quick-release landing gear structure for drones

Abstract

This utility model relates to the field of unmanned aerial vehicles (UAVs), and particularly to a quick-release landing gear structure for UAVs. The quick-release landing gear mainly consists of three parts: a fuselage fixing structure, a positioning and locking mechanism, and a disassembly and storage section. The fuselage fixing structure is composed of a landing gear mounting base (1). A quick-release landing gear latch (2) is fixed to the landing gear mounting base (1) with screws. A quick-release wrench (3) is used to install a locking plate (11) on the quick-release landing gear latch (2) via a quick-release T-shaped lever (13) and a quick-release lever knob (12). The top of the landing gear vertical tube (8) is axially positioned with the landing gear carbon tube seat (4) by rivets (7) and clamped by carbon tube clamping screws (6). The landing gear horizontal carbon tube (10) is fixed to the landing gear vertical tube (8) via a landing gear tee connector (9). The quick-release structure allows for disassembly and assembly. The disassembly and assembly speed is greatly increased, allowing the aircraft to be disassembled for transport and quickly assembled on-site.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to a quick-release landing gear structure for UAVs. Background Technology

[0002] The assembly speed of drones directly determines their market competitiveness, emergency response capabilities, and cost control effectiveness. Specifically, rapid assembly enables drones to quickly respond to various needs, especially in emergency scenarios such as disaster relief, security, and surveying, allowing for rapid deployment and playing a crucial role in critical moments, reducing losses and improving operational efficiency. Furthermore, rapid assembly significantly improves order delivery efficiency, helping companies meet customer needs faster, seize market share, and flexibly respond to fluctuations in industry demand, avoiding missed business opportunities due to production delays. From a cost perspective, high-speed assembly supports large-scale production, effectively amortizing fixed costs such as R&D and equipment through batch operations, thereby reducing unit product prices, enhancing price competitiveness, and making products more attractive in the market.

[0003] However, current drone-based modular transport technology has some significant drawbacks. Firstly, it suffers from low assembly and disassembly efficiency: some connecting structures still require auxiliary tools, such as screwdrivers or specialized equipment, leading to lengthy operation times for non-professionals, increasing deployment time, and potentially impacting the overall mission's progress.

[0004] There is currently no technology for quickly disassembling and assembling drone landing gear.

[0005] On December 3, 2025, a search was conducted in the China Utility Model Publication Database using "drone and rapid and disassembly and landing gear and wrench" as the abstract keywords and with the option to allow synonym expansion selected. No relevant literature was found.

[0006] On December 3, 2025, an abstract search was conducted on CNKI (China National Knowledge Infrastructure) for "UAV and rapid disassembly and landing gear". No relevant literature was found. The only literature was "HRS62XA Aerial Monitoring and Direction Finding System".

[0007] On December 3, 2025, a search was conducted on the U.S. Utility Model and Trademark Office website for "drone with quick with disassembly with lwithinggear", but no relevant documents were found; the search URL is https: / / ppubs.uspto.gov / pubwebapp / .

[0008] On December 3, 2025, a search was conducted on WIPO's website https: / / patentscope2.wipo.int / for the term "drone and quick and disassembly and landing gear," but no relevant literature was found.

[0009] On December 3, 2025, a search was conducted on the website of the Japan Patent Office (https: / / www.j-platpat.inpit.go.jp / ) for the term "drone and quick and disassembly and landing gear," but no relevant literature was found.

[0010] This is completely different from the concept of this utility model. Utility Model Content

[0011] The purpose of this utility model is to provide a better quick-release landing gear structure for drones. The specific purpose is explained in the several substantial technical effects described in the detailed implementation section.

