mechanism 5 is lifted and engaged, and reduce the fluctuations that may be caused by airflow impact.

[0026] In this embodiment, the equipment compartment 2 further includes a support block 22 for supporting the inspection camera 3. The support block 22 is slidably connected to the inner wall of the equipment compartment 2 and is used to drive the inspection camera 3 to extend and retract. Specifically, the bottom of the support block 22 has an inverted trapezoidal structure, which allows the inverted trapezoidal structure to protrude outside the equipment compartment to break wind and divert airflow. This helps achieve a wind-breaking and diverting effect during flight, thereby reducing wind resistance. The portion of the support block 22 protruding outside the equipment compartment 2 forms a wind-breaking and diverting structure to reduce wind resistance. In other words, the inverted trapezoidal structure can cooperate with the two upwardly inclined movable wing panels 4 to form an overall V-shaped structure. The support block 22 can be connected to a third drive mechanism 23. The power output end of the third drive mechanism 23 is connected to the support block 22, which is used to drive the support block 22 to slide, thereby driving the inspection camera 3 to extend and retract, thereby extending the inspection camera 3 outside the equipment compartment 2 or retracting it inside the equipment compartment 2. The third drive mechanism 23 can be a cylinder, positioned above the support block 22, and can drive the support block 22 to slide vertically. In this embodiment, the inspection camera 3 is rotatably positioned below the support block 22, at the end away from the cylinder, and can slide out of the equipment chamber 2 along with the inverted trapezoidal structure to capture images from multiple angles.

[0027] Continue to see Figure 1The side walls of the device housing 2 are provided with guide grooves 24, and the side walls of the support block 22 are provided with guide groove blocks 221 that mate with the guide grooves 24. A shock-absorbing spring 25 is also provided within the guide grooves 24. Specifically, the side walls of the device housing 2 are provided with guide grooves 24, and the side walls of the support block 22 are provided with guide groove blocks 221 that mate with the guide grooves 24. The guide grooves 24 and guide groove blocks 221 cooperate to guide and limit the vertical sliding of the support block 22. The shock-absorbing spring 25 provided within the guide grooves 24 provides excellent shock absorption, particularly in conditions of relatively turbulent external airflow, as the spring provides elastic cushioning.

[0028] Continue to see Figure 2 The equipment housing 2 is further provided with a second drive mechanism 26, whose power output end is connected to the movable flap 4 for driving the movable flap 4 to slide. Specifically, the second drive mechanism 26 can be two and respectively disposed at the lower portion of the left and right side walls of the equipment housing 2 to drive the movable flap 4 so that the movable flap 4 slides horizontally.

[0029] In this embodiment, the second drive mechanism 26 includes a second drive motor 261 and a second transmission member 262. The power input end of the second transmission member 262 is connected to the second drive motor 261, and the power output end of the second transmission member 262 is connected to the movable flap 4, thereby converting the rotation of the second drive motor 261 into reciprocating linear motion of the movable flap 4. Specifically, the second transmission member 262 may be a rack and pinion structure that converts rotation into linear motion, or may be other structures, such as a ball screw mechanism, which are not limited in this embodiment.

[0030] Continue to see Figure 2The second transmission member 262 is a gear rack structure, comprising a meshing drive gear 2621 and a transmission rack 2622. The drive gear 2621 is disposed on the output shaft of the second drive motor 261, and the transmission rack 2622 is disposed on the movable flap 4, and is configured to drive the movable flap 4 to perform reciprocating linear motion under the drive action of the second drive motor 261. Specifically, the movable flap 4 can be fixed to the flap fixing mechanism 5 and rotate synchronously with the flap fixing mechanism 5, so that the transmission rack 2622 disposed on the movable flap 4 also rotates synchronously. To prevent the drive gear 2621 and the second drive motor 261 from interfering with the rotation of the movable flap 4, preferably, the side walls of the compartment opening of the equipment compartment body 2 are also rotatably connected to support blocks 27. The second drive motor 261 is fixed to the support blocks 27, and the drive gear 2621 is fixed to the second drive motor 261. Moreover, the second drive motor 261 and the drive gear 2621 can rotate synchronously with the support blocks 27. The transmission rack 2622 is arranged on the upper surface of the movable wing plate 4 and is engaged with the driving gear 2621. After the transmission rack 2622 slides to both sides with the movable wing plate 4 and disengages from the sliding groove block 21 and is fixed on the wing plate fixing mechanism 5, the transmission rack 2622 and the movable wing plate 4 can rotate with the wing plate fixing mechanism 5. Since the transmission rack 2622 is engaged with the driving gear 2621, the driving gear 2621 can be rotated, and then the support block 27 is rotated relative to the left and right side walls of the equipment warehouse body 21. When the movable wing plate 4 rotates to a horizontal state, the support block 27 can also be rotated to a vertical state.

