Unmanned aerial vehicle body

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle fuselage which comprises a fuselage body, the fuselage body is arranged to be a plate-shaped fuselage body, the side walls of the two sides of the plate-shaped fuselage body are used for being in clearance fit with launching cylinders, and a connecting end is arranged at the head end of the plate-shaped fuselage body; a connecting part I is arranged at the bottom end of the head part of the plate-shaped machine body; a connecting part II is arranged in the middle of the top end of the plate-shaped machine body; the tail portion of the plate-shaped fuselage is arranged to be a V-shaped tail portion, the V-shaped tail portion is used for connecting a vertical fin assembly and a thrust system, and a connecting portion III is arranged at the bottom end of the V-shaped tail portion. According to the utility model, the plate-shaped fuselage is in clearance fit with the launch canister through the two side walls, and after the plate-shaped fuselage is connected with the fairing and the fuselage assembly, the stability of launching of the unmanned aerial vehicle in the launch canister and the utilization rate of launching kinetic energy can be guaranteed, and the light weight of the unmanned aerial vehicle fuselage is realized.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a UAV fuselage. Background Art

[0002] In order to meet the needs of front-line reconnaissance, the concept of a canister-launched drone was first proposed. That is, a drone with a foldable deployment mechanism is loaded into a launch tube of corresponding caliber by folding its wings. In the launch tube, the liquid / gas pressure energy is converted into mechanical kinetic energy, so that the drone is accelerated to a safe take-off speed in a launch tube of a certain length. After the reconnaissance mission is completed, the target can be selectively self-destructed or recovered by parachute landing. In order to adapt to the inner wall of the launch tube, the existing drone fuselage optimizes the use of launch kinetic energy, thereby setting the drone fuselage to a cylindrical fuselage. However, the cylindrical fuselage will increase the overall weight of the drone, which is not conducive to the demand for lightweight drones, and thus there is a need to achieve lightweight drone fuselages.

[0003] In the prior art, for example, utility model CN213921452U is a foldable tube-launched UAV. In this patent, the fuselage of the UAV is set as a cylindrical fuselage. Although the cylindrical fuselage can adapt to the inner wall of the launch tube to optimize the use of the launch kinetic energy, the cylindrical fuselage will cause the overall weight of the UAV to increase, which is not conducive to the demand for lightweight UAV.

[0004] Therefore, how to achieve lightweighting of the UAV fuselage is an urgent problem to be solved in this technical field. Utility Model Content

[0005] For the existing UAV fuselage, in order to adapt to the inner wall of the launch tube and optimize the utilization of the launch kinetic energy, the UAV fuselage is set to a cylindrical fuselage. However, the cylindrical fuselage will increase the overall weight of the UAV, which is not conducive to the insufficient lightweight demand of the UAV. A plate-shaped fuselage is provided, which is fitted with the gap between the side walls of the launch tube. After the plate-shaped fuselage is connected to the fairing and the fuselage assembly, it can ensure the stability of the UAV when launched from the launch tube and the utilization rate of the launch kinetic energy, thereby realizing a lightweight UAV fuselage.

[0006] In order to achieve the above-mentioned purpose of the utility model, the utility model provides the following technical solutions:

[0007] A UAV fuselage comprises a fuselage, wherein the fuselage is configured as a plate-shaped fuselage, side walls of the plate-shaped fuselage are configured to be gap-fitted with a launch tube, a connecting end is provided at the front end of the plate-shaped fuselage, and the connecting end is configured to be connected to a fairing;

[0008] The bottom end of the front portion of the plate-shaped fuselage is provided with a connecting portion I, and the connecting portion I is used to connect to the front wing assembly;

[0009] A connecting portion II is provided at the middle of the top of the plate-shaped fuselage, and the connecting portion II is used to connect the fuselage components;

[0010] The tail of the plate-shaped fuselage is configured as a V-shaped tail, which is used to connect the vertical tail assembly and the thrust system. The bottom end of the V-shaped tail is provided with a connecting portion III, which is used to connect the rear wing assembly.

[0011] As a preferred embodiment, the connecting end is configured as a frame connecting end, and the frame connecting end is used to reduce the weight of the front end of the plate-shaped fuselage.

[0012] As a preferred embodiment, guide sliders are symmetrically provided on both sides of the nose of the plate-like fuselage, and the guide sliders are used to guide the plate-like fuselage when it is launched from the launching device, so that the UAV can be launched smoothly from the launching device.

