A variable number of rotor unmanned aerial vehicle

Abstract

The application discloses a variable-rotor unmanned aerial vehicle, which comprises an unmanned aerial vehicle body, a control unit arranged in the unmanned aerial vehicle body, and an even number of rotor units, wherein the number of the rotor units is at least six; the rotor unit comprises a rotor arm and a rotor set; an electrically-controlled falling mechanism is arranged on the rotor arm; when a certain rotor unit fails, the failed rotor set automatically falls off; other rotor units automatically adjust positions to form a new working state, so that the unmanned aerial vehicle body forms a new balance and continues to work, and the unmanned aerial vehicle body is prevented from crashing due to the failure of the rotor unit.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to the field of UAVs with a variable number of rotors. Background Technology

[0002] A rotary-wing drone is an unmanned rotary-wing aircraft that generates lift and power through multiple rotating variable or fixed blades. Rotary-wing drones possess unique skills such as vertical takeoff and landing, hovering, and low-altitude flight. They achieve autonomous flight through remote control devices or pre-programmed autonomous controls and can be used to perform tasks that fixed-wing aircraft cannot. They have significant value in the civilian, police, and military markets, and their role is becoming increasingly prominent.

[0003] Typically, rotary-wing drones fly at low altitudes and operate in complex environments, especially in the military field. Besides terrain and environmental factors, they are also susceptible to human interference, such as attacks. Most existing rotary-wing drones have fixed rotors; if one rotor malfunctions, the drone will become unstable and crash, unable to continue its mission. Military drones often undertake important missions such as reconnaissance and strikes; a drone crash leading to mission failure can have a significant impact on the course of a battle. Summary of the Invention

[0004] This invention addresses the shortcomings of existing technologies by proposing a drone with a variable number of rotors to solve the technical problem of drone crashes caused by rotor malfunctions.

[0005] The specific technical solution of this invention is as follows.

[0006] This invention discloses a variable-number-of-rotors unmanned aerial vehicle (UAV), comprising a UAV body, a control unit disposed within the UAV body, and multiple rotor units, wherein the number of rotor units is not less than six and is an even number. Each rotor unit includes a rotor arm and a rotor assembly. One end of each rotor arm is rotatably connected to the UAV body, and all rotor arms have their rotation axes relative to the UAV body coincide. A rotation control mechanism is also provided for controlling the rotation of the rotor arms relative to the UAV body. The other end of each rotor arm is connected to the rotor assembly. An electrically controlled detachment mechanism is also provided on each rotor arm. When a rotor unit malfunctions, the corresponding rotor assembly can be detached from the UAV body. Under the control of the rotation control mechanism, the rotor arm drives other rotor units to rotate relative to the UAV body, reaching a new working position and achieving a new working state to continue operation.

[0007] Preferably, the UAV body is provided with a horizontally arranged track, which is a closed circular track, and the rotor arm slides on the track.

[0008] Furthermore, the rotation control mechanism includes a drive gear, a drive motor, and multiple driven gear blocks. The drive gear is horizontally positioned, and its center and the center of the track are on the same vertical line. The drive motor drives the drive gear to rotate. Each rotor arm has one driven gear block, which can slide vertically on the rotor arm. The driven gear block has tooth grooves that can mesh with the drive gear. A stop mechanism is also provided to control the sliding of the driven gear blocks. When the driven gear block slides to the drive gear, it meshes with the drive gear; when it leaves the drive gear, it disengages from the drive gear. When a rotor unit detaches and other rotor units need to be rotated to a new working position, the skip device controls the driven gear block to slide to the drive gear and mesh with the drive gear. The drive motor drives the drive gear to rotate, and the driven gear block, under the action of the drive gear, drives the rotor arm to rotate relative to the UAV body.

[0009] Preferably, the shifting device includes a shifting coil, a shifting magnetic block, and a toothed block spring. The shifting magnetic block is disposed on the driven toothed block, and the toothed block spring is disposed between the rotor arm and the driven toothed block. When the shifting coil is energized, the shifting magnetic block is pulled by the shifting coil, causing the driven toothed block to slide to the position of the drive gear; when the shifting coil is de-energized, the driven toothed block is pulled by the toothed block spring and moves away from the position of the drive gear.

