A fixed-wing unmanned aerial vehicle folding wing structure

Abstract

The utility model provides a fixed wing unmanned plane folding wing structure belongs to unmanned plane technical field, including bearing mechanism for providing structural support and installation base for whole folding wing structure, fixed part is located on bearing mechanism for realizing steady installation of wing and its folding subassembly, the fixed part includes fixed sleeve and fixed block, fixed sleeve is connected in bearing mechanism, the fixed block is located on fixed sleeve for reinforcing the stability and connecting strength of structure, folding mechanism includes elastic component and clamping component. The utility model through setting up elastic component who consists of torsion spring and limit block, and combining the clamping component who constitutes with the activity cover and the card slot, effectively solved the problem that the traditional fixed wing unmanned plane folding wing existed inconvenient operation, structure stability is poor, and the adaptability is insufficient etc.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a folding wing structure for a fixed-wing UAV. Background Technology

[0002] With the increasingly widespread application of fixed-wing drones, improving their portability and rapid deployment capabilities has become a key technological direction. Traditional fixed-wing drones mostly adopt fixed-wing structures, which, while possessing good aerodynamic efficiency, suffer from problems such as large size and time-consuming deployment when transported, stored, and used in complex environments. Some existing folding-wing structures offer certain portability advantages, but generally suffer from drawbacks such as complex operation, unreliable locking, and poor versatility, making it difficult to meet the high-efficiency usage requirements in diverse mission scenarios.

[0003] In existing technologies, traditional fixed-wing UAVs mostly use fixed or manually folding structures for their wings, which have problems such as complex folding operations, low efficiency, and unreliable locking. They are difficult to meet the needs of rapid deployment in the field and application in complex environments. Some folding structures lack elastic reset function and automatic locking mechanism, and are easily loosened by vibration or airflow, which affects flight safety. Utility Model Content

[0004] The purpose of this invention is to provide a folding wing structure for a fixed-wing unmanned aerial vehicle (UAV) to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] A folding wing structure for a fixed-wing unmanned aerial vehicle, including

[0007] The load-bearing mechanism is used to provide structural support and installation foundation for the entire folding wing structure;

[0008] A fastener, provided on the supporting mechanism, is used to securely install the wing and its folding assembly;

[0009] The fastener includes a fastening sleeve and a fastening block. The fastening sleeve is connected to the bearing mechanism, and the fastening block is disposed on the fastening sleeve to enhance the stability and connection strength of the structure.

[0010] The folding mechanism includes a flexible component and a snap-fit ​​component;

[0011] The elastic component includes a torsion spring and a limiting block. One end of the torsion spring is connected to the fixed block, and the other end is connected to the limiting block to realize the function of controlling and resetting the wing folding angle.

[0012] The locking assembly includes a movable sleeve and a slot. The movable sleeve is fitted over the outside of the fixed sleeve, and the slot is located inside the movable sleeve, for locking and unlocking the wing in the folded state.

[0013] As a preferred embodiment of this utility model, the load-bearing mechanism is made of high-strength lightweight material, which has good mechanical strength and weight reduction effect, and is suitable for load optimization requirements in long-duration flight missions.

[0014] As a preferred embodiment of this utility model, the torsion spring is equipped with a preload adjustment device, which can adjust the preload according to the mass of different types of wings and the required folding angle, thereby improving the flexibility and applicability of the folding wing structure.

[0015] As a preferred embodiment of this utility model, the surface of the limiting block is provided with a wear-resistant coating to reduce frictional loss between it and the fixing block, extend its service life and ensure transmission efficiency.

[0016] As a preferred embodiment of this utility model, a sealing ring is provided between the movable sleeve and the fixed sleeve to prevent dust and moisture from entering the internal structure and to ensure the long-term reliable operation of the folding mechanism.

[0017] As a preferred embodiment of this utility model, the slot is provided with a spring lock, which can automatically lock after the wing is folded into place, preventing accidental loosening due to vibration or airflow, and improving the safety and stability of the folding wing structure.