[0013] As a preferred embodiment, the plate-shaped body is provided with the connection portion I in the following manner:

[0014] The bottom end of the nose of the plate-shaped fuselage is integrally provided with a connecting boss, and a connecting groove I is provided on the connecting boss. The connecting groove I is used to connect the front wing assembly. The nose of the plate-shaped fuselage is symmetrically provided with two slots I, and the slots I are used to reduce the weight of the nose of the plate-shaped fuselage and connect the servo of the front wing assembly.

[0015] As a preferred embodiment, a V-shaped groove is further provided at the side end of the connecting end, and the V-shaped groove is used for locking and limiting the front wing after it is unfolded.

[0016] As a preferred embodiment, the plate-shaped body is provided with the connection portion II in the following manner:

[0017] A clamping plate is integrally provided on both sides of the top of the plate-shaped fuselage, and the clamping plate is used to engage with the fairing shell of the fuselage assembly. A mounting groove is also provided in the middle position of the top of the fuselage, and the mounting groove is used to place the communication control device of the fuselage assembly.

[0018] As a preferred embodiment, a plurality of slot holes II are symmetrically opened in the installation groove, and the slot holes II are used to reduce the weight of the middle part of the plate-shaped fuselage and fix the communication control device of the fuselage assembly.

[0019] As a preferred embodiment, the V-shaped tail is provided with the connection portion III in the following manner:

[0020] A connecting groove II is provided at the bottom end of the V-shaped tail, and the connecting groove II is used to connect the rear wing assembly. A slot hole III is provided in the middle position of the V-shaped tail, and the slot hole III is used to reduce the weight of the V-shaped tail.

[0021] As a preferred embodiment, a connecting frame is integrally provided at the top end of the V-shaped tail portion, and the connecting frame is used to connect to a control servo of the vertical tail assembly.

[0022] As a preferred embodiment, a plurality of threaded holes are provided on both sides of the V-shaped tail in an inclined shape, and the threaded holes are used to connect the foldable vertical tail of the vertical tail assembly. Upper inclined end surfaces are also provided on both sides of the V-shaped tail, and the upper inclined end surfaces are used to increase the deflection range of the foldable vertical tail.

[0023] By adopting the above technology, compared with the prior art, the beneficial effects of the present invention are:

[0024] The utility model has a plate-shaped fuselage that cooperates with the launch tube through the gap between the side walls on both sides. After the plate-shaped fuselage is connected to the fairing and the fuselage assembly, it can ensure the stability of the UAV when launched from the launch tube and the utilization rate of the launch kinetic energy. After the front wing assembly, rear wing assembly, vertical tail assembly and thrust system are folded on the plate-shaped fuselage, they can all enter the launch tube, thereby realizing the lightweight of the UAV fuselage. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0026] Figure 1 This is a schematic diagram of the structure of this application;

[0027] Figure 2 A side view of the present application;

[0028] Figure 3 This is an application diagram of this application;

[0029] Figure 4 This is a connection diagram of the connection part I of this application;

[0030] Figure 5 This is a schematic diagram of the V-shaped tail connection of this application;

[0031] Figure 6 A side view of the V-shaped tail section of the present application; DETAILED DESCRIPTION

[0032] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in combination with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments.

[0033] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the utility model product is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as a limitation on the present invention.

[0034] Furthermore, terms such as "horizontal" and "vertical" do not necessarily mean that a component must be absolutely horizontal or overhanging, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but rather that it can be slightly tilted.

[0035] It should also be noted that, in the description of this utility model, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections, electrical connections; direct connections, indirect connections through an intermediate medium, and internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on the specific circumstances.

[0036] Examples, such as Figures 1-6 As shown,

[0037] A UAV fuselage includes a fuselage, wherein the fuselage is configured as a plate-shaped fuselage 1, the side walls of the plate-shaped fuselage 1 being configured to be gap-fitted with a launch tube, and a connecting terminal 2 being provided at the front end of the plate-shaped fuselage 1, the connecting terminal 2 being configured to be connected to a fairing 22;

[0038] The front bottom end of the plate-shaped fuselage 1 is provided with a connecting portion I3, and the connecting portion I3 is used to connect to the front wing assembly 6;

[0039] A connecting portion II 4 is provided at the middle of the top of the plate-shaped fuselage 1, and the connecting portion II 4 is used to connect to the fuselage assembly 7;

[0040] The tail of the plate-shaped fuselage 1 is configured as a V-shaped tail 5, which is used to connect the vertical tail assembly 8 and the thrust system 9. The bottom end of the V-shaped tail 5 is provided with a connecting portion III 51, which is used to connect the rear wing assembly 10.