[0031] Continue to see Figure 1 and Figure 2 The wing plate fixing mechanism 5 may include: a rotating support shaft 51 and two lifting and lowering support rods 52; wherein the rotating support shaft 51 is rotatably arranged on the equipment warehouse body 2; the two lifting and lowering support rods 52 are respectively arranged at both ends of the rotating support shaft 51, and a lifting and lowering cross bar 53 is provided between the two lifting and lowering support rods 52, and the lifting and lowering cross bar 53, the two lifting and lowering support rods 52 and the rotating support shaft 53 form a quadrilateral structure; an auxiliary slot 521 is provided between the side walls on the opposite side of the two lifting and lowering support rods 52, which is used to support the movable wing plate 4 when the movable wing plate 4 slides out and opens the hatch of the equipment warehouse body 2, so that the two sides of the movable wing plate 4 can be slidably inserted into the two auxiliary slots 521 respectively, so that the movable wing plate 4 rotates with the quadrilateral structure.

[0032] In a specific implementation, the rotating support shaft 51 can be rotatably installed on the left side wall or the right side wall of the equipment warehouse body 2, and the lifting cross bar 53 can be arranged parallel to the rotating support shaft 51. The first ends of the two lifting support rods 52 (such as Figure 1The right end of the left lifting support rod 52 shown in the figure) can be fixedly connected to the two ends of the rotating support shaft 51, and the first end of the two lifting support rods 52 (as shown in the figure) can be fixedly connected to the two ends of the rotating support shaft 51. Figure 1 The left end of the left lifting support rod 52 shown in the figure can be fixedly connected to the two ends of the lifting cross bar 53: the rotating support shaft 51, the two lifting support rods 52 and the lifting cross bar 53 form a rectangular structure, which can be rotated as a whole. Figure 2 As shown, auxiliary slots 521 are provided between the opposing side walls of the two lifting and lowering support rods 52. This allows the two movable wing panels 4 to slide into the auxiliary slots 521 when the rectangular structure rotates to a horizontal position. The two lifting and lowering support rods 52 provide sliding support for the front and rear ends of the movable wing panels 4, ensuring the stability of the horizontal sliding of the movable wing panels 4 and the stability of the support for the movable wing panels 4. The slot walls of the auxiliary slots 521 may also be provided with rotating guide wheels 5211 to facilitate the rapid and smooth insertion of the movable wing panels 4. The lifting and lowering crossbars 53 can be engaged in the positioning slots 71 to achieve relative stability of the rectangular structure.

[0033] Continue to see Figure 2 The equipment housing 2 may also be provided with a first drive mechanism 28, whose power output end is connected to the flap-spanning plate securing mechanism 5, for driving the flap-spanning plate securing mechanism 5 to rotate, thereby driving the movable flap 4 to rotate. Specifically, two first drive mechanisms 28 may be provided, one located in the middle of the left and right side walls of the equipment housing 2, to drive the flap-spanning plate securing mechanism 5 to rotate. Multiple first drive mechanisms 28 may be provided, and multiple first drive mechanisms 28 may be arranged side by side and spaced apart along the axial direction of the rotation support shaft 51, thereby improving the stability of the actual driving operation.

[0034] In this embodiment, the first drive mechanism 28 includes a first drive motor 281 and a first transmission member 282. The power input end of the first transmission member 282 is connected to the first drive motor 281, and the power output end of the first transmission member 282 is connected to the rotating support shaft 51. The first drive motor 281 drives the rotating support shaft 51 to rotate, thereby driving the movable flap 4 secured to the flap securing mechanism 5 to rotate. Specifically, the first transmission member 282 may be a gear transmission mechanism or other structure, which is not limited in this embodiment.

[0035] Continue to see Figure 1In order to avoid interference between the support block 22 and the first drive motor 281 and the second drive motor 261, preferably, a groove 222 is provided on the side of the support block 22 for making way for the first drive motor 281 and the second drive motor 261, so that the first drive motor 281 and the second drive motor 261 can be embedded in the groove 222, thereby ensuring that there is no mutual interference between the movement of the support block 22 and the first drive motor 281 and the second drive motor 261.

