A retractable landing gear

Abstract

The utility model belongs to the technical field of unmanned plane, concretely relates to a retractable landing gear, including containing frame, landing support, limiting component and telescopic push rod. The utility model discloses the rotation direction adjustment is toward the advancing direction of unmanned plane when the landing support is stored in the internal storage cavity of containing frame, and when the landing support rotates to the vertical state, limiting support is realized by utilizing limiting component, so that in the ground taxiing stage of unmanned plane, the reverse torque borne by the landing support will not be transmitted to the telescopic push rod, effectively reduces the abrasion and fatigue damage of telescopic push rod, guarantees its stability in the long -term use process, and then prolongs the service life, and reduces maintenance cost and replacement frequency.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a retractable landing gear. Background Technology

[0002] Currently, most mainstream manned aircraft and large fixed-wing unmanned aerial vehicles adopt a landing gear structure that rotates backward and retracts (i.e., rotates backward and upward along the fuselage and retracts into the cabin); this design effectively meets the functional requirements of landing gear for ground support and in-flight storage, and has been widely used.

[0003] However, this structure has inherent mechanical defects during the ground taxiing phase. When the aircraft accelerates forward on the ground, the landing gear strut will simultaneously bear the rearward aerodynamic drag and the ground reaction force, thus generating a significant reverse torque around its rotation axis. This reverse torque is directly transmitted to the telescopic push rod mechanism that drives the landing gear retraction and extension, forcing it to continuously bear extremely large dynamic bending moments and axial shear loads in the deployed state, with operating conditions far exceeding its conventional design load.

[0004] To address the aforementioned overload issues, traditional techniques typically rely on increasing the diameter of the push rod or reinforcing its support structure to improve structural strength and ensure reliability. While this method is feasible on large platforms, when applied to small fixed-wing UAVs, it inevitably leads to a significant increase in the weight of the landing gear system and even the entire aircraft. This undoubtedly violates the core design principle of lightweighting small UAVs and will inevitably and significantly weaken key performance indicators such as endurance and load-bearing capacity. Utility Model Content

[0005] The purpose of this invention is to provide a retractable landing gear that solves the technical problem that the telescopic push rod in the existing landing gear structure is subject to reverse torque, which easily leads to wear and fatigue damage, thereby reducing long-term stability, shortening service life, and increasing maintenance costs and replacement frequency.

[0006] This utility model discloses a retractable landing gear, comprising:

[0007] The accommodating frame has an internal storage cavity and an inlet / outlet at the bottom;

[0008] The landing gear has its top end rotatably connected to the storage cavity through the inlet and outlet, and can be rotated upwards and forwards to be stored in the storage cavity.

[0009] A limiting component, installed in the storage cavity, is used to limit the landing gear from continuing to rotate upward in the rearward direction when the landing gear is rotated to a vertical position.

[0010] The telescopic push rod is hinged at one end to the landing support and rotatably connected to the storage cavity at the other end, and is used to drive the landing support to extend and retract.

[0011] This application achieves a limiting support function by adjusting the rotation direction of the landing gear when it is housed in the storage cavity of the accommodating frame to face the forward direction of the UAV. At the same time, when the landing gear rotates to the vertical position, the limiting component restricts its rotation in the backward direction of the UAV. This ensures that during the UAV's ground taxiing phase, the reverse torque borne by the landing gear will not be transmitted to the telescopic push rod, thereby effectively reducing the wear and fatigue damage of the telescopic push rod, ensuring its stability during long-term use, extending its service life, and reducing maintenance costs and replacement frequency.

[0012] Based on the above technical solution, the solution of this application can be further improved as follows:

[0013] Preferably, the landing gear includes:

[0014] Support column;

[0015] The machine wheel is installed at the bottom end of the support column;

[0016] Two support arms are symmetrically arranged on both sides of the top of the support column and are rotatably connected to both sides of the inner wall of the storage cavity. This design forms a compact structure and ensures force balance, enabling the UAV to remain stable during take-off, landing and ground taxiing, reducing the risk of fuselage swaying and damage caused by uneven force.