[0041] By setting the fuselage as a plate-shaped fuselage 1, the overall weight of the fuselage is reduced. When the plate-shaped fuselage 1 is located in the launch tube, the plate-shaped fuselage 1 cooperates with the launch tube through the clearance between the side walls on both sides to ensure the stability of the plate-shaped fuselage 1 when launched from the launch tube. After the plate-shaped fuselage 1 is connected to the fairing 22 through the connecting end 2, the front end of the plate-shaped fuselage 1 is formed into a cylindrical shape through the cooperation between the plate-shaped fuselage 1 and the fairing 22, so that the launch kinetic energy can be optimized. The plate-shaped fuselage 1 is connected to the front wing assembly 6 through the connecting part I3 and the rear wing assembly 10 through the connecting part III51. After folding, the front wing assembly 6 and the rear wing assembly 10 are both located at the bottom end of the front of the plate-shaped fuselage 1. The vertical tail assembly 8 and the thrust system 9 are connected to the V-shaped tail 5, so that the front wing assembly 6, After the rear wing assembly 10, the vertical tail assembly 8 and the thrust system 9 are folded, they can all enter the launch tube; and after the fuselage assembly 7 is connected through the connecting part II4, the top middle part of the plate-shaped fuselage 1 forms an arc shape that is adapted to the launch tube, thereby ensuring the stability of the UAV when launched from the launch tube and ensuring the utilization rate of the launch kinetic energy; in this technical solution, the plate-shaped fuselage 1 is fitted with the launch tube through the gap between the side walls on both sides. After the plate-shaped fuselage 1 is connected to the fairing 22 and the fuselage assembly 7, the stability of the UAV when launched from the launch tube and the utilization rate of the launch kinetic energy can be ensured. After the front wing assembly 6, the rear wing assembly 10, the vertical tail assembly 8 and the thrust system 9 are folded on the plate-shaped fuselage 1, they can all enter the launch tube, thereby realizing the lightweight of the UAV fuselage.

[0042] As a preferred embodiment, the connection end 2 is configured as a frame connection end, which is used to reduce the weight of the front end of the plate-shaped fuselage 1. By configuring the connection end 2 as a frame connection end, the weight of the front end of the plate-shaped fuselage 1 is reduced, further reducing the weight of the drone fuselage.

[0043] As a preferred embodiment, guide sliders 11 are symmetrically provided on both sides of the nose of the plate-shaped fuselage 1. The guide sliders 11 are used to guide the plate-shaped fuselage 1 when it is launched from the launch device, so that the UAV is launched smoothly from the launch device.

[0044] At the moment the drone is launched from the launch tube, the drone may roll and / or deflect, and the drone cannot maintain a horizontal flight state, which may lead to launch failure or damage of the drone; therefore, guide sliders 11 are respectively provided on both sides of the head of the plate-shaped fuselage 1, and the guide sliders 11 are clearance-matched with the guide grooves provided on the inner wall of the launch tube. At the moment the drone is launched, the guide sliders 11 slide along the guide grooves to guide and limit the drone, so that the drone cannot roll at the moment it is launched, thereby ensuring that the drone can be launched smoothly from the launch tube.

[0045] As a preferred embodiment, the plate-shaped body 1 is provided with the connection portion I3 in the following manner:

[0046] A connecting boss 31 is integrally provided at the bottom end of the nose of the plate-shaped fuselage 1, and a connecting groove I 32 is provided on the connecting boss 31. The connecting groove I 32 is used to connect the front wing assembly 6. Two slots I 33 are symmetrically provided through the nose of the plate-shaped fuselage 1. The slots I 33 are used to reduce the weight of the nose of the plate-shaped fuselage 1 and connect the servo 61 of the front wing assembly 6.

