Press-to-release landing gear

Abstract

This utility model relates to the field of unmanned aerial vehicles (UAVs), and particularly to a push-button quick-release landing gear. The overall structure includes a quick-release landing gear base (2) and a landing gear carbon tube base (3); the quick-release landing gear base (2) includes a quick-release button (7), and the end of the quick-release steel shaft (9) connected to the quick-release button (7) is fixed in the landing gear locking tongue block (10); a quick-release spring (8) is mounted on the side of the quick-release steel shaft (9) near the quick-release button (7); a notch (12) is arranged at the end of the landing gear carbon tube base (3); and a locking groove (13) is arranged on the side of the landing gear carbon tube base (3); the initial state of the quick-release spring (8) allows the landing gear locking tongue block (10) to be pressed in the locking groove (13); when the quick-release button (7) is pressed, it can move the quick-release steel shaft (9) as a whole, thereby allowing the landing gear locking tongue block (10) to disengage from the locking groove (13).

Description

Technical Field

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

[0002] The speed of drone assembly is crucial to the overall performance and application effectiveness of drone systems. Whether for military missions or civilian operations, rapid and accurate assembly not only enhances deployment flexibility but also directly impacts mission timeliness and success rate. Especially in scenarios involving multiple concurrent missions and high-intensity use, assembly efficiency has become a key indicator of drone system maturity. In the civilian sector, increased drone assembly speed brings significant economic and efficiency benefits: the application of automated assembly lines has enabled large-scale and standardized drone assembly; an advanced automated assembly line can assemble 10 drones per hour, significantly increasing production capacity and reducing the uncertainty of human intervention; intelligent assembly technology and vision-assisted systems effectively control production costs, reduce human error, and improve component assembly accuracy, enhancing product consistency and reliability; in emergency scenarios such as disaster relief and firefighting, rapid assembly allows drones to take off faster and perform missions, buying time to save lives and minimize losses. In commercial applications such as logistics and distribution, agricultural plant protection, and power line inspection, the rapid deployment capability of drones directly affects operational efficiency. For example, logistics companies can quickly assemble and switch task modules to achieve multi-point, high-frequency flight scheduling, significantly reducing time and labor costs.

[0003] There are six common ways to fix a drone, to suit different usage scenarios: Screw / bolt fixing: The bracket is fixed to the bottom or frame of the drone by threaded connection, usually with anti-loosening adhesive or mechanical locking structure.

[0004] Clip-on / clamp-on fixing: The bracket is connected to the machine body by pre-embedded slots or spring clips, and some designs support manual operation.

[0005] Cable ties / straps: Use nylon cable ties, elastic straps or Velcro straps to secure the bracket to the machine body.

[0006] Magnetic fixation: The bracket and the drone are quickly attached and separated by a strong magnet or electromagnetic structure.

[0007] Fixed bracket (non-folding): The bracket is rigidly connected to the main body of the drone and is generally a permanent fixed structure.

[0008] Foldable support: The support is designed to be rotatable or telescopic, unfolding during flight and folding up when parked.

[0009] All types of fixing methods have obvious defects, affecting user experience and safety: Screw / bolt fixing: Installation and disassembly rely on special tools, which are cumbersome and not suitable for rapid deployment; frequent disassembly and assembly can easily lead to thread wear, causing loose connections or even flight accidents; metal screws add extra weight, which is detrimental to endurance and maneuverability.

[0010] Clip-on / clamp-on fixing: has limited structural strength, making it difficult to support heavy equipment and limiting its application range; it is prone to displacement and detachment under high-frequency vibration or lifting and lowering impact, resulting in insufficient reliability; it is mostly designed for special models and lacks versatility.

[0011] Cable ties / straps: These are prone to loosening due to vibration, wind resistance, or long-term use, causing the equipment to shake and fall off; most are for single use, resulting in high long-term costs and environmental problems; exposed cable ties increase air resistance, affecting flight stability and range.

[0012] Magnetic fixation: The magnetic force is limited and it is only suitable for light equipment. The tensile strength is relatively low. It is susceptible to external electromagnetic interference and may break unexpectedly. High and low temperature environments will change the magnetic properties, weaken the adsorption force and pose a safety risk.