[0010] Preferably, the gear shifting device is an electrically controlled lifting device, which can be a hydraulic drive device or a motor drive device, capable of driving the driven gear block to slide under the action of an electronic control signal.

[0011] Furthermore, a limiting structure for the rotor arm is provided. This limiting structure includes a limiting gear ring, which is fixedly connected to the drone body. The limiting gear ring is circular, and its center is aligned vertically with the center of the track. The grooves of the limiting gear ring can mesh with the grooves on the driven gear block. When the driven gear block moves away from the drive gear, it meshes with the limiting gear ring. Therefore, when the rotor arm does not need to rotate relative to the drone body, its position is restricted by the limiting structure, preventing the rotor arm from deviating from its working position during drone operation.

[0012] Furthermore, the rotor arm includes a rotating section and a detachment section. The rotating section is rotatably connected to the UAV body, and the rotor assembly is fixedly connected to the detachment section. The rotating section and the detachment section are connected by an electronically controlled detachment mechanism, which can control the separation of the rotating section and the detachment section.

[0013] Furthermore, the electrically controlled detachment mechanism includes a clip, a latch, a detachment magnet, an electrically controlled detachment coil, and a detachment spring. A slot is provided at the end of the rotating section away from the UAV body. A latch is rotatably connected within the slot. An electrically controlled detachment coil is also provided on the rotating section. The latch has a detachment magnet that cooperates with the electrically controlled detachment coil. A detachment spring is also provided within the slot. The shape of the end of the detachment section away from the rotor assembly matches the slot. The clip is located at the end of the detachment section away from the rotor assembly, and the clip and the latch cooperate with each other. When the detachment section is inserted into the slot, the detachment spring abuts against the detachment section and is compressed. The electrically controlled detachment coil is energized, and the latch engages the clip. When the electrically controlled detachment coil is de-energized, the clip loses its restraint, and under the action of the detachment spring, the detachment section separates from the rotating section.

[0014] Preferably, a loading structure is also provided at the bottom of the UAV body for loading the work unit.

[0015] Preferably, the drone body has at least a portion of its surface covered with armor, including but not limited to full surface coverage, bottom coverage, and bottom and side coverage, to improve the drone's resistance to damage.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows: when the rotor unit fails, the rotor assembly on the failed rotor unit automatically detaches, and other rotor units automatically adjust their positions to form a new working state, so that the aircraft can form a new balance and continue to operate, thus avoiding a crash due to rotor unit failure. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be discussed below. Obviously, the technical solutions described in conjunction with the accompanying drawings are only some embodiments of the present invention. For those skilled in the art, other embodiments and their accompanying drawings can be obtained based on the embodiments shown in these drawings without creative effort.

[0018] Figure 1 This is a three-dimensional schematic diagram of the present invention;

[0019] Figure 2 This is a plan view of the rotation control mechanism of the present invention;

[0020] Figure 3 This is a front cross-sectional schematic diagram of an embodiment of the rotation control mechanism of the present invention;

[0021] Figure 4 This is a front cross-sectional schematic diagram of another embodiment of the rotation control mechanism of the present invention;

[0022] Figure 5 This is a schematic diagram of the structure of the electrically controlled detachment mechanism of the present invention.

[0023] In the diagram, 100 is the UAV body, 110 is the drive gear, 120 is the drive motor, 130 is the driven gear block, 131 is the gear block spring, 132 is the jump coil, 133 is the lifting device, 140 is the track, 150 is the limit gear ring, 200 is the rotor unit, 210 is the rotor arm, 211 is the rotating section, 212 is the detachment section, 220 is the rotor assembly, 230 is the electronically controlled detachment mechanism, 231 is the clip, 232 is the buckle, 233 is the detachment magnet, 234 is the electronically controlled detachment coil, 235 is the detachment spring, 240 is the wire contact, and 300 is the loading rack. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments described in the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] like Figure 1 As shown, the present invention proposes a variable rotor drone, comprising a drone body 100, a control unit disposed within the drone body 100, and a plurality of rotor units 200, wherein the number of rotor units 200 is not less than six and is an even number. For ease of design, the number of rotor units 200 is preferably six or eight.

[0026] The rotor unit 200 includes a rotor arm 210 and a rotor assembly 220. One end of the rotor arm 210 is rotatably connected to the UAV body 100, and all rotor arms 210 coincide with the rotation axis of the UAV body 100. A rotation control mechanism is also provided for controlling the rotation of the rotor arm 210 relative to the UAV body 100. The other end of the rotor arm 210 is connected to the rotor assembly 220.