[0036] The working process of the power inspection drone provided in this embodiment is as follows:

[0037] In the non-working state, the first driving motor 281 drives the lifting and lowering support rod 52 to fall, at which time the lifting and lowering cross bar 53 remains in contact with the bottom surface, the movable wing plate 4 is closed, the trapezoidal platform is not extended, and the inspection camera does not work;

[0038] After takeoff, the first drive motors 281 on both sides are turned on, first driving the rotating support shaft 51 to rotate, so that the lifting and landing support rod 52 rotates to a horizontal state and maintains it, and the second drive motor 261 works synchronously, driving a pair of movable wing panels 4 to move out to both sides and slide into the auxiliary slots 521 between the lifting and landing support rods 52. When the movable wing panels 4 completely slide out of the sliding slot blocks 12 and are stuck in the auxiliary slots 521, the first drive motor 281 continues to work, driving the entire lifting and landing support rods 52 and the lifting and landing cross bar 53 to flip toward the side close to the spiral wing drive block 7, that is, the left lifting and landing support rod 52 rotates clockwise and the right lifting and landing support rod 52 rotates counterclockwise until the lifting and landing cross bar 53 is engaged with the positioning slot 71. In this process, since the transmission rack 2622 is engaged with the driving gear 2621, the transmission rack 2622 rotates with the movable wing panels 4, and the support block 27 can rotate accordingly.

[0039] During the synchronization process, the third driving mechanism 23 pushes the support block 22 downward through the gas rod, and the inspection camera 3 extends out of the equipment compartment 2. At the same time, the support block 22 and the movable wing plates 4 arranged obliquely on both sides form a V-shaped structure;

[0040] When landing is required, the first drive motors 281 on both sides are started to work, first driving the rotating support shaft 51 to rotate, so that the lifting and lowering support rod 52 returns to the horizontal state, and the second drive motor 261 works synchronously, driving a pair of movable wing panels 4 to move relative to each other, sliding out of the auxiliary slots 521 between the lifting and lowering support rods 52 until the movable wing panels 4 slide into the sliding slot blocks 23; the driving mechanism connected to the movable landing gear continues to work, so that the movable landing gear on both sides are opened. During the synchronization process, the third driving mechanism 23 pushes the support block 22 upward through the gas rod, and the inspection camera 3 is retracted into the equipment compartment body 2.

[0041] In summary, the electric power inspection UAV provided in this embodiment closes the hatch of the equipment compartment body 2 through the movable wing plate 4, so that the inspection camera 3 is enclosed inside the equipment compartment body 2, and the movable wing plate 4 can also open the hatch of the equipment compartment body 2, so that the inspection camera 3 can slide from the hatch of the equipment compartment body 2 and extend to the outside of the equipment compartment body 2 for image acquisition; the sliding movable wing plate 4 is supported by the wing plate fixing mechanism 5, and the movable wing plate 4 is driven to rotate to an inclined upward position to form a V-shaped structure, which helps to achieve a wind-breaking and diverting effect during flight, achieves the purpose of reducing wind resistance, and reduces the damage to the inspection camera caused by the landing gear mounting of existing unmanned aerial equipment. The invention can not only reduce the impact of the head image acquisition, but also avoid the risk of friction between the landing gear and the power cables that may occur in the blind spot of monitoring, that is, by improving the structure of the bottom of the power inspection UAV, the aerodynamic performance of the UAV is optimized, which helps to achieve the wind-breaking and diverting effect during the flight, thereby achieving the purpose of reducing wind resistance, reducing energy consumption, and improving the inspection endurance. At the same time, it reduces the impact of the landing gear mounting of the existing unmanned aerial vehicle on the image acquisition of the inspection camera, and can also avoid the risk of friction between the landing gear and the power cables that may occur in the blind spot of monitoring, and solves the problem that the existing power inspection UAV increases the flight resistance during the flight under strong wind conditions, which reduces the continuous flight distance.

[0042] It should be noted that, in the description of the present invention, terms such as "up", "down", "left", "right", "inside", and "outside" indicating directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings. This is only for the convenience of description and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation on the present invention.

[0043] Furthermore, it should be noted that, in the description of the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they may refer to fixed connections, detachable connections, or integral connections; they may refer to direct connections, indirect connections through an intermediary, or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0044] Obviously, those skilled in the art may make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if such changes and modifications fall within the scope of the claims and their equivalents, the present invention is intended to include such changes and modifications.

