Distributed lift system vertical take-off and landing fixed-wing unmanned aerial vehicle without aileron

Abstract

The utility model relates to fixed wing unmanned plane technical field especially, more particularly to a kind of distributed lift system without rudder vertical take-off and landing fixed wing unmanned plane, including fuselage, further including anti-deviation component, the anti-deviation component includes the first filter air hole of symmetric setting in the side of fuselage, the drainage angle of setting in the top of fuselage, the second filter air hole of symmetric setting in the other side of fuselage and the spoiler component of setting in the side wall of fuselage.The utility model is through the setting of first filter air hole and drainage angle, when unmanned plane takes off, first filter air hole and second filter air hole will improve the pass rate of airflow passing through fuselage, and then reduce the deflection phenomenon of fuselage during take-off, and drainage angle can quickly divide airflow when fuselage takes off, so that airflow passes through first filter air hole and second filter air hole, further reduce the deviation of fuselage due to airflow interference, to reduce the deviation of fuselage when taking off.

Description

Technical Field

[0001] This utility model relates to the field of fixed-wing unmanned aerial vehicle (UAV) technology, and in particular to a rudderless vertical take-off and landing fixed-wing UAV with a distributed lift system. Background Technology

[0002] Fixed-wing unmanned aerial vehicles (UAVs) are a type of UAV with fixed wings whose outer wing sweep angle can be automatically or manually adjusted according to speed. Due to their excellent functionality and modular integration, they are now widely used in surveying, geology, petroleum, agriculture, and forestry, and have broad market prospects. Distributed lift systems utilize multi-segment wings, including at least a main wing and trailing-edge flaps, with optional leading-edge flaps. Ducted fan propellers are mounted side-by-side on the upper surface of the main wing's tail. In lift-enhancing mode, the trailing-edge flaps open, forming a high-speed jet airfoil that generates significant lift.

[0003] Before use, vertical take-off and landing fixed-wing drones are usually placed on a platform or in a box far from the ground. They are then manually adjusted by staff before taking off. Due to the unfavorable airflow, drones with current technology may tilt during take-off, causing their take-off trajectory to deviate. Furthermore, during landing, landing errors can cause the fuselage and the bottom of the fixed wings to scrape against the platform or box, which can easily lead to damage to the fuselage.

[0004] To address this, we designed a distributed lift system for a rudderless vertical takeoff and landing fixed-wing UAV. Utility Model Content

[0005] The purpose of this invention is to solve the problem of displacement and scraping of the fuselage and fixed wing caused by airflow in existing technologies, and to propose a distributed lift system for a rudderless vertical take-off and landing fixed-wing UAV.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A distributed lift system for a rudderless vertical takeoff and landing fixed-wing unmanned aerial vehicle (UAV) includes a fuselage, several rudderless fixed wings mounted on the sidewalls of the fuselage, brushless motors mounted on the rudderless fixed wings, and propulsion fan blades mounted on the brushless motors. Anti-drift components for adjusting takeoff drag are located on both sides of the fuselage. Aerodynamic disturbance components for disrupting airflow on both sides of the fuselage to adjust the fuselage's trajectory in the air are also located on both sides of the fuselage. A first anti-scratch component is located at the bottom of each brushless motor for protection. A second anti-scratch component is located at the bottom of each rudderless fixed wing for protecting the connection between the rudderless fixed wing and the fuselage. A third anti-scratch component is also located at the bottom of each rudderless fixed wing for protection.

[0008] Preferably, the anti-deviation component includes a first air filter hole symmetrically arranged on one side of the fuselage, a second air filter hole symmetrically arranged on the other side of the fuselage, and a guide angle arranged on the top of the fuselage.

[0009] Preferably, the spoiler assembly includes a fixed track symmetrically arranged on the side wall of the fuselage, a third electric shaft arranged on the inner wall of the fixed track, and an electric spoiler plate arranged on the end of the third electric shaft away from the fixed track.

