A connection structure and method for connecting the fuselage and landing gear of an unmanned aerial vehicle (UAV).

Abstract

This invention provides a connection structure and method for a drone fuselage and landing gear, including a main landing gear mounting plate, a front landing gear mounting auxiliary pad, and an actuator cylinder mounting bracket. The main landing gear mounting plate is glued to the fuselage, and multiple main landing gear mounting brackets are fixedly connected to one side of the main landing gear mounting plate. The main landing gear mounting brackets are connected and fixed to the landing gear with bolts. This invention achieves the connection between the fuselage and landing gear through the main landing gear mounting plate, the front landing gear mounting auxiliary pad, and the actuator cylinder mounting bracket. During the connection process, the landing gear position is adjusted in conjunction with an electric retraction device and a laser level. Simultaneously, the connection between the electric push rod, the second support rod, and the first support rod is used to control the landing gear installation angle. This provides convenient operation, a short design and manufacturing cycle, and faster completion of the structure's manufacturing and installation. Compared with traditional tooling-based landing gear installation, it significantly saves production costs.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and mainly to a connection structure and method for connecting the fuselage and landing gear of a UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment and their own program control devices. They are a general term for unmanned aerial vehicles, initially used in the military field. With the development and promotion of UAV technology, UAVs have been widely used in aerial photography, agriculture, forestry, surveying, and other fields.

[0003] Currently, due to project schedule requirements, the timeline from design to completion of the fuselage structure is long when designing the landing gear and fuselage connection structure. This means that the landing gear can only be purchased as existing finished products. The fuselage connection structure can only be designed and installed in detail after obtaining specific information about the landing gear or even after obtaining the finished product. Therefore, a connection structure and connection method for the UAV fuselage and landing gear are needed. Summary of the Invention

[0004] This invention provides a connection structure and method for connecting the fuselage and landing gear of a drone, in order to solve the technical problem mentioned in the background art of how to ensure the position accuracy of the landing gear installation when the drone is not positioned by tooling.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a connection structure and method for connecting the fuselage and landing gear of an unmanned aerial vehicle (UAV), comprising a main landing gear mounting plate, a front landing gear mounting auxiliary pad, and an actuator cylinder mounting bracket. The main landing gear mounting plate is glued to the fuselage. Multiple main landing gear mounting brackets are fixedly connected to one side of the main landing gear mounting plate. The main landing gear mounting brackets are connected and fixed to the landing gear by bolts. Multiple front landing gear support brackets are bolted to the lower part of one side of the front landing gear mounting auxiliary pad. Multiple front landing gear connecting brackets are glued to the lower part of the other side of the front landing gear mounting auxiliary pad. An actuator cylinder connecting bracket is fixedly connected to one side of the actuator cylinder mounting bracket near its end.

[0006] Preferably, the landing gear includes a lifting column, the upper end of which is connected to a main landing gear mounting base. The lifting column can be raised and lowered inside the main landing gear mounting base. The main landing gear mounting bracket is installed on the upper part of the main landing gear mounting base. A fixing sleeve is connected to the outside of the main landing gear mounting base. A first support rod is hinged to one side of the fixing sleeve. A second support rod is hinged to the upper end of the first support rod. The upper end of the second support rod is hinged to the side wall of the front landing gear mounting auxiliary pad. An electric push rod is installed on one side of the actuator mounting bracket. The end of the electric push rod is hinged to the inner side wall of the front landing gear mounting auxiliary pad.

[0007] Preferably, the bottom end of the lifting column is equipped with a wheel, the rubber surface of the wheel is made of wear-resistant and high-temperature resistant special material bonded with steel wire, and the wheel is about 20mm thick.

[0008] Preferably, the lifting column is slidably fitted with a movable sleeve, a first buffer rod is hinged to one side of the movable sleeve, a second buffer rod is hinged to the bottom end of the first buffer rod, and the first buffer rod is hinged to the lower part of the lifting column.

[0009] Preferably, an electric retraction device is installed on the upper part of one side of the main landing gear mounting base, and a laser level is installed on one side of the electric retraction device.

[0010] The present invention discloses a method for connecting the fuselage and landing gear of a drone, which adopts the above-mentioned connection structure of the fuselage and landing gear. Specifically, it includes the following steps: using three-dimensional design software according to the input of the landing gear manufacturer and in conjunction with the fuselage structure, the design of the connection structure is completed. First, the connection structure needs to be connected to the landing gear. The fuselage is leveled first, the landing gear is leveled using a laser level, and the electric retraction device is powered on so that the landing gear is in the lowered state, controlling the installation angle of the landing gear.

