A rotor self-deployable unmanned aerial vehicle

Abstract

The application discloses a rotor self-unfolding unmanned aerial vehicle and relates to the technical field of small unmanned aerial vehicles. The front self-unfolding assembly and the rear self-unfolding assembly are arranged. When in use, the rotor arm is manually pressed inward, the rotor arm drives the transmission gear at the root to synchronously rotate, the transmission gear meshes with the transmission rack to make the transmission rack linearly slide, the energy storage spring is deformed to store elastic potential energy, when the unmanned aerial vehicle is ejected out of the launching cylinder by the ejection thrust in the cylinder, the energy storage spring releases the elastic potential energy to contract and rebound, the transmission rack is pulled to reversely linearly slide, the left and right tooth surfaces of the transmission rack synchronously drive the two sides to reversely rotate, all the rotor arms at the front end and the rear end are synchronously unfolded outward under the driving of the transmission gear, the closed cylinder launching and the high-altitude throwing are realized without unmanned intervention, the traditional special driving motor for unfolding the rotor arm and the matched control circuit are cancelled, the self-weight of the fuselage is reduced, the cabin space is saved, and the endurance of the unmanned aerial vehicle is effectively improved under the same battery condition.

Description

Technical Field

[0001] This invention relates to the field of small unmanned aerial vehicle (UAV) technology, and in particular to a rotor-deployable UAV. Background Technology

[0002] Currently, multi-rotor drones have been widely used in various challenging operational scenarios such as emergency hoisting in mountainous areas, power line inspection in complex terrains, and forest fire fighting.

[0003] Currently, portable drones generally employ an inward-folding rotor arm structure to reduce storage size. A search reveals, for example, a capsule-shaped quadcopter drone disclosed in patent publication number CN116639276B, comprising a fuselage assembly, a quadcopter assembly, and a drone flight control system. The fuselage assembly is based on a capsule shape, with storage slots on the sides for housing the quadcopter assembly. The quadcopter assembly consists of four foldable rotor devices that can be stored in the storage slots. The quadcopter drone of this invention features a capsule-shaped fuselage assembly, which is tubular in shape, significantly reducing wind resistance in the forward direction and enabling high-speed flight. Combined with an electromagnetic shielding coating, it is extremely difficult to detect by radar and other electronic reconnaissance methods. The storage slots on the sides of the fuselage assembly, along with folding motors, enable automatic folding and unfolding of the rotor assembly. Combined with the control of the drone flight control system, it can perform in-flight rotor unfolding and folding actions as well as silent gliding maneuvers, allowing it to evade electronic reconnaissance through gliding. For example, patent publication number CN221091280U discloses an easily foldable drone. This easily foldable drone includes a fuselage body with several connecting mechanisms on it. Each connecting mechanism has a rotor mechanism. Each connecting mechanism includes a connecting seat, a mounting seat, and a connecting arm. The connecting seat is located on the surface of the fuselage body. When the drone needs to be folded, the connecting rod moves away from the connecting seat, and the mounting seat is positioned by a locking mechanism. The movable seat moves along the surface of the connecting arm, moving the movable seat and rotor to the appropriate position. The support rod is rotated to position the movable seat, thereby folding the connecting arm, reducing its footprint, and quickly and easily folding and folding the rotor and related components to meet the user's needs for more convenient carrying, storage, and transportation.

[0004] Based on the above search and combined with existing technology, it was found that existing products have two major defects: Firstly, conventional folding drones require users to manually unfold the rotors after they are folded and stored in the cylindrical storage box in order to take off. When the drone is taken out of the cylindrical storage box, it cannot be manually unfolded in time due to the limited space in the box. The operation steps in the field are cumbersome and delay the progress of the operation.

[0005] Secondly, most drones on the market with automatic wing opening function are equipped with a dedicated small motor to drive the rotor to unfold. The accompanying motor and power supply line will increase the weight of the fuselage, squeeze the space of the onboard battery, shorten the drone's flight time, and the electronic control structure has many components, which will result in a high failure rate in outdoor environments such as humid and dusty conditions, and the manufacturing cost will be relatively high.

[0006] Therefore, a self-deploying rotor drone is proposed to improve the above problems. Summary of the Invention

[0007] The purpose of this application is to provide a self-deploying rotor drone to solve the problems mentioned in the background art, such as manually deploying the rotor arm, cumbersome field operation procedures, delaying the operation progress, and the increased weight of the fuselage, encroachment on the airborne battery space, and shortened flight time of the drone due to the use of a dedicated small motor to drive the rotor deployment.