[0010] Preferably, the fuselage is provided with a connecting assembly, which includes a connector disposed at the end of the rudderless fixed wing and a second electric shaft fixedly connected to the output end of the brushless motor.

[0011] Preferably, the anti-scratch component includes a base disposed at the bottom of the connector and a second anti-scratch strip disposed at the bottom of the base.

[0012] Preferably, the anti-scratch component two includes several first anti-scratch rubber strips disposed on the bottom of the fuselage and several isolation plates disposed on the bottom of the rudderless fixed wing.

[0013] Preferably, the machine body is provided with an insertion assembly, which includes an angled body symmetrically arranged on the side wall of the machine body, an insertion plate arranged at the bottom of the angled body, and an insertion plate rotatably arranged outside the first electric shaft, wherein the first electric shaft is connected to the outside of the angled body.

[0014] Preferably, the fuselage is provided with a control component, which includes a flight control module disposed on the top of the fuselage for controlling the flight of the fuselage.

[0015] Preferably, the anti-scratch assembly includes multiple anti-collision bodies disposed at the bottom of the rudderless fixed wing, a thickened layer disposed at the end of the anti-collision body away from the rudderless fixed wing, and mounting studs disposed at the end of the anti-collision body near the rudderless fixed wing.

[0016] Preferably, the first air filter hole is provided with an anti-clogging component, which includes an anti-clogging body disposed in the first air filter hole, a third air filter hole disposed in the anti-clogging body, a sleeve disposed on the anti-clogging body, an extension column disposed on the sleeve, a wind-breaking cone disposed on the extension column at one end away from the sleeve, and a blocking blade disposed at the end of the extension column away from the wind-breaking cone.

[0017] The beneficial effects of this utility model are as follows:

[0018] 1. By setting the first air filter and the air diversion angle, this utility model can improve the airflow throughput of the UAV when it takes off. The first air filter and the second air filter will improve the airflow throughput of the fuselage, thereby reducing the deflection of the fuselage during takeoff. The air diversion angle can quickly divide the airflow when the fuselage takes off, allowing the airflow to pass through the first air filter and the second air filter, further reducing the deflection of the fuselage caused by airflow interference, thereby reducing the deflection of the fuselage during takeoff.

[0019] 2. By setting up a first anti-scratch rubber strip and a second anti-scratch rubber strip, when the fuselage is gradually descending while maintaining a vertical position, the second anti-scratch rubber strip set on the rudderless fixed wing can reduce the friction with the housing and platform, thereby improving the safety of the rudderless fixed wing. At the same time, since the fuselage is the component that first contacts the housing and platform, the first anti-scratch rubber strip can reduce the friction with the fuselage in the first instance. In addition, the first anti-scratch rubber strip can rebound the pressure generated by the fuselage's descent due to its own elasticity, and keep the fuselage, which is under impact, stable, further reducing the probability of friction with the fuselage.

[0020] 3. By setting up a collision protection body, this utility model can effectively reduce the frictional damage to the bottom of the fixed wing when the fuselage descents vertically and the bottom of the fixed wing collides with tree branches and stones on the predetermined path. In addition, the thickened layer on the collision protection body can effectively improve the collision protection life and further reduce the friction coefficient of the bottom of the fixed wing, thereby improving the service life of the fixed wing.

[0021] 4. By setting up the wind-breaking cone and the arresting blade, the airflow passes through the first air filter hole and reduces the wind resistance when the fuselage takes off vertically. Due to the different takeoff environment of the fuselage, the wind-breaking cone and the arresting blade can effectively prevent debris from clogging the first air filter hole, which would affect the takeoff of the fuselage and thus affect the wind resistance. At the same time, the wind-breaking cone can effectively divide the airflow passing through the first air filter hole, so that the airflow passes through the arresting blade evenly and reduces the drag of the fuselage. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of a distributed lift system for a rudderless vertical take-off and landing fixed-wing UAV proposed in this utility model;

[0023] Figure 2 This is a bottom view of a rudderless vertical take-off and landing fixed-wing UAV with a distributed lift system proposed in this utility model.