[0027] The rotor arm 210 is also equipped with an electronically controlled detachment mechanism 230. When a rotor unit 200 fails, the electronically controlled detachment mechanism 230 can control the corresponding rotor unit 220 to detach from the UAV body 100. Under the control of the rotation control mechanism, the rotor arm 210 drives other rotor units 200 to rotate relative to the UAV body 100, rotate to a new position, and thus reach a new working state to continue operation.

[0028] The UAV body 100 is equipped with a rotor unit monitoring device to monitor the position and working status of the rotor unit 200, such as whether the electronic circuit is unobstructed. The control unit is equipped with a rotor assembly 220 disengagement program. When the rotor unit 200 is in an abnormal working state, the control unit controls the electronically controlled disengagement mechanism 230 on the rotor assembly 220 to cause the corresponding rotor assembly 220 to detach.

[0029] Whether the rotor unit 200 is in an abnormal working state can be determined by the information fed back by the rotor unit monitoring device, or by the balance state of the UAV. After the control unit issues the flight command, the deviation state sensed by the gyroscope in the UAV can be used to determine whether the working state of the rotor unit 200 is abnormal.

[0030] The control unit contains multiple flight control programs. To simplify the algorithm, all flight control programs are for an even number of rotor units 200. When the number of rotor units 220 on the UAV body 100 is odd, one rotor unit 200 is in a non-operating state, while the remaining even-numbered rotor units 200 are in an operating state. The flight control program automatically switches to the flight control program corresponding to the number of rotor units 200 in an operating state.

[0031] Therefore, when the rotor unit 200 malfunctions or is damaged in complex and dangerous environments such as complex terrain or battlefield, and the corresponding rotor assembly 220 falls off, the drone can still continue to fly by relying on other rotor units 200 on the drone body 100, enabling the drone to continue operating.

[0032] like Figure 2-4 As shown, the UAV body 100 is provided with a horizontally arranged track 140, which is a closed circular track, and the rotor arm 210 slides on the track 140. When the rotor arm 210 slides on the track 140, its trajectory is such that the rotor arm 210 rotates relative to the UAV body 100 around the center of the circular track 140.

[0033] The track 140 can be fixedly connected to the UAV body 100, or it can be integrally formed with the UAV body 100. In order to ensure that the rotor arm 210 slides stably on the track 140, the track 140 can be composed of multiple sub-tracks.

[0034] In addition, the rotor arm 210 can also be hinged to the UAV body 100.

[0035] The rotation control mechanism includes a drive gear 110, a drive motor 120, and a plurality of driven gear blocks 130. The drive gear 110 is horizontally arranged, and the center of the drive gear 110 and the center of the track 140 are on the same vertical line. The drive motor 120 is used to drive the drive gear 110 to rotate. In order to facilitate the control of the rotation amount of the drive gear 110, the drive motor 120 is preferably a bidirectional servo motor.

[0036] The driven tooth block 130 is provided with tooth grooves that can mesh with the drive gear 110. Each rotor arm 210 is provided with one driven tooth block 130. The driven tooth block 130 can slide in the vertical direction on the rotor arm 210, that is, in the direction perpendicular to the plane of the circular track 140. A stop device is also provided to control the sliding of the driven tooth block 130. When the driven tooth block 130 slides to the drive gear 110, the driven tooth block 130 meshes with the drive gear 110. When the driven tooth block 130 leaves the drive gear 110, the driven tooth block 130 disengages from the drive gear 110.

[0037] When a rotor unit 220 detaches and other rotor units 200 need to rotate to a new working position, the skip device controls the driven gear block 130 to slide to and mesh with the drive gear 110. The drive motor 120 drives the drive gear 110 to rotate, and the driven gear block 130, under the action of the drive gear 110, drives the rotor arm 210 to rotate relative to the UAV body 100. This achieves control over the rotation of the rotor arm 210 relative to the UAV body 100. Furthermore, only one motor is needed to drive any one rotor arm 210 to rotate relative to the UAV body 100.

[0038] In addition, a motion drive device, such as a motor, can be installed on each rotor arm 210 to control the rotation of each rotor arm 210 relative to the UAV body 100.