[0011] Preferably, a method for connecting the fuselage and landing gear of a drone specifically includes the following steps:

[0012] 1) Complete the overall installation of the landing gear;

[0013] 2) Glue the main landing gear mounting plate to the fuselage. The structural adhesive application time needs to be more than 15 minutes. Use a laser level to measure and ensure that the landing gear installation angle is 90° with the fuselage, which will serve as the reference for subsequent installation.

[0014] 3) Insert the landing gear and connecting structure into the fuselage structure from above, and connect the landing gear and the main landing gear mounting bracket with bolts;

[0015] 4) Power on the electric retraction device and adjust the landing gear to the final lowered position;

[0016] 5) Glue the actuator mounting bracket to the machine body and allow it to cure for 24 hours;

[0017] 6) Adjust the position of the front landing gear mounting auxiliary pad to ensure that the angle between the landing gear and the fuselage centerline is above 90° and there is no inward bending. Attach the front landing gear mounting auxiliary pad to the lower fuselage skin and reinforce it with L-shaped aluminum profiles.

[0018] 7) Bolt the front landing gear support bracket, the front landing gear connecting bracket and the actuator connecting bracket. Adjust and reinforce the connection gaps with composite carbon plates. Fix the main landing gear mounting bracket and the actuator mounting bracket to the fuselage with adhesive rivets. Installation is complete.

[0019] Compared with the prior art, the beneficial effects of the present invention are:

[0020] This invention achieves the connection between the fuselage and the landing gear through the main landing gear mounting plate, the front landing gear mounting auxiliary pad, and the actuator cylinder mounting bracket. During the connection process, the position of the landing gear is adjusted in conjunction with the electric retraction device and the laser level. At the same time, the connection between the electric push rod, the second support rod, and the first support rod is used to control the installation angle of the landing gear. It has convenient operability, a short design and manufacturing cycle, and can complete the manufacturing and installation of the structure more quickly. Compared with the traditional tooling positioning and installation of landing gear, it greatly saves production costs. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the main landing gear mounting plate structure of the present invention;

[0022] Figure 2 This is a schematic diagram of the front landing gear mounting auxiliary pad structure of the present invention;

[0023] Figure 3 This is a schematic diagram of the actuator cylinder mounting support structure of the present invention;

[0024] Figure 4 This is a schematic diagram of the landing gear installation structure of the present invention;

[0025] Figure 5 This is a schematic diagram of the fuselage structure of the present invention.

[0026] In the diagram: 1. Main landing gear mounting plate; 101. Main landing gear mounting bracket; 2. Front landing gear mounting auxiliary pad; 201. Front landing gear support bracket; 202. Front landing gear connecting bracket; 3. Actuator cylinder mounting bracket; 301. Actuator cylinder connecting bracket; 4. Lifting column; 401. Movable sleeve; 5. Main landing gear mounting seat; 501. Fixed sleeve; 6. First support rod; 7. Second support rod; 8. Electric push rod; 9. Wheel; 10. First buffer bar; 11. Second buffer bar. Detailed Implementation

[0027] 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.

[0028] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "page," "bottom," "inner," "outer," "clockwise," "counterclockwise," "coaxial," "bottom," "one end," "top," "other end," "one side," "front," "both ends," and "both sides," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0029] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0030] In this invention, unless otherwise explicitly specified and limited, the terms "installed," "connected," "linked," "fixed," and "equipped" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0031] Referring now to the accompanying drawings, the various figures are intended only to illustrate certain exemplary embodiments and are not intended to limit the invention. In the various figures, the same reference numerals denote the same or corresponding parts. The dimensions and scales in the various figures are also for illustration only and should not be construed as limiting the invention; these dimensions may be enlarged relative to actual products.

[0032] Example 1

[0033] Please see Figure 1-5This embodiment describes a connection structure and method for connecting the fuselage and landing gear of an unmanned aerial vehicle (UAV). It includes a main landing gear mounting plate 1, a front landing gear mounting auxiliary plate 2, and an actuator cylinder mounting bracket 3. The main landing gear mounting plate 1 is glued to the fuselage. Multiple main landing gear mounting brackets 101 are fixedly connected to one side of the main landing gear mounting plate 1. The main landing gear mounting brackets 101 are connected and fixed to the landing gear by bolts, enabling a quick connection between the landing gear and the fuselage. Multiple front landing gear support brackets 201 are bolted to the lower part of one side of the front landing gear mounting auxiliary plate 2. Multiple front landing gear connecting brackets 202 are glued to the lower part of the other side of the front landing gear mounting auxiliary plate 2. An actuator cylinder connecting bracket 301 is fixedly connected to one side of the actuator cylinder mounting bracket 3 near its end. The front landing gear support brackets 201, front landing gear connecting brackets 202, and actuator cylinder connecting brackets 301 are all connected by bolts.