[0024] Figure 3 This invention proposes a distributed lift system for a rudderless vertical takeoff and landing fixed-wing unmanned aerial vehicle. Figure 2 Enlarged view of the structure of the Chinese A-label;

[0025] Figure 4This is a side view of a rudderless vertical take-off and landing fixed-wing UAV with a distributed lift system proposed in this utility model.

[0026] Figure 5 This invention proposes a distributed lift system for a rudderless vertical takeoff and landing fixed-wing unmanned aerial vehicle. Figure 4 Enlarged view of the structure of the Chinese B-number;

[0027] Figure 6 This is a head-up view of a distributed lift system vertical take-off and landing fixed-wing UAV with no control surfaces proposed in this utility model.

[0028] Figure 7 This invention presents a collision avoidance structure diagram for a distributed lift system rudderless vertical take-off and landing fixed-wing UAV.

[0029] Figure 8 This invention presents a structural diagram of an anti-blocking body for a distributed lift system, a rudderless vertical take-off and landing fixed-wing UAV.

[0030] In the diagram: 1. Fuselage; 101. Flight control module; 102. First air filter; 103. Drain angle; 104. Angled body; 105. First electric shaft; 106. Insert plate; 107. Second air filter; 108. First anti-scratch rubber strip; 2. Controlless fixed wing; 201. Isolation plate; 3. Connector; 301. Brushless motor; 302. Second electric shaft; 303. Propulsion fan blade; 304. Second anti-scratch rubber strip; 4. Fixed track; 401. Third electric shaft; 402. Electric spoiler; 5. Collision protector; 501. Thickened layer; 502. Mounting stud; 6. Anti-clogging body; 601. Third air filter; 602. Sleeve; 603. Extension column; 604. Wind-breaking cone; 605. Arresting blade. Detailed Implementation

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the protection scope of the present utility model.

[0032] Reference Figures 1-8A distributed lift system for a rudderless vertical take-off and landing fixed-wing UAV includes a fuselage 1, several rudderless fixed wings 2 mounted on the sidewalls of the fuselage 1, brushless motors 301 mounted on the rudderless fixed wings 2, and propulsion fan blades 303 mounted on the brushless motors 301. It also includes an anti-deviation component, which is mainly mounted on the fuselage 1 and ensures that the fuselage 1 maintains airflow during take-off and landing, reducing the wind resistance of the fuselage 1 and thus reducing the deviation of the fuselage 1 during take-off and landing, thereby increasing the stability of the fuselage 1 during take-off and landing.

[0033] When staff need to use the drone, they should first ensure that the fuselage 1 is tightly connected to the four rudderless fixed wings 2 and that there is no looseness. Then, they should ensure that the brushless motor 301 and the propulsion fan blade 303 at the end of the rudderless fixed wings 2 are connected and can operate normally. This will prevent the drone from failing to fly or crashing during takeoff due to the rudderless fixed wings 2 becoming loose, which could cause incalculable losses.

[0034] It should be noted that fuselage 1 is the mid-section structure of a fixed-wing UAV in the existing technology, and is a model that can take off and land vertically;

[0035] The term "rudderless fixed wing" refers to existing technology and specifically to a fixed-wing aircraft that achieves flight control through other innovative means rather than relying on traditional aerodynamic control surfaces.

[0036] The brushless motor 301 is an existing technology and is a high-efficiency electric motor that achieves operation through electronic commutation. It is widely used in drones, electric vehicles, industrial equipment and other fields.

[0037] The propulsion blade 303 is a core component of the UAV's power system, and its design directly affects flight efficiency, stability, and noise levels.

[0038] Specifically, anti-drift components are provided on both sides of the fuselage 1 to adjust the wind resistance of the fuselage 1 during takeoff; the anti-drift components include a first air filter 102 symmetrically arranged on one side of the fuselage 1, a deflector 103 arranged on the top of the fuselage 1, and a second air filter 107 symmetrically arranged on the other side of the fuselage 1.