[0047] After the front wing assembly 6 is connected to the connecting boss 31 through the connecting groove Ⅰ32, the front wing assembly 6 can be folded or unfolded along the connecting groove Ⅰ32. The connecting groove Ⅰ32 imposes restrictions on the movable position of the front wing assembly 6. Opening the connecting groove Ⅰ32 on the connecting boss 31 can increase the adjustment space of the front wing assembly 6 and avoid contact and collision between the front wing assembly 6 and the plate-like fuselage 1 during folding or unfolding. The two slots Ⅰ33 opened through the head of the plate-like fuselage 1 reduce the weight of the head of the plate-like fuselage 1 and can connect the servo 61 of the front wing assembly 6, further reducing the weight of the drone fuselage and ensuring the stability of the connection.

[0048] As a preferred embodiment, a V-shaped groove 21 is further provided at the side end of the connecting end 2, and the V-shaped groove 21 is used for locking and limiting the front wing after it is unfolded.

[0049] When the front wing of the drone is unfolded, the clamping plate 41 on the front wing is engaged with the V-shaped slot 21, and the V-shaped slot 21 is used to locate and limit the unfolding position of the front wing, ensuring that the front wing can be unfolded into place and at the same time ensuring the stability of the front wing during flight.

[0050] As a preferred embodiment, the plate-shaped body 1 is provided with the connecting portion II 4 in the following manner:

[0051] A clamping plate 41 is integrally provided on both sides of the top of the plate-shaped fuselage 1, and the clamping plate 41 is used to engage with the fairing shell of the fuselage assembly 7. A mounting groove 42 is also provided in the middle position of the top of the fuselage, and the mounting groove 42 is used to place the communication control device of the fuselage assembly 7.

[0052] The clamping plate 41 is engaged with the rectifier shell of the fuselage assembly 7 to ensure the stability of the connection between the plate-shaped fuselage 1 and the rectifier shell, and at the same time it is convenient for the staff to disassemble the rectifier shell to inspect and debug the internal communication control device; the installation position of the communication control device is located by the installation groove 42 to avoid the communication control device from abutting against the rectifier shell and thus avoiding damage to the communication control device.

[0053] Furthermore, multiple slots II 43 are symmetrically formed within the mounting slot 42. These slots II 43 are used to reduce the weight of the central portion of the plate-like fuselage 1 and to secure the communication control device of the fuselage assembly 7. By providing multiple slots II 43 within the mounting slot 42, the weight of the central portion of the plate-like fuselage 1 is reduced, further reducing the weight of the drone fuselage. At the same time, these slots II 43 securely connect to the communication control device of the fuselage assembly 7, preventing displacement of the communication control device during flight.

[0054] As a preferred embodiment, the V-shaped tail 5 is provided with the connecting portion III 51 in the following manner:

[0055] A connecting groove II 511 is provided at the bottom end of the V-shaped tail portion 5 , and the connecting groove II 511 is used to connect to the rear wing assembly 10 . A slot hole III 512 is provided in the middle position of the V-shaped tail portion 5 , and the slot hole III 512 is used to reduce the weight of the V-shaped tail portion 5 .

[0056] After the rear wing assembly 10 is connected to the connecting groove II511, the rear wing assembly 10 can be folded or unfolded along the connecting groove II511. The connecting groove II511 imposes restrictions on the movable position of the rear wing assembly 10 to prevent the rear wing assembly 10 from contacting and colliding with the plate-shaped fuselage 1 and / or the front wing assembly 6 during the folding or unfolding process; and the slot III512 opened in the middle position of the V-shaped tail 5 reduces the weight of the V-shaped tail 5, so that the weight of each part of the plate-shaped fuselage 1 is stable, avoiding the plate-shaped fuselage 1 being light at the front and heavy at the rear, further reducing the weight of the drone fuselage, and at the same time ensuring the stability of the drone flight.

[0057] As a preferred embodiment, a connecting frame 52 is integrally provided at the top end of the V-shaped tail portion 5 , and the connecting frame 52 is used to connect to the control steering gear 82 of the vertical tail assembly 8 .

[0058] The connecting frame 52 integrally provided on the V-shaped tail 5 is connected to the control servo 82 of the vertical tail assembly 8 to ensure the connection strength while setting the control servo 82 at a set height to ensure the control effect of the control servo 82 on the vertical tail assembly 8.

[0059] As a preferred embodiment, a plurality of threaded holes 53 are provided on both sides of the V-shaped tail 5 in an inclined shape, and the threaded holes 53 are used to connect the foldable vertical tail 81 of the vertical tail assembly 8. Upper inclined end surfaces 54 are also provided on both sides of the V-shaped tail 5, and the upper inclined end surfaces 54 are used to increase the deflection range of the foldable vertical tail 81.