[0013] Fixed support (non-folding): Extended support increases aerodynamic drag, reducing flight speed and range; it takes up a lot of space for storage and transportation, resulting in poor portability; the support attitude cannot be adjusted, leading to insufficient stability when landing on uneven ground.

[0014] Folding brackets: The folding mechanism has complex parts, which increases manufacturing costs and overall weight; the joints are prone to wear and tear after long-term use, which may prevent them from unfolding or locking properly; operation requires multiple people or additional steps, which is not conducive to rapid emergency deployment.

[0015] On November 30, 2025, a search was conducted in the China Utility Model Publication Database using "drone and landing gear and installation and detachable and pressable" as the abstract keywords and with the option to allow synonym expansion. No relevant literature was found.

[0016] On November 30, 2025, an abstract search was conducted on CNKI (China National Knowledge Infrastructure) for the keywords "drone and landing gear and installation and detachable and press-to-open". No relevant literature was found.

[0017] On November 30, 2025, a search was conducted on the U.S. Utility Model and Trademark Office website for the term "drone with lwithing gear with install with removable with press," but no relevant literature was found; the search URL is https: / / ppubs.uspto.gov / pubwebapp / .

[0018] On November 30, 2025, a search was conducted on WIPO's website https: / / patentscope2.wipo.int / for the term "drone and landing gear and install and removable and press", but no relevant literature was found.

[0019] On November 30, 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 landing gear and install and removable and press," but no relevant literature was found.

[0020] This is completely different from the concept of this utility model. Utility Model Content

[0021] The purpose of this utility model is to provide a more effective push-to-release landing gear. The specific purpose is explained in the several substantial technical effects described in the detailed implementation section.

[0022] To achieve the above objectives, the present invention adopts the following technical solution: The push-button quick-release landing gear is characterized by... The overall structure includes a quick-release landing gear base 2 and a landing gear carbon tube base 3; The quick-release landing gear base 2 includes a quick-release button 7, and the end of the quick-release steel shaft 9 connected to the quick-release button 7 is fixed in the landing gear locking tongue block 10. A quick-release spring 8 is installed on the side of the quick-release steel shaft 9 near the quick-release button 7; A notch 12 is provided at the end of the landing gear carbon tube seat 3; and a locking groove 13 is provided on the side of the landing gear carbon tube seat 3. The initial state of the quick-release spring 8 allows the landing gear locking tongue block 10 to be pressed into the locking groove 13; When the quick-release button 7 is pressed, the quick-release steel shaft 9 moves as a whole, allowing the landing gear locking tongue block 10 to disengage from the locking groove 13.

[0023] A further technical solution of this utility model is that the landing gear carbon tube seat 3 is connected to the landing gear vertical carbon tube 4, the landing gear vertical carbon tube 4 is connected to the landing gear tee connector 5, the landing gear tee connector 5 includes a clamp, and the landing gear horizontal carbon tube 6 is arranged in the clamp.

[0024] A further technical solution of this utility model is that the quick-release landing gear base 2 includes a landing gear mounting base 1.

[0025] A further technical solution of this utility model is that the landing gear mounting base 1 is installed on the fuselage structure of the UAV, and the quick-release landing gear female base 2 is fixed to the landing gear mounting base 1 by screws.

[0026] A further technical solution of this utility model is that the landing gear locking tongue block 10 includes an movable space 15 on the wall of the quick-release landing gear mother seat 2 for forward and backward movement.

[0027] A further technical solution of this utility model is that a locking protrusion 11 is arranged at the end of the quick-release steel shaft 9, and the locking protrusion 11 is inserted into the hole of the landing gear locking tongue block 10 and locked by the protrusion.