[0039] Furthermore, spoiler components are also provided on both sides of the fuselage 1 to adjust the direction of the fuselage 1 in the air; the spoiler components include fixed rails 4 symmetrically arranged on the side walls of the fuselage 1, electric spoilers 402 arranged on the fixed rails 4, and a third electric shaft 401 rotatably connected to the electric spoilers 402.

[0040] When the operator takes off the drone, the two first air filter holes 102 on the front side of the fuselage 1 will prioritize the delivery of airflow. After the fuselage 1 is one meter off the ground, the surrounding airflow flows to both sides of the fuselage 1 with the blasting of the propulsion fan blades 303. At this time, the two second air filter holes 107 on the rear side of the fuselage 1 will smoothly pass through the airflow, thereby achieving the effect of reducing the wind resistance of the fuselage 1, improving the stability of the drone during takeoff, and reducing the deflection phenomenon during takeoff and landing.

[0041] During takeoff, staff can control the direction of the electric spoiler 402 via the drone's control handle, thereby converting the interference of the lateral airflow on the fuselage 1 during takeoff and landing into vertical airflow to assist the drone's takeoff and landing.

[0042] It should be noted that the electric spoiler 402 is existing technology. The staff mainly operate it remotely through the drone control handle. It is an important device for the aerodynamic control of the drone. It achieves flight attitude adjustment or deceleration by partially disrupting the lift of the wing.

[0043] The fixed track 4 and the third electric shaft 401 are auxiliary components. The fixed track 4 is made of aluminum alloy and is fixed to the side wall of the fuselage 1 by rivets. The third electric shaft 401 is an electrically operated structure, mainly operated by the drone's control handle. The third electric shaft 401 mainly drives the electric spoiler 402 to move under the restriction of the fixed track 4, thereby enabling the drone to be used in different scenarios.

[0044] Furthermore, the bottom of the brushless motor 301 is provided with an anti-scratch component to protect the outer wall of the brushless motor 301; the anti-scratch component includes a second anti-scratch strip 304 provided at the bottom of the connector 3 and a base fixedly connected to the second anti-scratch strip 304.

[0045] The fuselage 1 is provided with a connecting assembly, which includes a connecting body 3 located at the end of the rudderless fixed wing 2 and a second electric shaft 302 fixedly connected to the output end of the brushless motor 301.

[0046] Since the brushless motor 301 needs to be fixed on the rudderless fixed wing 2, the connecting body 3 needs to be fixed to the end of the rudderless fixed wing 2 with rivets first. Then, the brushless motor 301 is placed inside the connecting body 3, and a washer is placed on the outer ring of the brushless motor 301 to ensure the stability of the brushless motor 301 inside the connecting body 3. Then, the second electric shaft 302 is installed on the output end of the brushless motor 301. The purpose is to avoid the output end of the brushless motor 301 directly contacting the propulsion blade 303. The transmission efficiency is improved by the second electric shaft 302, thereby improving the rotation efficiency of the propulsion blade 303 on the brushless motor 301.

[0047] When the drone is landing, the second anti-scratch rubber strip 304 at the bottom of the rudderless fixed wing 2 can prevent it from touching the ground. At the same time, when the second anti-scratch rubber strip 304 touches the ground, it will spread out in all directions. The spread rubber strip can increase the contact area, thereby ensuring the stability of the rudderless fixed wing 2 against the ground.

[0048] It should be noted that the second anti-scratch rubber strip 304 is made of existing rubber material and is cylindrical with a cross-shaped slit in the middle. Its bottom is fixed to the bottom of the connecting body 3 by a base. The cross-shaped slit allows the rubber strip to spread outwards after contacting the ground. The base is an auxiliary component that provides basic support for the second anti-scratch rubber strip 304 when it contacts the ground. Furthermore, the rubber strip will not directly contact the connecting body 3 with the ground after it spreads out, which further improves the safety of the rudderless fixed wing 2.