[0008] To achieve the above objectives, this application provides the following technical solution: a rotor-mounted self-deploying unmanned aerial vehicle, comprising: Rotor-deployable drone frame; The front rotor mechanism includes a front rotor arm and a front self-deploying assembly. The front rotor arm is provided in two sets, and the two sets of front rotor arms are symmetrically installed on opposite sides of the front end of the rotor self-deploying UAV frame. The front self-deploying assembly is installed on the inner side of the rotor self-deploying UAV frame and connected to the two sets of front rotor arms to cause the two sets of front rotor arms to automatically deploy. The rear rotor mechanism includes a rear rotor arm and a rear self-deploying assembly. Two sets of rear rotor arms are provided, and the two sets of rear rotor arms are symmetrically installed on opposite sides of the rear end of the self-deploying rotor drone frame. The rear self-deploying assembly is installed on the inner side of the self-deploying rotor drone frame and is connected to the two sets of rear rotor arms to cause the two sets of rear rotor arms to automatically deploy.

[0009] As a further supplement to this solution, the rotor self-deploying UAV frame includes a front rotor pressure plate, a rear rotor pressure plate, a frame top plate, and a frame bottom plate. The front rotor pressure plate and the rear rotor pressure plate are each provided in two sets. The two sets of front rotor pressure plates are symmetrically and integrally provided on both sides of the front end of the frame base plate, and the two sets of front rotor arms are respectively rotatably mounted on the two sets of front rotor pressure plates. The two sets of rear rotor pressure plates are symmetrically and integrally arranged on both sides of the rear end of the frame base plate, and the two sets of rear rotor arms are respectively rotatably mounted on the two sets of rear rotor pressure plates; The top plate of the frame is horizontally mounted on top of the bottom plate of the frame via a bracket, and a power supply device is installed at the top of the top plate of the frame.

[0010] As a further supplement to this solution, an equipment compartment is reserved between the frame base plate and the frame top plate for assembling the flight control module.

[0011] As a further supplement to this solution, the front self-deploying assembly includes a first transmission group and a front energy storage spring. One end of the front energy storage spring is connected to the frame base plate, and the other end of the front energy storage spring is connected to the front rotor arm through the first transmission group.

[0012] As a further supplement to this solution, the first transmission group includes a front transmission gear and a front transmission rack. There are two sets of front transmission gears, which are fixed to two sets of front rotor arms respectively. The axis of the front transmission gear coincides with the rotation axis of the front rotor arm. The front transmission rack is slidably mounted on the surface of the frame base plate. One end of the front transmission rack is fixed to the front energy storage spring. The front transmission rack meshes with the two sets of front transmission gears.

[0013] As a further supplement to this solution, the rear-mounted self-deploying assembly includes a second transmission group and a rear-end energy storage spring. One end of the rear-end energy storage spring is connected to the frame base plate, and the other end of the rear-end energy storage spring is connected to the rear rotor arm through the second transmission group.

[0014] As a further supplement to this solution, the second transmission group includes a rear transmission rack and a rear transmission gear. There are two sets of rear transmission gears, which are fixed to two sets of rear rotor arms respectively. The axis of the rear transmission gear coincides with the rotation axis of the rear rotor arm. The rear transmission rack is slidably mounted on the surface of the frame base plate. One end of the rear transmission rack is fixed to the rear energy storage spring. The rear transmission rack meshes with the two sets of rear transmission gears.

[0015] As a further supplement to this solution, the front drive rack and the rear drive rack are symmetrically slidably mounted on the upper and lower end faces of the frame base plate, and the front rotor arm and the rear rotor arm are staggered vertically.

[0016] As a further supplement to this solution, both the front drive gear and the rear drive gear are half gears, and both the front drive gear and the rear drive gear are provided with weight reduction holes.

[0017] As a further supplement to this solution, limit stops are installed on both the front rotor pressure plate and the rear rotor pressure plate. The limit stops are used to limit the maximum deployment angle of the front rotor arm and the rear rotor arm.