[0018] Compared with the prior art, the beneficial effects of this utility model are: by setting an elastic component composed of a torsion spring and a limiting block, and combining it with a snap-fit ​​component composed of a movable sleeve and a slot, the problems of inconvenient operation, poor structural stability, and insufficient adaptability of traditional fixed-wing UAV folding wings are effectively solved, thereby improving the automation level of the wing folding process, connection reliability, and adaptability to different mission scenarios. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Among them:

[0020] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0021] Figure 2 This is a schematic diagram of the overall structure of this utility model from another perspective;

[0022] Figure 3 This is a schematic diagram of the unfolded folding mechanism of this utility model;

[0023] Figure 4 This is a schematic diagram of the structure of the elastic component of this utility model.

[0024] In the diagram: 100, bearing mechanism; 101, fastener; 1011, fixing sleeve; 1012, fixing block; 200, folding mechanism; 201, elastic component; 2011, torsion spring; 2012, limiting block; 202, snap-fit ​​component; 2021, movable sleeve; 2022, slot. Detailed Implementation

[0025] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings.

[0026] Many specific details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0027] Secondly, the term "an embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that excludes other embodiments.

[0028] Example

[0029] Reference Figures 1-4 This is an embodiment of the present invention, which provides a folding wing structure for a fixed-wing unmanned aerial vehicle, comprising:

[0030] The load-bearing mechanism 100 is used to provide structural support and installation foundation for the entire folding wing structure;

[0031] The fastener 101 is provided on the support mechanism 100 and is used to achieve a stable installation of the wing and its folding assembly;

[0032] The fastener 101 includes a fastening sleeve 1011 and a fastening block 1012. The fastening sleeve 1011 is connected to the bearing mechanism 100, and the fastening block 1012 is disposed on the fastening sleeve 1011 to enhance the stability of the structure and the connection strength.

[0033] The folding mechanism 200 includes an elastic component 201 and a snap-fit ​​component 202;

[0034] The elastic component 201 includes a torsion spring 2011 and a limiting block 2012. One end of the torsion spring 2011 is connected to the fixed block 1012, and the other end is connected to the limiting block 2012 to realize the control and reset function of the wing folding angle.

[0035] The snap-fit ​​assembly 202 includes a movable sleeve 2021 and a slot 2022. The movable sleeve 2021 is fitted onto the outside of the fixed sleeve 1011, and the slot 2022 is located inside the movable sleeve 2021, which is used to lock and unlock the wing in the folded state.

[0036] Specifically, the load-bearing mechanism 100 is made of high-strength, lightweight materials, which has good mechanical strength and weight reduction effect, and is suitable for load optimization needs in long-duration flight missions.

[0037] It should be noted that the load-bearing mechanism 100 is made of high-strength lightweight materials, which effectively reduces weight while ensuring the overall structural strength and stability, thereby improving the payload capacity and endurance of the UAV. It is particularly suitable for weight-sensitive fixed-wing UAV platforms, meeting the structural strength and lightweight requirements for long-duration flight missions.

[0038] Specifically, the torsion spring 2011 is equipped with a preload adjustment device, which can adjust the preload according to the mass of different wing models and the required folding angle, thereby improving the flexibility and applicability of the folding wing structure.

[0039] It should be noted that the torsion spring 2011 is equipped with a preload adjustment device, which can flexibly adjust the return torque output by the torsion spring according to the size, weight and required folding angle of the connected wing, to ensure that different models of UAVs move smoothly and respond quickly during folding and unfolding, and improve the versatility and mission adaptability of the folding wing structure.

[0040] Specifically, the surface of the limiting block 2012 is provided with a wear-resistant coating to reduce frictional loss between it and the fixing block 1012, extend its service life and ensure transmission efficiency.

[0041] It should be noted that the surface of the limiting block 2012 is provided with a wear-resistant coating, which can significantly reduce the coefficient of friction, reduce wear and heat accumulation, and extend the service life of the limiting block and the overall folding mechanism when it forms a sliding engagement with the fixing block 1012 during the folding process, while ensuring the stability of the folding angle control and the reliability of the reset action.

[0042] Specifically, a sealing ring is provided between the movable sleeve 2021 and the fixed sleeve 1011 to prevent dust and moisture from entering the internal structure and ensure the long-term reliable operation of the folding mechanism.