[0049] Furthermore, the bottom of the rudderless fixed wing 2 is provided with an anti-scratch component 2 to protect the connection between the rudderless fixed wing 2 and the fuselage 1; the anti-scratch component 2 includes several first anti-scratch rubber strips 108 provided at the bottom of the fuselage 1 and several isolation plates 201 provided at the bottom of the rudderless fixed wing 2.

[0050] Since the rudderless fixed wing 2 is set on the side wall of the fuselage 1 and is vertically horizontal in the center of the side wall of the fuselage 1, the take-off and landing of the UAV are all based on the fuselage 1 prioritizing moving away from and contacting the ground. With the setting of the first anti-scratch rubber strip 108, the bottom of the fuselage 1 can be indirectly prevented from scraping against the ground, which would cause damage to the surface of the fuselage 1 and affect its service life.

[0051] It should be noted that the first anti-scratch rubber strip 108 is a rubber material in the prior art. It is fixed to the bottom of the machine body 1 by rivets and arranged in a ring shape, which can effectively cover the bottom of the machine body 1 and complete the anti-scratch work.

[0052] Furthermore, the fuselage 1 is provided with an insertion assembly, which includes an angled body 104 symmetrically arranged on the side wall of the fuselage 1, an insertion plate 106 arranged at the bottom of the angled body 104, and a first electric shaft 105 that rotates the insertion plate 106 on the angled body 104.

[0053] When the drone needs to land on soft ground, the first electric shaft 105 can be activated by the drone control handle, causing the insertion plate 106 on the angled body 104 to rotate 180 degrees and stick tightly to the fuselage 1. After the drone lands, the insertion plate 106, being perpendicular to the side wall of the fuselage 1, will directly insert into the soft ground. Then, in conjunction with the first anti-scratch rubber strip 108, the stability of the drone after landing is improved.

[0054] It should be noted that the insertion plate 106 is an auxiliary component, made of existing aluminum alloy material, and its end is cone-shaped, which makes it easier to insert into soft ground.

[0055] The fuselage 1 is equipped with a control component, which includes a flight control module 101 located on the top of the fuselage 1. The flight control module 101 on the fuselage 1 is existing technology and is the "brain" of the UAV, responsible for core functions such as flight attitude stabilization, navigation control, and mission execution.

[0056] Furthermore, the bottom of the rudderless fixed wing 2 is also provided with an anti-scratch component 3 to protect the bottom of the rudderless fixed wing 2; the anti-scratch component 3 includes multiple anti-collision bodies 5 set at the bottom of the rudderless fixed wing 2, a thickened layer 501 set on the anti-collision body 5 at the end away from the rudderless fixed wing 2, and a mounting stud 502 set on the anti-collision body 5 at the end close to the rudderless fixed wing 2.

[0057] Before takeoff, the fuselage 1 and the rudderless fixed wing 2 need to have multiple collision protection bodies 5 installed on the bottom of the rudderless fixed wing 2. The mounting studs 502 on the bottom of the collision protection body 5 need to be installed on the pre-drilled holes on the bottom of the rudderless fixed wing 2 and tightened by manual rotation.

[0058] When the fuselage 1 descends vertically with the assistance of the fixed wing 2, if the bottom of the fixed wing 2 is accidentally bumped during the vertical descent, the anti-collision body 5 can effectively isolate the impact force from damaging the fixed wing 2. The thickened layer 501 on the surface of the anti-collision body 5 can effectively improve the service life of the anti-collision body 5, and multiple linearly arranged anti-collision bodies 5 can be effectively laid on the bottom of the fixed wing 2 to form a protective measure.

[0059] It should be noted that the holes pre-drilled at the bottom of the rudderless fixed wing 2 are existing threaded holes, which are not explicitly marked in the text;

[0060] The entire impact protector 5 is made of soft rubber, and the thickened layer 501 is made by adding a layer of hard rubber on top of the soft rubber to extend the service life of the soft rubber on the side that is frequently in contact with objects.