[0018] In summary, the technical effects and advantages of this invention are as follows: 1. In this invention, by setting up a front-mounted self-deploying component and a rear-mounted self-deploying component, during use, the rotor arm is manually pressed inward, and the rotor arm drives the transmission gear at the root to rotate synchronously. The transmission gear meshes with the transmission rack, causing the transmission rack to slide linearly, thereby pulling the energy storage spring to deform and store elastic potential energy. When the rotor arm is completely close to the fuselage and the outer diameter of the entire aircraft is reduced to its minimum, the UAV is loaded into the launch tube. Relying on the inner wall of the tube to constrain the outer ring of the rotor arm, the spring continues to store energy and the rotor arm is in a retracted and locked state. When the UAV is ejected from the launch tube by the ejection thrust inside the tube, the outer ring limit constraint of the tube wall disappears, the energy storage spring releases elastic potential energy and contracts and rebounds, pulling the transmission rack to slide linearly in the opposite direction. The left and right tooth surfaces of the transmission rack synchronously drive the meshing transmission gears on both sides to rotate in opposite directions. All rotor arms at the front and rear ends are synchronously flipped outward and deployed under the drive of the transmission gears, realizing that the UAV automatically opens all rotor arms the moment it is ejected from the tube, without the need for personnel to manually pry the rotor arms, meeting the requirements of closed tube launch, high-altitude drop and unmanned takeoff.

[0019] 2. In this invention, by using the combination of springs, transmission gears, and transmission racks, compared with traditional rotary-wing drones, the dedicated drive motor and supporting control circuit for rotor arm deployment are eliminated, reducing the weight of the fuselage, saving cabin space, and effectively improving the drone's endurance under the same battery conditions; and because the drone in this solution has a fully mechanical spring transmission gear structure with no electronic components, it is resistant to sand, dust, low temperature, and humid environments, has a low failure rate, and uses interchangeable parts with low processing costs.

[0020] 3. In this invention, by symmetrically sliding the front drive rack and the rear drive rack on the upper and lower end faces of the frame base plate, and by staggering the front rotor arm and the rear rotor arm vertically, the interference between the front rotor mechanism and the rear rotor mechanism during the storage process can be avoided. Furthermore, the front rotor arm and the rear rotor arm are both folded and stored close to the fuselage, making the storage more compact and further reducing the footprint.

[0021] 4. In this invention, by setting both the front and rear transmission gears as half gears and providing weight reduction holes on both the front and rear transmission gears, the overall weight of the fuselage is further reduced while meeting the strength requirements of the transmission structure. This reduces unnecessary flight load, thereby further extending the flight endurance and improving the effective operating time of the UAV, which meets the requirements of lightweight design. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the UAV rotor arm deployment structure of the present invention; Figure 2 This is a schematic diagram of the UAV rotor arm retraction structure of the present invention; Figure 3 This is a schematic diagram of the front rotor mechanism of the present invention; Figure 4 This is a schematic diagram of the rear rotor mechanism of the present invention.

[0024] In the picture: 10. Rotor-deployable drone frame; 101. Front rotor clamping plate; 102. Rear rotor clamping plate; 103. Frame base plate; 104. Power supply unit; 200. Front rotor mechanism; 201. Front rotor arm; 202. Front drive gear; 203. Front drive rack; 204. Front energy storage spring; 300. Rear rotor mechanism; 301. Rear energy storage spring; 302. Rear drive rack; 303. Rear drive gear; 304. Rear rotor arm. Detailed Implementation

[0025] 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 some embodiments of the present invention, and not all embodiments. Based on the embodiments of 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.

[0026] Example 1: Reference Figure 1-4 The illustrated rotary-wing self-deployable drone includes a rotary-wing self-deployable drone frame 10 and a front rotor mechanism 200 and a rear rotor mechanism 300 respectively disposed at the front and rear ends of the rotary-wing self-deployable drone frame 10.

[0027] Among them, such as Figure 1As shown, the rotor self-deploying UAV frame 10 includes a front rotor pressure plate 101, a rear rotor pressure plate 102, a frame top plate, and a frame bottom plate 103. Both the front rotor pressure plate 101 and the rear rotor pressure plate 102 are provided in two sets. The two sets of front rotor pressure plates 101 are symmetrically and integrally arranged on both sides of the front end of the frame bottom plate 103. The front rotor mechanism 200 is mounted on the front rotor pressure plate 101. The two sets of rear rotor pressure plates 102 are symmetrically and integrally arranged on both sides of the rear end of the frame bottom plate 103. The rear rotor mechanism 300 is mounted on the rear rotor pressure plate 102. The frame top plate is horizontally mounted on the top of the frame bottom plate 103 by a bracket. A conventional power supply device 104, such as a lithium battery, is installed at the top of the frame top plate to power all the electrical equipment of the UAV.