[0043] It should be noted that a sealing ring is provided between the movable sleeve 2021 and the fixed sleeve 1011, which can effectively prevent external impurities such as dust and rainwater from entering the internal structure during the folding and unfolding of the wings, ensuring the long-term stable operation of the folding mechanism in complex environments and improving the environmental adaptability and maintenance cycle of the equipment.

[0044] Specifically, the slot 2022 is equipped with a spring lock that can automatically lock after the wing is folded into place, preventing accidental loosening due to vibration or airflow and improving the safety and stability of the folding wing structure.

[0045] It should be noted that the slot 2022 is equipped with a spring lock that can automatically lock after the wing is folded into place, preventing the folding structure from loosening or accidentally unfolding due to airflow disturbances or airframe vibrations during flight, thus significantly improving the safety and structural stability of the folding wing during transportation, takeoff and landing and flight.

[0046] In use, the support mechanism 100 is first installed on the UAV fuselage structure, serving as the structural support and installation foundation for the entire folding wing system. The support mechanism 100 is made of high-strength, lightweight materials, effectively reducing weight while ensuring overall structural strength and stability, thus improving the UAV's payload capacity and endurance. It is particularly suitable for weight-sensitive fixed-wing UAV platforms, meeting the structural strength and lightweight requirements for long-duration flight missions. The fixing component 101 includes a fixing sleeve 1011 and a fixing block 1012, wherein the fixing sleeve 1011 is connected to the support mechanism 1012. 0, the overall structure supporting the folding mechanism, the fixing block 1012 is set on the fixing sleeve to enhance the connection strength and structural stability, the folding mechanism 200 is set on the fixing member 101 to realize the rapid folding and unfolding of the wing, mainly including the elastic component 201 and the snap-fit ​​component 202. The elastic component 201 is composed of a torsion spring 2011 and a limiting block 2012, wherein one end of the torsion spring 2011 is connected to the fixing block 1012, and the other end is connected to the wing through the limiting block 2012, to provide the reset torque and control the folding angle, and the torsion spring 2011 is equipped with a preload adjustment device. It can flexibly adjust the output torque according to the size, weight, and required folding angle of the connected wing, ensuring smooth operation and rapid response during folding and unfolding of different UAV models, improving the versatility and mission adaptability of the structure. The surface of the limiting block 2012 is coated with a wear-resistant coating, which can significantly reduce the coefficient of friction, reduce wear and heat accumulation, and extend the service life of the limiting block and the overall folding mechanism when it forms a sliding fit with the fixed block during folding. At the same time, it ensures the stability of folding angle control and the reliability of reset action. The snap-fit ​​assembly 202 includes a movable sleeve 2021 and a slot 2. 022, wherein the movable sleeve 2021 is fitted outside the fixed sleeve 1011 and a sealing ring is provided between the two to prevent external impurities such as dust and rainwater from entering the internal structure, ensuring the long-term stable operation of the folding mechanism in complex environments, improving the environmental adaptability and maintenance cycle of the equipment. The slot 2022 is located inside the movable sleeve and has a built-in spring lock, which can automatically lock after the wing is folded into place, preventing the folding structure from loosening or accidentally unfolding due to airflow disturbance or airframe vibration during flight, significantly improving the safety and structural stability of the folding wing during transportation, take-off and landing and flight.

[0047] In summary, by setting up an elastic component 201 consisting of a torsion spring 2011 and a limiting block 2012, and combining it with a snap-fit ​​component 202 consisting of a movable sleeve 2021 and a slot 2022, the problems of inconvenient operation, poor structural stability, and insufficient adaptability of traditional fixed-wing UAV folding wings are effectively solved, thereby improving the automation level of the wing folding process, connection reliability, and adaptability to different mission scenarios.