[0028] The present invention, which adopts the above technical solution, has the following advantages over the prior art: Compared with the installation structure of the prior art, the present invention can be quickly installed and disassembled; it can innovatively realize the quick disassembly and quick assembly of drones, allowing them to be directly disassembled for transport and then quickly assembled on site. Attached Figure Description

[0029] 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 core part of the utility model; Figure 3 Diagram showing the fixing of the landing gear locking tongue block end; Figure 4 This is a partial perspective view of the utility model; Figure 5 This is a partial view of the landing gear locking tongue block of a utility model. The components include: 1. Landing gear mounting base; 2. Quick-release landing gear female base; 3. Landing gear carbon tube base; 4. Landing gear vertical carbon tube; 5. Landing gear tee connector; 6. Landing gear horizontal carbon tube; 7. Quick-release push button; 8. Quick-release spring; 9. Quick-release steel shaft; 10. Landing gear locking tongue block; 11. Locking protrusion; 12. Notch; 13. Locking groove; 14. Locking tongue end; 15. Movement space. Detailed Implementation

[0030] 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.

[0031] 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.

[0032] 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.

[0033] Example 1: Referring to all the attached drawings; The push-button quick-release landing gear is characterized in that... The overall structure includes a quick-release landing gear base 2 and a landing gear carbon tube base 3; The quick-release landing gear base 2 includes a quick-release button 7, and the end of the quick-release steel shaft 9 connected to the quick-release button 7 is fixed in the landing gear locking tongue block 10. A quick-release spring 8 is installed on the side of the quick-release steel shaft 9 near the quick-release button 7; A notch 12 is provided at the end of the landing gear carbon tube seat 3; and a locking groove 13 is provided on the side of the landing gear carbon tube seat 3. The initial state of the quick-release spring 8 allows the landing gear locking tongue block 10 to be pressed into the locking groove 13; When the quick-release button 7 is pressed, the quick-release steel shaft 9 moves as a whole, allowing the landing gear locking tongue block 10 to disengage from the locking groove 13. The actual technical effect and its implementation process, i.e., the basic function and non-obvious aspects, are as follows: The landing gear mounting base 1 is installed on the fuselage structure of the UAV. The quick-release landing gear female base 2 is fixed to the landing gear mounting base 1 with screws. The quick-release steel shaft 9 passes through the steel shaft mounting hole of the quick-release landing gear female base 2 and is fixed to the landing gear locking tongue block 10 through the thread at the end of the quick-release steel shaft 9. The quick-release button 7 is fixed to the threaded hole at the other end of the quick-release steel shaft 9 with screws. The quick-release button 7 presses two quick-release springs into the quick-release button mounting groove of the quick-release landing gear female base 2.

[0034] The top end of the landing gear vertical carbon tube 4 is fixed to the carbon tube mounting end of the landing gear carbon tube seat 3 by screws and the clamping structure of the landing gear carbon tube seat 3. The landing gear horizontal carbon tube 6 is fixed to the landing gear vertical carbon tube 4 by the landing gear tee connector 5.

[0035] Landing gear quick-release procedure: When disassembling the landing gear, press the quick-release button 7 by hand. The quick-release button compresses the quick-release spring 8 downward, and drives the quick-release steel shaft 9 and the landing gear locking tongue block 10 fixed at the other end of the quick-release steel shaft to slide along the steel shaft mounting hole of the quick-release landing gear mother seat 2 in the pressing direction. When the quick-release button 7 is pressed to the bottom, the wedge-shaped locking surface of the landing gear locking tongue block 10 disengages from the locking groove on the landing gear carbon tube seat 3. Grasp the landing gear vertical carbon tube by hand and pull it outward to disassemble the disassembly and storage part. Landing gear quick-assembly process: Align the tapered mounting end of the landing gear carbon tube seat 3 in the disassembly and storage section with the mounting opening of the quick-release landing gear female seat 2, and push it inward forcefully. The tapered surface of the landing gear carbon tube seat 3 presses against the wedge-shaped locking surface of the landing gear locking tongue block 10. After being pushed into place, the landing gear locking tongue block 10 slides into the locking groove on the landing gear carbon tube seat 3 through the quick-release spring 8 pushing the quick-release button 7 and the quick-release steel shaft 9, thus locking the disassembly and storage section and the fuselage fixing structure, completing the landing gear installation.