[0028] Of course, an equipment compartment is reserved between the frame base plate 103 and the frame top plate for assembling conventional flight control modules, such as mainstream open-source flight control boards on the market, which can meet the general requirements of flight control without the need for additional customized electronic control structures, thus reducing production adaptation costs.

[0029] Among them, such as Figure 1 and Figure 3 As shown, the front rotor mechanism 200 includes a front rotor arm 201 and a front self-deploying assembly. There are two sets of front rotor arms 201, and the two sets of front rotor arms 201 are symmetrically installed on opposite sides of the front end of the rotor self-deploying UAV frame 10. Specifically, the two sets of front rotor arms 201 are rotatably installed on two sets of front rotor pressure plates 101. The front self-deploying assembly is installed on the inner side of the rotor self-deploying UAV frame 10 and connected to the two sets of front rotor arms 201 to cause the two sets of front rotor arms 201 to automatically deploy.

[0030] Regarding the front-mounted self-expanding component, specifically, such as Figure 1 and Figure 3 As shown, the front self-deploying assembly includes a first transmission group and a front energy storage spring 204. One end of the front energy storage spring 204 is connected to the frame base plate 103, and the other end of the front energy storage spring 204 is connected to the front rotor arm 201 through the first transmission group.

[0031] The first transmission group includes a front transmission gear 202 and a front transmission rack 203. There are two sets of front transmission gears 202, which are fixed to two sets of front rotor arms 201 respectively. The axis of the front transmission gear 202 coincides with the rotation axis of the front rotor arm 201. The front transmission rack 203 is slidably mounted on the surface of the frame base plate 103. One end of the front transmission rack 203 is fixed to the front energy storage spring 204. The front transmission rack 203 meshes with the two sets of front transmission gears 202.

[0032] Similarly, such as Figure 1 and Figure 4As shown, the rear rotor mechanism 300 includes a rear rotor arm 304 and a rear self-deploying assembly. Two sets of rear rotor arms 304 are provided, and the two sets of rear rotor arms 304 are symmetrically installed on opposite sides of the rear end of the rotor self-deploying UAV frame 10. Specifically, the two sets of rear rotor arms 304 are rotatably installed on two sets of rear rotor pressure plates 102. The rear self-deploying assembly is installed on the inner side of the rotor self-deploying UAV frame 10 and connected to the two sets of rear rotor arms 304 to cause the two sets of rear rotor arms 304 to automatically deploy.

[0033] Regarding the rear-mounted self-expanding component, specifically, such as Figure 1 and Figure 4 As shown, the rear self-deploying assembly includes a second transmission group and a rear energy storage spring 301. One end of the rear energy storage spring 301 is connected to the frame base plate 103, and the other end of the rear energy storage spring 301 is connected to the rear rotor arm 304 through the second transmission group.

[0034] The second transmission group includes a rear transmission rack 302 and a rear transmission gear 303. There are two sets of rear transmission gears 303, which are fixed to two sets of rear rotor arms 304 respectively. The axis of the rear transmission gear 303 coincides with the rotation axis of the rear rotor arm 304. The rear transmission rack 302 is slidably mounted on the surface of the frame base plate 103. One end of the rear transmission rack 302 is fixed to the rear energy storage spring 301. The rear transmission rack 302 meshes with the two sets of rear transmission gears 303.

[0035] Both the front-end energy storage spring 204 and the rear-end energy storage spring 301 can be conventional energy storage springs. In this embodiment, a tension spring is used. During use, the rotor arm is manually pressed inward, and the rotor arm drives the transmission gear at the root to rotate synchronously. The transmission gear meshes with the transmission rack, causing the transmission rack to slide linearly, thereby pulling the energy storage spring to produce a tensile deformation and store elastic potential energy. When the rotor arm is completely close to the fuselage and the outer diameter of the entire machine is reduced to its minimum, the UAV is loaded into the launch tube. The inner wall of the tube constrains the outer ring of the rotor arm, keeping the tension spring continuously stretched and storing energy, and the rotor arm in a retracted and locked state. After retraction, the rotor arm is close to the fuselage, making the whole machine compact and suitable for loading into a standard portable launch tube.