[0048] It is important to note that the constructions and arrangements of this application shown in several different exemplary embodiments are merely illustrative. Although only a few embodiments are described in detail in this disclosure, those who consult this disclosure will readily understand that many modifications are possible (e.g., changes in the size, dimensions, structure, shape and proportion of various elements, as well as parameter values ​​(e.g., temperature, pressure, etc.), mounting arrangements, use of materials, color, orientation, etc.) without substantially departing from the novel teachings and advantages of the subject matter described in this application). For example, an element shown as integrally formed may be composed of multiple parts or elements, the position of elements may be inverted or otherwise altered, and the nature or number or position of discrete elements may be changed or altered. Therefore, all such modifications are intended to be included within the scope of this utility model. The order or sequence of any process or method steps may be changed or reordered according to alternative embodiments. In the claims, any "device plus function" clause is intended to cover the structure described herein that performs the function, and not only structural equivalents but also equivalent structures. Without departing from the scope of this invention, other substitutions, modifications, alterations, and omissions may be made in the design, operation, and arrangement of the exemplary embodiments. Therefore, this invention is not limited to the specific embodiments, but extends to various modifications that still fall within the scope of the appended claims.

[0049] Furthermore, in order to provide a concise description of exemplary embodiments, not all features of actual embodiments (i.e., those features that are not relevant to the best mode of carrying out the present invention as currently considered, or those features that are not relevant to implementing the present invention) may be omitted.

[0050] It should be understood that numerous specific implementation decisions can be made during the development of any practical implementation, such as in any engineering or design project. Such development efforts may be complex and time-consuming, but for those skilled in the art who benefit from this disclosure, the development effort will be a routine work of design, manufacturing, and production without requiring much experimentation.

[0051] It should be noted that the above embodiments are only used to illustrate the technical solution of this utility model and are not intended to limit it. Although this utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solution of this utility model without departing from the spirit and scope of the technical solution of this utility model, and all such modifications or substitutions should be covered within the scope of the claims of this utility model.

Claims

1. A folding wing structure for a fixed-wing unmanned aerial vehicle, characterized in that: include, The load-bearing mechanism (100) is used to provide structural support and installation foundation for the entire folding wing structure; A fastener (101) is provided on the bearing mechanism (100) for the secure installation of the wing and its folding assembly; The fastener (101) includes a fastening sleeve (1011) and a fastening block (1012). The fastening sleeve (1011) is connected to the bearing mechanism (100), and the fastening block (1012) is disposed on the fastening sleeve (1011) to enhance the stability and connection strength of the structure. The folding mechanism (200) includes an elastic component (201) and a snap-fit ​​component (202); The elastic component (201) includes a torsion spring (2011) and a limiting block (2012). One end of the torsion spring (2011) is connected to the fixing block (1012), and the other end is connected to the limiting block (2012) to control and reset the wing folding angle. The snap-fit ​​assembly (202) includes a movable sleeve (2021) and a slot (2022). The movable sleeve (2021) is fitted onto the outside of the fixed sleeve (1011), and the slot (2022) is located inside the movable sleeve (2021) to realize the locking and unlocking of the wing in the folded state.

2. The fixed-wing UAV folding wing structure according to claim 1, characterized in that: The load-bearing mechanism (100) is made of high-strength lightweight material, which has good mechanical strength and weight reduction effect, and is suitable for load optimization needs in long-duration flight missions.

3. The folding wing structure of a fixed-wing UAV according to claim 2, characterized in that: The torsion spring (2011) is equipped with a preload adjustment device, which can adjust the preload according to the mass of different models of wings and the required folding angle, thereby improving the flexibility and applicability of the folding wing structure.

4. The folding wing structure of a fixed-wing UAV according to claim 3, characterized in that: The surface of the limiting block (2012) is provided with a wear-resistant coating to reduce frictional loss between it and the fixing block (1012), extend service life and ensure transmission efficiency.

5. The folding wing structure of a fixed-wing UAV according to claim 4, characterized in that: A sealing ring is provided between the movable sleeve (2021) and the fixed sleeve (1011) to prevent dust and moisture from entering the internal structure and ensure the long-term reliable operation of the folding mechanism.

6. The folding wing structure of a fixed-wing unmanned aerial vehicle according to claim 5, characterized in that: The slot (2022) is equipped with a spring lock that can automatically lock after the wing is folded into place, preventing accidental loosening due to vibration or airflow, and improving the safety and stability of the folding wing structure.

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