[0017] Preferably, it includes:

[0018] The first horizontal axis is mounted between the two sides of the inner wall of the storage cavity, and each end of the first horizontal axis is rotatably connected to one of the support arms. By adopting this solution, the force transmitted from the support arms can be evenly distributed to both sides of the inner wall of the storage cavity, thereby ensuring the uniformity of the force on the UAV body and improving the structural stability.

[0019] Preferably, protrusions are formed on both sides of the inner wall of the storage cavity around the outer periphery of the first transverse axis, and the protrusions abut against the adjacent support arms. With this solution, the landing gear can be axially limited, thereby improving the operational stability of the landing gear. Moreover, the contact area between the landing gear and the support arms is small, which will not cause too much frictional resistance to the rotation and ensure smooth rotation.

[0020] Preferably, the limiting component includes:

[0021] The first crossbeam is installed between the two sides of the inner wall of the storage cavity and is located above the first horizontal axis;

[0022] The second crossbeam is installed between the two sides of the inner wall of the storage cavity and is located below the first cross axis;

[0023] When the landing gear is rotated to a vertical position, the front side of the support arm is in contact with the first crossbeam, and the rear side of the support column is in contact with the second crossbeam. This design enables a double mechanical locking mechanism when the landing gear is in a vertical position, thereby better dispersing and bearing external forces such as ground impacts, improving the overall structural strength, reducing stress concentration, and ensuring the effectiveness of the limiting support.

[0024] Preferably, the front side of the second crossbeam is provided with a limiting groove that matches the support column, and when the support column is fitted into the limiting groove, the rear side of the support arm is fitted into the second crossbeam. This solution can accurately position the support column, improve the take-off and landing stability of the UAV, and also more evenly transfer the force borne by the landing bracket to the second crossbeam, thereby further reducing stress concentration and enhancing structural strength.

[0025] Preferably, the front side of the accommodating frame has an accommodating opening that communicates with the inlet and outlet; when the landing gear is rotated to a lateral position, the support column falls into the accommodating opening and the wheels are positioned in front of the accommodating frame; by adopting this solution, the length of the accommodating frame can be shortened, thereby effectively reducing the overall weight of the accommodating frame, thereby improving the payload capacity, endurance and flight efficiency of the UAV.

[0026] Preferably, it includes:

[0027] A fixed partition frame is installed on the front side of the receiving frame and covers the receiving opening. This solution can support the casing surrounding the receiving frame, thereby improving the overall structural stability.

[0028] Preferably, it includes:

[0029] The second horizontal axis is mounted between the two sides of the inner wall of the storage cavity and is rotatably connected to one end of the telescopic push rod; this design ensures uniform force distribution and improves structural stability.

[0030] Through the above technical solution, this utility model achieves the following beneficial effects:

[0031] 1. This application adjusts the rotation direction of the landing gear when it is stored in the internal storage cavity of the accommodating frame to face the forward direction of the UAV. At the same time, when the landing gear rotates to the vertical position, the limiting component restricts its rotation in the backward direction of the UAV, thereby realizing the limiting support function. This ensures that during the UAV's ground taxiing phase, the reverse torque borne by the landing gear will not be transmitted to the telescopic push rod, thereby effectively reducing the wear and fatigue damage of the telescopic push rod, ensuring its stability during long-term use, extending its service life, and reducing maintenance costs and replacement frequency.

[0032] 2. By setting up a first crossbeam and a second crossbeam, this application can form a double mechanical lock on the landing gear when it is in a vertical position. This allows the landing gear to better disperse and bear external forces such as ground impact, thereby improving the overall structural strength, reducing stress concentration, and ensuring the effectiveness of the limiting support. Attached Figure Description

[0033] To more clearly illustrate the specific embodiments of this utility model or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0034] Figure 1 This is a schematic diagram of the retractable landing gear described in a specific embodiment of this application;

[0035] Figure 2 for Figure 1 A schematic diagram of the retractable landing gear (front side view).