[0036] When the drone is ejected from the launch tube by the ejection force inside the tube, the outer ring limit constraint of the tube wall disappears, the energy storage spring releases elastic potential energy and contracts and rebounds, pulling the transmission rack to slide in the opposite direction in a straight line; the left and right tooth surfaces of the transmission rack synchronously drive the meshing transmission gears on both sides to rotate in the opposite direction, and all the rotor arms at the front and rear ends synchronously flip outward and unfold under the drive of the transmission gears.

[0037] Based on the above-mentioned structural configuration, the drone automatically opens all rotor arms the instant it leaves the launch tube, without the need for manual operation of the rotor arms, thus meeting the requirements for unmanned takeoff for sealed launch and high-altitude drop.

[0038] Compared to traditional rotary-wing drones, this solution eliminates the need for a dedicated drive motor and control circuitry for rotor arm deployment, reducing the drone's weight, saving cabin space, and effectively improving the drone's range under the same battery conditions.

[0039] In addition, due to the fully mechanical spring-driven gear structure of the UAV in this solution, there are no electronic components, making it resistant to sand, dust, low temperature and humid environments, with a low failure rate, and the parts are universal and the processing cost is low.

[0040] To avoid interference between the front rotor mechanism 200 and the rear rotor mechanism 300 during storage, such as Figure 1 and Figure 2 As shown, the front drive rack 203 and the rear drive rack 302 are symmetrically slidably mounted on the upper and lower end faces of the frame base plate 103, respectively, and the front rotor arm 201 and the rear rotor arm 304 are staggered vertically.

[0041] In addition, to further reduce the overall weight of the airframe, both the front drive gear 202 and the rear drive gear 303 are half gears, and both the front drive gear 202 and the rear drive gear 303 are provided with weight reduction holes. Under the premise of meeting the strength of the transmission structure, the overall weight of the airframe is further reduced, and unnecessary flight load is reduced.

[0042] Both the front rotor pressure plate 101 and the rear rotor pressure plate 102 are equipped with limit stops. The limit stops are used to limit the maximum deployment angle of the front rotor arm 201 and the rear rotor arm 304. When the rotor arm rotates to the horizontal working position, the side wall of the rotor arm abuts against the limit stop of the fuselage and stops rotating. The rotor arm is fixed in the flight position, and the airborne motor drives the blades to rotate and take off.

[0043] When in use, after the rotor arm rotates and unfolds to the preset angle, the end will be blocked by the corresponding limit stop, so that the rotor arm stops at the working angle and stops rotating, ensuring accurate unfolding position. No additional locking structure is needed to maintain the unfolded state, and the rotor can be started and flown normally after unfolding. When retracting the rotor arm, only a slight inward rotational force needs to be applied to the rotor arm. The compressed spring causes the transmission rack to move in the opposite direction, which can retract the rotor arm to the side of the fuselage and complete the retraction. The retraction operation can be repeated.

[0044] As can be seen from the above, the overall structure does not require an additional dedicated drive motor and power supply line. It can automatically unfold by relying on spring energy storage, which reduces the use of electronic control components, lowers the weight of the fuselage and the probability of failure, and compresses manufacturing costs. At the same time, it reserves more airborne space for battery installation, effectively extending the drone's flight time and meeting the needs of use in complex outdoor environments.

[0045] Among them, the front rotor pressure plate 101, rear rotor pressure plate 102, frame top plate, frame bottom plate 103, bracket, front rotor arm 201, front drive gear 202, front drive rack 203, rear drive rack 302, rear drive gear 303, rear rotor arm 304, and limit stop are all made of high-strength lightweight materials, such as carbon fiber composite materials or high-strength engineering plastics. While ensuring that the overall structural strength meets the requirements of flight operation, it further controls the overall weight of the fuselage, which is in line with the development direction of lightweight design of UAVs and is also more suitable for the weight requirements of special launch scenarios such as tube firing and drop. In addition, the above-mentioned structural surfaces are also coated with anti-rust or anti-corrosion coatings, which can further improve the weather resistance of the components, extend their service life in complex and harsh outdoor environments, and reduce the frequency of maintenance and replacement.