Claims

1. A power inspection drone, characterized by: include: Machine body, equipment compartment and inspection camera; among them, The equipment compartment is arranged on the machine body, and the inspection camera is movably arranged in the equipment compartment; A pair of movable wing plates are provided at the opening of the equipment warehouse; The movable wing plate is connected to the equipment compartment body along the compartment opening wall of the equipment compartment body in a slidable manner, and is used to close the compartment opening of the equipment compartment body so that the inspection camera is enclosed inside the equipment compartment body. The movable wing plate can also open the compartment opening of the equipment compartment body so that the inspection camera can slide from the compartment opening of the equipment compartment body and extend to the outside of the equipment compartment body for image acquisition; Both sides of the equipment compartment are rotatably connected to a wing plate fixing mechanism for supporting the sliding movable wing plate and driving the movable wing plate to rotate to an inclined upward position to form a V-shaped structure, thereby reducing the wind resistance during the flight of the drone; The wing plate fixing mechanism includes: a rotating support shaft and two lifting and lowering support rods; wherein, The rotating support shaft is rotatably arranged on the equipment warehouse body; The two lifting and lowering support rods are respectively arranged at both ends of the rotating support shaft, and a lifting and lowering cross bar is provided between the two lifting and lowering support rods, and the lifting and lowering cross bar, the two lifting and lowering support rods and the rotating support shaft form a quadrilateral structure; Auxiliary slots are provided between the side walls on opposite sides of the two lifting and lowering support rods, which are used to support the movable wing panel when the movable wing panel slides out and opens the hatch of the equipment compartment body, so that the two sides of the movable wing panel can be slidably inserted into the two auxiliary slots respectively, thereby allowing the movable wing panel to rotate with the quadrilateral structure; The equipment compartment body is provided with a first driving mechanism, the power output end of which is connected to the wing plate fixing mechanism for driving the wing plate fixing mechanism to rotate; The equipment warehouse body is also provided with a second driving mechanism for driving the movable wing plate to slide.

2. The power inspection drone according to claim 1, characterized in that: The first driving mechanism includes: a first driving motor and a first transmission member; wherein, The power input end of the first transmission member is connected to the first drive motor, and the power output end of the first transmission member is connected to the rotating support shaft of the wing plate fixing mechanism, so as to drive the rotating support shaft to rotate under the action of the first drive motor, so as to drive the movable wing plate fixed on the wing plate fixing mechanism to rotate.

3. The power inspection drone according to claim 1, characterized in that: The second driving mechanism includes: a second driving motor and a second transmission member; wherein, The power input end of the second transmission member is connected to the second drive motor, and the power output end of the second transmission member is connected to the movable wing plate, for converting the rotation of the second drive motor into reciprocating linear motion of the movable wing plate.

4. The power inspection drone according to claim 3, characterized in that: The second transmission member includes: a driving gear and a transmission rack that are meshed with each other; wherein, The driving gear is arranged on the output shaft of the second driving motor, and the transmission rack is arranged on the movable wing plate, and is used for driving the movable wing plate to perform reciprocating linear motion under the driving action of the second driving motor.

5. The power inspection drone according to claim 1, characterized in that: The equipment warehouse body is also provided with a support block for supporting the inspection camera, and the support block is slidably connected to the inner wall of the equipment warehouse body, and the support block is connected to a third driving mechanism for driving the support block to slide so that the inspection camera on the support block extends out of the equipment warehouse body or retracts into the interior of the equipment warehouse body.

6. The power inspection drone according to claim 5, characterized in that: The bottom of the support block is in an inverted trapezoidal structure, which is used to enable the inverted trapezoidal structure to protrude outside the equipment compartment to break wind and divert air; A guide groove is provided on the side wall of the equipment bin body, a guide groove block adapted to the guide groove is provided on the side wall of the support block, and a shock absorbing spring is further provided in the guide groove.

7. The power inspection drone according to claim 1, characterized in that: The opening wall of the equipment compartment body is provided with a sliding groove block for guiding and supporting the sliding of the movable wing plate; The four corners of the body are provided with a spiral wing drive support rod and a spiral wing drive block, and each of the spiral wing drive blocks is provided with a positioning groove for clamping the wing plate clamping mechanism when the wing plate clamping mechanism is rotated to an inclined upward position, so that the end of the wing plate clamping mechanism can be clamped in the positioning groove; The movable wing plate is also provided with a drainage groove.

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