[0039] like Figure 3As shown, in a preferred embodiment, the shifting device includes a shifting coil 132, a shifting magnetic block, and a toothed block spring 131. The shifting magnetic block is disposed on the driven toothed block 130, and the toothed block spring 131 is disposed between the rotor arm 210 and the driven toothed block 130. The shifting magnetic block is made of a ferromagnetic material, which can be a permanent magnet or a material such as iron-cobalt-nickel. The shifting magnetic block can be fixed to the driven toothed block 130 or integrally formed with the driven toothed block 130. The driven toothed block 130 itself can also be made of a ferromagnetic material.

[0040] When the trip coil 132 is energized, the trip magnetic block is pulled by the trip coil 132, causing the driven tooth block 130 to slide to the position of the drive gear 110; when the trip coil 132 is de-energized, the driven tooth block 130 is pulled by the tooth block spring 131 and moves away from the position of the drive gear 110. Thus, the control of the driven tooth block 130 is completed.

[0041] The function of the toothed block spring 131 is to apply a spring force to the driven toothed block 130, so that when the shift coil 132 is not energized, the driven toothed block 130 moves away from the drive gear 110. Therefore, the toothed block spring 131 should be set according to its position; it can be a tension spring that provides tension or a compression spring that provides thrust. When the toothed block spring 131 is located between the driven toothed block 130 and the shift coil 132, the toothed block spring 131 is a compression spring; when the toothed block spring 131 is located on the side of the driven toothed block 130 away from the shift coil 132, the toothed block spring 131 is a tension spring.

[0042] like Figure 4 As shown, in another embodiment, the gear shifting device is an electrically controlled lifting device 133, which can be a hydraulic drive device or a motor drive device, and can drive the driven gear block 130 to slide under the action of an electronic control signal.

[0043] like Figure 3-4As shown, when there is no need to adjust the position of the rotor arm 210 relative to the drone body 100, a limiting structure for the rotor arm 210 is provided to restrict the rotation of the rotor arm 210 relative to the drone body 100. The limiting structure includes a limiting gear ring 150, which is fixedly connected to the drone body 100. The limiting gear ring 150 is circular, and it has the same diameter and the same number of tooth grooves as the drive gear 110. The center of the limiting gear ring 150 and the center of the track 140 are on the same vertical line. The toothed grooves of the limiting gear ring 150 can mesh with the toothed grooves on the driven gear block 130. When the driven gear block 130 leaves the position of the drive gear 110, it meshes with the limiting gear ring 150. That is, when the jump coil 132 is de-energized, the driven gear block 130 leaves the position of the drive gear 110 under the traction of the gear block spring 131 and slides to the position of the limiting gear ring 150, where it meshes with the limiting gear ring 150. Thus, when the rotor arm 210 does not need to rotate relative to the UAV body 100, the position of the rotor arm 210 is restricted by the limiting structure to prevent the rotor arm 210 from deviating from its working position during operation. The limiting gear ring 150 can be fixedly connected to the UAV body 100 or integrally formed with the UAV body 100.

[0044] The rotor arm 210 includes a rotating section 211 and a detachment section 212. The rotating section 211 is rotatably connected to the UAV body 100, and the rotor assembly 220 is fixedly connected to the detachment section 212. The rotating section 211 and the detachment section 212 are connected by an electrically controlled detachment mechanism 230, which can control the separation of the rotating section 211 and the detachment section 212.

[0045] like Figure 5As shown, the electrically controlled detachment mechanism 230 includes a clip 231, a latch 232, a detachment magnet 233, an electrically controlled detachment coil 234, and a detachment spring 235. A slot is provided at the end of the rotating section 211 away from the UAV body 100. The latch 232 is rotatably connected within the slot. An electrically controlled detachment coil 234 is also provided on the rotating section 211. The latch 232 has a detachment magnet 233 that cooperates with the electrically controlled detachment coil 234. A detachment spring 235 is also provided within the slot. The shape of the end of the detachment section 212 away from the rotor assembly 220 matches the slot, allowing the detachment section 212 to be inserted into the slot. The clip 231 is located at the end of the detachment section 212 away from the rotor assembly 220, and the clip 231 cooperates with the latch 232. The detachable magnetic block 233 is made of a ferromagnetic material, which can be a permanent magnet or a material such as iron, cobalt, or nickel. The detachable magnetic block 233 can be fixed to the buckle 232 or integrally formed with the buckle 232. The buckle 232 itself can also be made of a ferromagnetic material. The clip 231 can be fixedly connected to the detachable section 212 or integrally formed with the detachable section 212.