[0046] The working principle of this invention is as follows: When in use, the rotor arm is manually pressed inward, which drives the transmission gear at the root to rotate synchronously. The transmission gear meshes with the transmission rack, causing the transmission rack to slide linearly, thereby pulling the energy storage spring to produce a tensile deformation and store elastic potential energy. When the rotor arm is completely close to the fuselage and the outer diameter of the entire aircraft is reduced to its minimum, the UAV is loaded into the launch tube. Relying on the constraint of the inner wall of the tube on the outer ring of the rotor arm, the tension spring is kept stretched and stored, and the rotor arm is in a retracted and locked state.

[0047] When the drone is ejected from the launch tube by the ejection force inside the tube, the outer ring limit constraint of the tube wall disappears, the energy storage spring releases elastic potential energy and contracts and rebounds, pulling the transmission rack to slide in the opposite direction in a straight line; the left and right tooth surfaces of the transmission rack synchronously drive the meshing transmission gears on both sides to rotate in the opposite direction, and all the rotor arms at the front and rear ends synchronously flip outward and unfold under the drive of the transmission gears. Once the rotor arm has rotated and extended to the preset angle, its end will be blocked by a limit stop at the corresponding position, causing the rotor arm to stop at the working angle and no longer rotate. This ensures accurate deployment and maintains the deployed state without the need for an additional locking structure. After deployment, the rotor can be started and flown normally.

[0048] Example 2:

[0049] Unlike Embodiment 1, this embodiment uses a single transmission rack with multiple sets of transmission gears meshing on both sides, so that the front, rear, left and right rotor arms can be deployed synchronously and in unison. The rotor arms open in a consistent manner, and there will be no problem of one-sided rotor arm jamming or misalignment.

[0050] Example 3:

[0051] Unlike Embodiments 1 and 2, the energy storage spring in this embodiment is a compression spring. In use, the rotor arm is manually pressed inward, and the rotor arm drives the transmission gear at the root to rotate synchronously. The transmission gear meshes with the transmission rack, causing the transmission rack to slide linearly, thereby pulling the energy storage spring to produce compression deformation and store elastic potential energy. When the rotor arm is completely close to the fuselage and the outer diameter of the whole machine is reduced to its minimum, the UAV is installed in the launch tube. Relying on the constraint of the inner wall of the tube on the outer ring of the rotor arm, the tension spring is kept in a state of continuous compression and energy storage, and the rotor arm is in a retracted and locked state.

[0052] When the drone is ejected from the launch tube by the ejection force inside the tube, the outer ring limit constraint of the tube wall disappears, the energy storage spring releases elastic potential energy and contracts and rebounds, pushing the transmission rack to slide in the opposite direction in a straight line; the left and right tooth surfaces of the transmission rack synchronously drive the meshing transmission gears on both sides to rotate in the opposite direction, and all the rotor arms at the front and rear ends synchronously flip outward and unfold under the drive of the transmission gears.

[0053] Example 4:

[0054] Unlike Embodiments 1, 2, and 3, the frame base plate 103 in this embodiment has a built-in conventional mechanical buckle to replace the cylinder wall limit: the outer wall limit of the launch tube is eliminated, and a built-in buckle is set in the fuselage to lock the retracted rotor arm. The instantaneous inertial release during ejection unlocks the buckle, and the spring drives the transmission rack and pinion to open the wing. The bare machine can be stored without relying on the launch tube limit.

[0055] It should be noted that the specific models and specifications of the electrical equipment involved in this solution need to be selected and determined according to the actual specifications of the device. The specific selection and calculation methods adopt the existing technology in this field, so they will not be described in detail here. The power supply and principle of the electrical equipment involved are clear to those skilled in the art, and will not be described in detail here.

[0056] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A self-deploying rotor-type unmanned aerial vehicle, characterized in that, include: Rotor-deployable unmanned aerial vehicle frame (10); The front rotor mechanism (200) includes a front rotor arm (201) and a front self-deploying assembly. The front rotor arm (201) is provided in two sets, and the two sets of front rotor arms (201) are symmetrically installed on opposite sides of the front end of the rotor self-deploying UAV frame (10). The front self-deploying assembly is installed on the inner side of the rotor self-deploying UAV frame (10) and connected to the two sets of front rotor arms (201) to cause the two sets of front rotor arms (201) to automatically deploy. The rear rotor mechanism (300) includes a rear rotor arm (304) and a rear self-deploying assembly. The rear rotor arm (304) is provided in two sets, and the two sets of rear rotor arms (304) are symmetrically installed on opposite sides of the rear end of the rotor self-deploying UAV frame (10). The rear self-deploying assembly is installed on the inner side of the rotor self-deploying UAV frame (10) and connected to the two sets of rear rotor arms (304) to cause the two sets of rear rotor arms (304) to automatically deploy.