[0061] In addition, the first air filter hole 102 is provided with an anti-clogging component, which includes an anti-clogging body 6 disposed in the first air filter hole 102, a third air filter hole 601 disposed in the anti-clogging body 6, a sleeve 602 disposed on the anti-clogging body 6, an extension column 603 disposed on the sleeve 602, a wind-breaking cone 604 disposed on the extension column 603 at one end away from the sleeve 602, and a blocking blade 605 disposed on the extension column 603 at one end away from the wind-breaking cone 604.

[0062] During takeoff, airflow passes through the first air filter 102, reducing the drag of the fuselage 1 and thus improving the efficiency of the fuselage 1 during takeoff. Since the diameter of the first air filter 102 is smaller than that of the second air filter 107, although it is beneficial for gas to pass through and reduce drag, during takeoff, the fuselage 1 is affected by the propulsion of the propeller blades 303, which causes dust and lint in the air to approach the fuselage 1 and enter the first air filter 102, causing internal blockage and reducing the drag of the fuselage 1.

[0063] Before takeoff, staff need to check whether the extension column 603 on the anti-blocking body 6 inside the first air filter 102 is loose. If it is loose, it needs to be tightened. Then, during takeoff, the airflow can quickly pass through the arresting blade 605 under the cutting of the wind-breaking cone 604, and the arresting blade 605 evenly distributes the airflow. When the fuselage 1 lands, the fuselage 1 needs to fall downwards towards the arresting blade 605. At this time, the arresting blade 605 divides the falling airflow. At the same time, the multiple blades of the arresting blade 605 can block dust and velvety particles, further improving the takeoff and landing efficiency of the fuselage 1.

[0064] It should be noted that the anti-blocking body 6 is an auxiliary component, and both the anti-blocking body 6 and the sleeve 602 are integrally formed with the first air filter hole 102, and the third air filter hole 601 on the anti-blocking body 6 was opened later.

[0065] The extension post 603 is an existing screw, with a thread in its middle section that is compatible with the inside of the sleeve 602. It can be fixed simply by passing one end of the extension post 603 through the sleeve 602 and then rotating it.

[0066] The working principle of this utility model is as follows:

[0067] When staff need to start the drone for surveying operations, they use the drone control handle to start the brushless motor 301. The propulsion fan blades 303, powered by the second electric shaft 302, drive the fuselage 1 upwards. During takeoff, the first and second air filters 102 and 107 reduce wind resistance around the fuselage 1, allowing airflow to pass quickly and increasing takeoff efficiency. Subsequently, the third electric shaft 401 can be operated to change the drone's flight direction and speed using the electric spoiler 402. During ascent, the deflector angle 103 improves the drone's wind-breaking efficiency. Simultaneously, the drone can also form a... The airflow trail increases the efficiency of the fuselage 1's flight. When the drone needs to land, the second anti-scratch strip 304 at the bottom of the connector 3 prevents the fixed wing 2 from scraping against the ground. Simultaneously, the first anti-scratch strip 108 at the bottom of the fuselage 1 increases the contact area, reducing the impact of landing and mitigating the impact, thus protecting the bottom of the fuselage 1 from scraping. If landing on soft ground, the first electric shaft 105 can be operated to rotate the insertion plate 106, making it fit tightly against the side wall of the fuselage 1. After the fuselage 1 contacts the soft ground, the insertion plate 106 can quickly insert into the soft ground for a fixing effect, thereby improving the stability of the fuselage 1. Through the setting of the first air filter 102 and the airflow guide angle 103, when the drone takes off, the first air filter 102 and the second air filter 107 increase the airflow throughput through the fuselage 1, thereby reducing the deflection phenomenon of the fuselage 1 during takeoff.