[0046] When the detachment section 212 is inserted into the slot, the detachment spring 235 abuts against the detachment section 212 and is compressed, energizing the electrically controlled detachment coil 234. The latch 232, under the action of the electrically controlled detachment coil 234, engages the clip 231. When the electrically controlled detachment coil 234 is de-energized, the clip 231 loses the restraint of the latch 232, and under the action of the detachment spring 235, the detachment section 212 separates from the rotating section 211.

[0047] Therefore, if the rotating section 211 is damaged, causing the electronic circuit to disconnect, the detachment coil will be de-energized, and the detachment section 212 will automatically detach. This avoids the situation where the control unit cannot control the electronically controlled detachment mechanism 230 due to damage to the electronic circuit inside the rotating section 211, resulting in the detachment section 212 failing to detach.

[0048] To prevent the buckle 232 from wobbling in the slot when the detached coil is de-energized, the buckle 232 is hinged in the slot, and a torsion spring is provided on the hinge.

[0049] Multiple wire contacts 240 are provided on the inner wall of the slot of the rotating section 211 and the outer wall of the detachment section 212. The wire contacts 240 on the rotating section 211 and the detachment section 212 cooperate with each other so that when the detachment section 212 is inserted into the slot, the electronic circuit between the rotating section 211 and the detachment section 212 is connected through the 240.

[0050] In addition, the electrically controlled ejection mechanism 230 can also be other types of electrically controlled ejection devices.

[0051] like Figure 1 As shown, in order to enable the drone to have more functions, a loading structure is also provided at the bottom of the drone body 100 for loading operational units, such as offensive weapons, reconnaissance equipment, and supply materials.

[0052] To enhance the defensive capabilities of the drone, at least a portion of the drone body 100 is covered with armor, including but not limited to full surface coverage, bottom coverage, and bottom and side coverage, thereby improving the drone's resistance to damage.

[0053] The present invention discloses a variable-number-of-rotors UAV. In the non-operating state, the rotor assembly 220 and the detachment section 212 are detachable for easy storage. When operation is required, the rotor assembly 220 and the detachment section 212 are mounted on the rotating section 211 via the electronically controlled detachment mechanism, enabling flight operations. At this time, the driven tooth block 130 on the rotor arm 210 meshes with the limiting tooth ring 150, and each rotor unit 200 maintains a fixed relative position due to the interaction between the driven tooth block 130 and the limiting tooth ring 150.

[0054] When the rotor unit 200 malfunctions and is in an abnormal operating state, the rotor assembly 220 and the detachment section 212 on the malfunctioning rotor unit 200 detach. Under the action of the skip device, the driven gear blocks 130 on other rotor units 200 slide to the drive gear 110 and mesh with it. The drive motor 120 drives the drive gear 110 to rotate, and the driven gear blocks 130, under the action of the drive gear 110, drive the rotor arms 210 to rotate relative to the UAV body 100. Considering that the amount of rotation required by different rotor arms 210 in the same direction may not be the same, the drive motor 120 and the drive gear 110 drive only one rotor arm 210 to rotate at a time, or drive multiple rotor arms 210 to rotate with the same amount of rotation in the same direction.

[0055] When the rotor arm 210 rotates to the preset working position, the drive motor 120 stops rotating, and the shifting device controls the driven tooth block 130 to slide again to the limiting tooth ring 150. The driven tooth block 130 and the limiting tooth ring 150 mesh, thereby fixing the position of the rotor arm 210, that is, fixing the position of the rotor unit 200.

[0056] The control unit also includes a temporary balancing program to maintain the balance of the UAV body 100 during the period from when the rotor unit 200 is in an abnormal working state until the other rotor units 200 rotate to a new working position. The program adjusts the working status of the rotor units 200 according to the number of rotor units 200 remaining in normal working state on the UAV body 100, so that an even number of rotor units 200 keep working, and adjusts their rotor speed according to the position of the rotor units 200 to maintain balance, until all rotor units 200 rotate to a new working position, and then switches to a new flight control program.