2. The self-deploying rotor drone according to claim 1, characterized in that: The rotor self-deployable UAV frame (10) includes a front rotor pressure plate (101), a rear rotor pressure plate (102), a frame top plate, and a frame bottom plate (103). The front rotor pressure plate (101) and the rear rotor pressure plate (102) are each provided in two sets. The two sets of front rotor pressure plates (101) are symmetrically and integrally provided on both sides of the front end of the frame base plate (103), and the two sets of front rotor arms (201) are respectively rotatably mounted on the two sets of front rotor pressure plates (101). The two sets of rear rotor pressure plates (102) are symmetrically and integrally arranged on both sides of the rear end of the frame base plate (103), and the two sets of rear rotor arms (304) are respectively rotatably mounted on the two sets of rear rotor pressure plates (102); The top plate of the frame is horizontally mounted on the top of the bottom plate of the frame (103) by a bracket, and a power supply device (104) is installed at the top of the top plate of the frame.

3. The self-deploying rotor drone according to claim 2, characterized in that: An equipment compartment is reserved between the frame base plate (103) and the frame top plate for assembling the flight control module.

4. The self-deploying rotor drone according to claim 1, characterized in that: The front self-deploying assembly includes a first transmission group and a front energy storage spring (204). One end of the front energy storage spring (204) is connected to the frame base plate (103), and the other end of the front energy storage spring (204) is connected to the front rotor arm (201) through the first transmission group.

5. A self-deploying rotor-type unmanned aerial vehicle according to claim 4, characterized in that: The first transmission group includes a front transmission gear (202) and a front transmission rack (203). There are two sets of front transmission gears (202). The two sets of front transmission gears (202) are fixed to the two sets of front rotor arms (201) respectively. The axis of the front transmission gear (202) coincides with the rotation axis of the front rotor arm (201). The front transmission rack (203) is slidably mounted on the surface of the frame base plate (103). One end of the front transmission rack (203) is fixed to the front energy storage spring (204). The front transmission rack (203) meshes with the two sets of front transmission gears (202).

6. A self-deploying rotor unmanned aerial vehicle according to claim 4, characterized in that: The rear self-deploying assembly includes a second transmission group and a rear energy storage spring (301). One end of the rear energy storage spring (301) is connected to the frame base plate (103), and the other end of the rear energy storage spring (301) is connected to the rear rotor arm (304) through the second transmission group.

7. A self-deploying rotor unmanned aerial vehicle according to claim 6, characterized in that: The second transmission group includes a rear transmission rack (302) and a rear transmission gear (303). There are two sets of rear transmission gears (303). The two sets of rear transmission gears (303) are fixed to the two sets of rear rotor arms (304) respectively, and the axis of the rear transmission gear (303) coincides with the rotation axis of the rear rotor arm (304). The rear transmission rack (302) is slidably mounted on the surface of the frame base plate (103). One end of the rear transmission rack (302) is fixed to the rear energy storage spring (301). The rear transmission rack (302) meshes with the two sets of rear transmission gears (303).

8. A self-deploying rotor unmanned aerial vehicle according to claim 7, characterized in that: The front drive rack (203) and the rear drive rack (302) are symmetrically slidably mounted on the upper and lower end faces of the frame base plate (103), and the front rotor arm (201) and the rear rotor arm (304) are staggered vertically.

9. A self-deploying rotor unmanned aerial vehicle according to claim 7, characterized in that: Both the front drive gear (202) and the rear drive gear (303) are half gears, and both the front drive gear (202) and the rear drive gear (303) are provided with weight reduction holes.

10. A self-deploying rotor unmanned aerial vehicle according to claim 7, characterized in that: Limiting stops are installed on both the front rotor pressure plate (101) and the rear rotor pressure plate (102), and the limiting stops are used to limit the maximum deployment angle of the front rotor arm (201) and the rear rotor arm (304).

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