[0036] Figure 3 for Figure 1 A schematic diagram of the retractable landing gear (rear side view).

[0037] Figure 4 for Figure 1 A schematic diagram of the internal structure of the retractable landing gear (side view).

[0038] Figure 5 for Figure 1 A schematic diagram of the internal structure of the boss in the retractable landing gear shown.

[0039] Explanation of reference numerals in the attached figures:

[0040] 1. Receiving frame; 101. Storage cavity; 1011. Boss; 102. Inlet / outlet; 103. Receiving opening;

[0041] 2. Landing support; 21. Support column; 22. Wheels; 23. Support arm;

[0042] 3. Limiting component; 31. First crossbeam; 32. Second crossbeam; 3201. Limiting groove;

[0043] 4. Telescopic push rod; 5. First horizontal axis; 6. Fixed partition frame; 7. Second horizontal axis. Detailed Implementation

[0044] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings. These embodiments are merely illustrative of the present invention and should not be construed as limiting the scope of protection of the present invention.

[0045] It should be noted that the forward direction refers to the direction in which the drone's head is facing when it is flying, which is the direction in which the drone is moving forward; while the rearward direction refers to the direction in which the drone's tail is facing when it is flying, which is the direction in which the drone is moving backward.

[0046] 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. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features.

[0047] In this application, unless otherwise expressly specified and limited, the terms "installation" and "connection" 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 direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0048] To better understand the above technical solutions, the following will provide a detailed description of the technical solutions in conjunction with the accompanying drawings and specific embodiments.

[0049] Example:

[0050] like Figure 1 As shown in the figure, this application discloses a retractable landing gear for automatic retraction and extension of the landing gear. Its specific structure includes: a housing frame 1, a landing support 2, a limiting component 3, and a telescopic push rod 4.

[0051] The housing frame 1 has a storage cavity 101 inside, which provides storage space for the landing gear 2, and the bottom has an inlet and outlet 102, which is the channel for the landing gear 2 to enter and exit the storage cavity 101; thus, the landing gear 2 can be stored in the housing frame 1 when it is not in use, thereby reducing the air resistance during the flight of the UAV and improving the flight efficiency.

[0052] The top of the landing gear 2 passes through the inlet / outlet 102 and is rotatably connected to the storage cavity 101. It can also be rotated upwards and forwards to be stored in the storage cavity 101. This retraction method is simple and direct, facilitates automated control, and allows the landing gear 2 to be retracted during flight to reduce flight drag, and rotated down during landing to provide stable support.

[0053] The limiting component 3 is installed in the storage cavity 101 to limit the landing support 2 from continuing to rotate upward in the rearward direction when it is rotated to a vertical position.

[0054] One end of the telescopic push rod 4 is hinged to the landing gear 2, and the other end is rotatably connected to the storage cavity 101. It is used to drive the landing gear 2 to rotate around its top through telescopic movement, so as to realize the retraction and extension of the landing gear 2. This drive method has a simple structure and is easy to control, which can meet the requirements of UAVs for rapid and accurate retraction and extension of the landing gear.

[0055] This invention adjusts the rotation direction of the landing gear 2 when it is housed in the storage cavity 101 of the accommodating frame 1 to face the forward direction of the drone. At the same time, when the landing gear 2 rotates to the vertical position, the limiting component 3 restricts its rotation in the backward direction of the drone, thereby realizing the limiting support function. This ensures that during the ground taxiing phase of the drone, the reverse torque borne by the landing gear 2 will not be transmitted to the telescopic push rod 4, thus effectively reducing the wear and fatigue damage of the telescopic push rod 4, ensuring its stability during long-term use, extending its service life, and reducing maintenance costs and replacement frequency.

[0056] In some embodiments, such as Figure 2 As shown, the landing gear 2 includes:

[0057] Support column 21 serves to provide support and connection;

[0058] The wheel 22 is installed at the bottom of the support column 21 and is used to make direct contact with the ground and use rolling friction to enable the drone to accelerate or decelerate smoothly.