[0036] Compared to existing installation structures, this invention enables rapid installation and disassembly; it innovatively enables the quick assembly and disassembly of drones, allowing them to be directly disassembled for transport and then quickly assembled on-site.

[0037] Example 2: As a further improvement, parallel, or optional independent solution, the landing gear carbon tube seat 3 is connected to the landing gear vertical carbon tube 4, the landing gear vertical carbon tube 4 is connected to the landing gear tee connector 5, and the landing gear tee connector 5 includes a clamp, in which the landing gear horizontal carbon tube 6 is arranged. The substantial technical effect and its implementation process, i.e., the basic function and non-obviousness, are as follows: a specific structure for a UAV landing gear is provided.

[0038] Example 3: As a further improvement, parallel, or optional independent solution, the quick-release landing gear base 2 includes a landing gear mounting base 1. The substantial technical effect and its implementation process, i.e., basic function and non-obviousness, are as follows: for mounting onto a UAV.

[0039] Example 4: As a further improvement, parallel, or optional independent solution, the landing gear mounting base 1 is installed on the fuselage structure of the UAV, and the quick-release landing gear female base 2 is fixed to the landing gear mounting base 1 with screws. The substantial technical effects and implementation process, i.e., the basic functions and non-obvious aspects, are as follows: similar fixing methods are all within the protection scope of this utility model.

[0040] Example 5: As a further improvement, parallel, or optional independent solution, the landing gear locking tongue block 10 includes a movable space 15 on the wall of the quick-release landing gear base 2 for forward and backward movement. The substantial technical effect and its implementation process, i.e., the basic function and non-obviousness, are as follows: to provide a gap for easy locking and unlocking.

[0041] Example 6: As a further improvement, parallel, or optional independent solution, the end of the quick-release steel shaft 9 is provided with a locking protrusion 11, which is inserted into the hole of the landing gear locking tongue block 10 and locked by the protrusion.

[0042] Innovatively, each of the above effects exists independently, yet a single structure can be used to combine the results.

[0043] 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.

[0044] 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.

[0045] 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 push-button quick-release landing gear, characterized in that, The overall structure includes a quick-release landing gear base (2) and a landing gear carbon tube base (3). The quick-release landing gear base (2) includes a quick-release button (7), and the end of the quick-release steel shaft (9) connected to the quick-release button (7) is fixed in the landing gear locking tongue block (10); A quick-release spring (8) is mounted on the side of the quick-release steel shaft (9) near the quick-release button (7). A notch (12) is provided at the end of the landing gear carbon tube seat (3); and a locking groove (13) is provided on the side of the landing gear carbon tube seat (3). The initial state of the quick-release spring (8) allows the landing gear locking tongue block (10) to be pressed into the locking groove (13); When the quick release button (7) is pressed, the quick release steel shaft (9) moves as a whole, allowing the landing gear locking tongue block (10) to disengage from the locking groove (13).

2. The push-button quick release landing gear according to claim 1, wherein, The landing gear carbon tube seat (3) is connected to the landing gear vertical carbon tube (4), the landing gear vertical carbon tube (4) is connected to the landing gear tee connector (5), the landing gear tee connector (5) includes a hoop, and the landing gear horizontal carbon tube (6) is arranged in the hoop.

3. The push-button quick release landing gear as claimed in claim 1, wherein, The quick-release landing gear base (2) includes a landing gear mounting base (1).

4. The push-button quick release landing gear as set forth in claim 1, wherein, The landing gear mounting bracket (1) is installed on the fuselage structure of the UAV, and the quick-release landing gear female bracket (2) is fixed to the landing gear mounting bracket (1) by screws.

5. The push-button quick release landing gear as set forth in claim 1, wherein, The landing gear locking tongue block (10) has a movable space (15) on the wall of the quick-release landing gear mother seat (2) for forward and backward movement.

6. The push-button quick release landing gear of claim 1, wherein, The end of the quick-release steel shaft (9) is provided with a locking protrusion (11), which is inserted into the hole of the landing gear locking tongue block (10) and locked by the protrusion.

Images