[0012] To achieve the above objectives, the present invention adopts the following technical solution: The quick-release landing gear structure for drones is characterized by, The quick-release landing gear mainly consists of three parts: the fuselage fixing structure, the positioning and locking mechanism, and the disassembly and storage section. The fuselage fixed structure consists of the landing gear mounting base 1; The positioning and locking mechanism mainly consists of a quick-release landing gear latch 2, a quick-release wrench 3, a locking pressure plate 11, a quick-release pull rod knob 12, and a quick-release T-shaped pull rod 13; The disassembly and storage section mainly consists of landing gear carbon tube seat 4, carbon tube clamping screw 6, rivet 7, landing gear vertical tube 8, landing gear tee connector 9, and landing gear horizontal carbon tube 10. The landing gear mounting base 1 is installed on the fuselage structure of the UAV. The quick-release landing gear latch 2 is fixed to the landing gear mounting base 1 with screws. The quick-release wrench 3 installs the locking plate 11 on the quick-release landing gear latch 2 through the quick-release T-shaped pull rod 13 and the quick-release pull rod knob 12. The top end of the landing gear vertical tube 8 is axially positioned with the landing gear carbon tube seat 4 by rivets 7 and clamped tightly by carbon tube clamping screws 6. The landing gear horizontal carbon tube 10 is fixed to the landing gear vertical tube 8 by the landing gear tee connector 9.

[0013] A further technical solution of this utility model is that the positioning and locking mechanism includes a stainless steel ball plunger 5, which is located on the landing gear carbon tube seat 4. The stainless steel ball plunger 5 on the landing gear carbon tube seat 4 can slide into the positioning hole below the quick-release landing gear latch 2.

[0014] A further technical solution of this utility model is that both the landing gear carbon tube seat 4 and the quick-release landing gear latch 2 include a positioning plane 14.

[0015] A further technical solution of this utility model is that the bottom of the quick-release landing gear latch 2 includes a notch 15, and the locking plate 11 can be pressed against the notch at the bottom of the quick-release landing gear latch 2. The notch at the bottom of the quick-release landing gear latch 2 can be contracted after being pressed.

[0016] A further technical solution of this utility model is that the locking pressure plate 11 is an arc-shaped sheet structure.

[0017] The present invention, employing the above technical solution, has the following advantages over the prior art: This embodiment adopts a rapid structure, enabling disassembly and assembly. The disassembly and assembly speed is greatly increased, allowing the aircraft to be transported in separate parts and quickly assembled on-site. Attached Figure Description

[0018] To further illustrate this utility model, the following description is provided in conjunction with the accompanying drawings: Figure 1 A perspective view of the utility model; Figure 2 This is a cross-sectional view of the clamping part of the utility model; Figure 3 This is a three-dimensional view of the entire utility model; Figure 4 For utility model Figure 3 A partial structural diagram; The components include: 1. Landing gear mounting bracket; 2. Quick-release landing gear latch; 3. Quick-release wrench; 4. Landing gear carbon tube mount; 5. Stainless steel ball plunger; 6. Carbon tube clamping screw; 7. Rivet; 8. Landing gear vertical tube; 9. Landing gear tee connector; 10. Landing gear transverse carbon tube; 11. Locking plate; 12. Quick-release lever knob; 13. Quick-release T-shaped lever; 14. Positioning plane; 15. Notch. Detailed Implementation

[0019] The present invention will be further explained below with reference to the accompanying drawings and specific embodiments. It should be understood that the following specific embodiments are only for illustrating the present invention and are not intended to limit the scope of the present invention. In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," "top," and "bottom," 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 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, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joining" 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; they can refer to the internal connection of two components. For those skilled in the art, the specific meaning of the above terms in the present invention can be understood according to the specific circumstances.

[0020] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0021] This utility model provides multiple parallel solutions. The different descriptions represent improved or parallel solutions based on the basic solution. Each solution has its own unique characteristics. Furthermore, the technical features involved in the different embodiments of this utility model described below can be combined with each other as long as they do not conflict with each other. Fixing methods not described herein can be any type of fixing, such as threaded fixing, bolt fixing, or adhesive bonding.