[0060] By means of the multiple threaded holes 53 that are obliquely opened on both sides of the V-shaped tail 5, the foldable vertical tail 81 of the vertical tail assembly 8 can be stably connected to the V-shaped tail 5. At the same time, the connection position of the foldable vertical tail 81 can be positioned through the multiple threaded holes 53 to ensure the connection accuracy of the foldable vertical tail 81 and the V-shaped tail 5; and the upper inclined end surfaces 54 provided on both sides of the V-shaped tail 5 increase the deflection range of the foldable vertical tail 81, so that the foldable vertical tail 81 can have a larger deflection adjustment space.

[0061] The above description is merely a preferred embodiment of the utility model and is not intended to limit the technical solution of the utility model. Those skilled in the art will readily appreciate that the utility model is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the technical solution of the utility model shall be included within the scope of protection of the utility model.

Claims

1. A drone fuselage, comprising a fuselage, characterized in that: The fuselage is configured as a plate-shaped fuselage, the side walls of which are used to fit with the launch tube in a clearance manner, and a connecting end is provided at the front end of the plate-shaped fuselage, and the connecting end is used to connect to the fairing; The bottom end of the front portion of the plate-shaped fuselage is provided with a connecting portion I, and the connecting portion I is used to connect to the front wing assembly; A connecting portion II is provided at the middle of the top of the plate-shaped fuselage, and the connecting portion II is used to connect the fuselage components; The tail of the plate-shaped fuselage is configured as a V-shaped tail, which is used to connect the vertical tail assembly and the thrust system. The bottom end of the V-shaped tail is provided with a connecting portion III, which is used to connect the rear wing assembly.

2. The UAV fuselage according to claim 1, characterized in that: The connecting end is configured as a frame connecting end, and the frame connecting end is used to reduce the weight of the front end of the plate-shaped fuselage.

3. The UAV fuselage according to claim 1, characterized in that: Guide sliders are symmetrically provided on both sides of the nose of the plate-like fuselage, and the guide sliders are used to guide the plate-like fuselage when it is launched from the launching device, so that the UAV can be launched smoothly from the launching device.

4. The UAV fuselage according to claim 1, characterized in that: The plate-shaped body is provided with the connection portion I in the following manner: The bottom end of the nose of the plate-shaped fuselage is integrally provided with a connecting boss, and a connecting groove I is provided on the connecting boss. The connecting groove I is used to connect the front wing assembly. The nose of the plate-shaped fuselage is symmetrically provided with two slots I, and the slots I are used to reduce the weight of the nose of the plate-shaped fuselage and connect the servo of the front wing assembly.

5. The UAV fuselage according to claim 1, characterized in that: A V-shaped slot is also provided on the side of the connecting end, and the V-shaped slot is used for locking and limiting the front wing after it is unfolded.

6. The UAV fuselage according to claim 1, characterized in that: The plate-shaped body is provided with the connection portion II in the following manner: A clamping plate is integrally provided on both sides of the top of the plate-shaped fuselage, and the clamping plate is used to engage with the fairing shell of the fuselage assembly. A mounting groove is also provided in the middle position of the top of the fuselage, and the mounting groove is used to place the communication control device of the fuselage assembly.

7. The UAV fuselage according to claim 6, characterized in that: A plurality of slot holes II are symmetrically opened in the installation slot, and the slot holes II are used to reduce the weight of the middle part of the plate-shaped fuselage and fix the communication control device of the fuselage assembly at the same time.

8. The UAV fuselage according to claim 1, characterized in that: The V-shaped tail is provided with the connection portion III in the following manner: A connecting groove II is provided at the bottom end of the V-shaped tail, and the connecting groove II is used to connect the rear wing assembly. A slot hole III is provided in the middle position of the V-shaped tail, and the slot hole III is used to reduce the weight of the V-shaped tail.

9. The UAV fuselage according to claim 1, characterized in that: A connecting frame is integrally provided at the top end of the V-shaped tail, and the connecting frame is used to connect to the control steering gear of the vertical tail assembly.

10. The UAV fuselage according to claim 1, characterized in that: A plurality of threaded holes are provided on both sides of the V-shaped tail in an inclined shape, and the threaded holes are used to connect the foldable vertical tail of the vertical tail assembly. Upper inclined end surfaces are also provided on both sides of the V-shaped tail, and the upper inclined end surfaces are used to increase the deflection range of the foldable vertical tail.

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