A conformal external store and a vertical take-off and landing fixed-wing unmanned aerial vehicle

Abstract

The application provides a conformal external store and a vertical take-off and landing fixed-wing unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The conformal external store comprises a fuselage, an external store is arranged at the lower part of the fuselage, an elastic skin is wrapped outside the external store, the skin is detachably connected to the fuselage, an elastic keel is arranged outside the external store, the keel is movably connected to the fuselage, a driving mechanism is arranged in the fuselage, and the driving mechanism drives the keel to stretch and retract. The application has the following effects: the driving mechanism is used for driving the keel to stretch and retract, so that different volumes of goods can be adapted; the elasticity of the keel is used for keeping a round shape, the skin is supported, and the target of a streamlined shape is achieved, so that the flight resistance can be reduced; and the keel can also provide protection for the goods.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a conformal external mount and a vertical take-off and landing (VTOL) fixed-wing UAV. Background Technology

[0002] Vertical takeoff and landing (VTOL) fixed-wing drones generally adopt a quadcopter + fixed-wing hybrid layout, where the quadcopter part is used for vertical takeoff and landing, and the fixed-wing part is used for cruise flight. This layout combines the advantages of multi-rotor drones, which allow for flexible takeoff and landing, and fixed-wing drones, which do not require runways, with the ability of fixed-wing drones to fly for extended periods of time.

[0003] For example, Chinese patent application number CN201920864921.0 discloses a vertical take-off and landing fixed-wing drone. If this type of drone wants to carry additional cargo, it usually sets up external racks on the wings or under the fuselage. However, the external cargo will cause a significant increase in cruising drag, and it is difficult to set up conformal shells for different cargoes. Utility Model Content

[0004] To overcome the above deficiencies, this application provides a conformal external mount and a vertical take-off and landing fixed-wing UAV, which aims to improve the problems mentioned in the background art.

[0005] In a first aspect, embodiments of this application provide a conformal external mounting bracket, including a body, an external mounting bracket disposed at the lower part of the body, an elastic skin covering the outside of the external mounting bracket, the skin being detachably connected to the body, an elastic keel disposed outside the external mounting bracket, the keel being movably connected to the body, and a drive mechanism disposed inside the body, the drive mechanism driving the keel to extend and retract.

[0006] In one specific implementation, the outer ring of the skin is fixedly connected to an outer frame, and the outer frame is connected to the fuselage screws.

[0007] In the above process, when loading and unloading goods, the outer frame connecting the skin can be disassembled. This can be done through the gaps in the keel or by removing the keel itself. Finally, the outer frame is fixed to the machine body with screws.

[0008] In one specific implementation, the keel includes horizontal bars and vertical bars, which are hinged together in a grid shape. Both ends of the horizontal bars and vertical bars are inserted into the machine body, and both the horizontal bars and vertical bars are flat.

[0009] In the above implementation process, two crossbars and two longitudinal bars are spliced ​​together in a grid pattern, with connecting pins at the splicing points. Both the crossbars and longitudinal bars have slots, and the connecting pins pass through the two slots to hinge the crossbars and longitudinal bars together. In this way, when the crossbars and longitudinal bars deform, the hinge points can move freely, reducing interference with the deformation. The flat structure facilitates the deformation of the keel in a specific direction, thereby supporting the skin. In another embodiment, compressed air is used instead of the keel to support the skin, which can reduce the weight of the drive mechanism and the keel. However, the inflated skin is prone to shaking during flight, affecting flight, and is not as stable as the keel.

[0010] In one specific implementation, the drive mechanism includes a motor and a gear. The motor is installed inside the body, the gear is fixedly connected to the output end of the motor, and the outer end of the crossbar is provided with teeth that mesh with the gear.

[0011] In the above process, the geared motor drives the crossbar to extend and retract through gears, and the longitudinal bar also extends or retracts along with the crossbar, thereby changing the space inside the keel cavity.

[0012] In one specific implementation, the drive mechanism further includes an electromagnetic lock, and both ends of the longitudinal rod are arrayed with pin holes adapted to the latch of the electromagnetic lock.

[0013] In the above process, after the motor adjusts the keel, the electromagnetic lock extends its locking tongue and inserts it into the corresponding pin hole, pinning both ends of the longitudinal rod to the fuselage. In this way, the outer ends of the keel are fixed, thus better protecting the internal cargo and making it less likely to deform during flight. When the electromagnetic lock retracts and the motor continues to push the crossbar out, the keel can be completely detached from the fuselage, making it easier to load and unload cargo.

[0014] In one specific implementation, a cargo cavity is provided in the lower part of the fuselage, the external bracket is located in the cargo cavity, and the keel covers the opening of the cargo cavity when it is retracted.

[0015] In the above implementation process, the cargo cavity can increase the cargo space. When there is a small amount of cargo, it can be stored in the cargo cavity. The keel covers the opening of the cargo cavity, and the skin and the fuselage have a smooth transition, which can ensure the streamlined shape.