[0022] Example 1: Referring to all the attached drawings; A quick-release landing gear structure for unmanned aerial vehicles, characterized in that, The quick-release landing gear mainly consists of three parts: the fuselage fixing structure, the positioning and locking mechanism, and the disassembly and storage section. The fuselage fixed structure consists of the landing gear mounting base 1; The positioning and locking mechanism mainly consists of a quick-release landing gear latch 2, a quick-release wrench 3, a locking pressure plate 11, a quick-release pull rod knob 12, and a quick-release T-shaped pull rod 13; The disassembly and storage section mainly consists of landing gear carbon tube seat 4, carbon tube clamping screw 6, rivet 7, landing gear vertical tube 8, landing gear tee connector 9, and landing gear horizontal carbon tube 10. The landing gear mounting base 1 is installed on the fuselage structure of the UAV. The quick-release landing gear latch 2 is fixed to the landing gear mounting base 1 with screws. The quick-release wrench 3 installs the locking plate 11 on the quick-release landing gear latch 2 through the quick-release T-shaped pull rod 13 and the quick-release pull rod knob 12. The top end of the landing gear vertical tube 8 is axially positioned to the landing gear carbon tube seat 4 by rivets 7 and clamped tightly by carbon tube clamping screws 6. The landing gear transverse carbon tube 10 is fixed to the landing gear vertical tube 8 by the landing gear tee connector 9. The substantial technical effect and its implementation process, i.e., the basic function and non-obvious aspects, are as follows: The quick-release landing gear mainly consists of three parts: the fuselage fixing structure, the positioning and locking mechanism, and the disassembly and storage section. The fuselage fixing structure mainly consists of 1. the landing gear mounting base; the positioning and locking mechanism mainly consists of 2. the quick-release landing gear latch, 3. the quick-release wrench, 5. the stainless steel ball plunger, 11. the locking pressure plate, 12. the quick-release lever knob, and 13. the quick-release T-shaped lever; and the disassembly and storage section mainly consists of 4. the landing gear carbon tube seat, 6. the carbon tube clamping screw, 7. the rivet, 8. the landing gear vertical tube, 9. the landing gear tee connector, and 10. the landing gear transverse carbon tube.

[0023] The landing gear mounting base 1 is installed on the fuselage structure of the UAV. The quick-release landing gear latch 2 is fixed to the landing gear mounting base 1 with screws. The quick-release wrench 3 installs the locking plate 11 on the quick-release landing gear latch 2 through the quick-release T-shaped pull rod 13 and the quick-release pull rod knob 12.

[0024] The top end of the landing gear vertical tube 8 is axially positioned with the landing gear carbon tube seat 4 by rivets 7 and clamped by carbon tube clamping screws 6. The landing gear horizontal carbon tube 10 is fixed to the landing gear vertical tube 8 by the landing gear tee connector 9.

[0025] Landing gear quick-release procedure: When disassembling the landing gear, pry open the quick-release wrench 3 by hand. The locking plate 11 is no longer squeezed by the quick-release wrench 3, and the bottom notch of the quick-release landing gear lock 2 is no longer squeezed by the locking plate 11, thus losing the gripping force on the landing gear carbon tube seat 4. Hold the landing gear vertical tube 8 by hand and pull the disassembly and storage part to remove the disassembly and storage part of the landing gear. Landing gear quick-assembly process: Align the landing gear carbon tube seat 4 in the disassembly and storage section with the installation port of the quick-release landing gear latch 2, push the positioning surface of the landing gear carbon tube seat 4 along the positioning plane of the quick-release landing gear latch 2 and insert it. The stainless steel ball plunger 5 installed on the landing gear carbon tube seat 4 slides into the positioning hole below the quick-release landing gear latch 2. Press the quick-release wrench 3 by hand and pull the quick-release T-shaped lever 13 to press the locking plate 11 against the bottom notch of the quick-release landing gear latch 2. The bottom notch of the quick-release landing gear latch 2 is compressed and contracts, clamping the landing gear carbon tube seat 4 tightly, thus completing the landing gear installation.

[0026] Compared to the shortcomings of existing technologies, "firstly, the disassembly and assembly efficiency is low: some connection structures still require auxiliary tools, such as screwdrivers or specialized instruments, resulting in longer operation times for non-professionals, increasing deployment time, and potentially affecting the overall mission execution schedule."; this embodiment adopts a rapid structure that enables disassembly and assembly. The disassembly and assembly speed is greatly increased, allowing the aircraft to be transported in separate parts and quickly reassembled on-site.