[0059] Two support arms 23 are symmetrically arranged on both sides of the top of the support column 21, which helps to ensure force balance and are rotatably connected to both sides of the inner wall of the storage cavity 101.

[0060] The above structural design of the landing gear 2 forms a compact structure and ensures force balance, enabling the UAV to remain stable during takeoff, landing and ground taxiing, reducing the risk of fuselage swaying and damage caused by uneven force.

[0061] Based on the above embodiments, such as Figure 2 As shown, it also includes:

[0062] The first horizontal shaft 5 is mounted between the two sides of the inner wall of the storage cavity 101, and each end of the first horizontal shaft 5 is rotatably connected to a support arm 23, serving as the axis of rotation of the landing support 2 and providing stable rotational support for the support arm 23.

[0063] By setting the first horizontal axis 5, the force transmitted from the support arm 23 can be evenly distributed to both sides of the inner wall of the storage cavity 101, ensuring the uniformity of the force on the drone body and improving the structural stability.

[0064] In this embodiment, as Figure 5 As shown, protrusions 1011 are formed on both sides of the inner wall of the storage cavity 101 around the outer periphery of the first transverse axis 5, and the protrusions 1011 abut against the adjacent support arm 23.

[0065] By setting the boss 1011, the landing gear 2 can be axially limited, thereby improving the operational stability of the landing gear 2. In addition, the small contact area between the boss and the support arm 23 will not cause too much frictional resistance to the rotation, thus ensuring smooth rotation.

[0066] In this embodiment, as Figure 2 and Figure 5 As shown, the limiting component 3 includes:

[0067] The first crossbeam 31 is installed between the two sides of the inner wall of the storage cavity 101 and is located above the first horizontal axis 5;

[0068] The second crossbeam 32 is installed between the two sides of the inner wall of the storage cavity 101 and is located below the first cross axis 5;

[0069] When the landing gear 2 is rotated to a vertical position, the front side of the support arm 23 is in contact with the first crossbeam 31, and the rear side of the support column 21 is in contact with the second crossbeam 32.

[0070] With the above settings, a double mechanical lock can be formed when the landing gear 2 is in a vertical state. This allows the landing gear 2 to better disperse and bear external forces such as ground impact, thereby improving the overall structural strength, reducing stress concentration, and ensuring the limiting support effect.

[0071] In some embodiments, such as Figure 5 As shown, a limiting groove 3201 adapted to the support column 21 is provided on the front side of the second crossbeam 32, and when the support column 21 is fitted into the limiting groove 3201, the rear side of the support arm 23 is fitted into the second crossbeam 32.

[0072] For example, the support column 21 is cylindrical, and the limiting groove 3201 is a corresponding arc-shaped groove, which has a large contact area and improves the stress dispersion effect; but it is not limited to this, and can also be other shapes.

[0073] The above settings enable precise positioning of the support column 21, improving the take-off and landing stability of the UAV. They also allow the force borne by the landing bracket 2 to be transmitted more evenly to the second crossbeam 32, thereby further reducing stress concentration and enhancing structural strength.

[0074] In some embodiments, such as Figure 5 As shown, the front side of the accommodating frame 1 has an accommodating opening 103 that communicates with the inlet and outlet 102; when the landing gear 2 is rotated to the lateral position, the support column 21 falls into the accommodating opening 103 and the wheel 22 is located on the front side of the accommodating frame 1.

[0075] By adopting the above settings, the length of the housing frame 1 can be shortened, thereby effectively reducing the overall weight of the housing frame 1, which improves the payload capacity, endurance, and flight efficiency of the UAV.

[0076] In some embodiments, such as Figure 1 As shown, it includes:

[0077] The fixed partition 6 is installed on the front side of the receiving frame 1 and covers the receiving opening 103. It can support the casing surrounding the receiving frame 1, thereby improving the overall structural stability.