[0016] In one specific implementation, the two ends of the crossbar are vertically inserted into the cargo cavity, and the two ends of the longitudinal bar are obliquely inserted into the cargo cavity.

[0017] In the above implementation process, the crossbar is U-shaped with the opening facing inward. When the motor drives the crossbar to extend, both ends of the crossbar extend diagonally downward. Under the action of elasticity, the lower end of the crossbar expands, which can increase the accommodating space laterally.

[0018] Secondly, this application also provides a vertical take-off and landing fixed-wing unmanned aerial vehicle, including the aforementioned conformal external rack.

[0019] Compared with the prior art, the beneficial effects of this application are: the keel can be extended and retracted by a drive mechanism to adapt to cargo of different volumes; the keel's own elasticity can be used to maintain a rounded shape and support the skin to achieve a streamlined shape, which can reduce flight resistance; the keel can also provide protection for the cargo. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the conformal external bracket structure provided in the embodiments of this application;

[0022] Figure 2 A schematic diagram illustrating the connection between the keel and the fuselage provided for an embodiment of this application;

[0023] Figure 3 A schematic diagram illustrating the connection relationship between the keel and the drive mechanism provided in this embodiment of the application;

[0024] Figure 4 This is a schematic diagram of the connection relationship between the horizontal and vertical bars provided in the embodiments of this application.

[0025] In the diagram: 10-body; 20-external bracket; 30-skin; 31-outer frame; 40-keel; 41-crossbar; 42-longitudinal bar; 43-joint pin; 50-drive mechanism; 51-motor; 52-gear; 53-electromagnetic lock. Detailed Implementation

[0026] The technical solutions in the embodiments of this application will now be described with reference to the accompanying drawings.

[0027] Please see Figures 1-4 This application provides a conformal external rack, including a fuselage 10, an external rack 20 disposed at the lower part of the fuselage 10, an elastic skin 30 covering the outside of the external rack 20, the skin 30 being detachably connected to the fuselage 10, and an elastic keel 40 disposed outside the external rack 20, the keel 40 being movably connected to the fuselage 10. A drive mechanism 50 is disposed inside the fuselage 10, the drive mechanism 50 driving the keel 40 to extend and retract. The drive mechanism 50 drives the keel 40 to extend and retract, thereby adapting to cargo of different volumes; and the keel 40's own elasticity maintains a rounded shape, supporting the skin 30 to achieve a streamlined design, reducing flight drag; the keel 40 also provides protection for the cargo.

[0028] Please see Figures 1-4 The outer frame 31 is fixedly connected to the outer ring of the skin 30, and the outer frame 31 is screwed to the body 10. When loading and unloading goods, the outer frame 31 can be disassembled from the skin 30. This can be done through the gap of the keel 40, or the keel 40 can be removed. Finally, the outer frame 31 is fixed to the body 10 with screws.

[0029] Please see Figures 1-4 The keel 40 includes crossbars 41 and longitudinal bars 42, which are hinged together in a grid shape. Both ends of the crossbars 41 and longitudinal bars 42 are inserted into the fuselage 10. Both the crossbars 41 and longitudinal bars 42 are flat. The two crossbars 41 and two longitudinal bars 42 are spliced ​​together in a grid shape, and the splicing point is provided with a connecting pin 43. Both the crossbars 41 and longitudinal bars 42 have slots, and the connecting pin 43 passes through the two slots to hinge the crossbars 41 and longitudinal bars 42 together. In this way, when the crossbars 41 and longitudinal bars 42 deform, the hinge point can move freely, reducing interference with the deformation. The flat structure facilitates the deformation of the keel 40 in a specific direction, thereby supporting the skin 30. In another embodiment, compressed air is used instead of the keel 40 to support the skin 30, which can reduce the weight of the drive mechanism 50 and the keel 40. However, the inflated skin 30 is prone to shaking during flight, affecting flight, and is not as stable as the keel 40.

[0030] Please see Figures 1-4 The drive mechanism 50 includes a motor 51 and a gear 52. The motor 51 is installed inside the body 10, and the gear 52 is fixedly connected to the output end of the motor 51. The outer end of the crossbar 41 is provided with teeth that mesh with the gear 52. The geared motor 51 drives the crossbar 41 to extend and retract through the gear 52, and the longitudinal bar 42 also extends or retracts along with the crossbar 41, thereby changing the space inside the keel 40.

[0031] Please see Figures 1-4 The drive mechanism 50 also includes an electromagnetic lock 53. Both ends of the longitudinal rod 42 are arrayed with pin holes that match the locking tongue of the electromagnetic lock 53. After the motor 51 adjusts the keel 40, the electromagnetic lock 53 extends its locking tongue and inserts it into the corresponding pin hole, pinning both ends of the longitudinal rod 42 to the fuselage 10. In this way, the outer ends of the keel 40 are fixed, thus better protecting the internal cargo and making it less likely to deform during flight. When the electromagnetic lock 53 retracts and the motor 51 continues to push out the crossbar 41, the keel 40 can be completely detached from the fuselage 10, facilitating the loading and unloading of cargo.