[0027] Example 2: As a further improvement, parallel, or optional independent solution, the positioning and locking mechanism includes a stainless steel ball plunger 5, which is located on the landing gear carbon tube seat 4. The stainless steel ball plunger 5 on the landing gear carbon tube seat 4 can slide into the positioning hole below the quick-release landing gear latch 2. The substantial technical effect and its implementation process, i.e., the basic function and non-obvious aspects, are as follows: Therefore, effective positioning and more precise installation are achieved.

[0028] Example 3: As a further improvement, parallel, or optional independent solution, both the landing gear carbon tube seat 4 and the quick-release landing gear latch 2 include a positioning plane 14. The substantial technical effect and its implementation process, i.e., the basic function and non-obviousness, are as follows: making disassembly and alignment more convenient.

[0029] Example 4: As a further improvement, parallel, or optional independent solution, the bottom of the quick-release landing gear latch 2 includes a notch 15. The locking plate 11 can press against the notch at the bottom of the quick-release landing gear latch 2, and the notch at the bottom of the quick-release landing gear latch 2 can retract after being pressed. The substantial technical effect and its implementation process, i.e., the basic function and non-obviousness, are as follows: it can then be pressed inward to achieve tight positioning and installation.

[0030] Example 5: As a further improvement, parallel, or optional independent solution, the locking plate 11 is an arc-shaped sheet structure. Its substantial technical effect and implementation process, i.e., its basic function and non-obviousness, are as follows: it can fit the pressing notch, facilitating stable fixation.

[0031] Innovatively, each of the above effects exists independently, yet a single structure can be used to combine the results.

[0032] It should be noted that the multiple modules of this utility model are an integration of existing technology modules and do not involve any new modules. Even if some modules use programs, these programs are undoubtedly known programs.

[0033] It should be noted that the multiple solutions provided by this utility model include their own basic solutions, are independent of each other and do not restrict each other, but they can also be combined with each other without conflict to achieve multiple effects together.

[0034] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claims.

Claims

1. A quick-release landing gear structure for unmanned aerial vehicles (UAVs), characterized in that: The quick-release landing gear mainly consists of three parts: the fuselage fixing structure, the positioning and locking mechanism, and the disassembly and storage section. The fuselage fixed structure consists of the landing gear mounting base (1); The positioning and locking mechanism mainly consists of a quick-release landing gear latch (2), a quick-release wrench (3), a locking plate (11), a quick-release lever knob (12), and a quick-release T-shaped lever (13); The disassembly and storage section mainly consists of landing gear carbon tube seat (4), carbon tube clamping screw (6), rivet (7), landing gear vertical tube (8), landing gear tee connector (9), and landing gear horizontal carbon tube (10); The landing gear mounting bracket (1) is installed on the fuselage structure of the UAV. The quick-release landing gear latch (2) is fixed to the landing gear mounting bracket (1) by screws. The quick-release wrench (3) installs the locking plate (11) on the quick-release landing gear latch (2) through the quick-release T-shaped pull rod (13) and the quick-release pull rod knob (12). The top end of the landing gear vertical tube (8) is axially positioned with the landing gear carbon tube seat (4) by rivets (7) and clamped by carbon tube clamping screws (6). The landing gear horizontal carbon tube (10) is fixed to the landing gear vertical tube (8) by the landing gear tee connector (9). 2.The quick-release landing gear structure of the UAV according to claim 1, wherein, The positioning and locking mechanism includes a stainless steel ball plunger (5), which is located on the landing gear carbon tube seat (4). The stainless steel ball plunger (5) on the landing gear carbon tube seat (4) can slide into the positioning hole below the quick-release landing gear latch (2). 3.The quick-release landing gear structure of the UAV according to claim 1, wherein, Both the landing gear carbon tube mount (4) and the quick-release landing gear latch (2) include a positioning plane (14). 4.The quick-release landing gear structure of the UAV according to claim 1, wherein, The bottom of the quick-release landing gear latch (2) includes a notch (15), and the locking plate (11) can press against the notch at the bottom of the quick-release landing gear latch (2). The notch at the bottom of the quick-release landing gear latch (2) can shrink after being pressed. 5.The quick-release landing gear structure of the UAV according to claim 1, wherein, The locking plate (11) is an arc-shaped sheet structure.

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