[0034] Please see Figure 4 The landing gear includes a lifting column 4, the upper end of which is connected to a main landing gear mounting base 5. The lifting column 4 can be raised and lowered inside the main landing gear mounting base 5. The main landing gear mounting bracket 101 is installed on the upper part of the main landing gear mounting base 5. A fixing sleeve 501 is connected to the outside of the main landing gear mounting base 5. A first support rod 6 is hinged to one side of the fixing sleeve 501. A second support rod 7 is hinged to the upper end of the first support rod 6. The upper end of the second support rod 7 is hinged to the side wall of the front landing gear mounting auxiliary pad 2. An electric push rod 8 is installed on one side of the actuator mounting bracket 3. The end of the electric push rod 8 is hinged to the inner side wall of the front landing gear mounting auxiliary pad 2.

[0035] It should be noted that the position of the front landing gear mounting auxiliary pad 2 is adjusted by using the electric push rod 8 to ensure that the landing gear is at an angle of more than 90° with the fuselage centerline to prevent inward bending. At the same time as the position of the front landing gear mounting auxiliary pad 2 is adjusted, the first support rod 6 and the second support rod 7 rotate to provide connection and support for the front landing gear mounting auxiliary pad 2.

[0036] Please see Figure 4 The bottom of the lifting column 4 is equipped with a wheel 9. The rubber surface of the wheel 9 is made of wear-resistant and high-temperature resistant special material bonded with steel wire. The wheel 9 is about 20mm thick.

[0037] It should be noted that this extends the lifespan of wheel 9.

[0038] Please see Figure 4 The lifting column 4 is externally slidably fitted with a movable sleeve 401. A first buffer rod 10 is hinged to one side of the movable sleeve 401. A second buffer rod 11 is hinged to the bottom of the first buffer rod 10. The first buffer rod 10 is hinged to the lower part of the lifting column 4.

[0039] It should be noted that when the lifting column 4 drives the wheel 9 to descend, the movable sleeve 401 slides downward on the lifting column 4, and the first buffer rod 10 and the second buffer rod 11 rotate, reducing the included angle and providing a certain buffering effect for the descent of the landing gear.

[0040] Please see Figure 4 An electric retraction device is installed on the upper part of one side of the main landing gear mounting base 5, and a laser level is installed on one side of the electric retraction device.

[0041] It should be noted that the electric retraction device is used to adjust and power on the laser level to ensure that the landing gear installation angle is 90° with the fuselage.

[0042] Example 2

[0043] This embodiment of a method for connecting a UAV fuselage and landing gear adopts the method of UAV fuselage and landing gear connection in Embodiment 1. The specific steps include: using 3D design software based on the landing gear manufacturer's input and in conjunction with the fuselage structure, the design of the connection structure is completed. First, the connection structure needs to be connected to the landing gear. The fuselage is leveled, and the landing gear is leveled using a laser level. The electric retraction device is powered on, allowing the landing gear to be in the lowered state, controlling the landing gear installation angle. Specific connection and adjustment methods: The landing gear is installed as a whole; the main landing gear mounting plate 1 is glued to the fuselage, requiring at least 15 minutes of structural adhesive application. A laser level is used to ensure the landing gear installation angle is 90° to the fuselage, serving as a reference for subsequent installation; the landing gear and connection structure are inserted into the fuselage structure from above, and the landing gear is connected to the main landing gear mounting bracket 101 using bolts; the electric retraction device is powered on, and the landing gear is adjusted to the final lowered state; the actuator mounting bracket 3 is glued to the fuselage and cured for 24 hours. Then, adjust the position of the front landing gear mounting auxiliary pad 2 to ensure that the angle between the landing gear and the fuselage centerline is above 90° and there is no inward bending. Adhere the front landing gear mounting auxiliary pad 2 to the lower skin of the fuselage and reinforce it with L-shaped aluminum profiles. Bolt the front landing gear support bracket 201, the front landing gear connecting bracket 202 and the actuator connecting bracket 301. Adjust and reinforce the connection gap with composite carbon plates. Fix the main landing gear mounting bracket 101 and the actuator mounting bracket 3 to the fuselage with adhesive rivets. The installation is complete.