[0032] Please see Figures 1-4 The lower part of the fuselage 10 has a cargo cavity, and the external rack 20 is located inside the cargo cavity. When retracted, the keel 40 covers the opening of the cargo cavity. The cargo cavity can increase the cargo space. When there is a small amount of cargo, it can be stored in the cargo cavity. The keel 40 covers the opening of the cargo cavity. The skin 30 and the fuselage 10 have a smooth transition to ensure a streamlined shape.

[0033] Please see Figures 1-4 The two ends of the crossbar 41 are vertically inserted into the cargo cavity, and the two ends of the longitudinal bar 42 are obliquely inserted into the cargo cavity. The crossbar 41 is U-shaped with its opening facing inward. When the motor 51 drives the crossbar 41 to extend, the two ends of the crossbar 41 extend obliquely downward. Under the action of elasticity, the lower end of the crossbar 41 expands, which can increase the lateral capacity.

[0034] Please see Figures 1-4 This application also provides a vertical take-off and landing fixed-wing unmanned aerial vehicle, including the aforementioned conformal external rack.

[0035] The working principle of this conformal external rack is as follows: During loading, the cargo is hoisted onto the external rack 20, and then the crossbar 41 and the vertical bar 42 are inserted into their corresponding slots. The motor 51 retracts both ends of the crossbar 41 into the fuselage 10 through the gear 52. The vertical bar also retracts into the fuselage 10 along with the crossbar 41, thereby reducing the space inside the keel 40 until it just covers the cargo. Then the motor 51 stops rotating, and the electromagnetic lock 53 extends its locking tongue to engage the vertical bar 42 in the slot, thereby fixing the keel 40. Finally, the outer frame 31 is screwed onto the fuselage 10. In this way, the skin 30 wraps around the keel 40, forming a streamlined shape, thereby reducing flight drag.

[0036] In summary, the drive mechanism 50 is used to extend and retract the keel 40 to accommodate cargo of different sizes; and the keel 40's own elasticity is used to maintain a rounded shape, supporting the skin 30 to achieve a streamlined shape, which can reduce flight drag; the keel 40 can also provide protection for the cargo.

[0037] The execution and testing equipment involved in this application is automatically controlled by a Siemens S7-1200 series PLC. The patent specification fully discloses its control logic; those skilled in the art can implement the corresponding control program using ladder diagrams or structured text programming languages ​​based on the logical relationships. The related equipment is connected according to the IEC 61131-2 electrical standard, which is a common connection technology in the field of automation; therefore, redundant descriptions are not provided.

[0038] The above are merely embodiments of this application and are not intended to limit the scope of protection of this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application. It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

Claims

1. A conformal external mount, characterized by, Includes a body (10), an external bracket (20) is provided at the lower part of the body (10), the external bracket (20) is covered with an elastic skin (30), the skin (30) is detachably connected to the body (10), an elastic keel (40) is provided outside the external bracket (20), the keel (40) is movably connected to the body (10), and a drive mechanism (50) is provided inside the body (10), the drive mechanism (50) drives the keel (40) to extend and retract.

2. A conformal external store as claimed in claim 1, characterised in that, The outer ring of the skin (30) is fixedly connected to the outer frame (31), and the outer frame (31) is screwed to the body (10).

3. A conformal cradle as claimed in claim 2, wherein, The keel (40) includes a crossbar (41) and a longitudinal bar (42). The crossbar (41) and the longitudinal bar (42) are hinged together in a grid shape. Both ends of the crossbar (41) and the longitudinal bar (42) are inserted into the body (10). Both the crossbar (41) and the longitudinal bar (42) are flat.

4. A conformal cradle as claimed in claim 3, wherein, The drive mechanism (50) includes a motor (51) and a gear (52). The motor (51) is installed inside the body (10). The gear (52) is fixedly connected to the output end of the motor (51). The outer end of the crossbar (41) is provided with teeth that mesh with the gear (52).

5. A conformal cradle as claimed in claim 4, wherein, The drive mechanism (50) also includes an electromagnetic lock (53), and both ends of the longitudinal rod (42) are arrayed with pin holes that are adapted to the locking tongue of the electromagnetic lock (53).

6. A conformal cradle as claimed in claim 5, wherein, The lower part of the body (10) has a cargo cavity, the external bracket (20) is located in the cargo cavity, and the keel (40) covers the opening of the cargo cavity when it is retracted.

7. A conformal cradle as claimed in claim 6, wherein, The two ends of the crossbar (41) are vertically inserted into the cargo cavity, and the two ends of the longitudinal bar (42) are obliquely inserted into the cargo cavity.

8. A vertical take-off and landing fixed-wing drone, characterized in that, Includes the conformal mounting bracket as described in any one of claims 1-7.

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