[0057] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered illustrative and non-limiting in all respects. The scope of the invention is defined by the appended claims, not by the foregoing description, and thus all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0058] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A drone with a variable number of rotors, comprising a drone body, a control unit disposed within the drone body, and a plurality of rotor units, wherein the number of rotor units is not less than six and is an even number, and each rotor unit includes a rotor arm and a rotor assembly, characterized in that: One end of the rotor arm is rotatably connected to the UAV body, and all rotor arms have the same rotation axis relative to the UAV body. A rotation control mechanism is also provided for controlling the rotation of the rotor arms relative to the UAV body. The other end of the rotor arm is connected to the rotor assembly. An electronically controlled detachment mechanism is also provided on the rotor arm, which can control the rotor assembly to detach from the UAV body.

2. The UAV with a variable number of rotors according to claim 1, characterized in that: The drone body is equipped with a horizontally arranged track, which is a closed circular track, and the rotor arm slides on the track.

3. A drone with a variable number of rotors according to claim 2, characterized in that: The rotation control mechanism includes a drive gear, a drive motor, and multiple driven gear blocks. The drive gear is horizontally positioned, and its center and the center of the track are on the same vertical line. The drive motor drives the drive gear to rotate. Each rotor arm is provided with one driven gear block, which can slide vertically on the rotor arm. The driven gear block has tooth grooves that can mesh with the drive gear. A skip device is also provided to control the sliding of the driven gear block. When the driven gear block slides to the drive gear, it meshes with the drive gear. When the driven gear block leaves the drive gear, it disengages from the drive gear.

4. A drone with a variable number of rotors according to claim 3, characterized in that: The shifting device includes a shifting coil, a shifting magnetic block, and a toothed block spring. The shifting magnetic block is disposed on the driven toothed block, and the toothed block spring is disposed between the rotor arm and the driven toothed block. When the shifting coil is energized, the shifting magnetic block is pulled by the shifting coil, causing the driven toothed block to slide to the position of the drive gear. When the shifting coil is de-energized, the driven toothed block is pulled by the toothed block spring and moves away from the position of the drive gear.

5. A drone with a variable number of rotors according to claim 3, characterized in that: The shifting device is an electrically controlled lifting device that can drive the driven tooth block to slide under the action of an electronic control signal.

6. A drone with a variable number of rotors according to claim 3, characterized in that: The device also includes a limiting structure for the rotor arm, which includes a limiting gear ring. The limiting gear ring is fixedly connected to the UAV body. The limiting gear ring is circular, and the center of the limiting gear ring and the center of the track are on the same vertical line. The tooth groove of the limiting gear ring can mesh with the tooth groove on the driven tooth block. When the driven tooth block leaves the position of the drive gear, it meshes with the limiting gear ring.

7. A drone with a variable number of rotors according to claim 1, characterized in that: The rotor arm includes a rotating section and a detachment section. The rotating section is rotatably connected to the UAV body, and the rotor assembly is fixedly connected to the detachment section. The rotating section and the detachment section are connected by an electronically controlled detachment mechanism, which can control the separation of the rotating section and the detachment section.

8. A drone with a variable number of rotors according to claim 7, characterized in that: The electrically controlled detachment mechanism includes a clip, a latch, a detachment magnet, an electrically controlled detachment coil, and a detachment spring. A slot is provided at the end of the rotating section away from the UAV body. A latch is rotatably connected within the slot. An electrically controlled detachment coil is also provided on the rotating section. A detachment magnet that cooperates with the electrically controlled detachment coil is provided on the latch. A detachment spring is also provided within the slot. The shape of the end of the detachment section away from the rotor assembly matches the slot. The clip is located at the end of the detachment section away from the rotor assembly, and the clip cooperates with the latch. When the detachment section is inserted into the slot, the detachment spring abuts against the detachment section and is compressed, the electrically controlled detachment coil is energized, and the latch holds the clip; when the electrically controlled detachment coil is de-energized, the clip loses the restraint of the latch, and under the action of the detachment spring, the detachment section separates from the rotating section.

9. A variable-number unmanned aerial vehicle (UAV) according to any one of claims 1-8, characterized in that: A loading structure is also provided at the bottom of the drone body for loading the work unit.

10. A drone with a variable number of rotors according to claim 9, characterized in that: The drone body is at least partially covered with armor.

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