[0078] In some embodiments, such as Figure 2 and Figure 3 As shown, it includes:

[0079] The second horizontal shaft 7 is mounted between the two sides of the inner wall of the storage cavity 101 and is rotatably connected to one end of the telescopic push rod 4. It can evenly distribute the force transmitted by the telescopic push rod 4 to both sides of the inner wall of the storage cavity 101, ensuring uniform force distribution and improving structural stability.

[0080] Further explanation regarding this application:

[0081] When it is necessary to lower the landing gear, the telescopic push rod 4 gradually extends, thus pushing the landing support 2 to rotate downwards around its top rotation axis in the direction of the drone's backward movement, thereby completing the deployment action;

[0082] When the landing gear 2 rotates to a vertical position, it is limited by the limiting component 3, thereby preventing it from continuing to rotate upward in the rear direction, thus providing reliable support for the drone;

[0083] During the ground taxiing phase of the drone, the reverse torque borne by the landing gear 2 will be directly transmitted to the limiting component 3, and will not be borne by the telescopic push rod 4.

[0084] Numerous specific details are set forth in this specification. However, it will be understood that embodiments of this invention may be practiced without these specific details. In some instances, well-known methods, structures, and techniques have not been shown in detail so as not to obscure the understanding of this specification.

[0085] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0086] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model, and they should all be covered within the scope of the claims and specification of this utility model.

Claims

1. A retractable landing gear, characterized in that, include: The accommodating frame has an internal storage cavity and an inlet / outlet at the bottom; The landing gear has its top end rotatably connected to the storage cavity through the inlet and outlet, and can be rotated upwards and forwards to be stored in the storage cavity. A limiting component, installed in the storage cavity, is used to limit the landing gear from continuing to rotate upward in the rearward direction when the landing gear is rotated to a vertical position. The telescopic push rod is hinged at one end to the landing bracket and rotatably connected to the storage cavity at the other end, and is used to drive the landing bracket to extend and retract.

2. The retractable landing gear according to claim 1, characterized in that, The landing gear includes: Support column; The machine wheel is installed at the bottom end of the support column; Two support arms are symmetrically arranged on both sides of the top of the support column and are rotatably connected to both sides of the inner wall of the storage cavity.

3. The retractable landing gear according to claim 2, characterized in that, include: The first horizontal shaft is mounted between the two sides of the inner wall of the storage cavity, and each end of the first horizontal shaft is rotatably connected to one of the support arms.

4. The retractable landing gear according to claim 3, characterized in that, The inner wall of the storage cavity has protrusions formed on both sides of the outer periphery of the first horizontal axis, and the protrusions abut against the adjacent support arms.

5. The retractable landing gear according to claim 3, characterized in that, The limiting component includes: The first crossbeam is installed between the two sides of the inner wall of the storage cavity and is located above the first horizontal axis; The second crossbeam is installed between the two sides of the inner wall of the storage cavity and is located below the first cross axis; When the landing gear is rotated to a vertical position, the front side of the support arm is in contact with the first crossbeam, and the rear side of the support column is in contact with the second crossbeam.

6. The retractable landing gear according to claim 5, characterized in that, The second crossbeam has a limiting groove on its front side that is adapted to the support column, and when the support column is fitted into the limiting groove, the rear side of the support arm is fitted into the second crossbeam.

7. The retractable landing gear according to claim 5, characterized in that, The front side of the accommodating frame has an accommodating opening that communicates with the inlet and outlet; when the landing gear is rotated to a lateral position, the support column falls into the accommodating opening and the wheel is positioned in front of the accommodating frame.

8. The retractable landing gear according to claim 7, characterized in that, include: A fixed partition frame is installed on the front side of the receiving frame and covers the outside of the receiving opening.

9. The retractable landing gear according to claim 1, characterized in that, include: The second horizontal shaft is mounted between the two sides of the inner wall of the storage cavity and is rotatably connected to one end of the telescopic push rod.

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