[0068] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A distributed lift system for a rudderless vertical takeoff and landing fixed-wing unmanned aerial vehicle (UAV), comprising a fuselage (1), a plurality of rudderless fixed wings (2) disposed on the sidewalls of the fuselage (1), brushless motors (301) disposed on the rudderless fixed wings (2), and propulsion blades (303) disposed on the brushless motors (301), characterized in that, The fuselage (1) is provided with anti-drift components on both sides for adjusting the takeoff wind resistance of the fuselage (1). The fuselage (1) is also provided with turbulence components on both sides for disturbing the airflow on both sides of the fuselage (1) to adjust the direction of the fuselage (1) in the air. The brushless motor (301) is provided with anti-scratching component one for protection at the bottom. The rudderless fixed wing (2) is provided with anti-scratching component two for protecting the connection between the rudderless fixed wing (2) and the fuselage (1) at the bottom. The rudderless fixed wing (2) is also provided with anti-scratching component three for protection at the bottom.

2. The distributed lift system, a controlless vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, The anti-deviation component includes a first air filter (102) symmetrically arranged on one side of the body (1), a second air filter (107) symmetrically arranged on the other side of the body (1), and a drainage angle (103) arranged on the top of the body (1).

3. The distributed lift system, a controlless vertical takeoff and landing fixed-wing UAV according to claim 2, characterized in that, The spoiler assembly includes a fixed track (4) symmetrically arranged on the side wall of the fuselage (1), a third electric shaft (401) arranged on the inner wall of the fixed track (4), and an electric spoiler (402) arranged on the end of the third electric shaft (401) away from the fixed track (4).

4. The distributed lift system, a controlless vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, The fuselage (1) is provided with a connecting assembly, which includes a connecting body (3) disposed at the end of the rudderless fixed wing (2) and a second electric shaft (302) fixedly connected to the output end of the brushless motor (301).

5. A distributed lift system for a rudderless vertical takeoff and landing fixed-wing UAV according to claim 4, characterized in that, The anti-scratch component includes a base disposed at the bottom of the connector (3) and a second anti-scratch strip (304) disposed at the bottom of the base.

6. The distributed lift system, a controlless vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, The anti-scratch component 2 includes several first anti-scratch rubber strips (108) disposed at the bottom of the fuselage (1) and several isolation plates (201) disposed at the bottom of the rudderless fixed wing (2).

7. A distributed lift system for a rudderless vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, The body (1) is provided with an insertion assembly, which includes an oblique body (104) symmetrically arranged on the side wall of the body (1), an insertion plate (106) arranged at the bottom of the oblique body (104), and an insertion plate (106) rotatably arranged outside the first electric shaft (105). The first electric shaft (105) is connected to the outside of the oblique body (104).

8. A distributed lift system for a rudderless vertical takeoff and landing fixed-wing UAV according to claim 1, characterized in that, The fuselage (1) is provided with a control component, which includes a flight control module (101) located on the top of the fuselage (1) for controlling the flight of the fuselage (1).

9. A distributed lift system for a rudderless vertical takeoff and landing fixed-wing unmanned aerial vehicle according to claim 1, characterized in that, The anti-scratch assembly includes multiple anti-collision bodies (5) disposed at the bottom of the rudderless fixed wing (2), a thickened layer (501) disposed at the end of the anti-collision body (5) away from the rudderless fixed wing (2), and a mounting stud (502) disposed at the end of the anti-collision body (5) near the rudderless fixed wing (2).

10. A distributed lift system for a rudderless vertical takeoff and landing fixed-wing unmanned aerial vehicle according to claim 2, characterized in that, The first air filter hole (102) is provided with an anti-clogging component, which includes an anti-clogging body (6) disposed in the first air filter hole (102), a third air filter hole (601) disposed in the anti-clogging body (6), a sleeve (602) disposed on the anti-clogging body (6), an extension column (603) disposed on the sleeve (602), a wind-breaking cone (604) disposed on the extension column (603) at one end away from the sleeve (602), and a blocking blade (605) disposed on the extension column (603) at the end away from the wind-breaking cone (604).

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