[0044] In summary, the invention achieves the connection between the fuselage and the landing gear through the main landing gear mounting plate 1, the front landing gear mounting auxiliary pad 2, and the actuator cylinder mounting bracket 3. During the connection process, the position of the landing gear is adjusted in conjunction with the electric retraction device and the laser level. At the same time, the connection between the electric push rod 8, the second support rod 7, and the first support rod 6 is used to control the installation angle of the landing gear. It has convenient operability, a short design and manufacturing cycle, and can complete the manufacturing and installation of the structure more quickly. Compared with the traditional tooling positioning and installation of landing gear, it greatly saves production costs.

[0045] The above-described embodiments are merely illustrative of certain implementations of the present invention, and are described in a relatively specific and detailed manner. However, they should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements are all within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the appended claims.

Claims

1. An unmanned aerial vehicle fuselage and landing gear connection structure, characterized in that: Including main landing gear mounting plate (1), front landing gear mounting auxiliary pad plate (2) and actuator mounting support (3), the main landing gear mounting plate (1) is glued on the fuselage, a plurality of main landing gear mounting supports (101) are fixedly connected on one side of the main landing gear mounting plate (1), the main landing gear mounting support (101) is fixedly connected with the landing gear through bolts, a plurality of front landing gear support brackets (201) are connected on the lower part of one side of the front landing gear mounting auxiliary pad plate (2) through bolts, a plurality of front landing gear connecting frames (202) are glued on the lower part of the other side of the front landing gear mounting auxiliary pad plate (2), the actuator mounting support (3) is fixedly connected with actuator connecting frame (301) on one side near the end; The landing gear includes lifting column (4), the upper end of the lifting column (4) is connected with main landing gear mounting seat (5), the lifting column (4) can be lifted in the inside of the main landing gear mounting seat (5), the main landing gear mounting support (101) is installed on the upper part of the main landing gear mounting seat (5), the outside of the main landing gear mounting seat (5) is connected with fixed sleeve (501), the first branch rod (6) is hinged on one side of the fixed sleeve (501), the second branch rod (7) is hinged on the upper end of the first branch rod (6), the second branch rod (7) is hinged on the side wall of the front landing gear mounting auxiliary pad plate (2) on the upper end, the electric push rod (8) is installed on one side of the actuator mounting support (3), the inside wall of the front landing gear mounting auxiliary pad plate (2) is hinged on the end of the electric push rod (8) execution rod; The bottom end of the lifting column (4) is equipped with wheels (9), the rubber surface of the wheel (9) is made of special material rubber wire resistant to wear and high temperature, the thickness of the wheel (9) is 20mm; The outside of the lifting column (4) is slidably fitted with movable sleeve (401), the first buffer rod (10) is hinged on one side of the movable sleeve (401), the second buffer rod (11) is hinged on the bottom end of the first buffer rod (10), the first buffer rod (10) is hinged on the lower part of the lifting column (4); The electric winding and unwinding device is installed on one side of the upper part of the main landing gear mounting seat (5), the laser level is installed on one side of the electric winding and unwinding device; Further comprising the following steps: 1) the whole landing gear is installed; 2) the main landing gear mounting plate (1) is glued on the fuselage, the structure glue operation time needs more than 15 minutes, the landing gear installation angle is measured by the laser level to ensure that the fuselage is 90°, which is used as the reference for subsequent installation; 3) the landing gear and the connecting structure are put into the body structure from the side of the fuselage, and the landing gear and the main landing gear mounting support (101) are connected by bolts; 4) the electric winding and unwinding device is powered on, and the landing gear is adjusted to the final state of being unwound; 5) the actuator mounting support (3) is glued on the fuselage, and is cured for 24 hours; 6) the position of the front landing gear mounting auxiliary pad plate (2) is adjusted to ensure that the angle between the landing gear and the fuselage center axis is more than 90°, the front landing gear mounting auxiliary pad plate (2) is bonded with the fuselage lower skin, and is reinforced by L-shaped aluminum profile. 7) bolt connection before landing gear support bracket (201), front landing gear connecting frame (202) and actuator connecting frame (301), connecting gap uses composite carbon plate to adjust reinforcement, main landing gear mounting support (101) and actuator mounting support (3) are fixed with fuselage by glue riveting, and installation is finished.

2. A method for connecting a UAV fuselage and landing gear, using the connecting structure of claim 1, characterized in that, It specifically includes the following steps: by using three-dimensional design software, according to the input of the landing gear manufacturer, cooperate with the fuselage structure, complete the design of the connecting structure, first the connecting structure needs to be connected with the landing gear, first adjust the fuselage to be flat, use laser level to adjust the landing gear to be flat, and power on the electric retraction device, so that the landing gear is in the lowered state, control the installation angle of the landing gear.

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