Folding mechanism
By designing a folding mechanism including a rotary member stator, a rotary member rotor, a pin, a fixing block, a connecting block and a locking mechanism, the size and weight problems caused by the single design of the existing aircraft folding parts are solved, and the compact folding and stable deployment of the aircraft arm is achieved, and the endurance and designability of the aircraft are improved.
Patent Information
- Application Number
- CN202422076633.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-27
- Publication Date
- 2025-05-27
- Estimated Expiration
- 2034-08-27
AI Technical Summary
The design of existing aircraft folding parts is single, which leads to a large size after folding, which is difficult to transport, and has a large weight and volume, which cannot meet the needs of high-end lightweighting, affecting the endurance and designability of the aircraft.
A folding mechanism is designed, through the combination of rotary member stator, rotary member rotor, pin, fixed block, connecting block and locking mechanism, the opposite inclined folding and unfolding of the aircraft arm is realized, and the elastic locking method is adopted, which is stable, reliable and easy to use.
The aircraft arm is folded in an opposite direction, greatly reducing the size of the folded equipment, significantly better than the size and weight of other products, reducing the total weight of the equipment, improving battery life, and leaving more load space for the mounted equipment.
Smart Images
Figure CN222905857U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft accessories, and particularly relates to a folding mechanism. Background Technique
[0002] An aircraft is a flying object manufactured by humans, capable of flying off the ground, flying in space and controlled by humans. Aircraft can be classified according to their flight environment and functional characteristics, mainly including aircraft, spacecraft, rockets and missiles, etc. Different types of aircraft have different structural characteristics, but all contain core components for supporting their flight and completing tasks. The flight principle of an aircraft is mainly based on Bernoulli's law and Newton's third law. The specific shape of the wing causes the air flow velocity on the upper and lower surfaces of the wing to be different, thus generating a pressure difference to form lift. At the same time, the thrust generated by the engine overcomes air resistance and gravity, enabling the aircraft to move forward and rise. Intelligent aircraft such as unmanned aerial vehicles have also made remarkable progress in the process of civilianization, and the market scale is constantly expanding. In the future, with the continuous progress of technology and the continuous expansion of application fields, aircraft will play an important role in more fields, bringing more convenience and possibilities to the life and development of mankind.
[0003] In the prior art, there are only two common folding methods for aircraft folding parts in the market, namely horizontal folding and umbrella folding, and the folding locking method is single, only the two common methods of horizontal folding and umbrella folding. After folding, the size of the equipment is large and not easy to transport, and generally the weight and volume are large, which cannot meet the high-end lightweight requirements, bringing pressure to the aircraft endurance and designability.
[0004] Therefore, a folding mechanism is proposed. Content of the Utility Model
[0005] The purpose of the utility model is: to solve the problems raised in the above background technique, the utility model provides a folding mechanism.
[0006] The utility model specifically adopts the following technical solutions to achieve the above purpose:
[0007] A folding mechanism includes a mounting base. A rotating part stator is arranged on the top of the mounting base. A pin shaft is arranged on the rotating part stator. A rotating part rotor is rotatably arranged on the pin shaft, and the rotating part stator is in contact with the rotating part rotor. A fixing block is arranged on the surface of the rotating part rotor. A connecting block is arranged on the surface of the rotating part stator. The number of the connecting blocks is two. A locking mechanism for inserting and limiting the fixing block is arranged on one of the connecting blocks.
[0008] Further, a threaded hole penetrates through the rotating part stator, and the pin shaft is threadedly installed on the inner wall of the threaded hole.
[0009] Furthermore, the locking mechanism includes a connecting piece, which is installed on the surface of one of the connecting blocks, a sliding hole is penetrated on the surface of one of the connecting blocks, a fixing pin is slidably installed on the inner wall of the sliding hole, and the fixing pin is slidably installed on the connecting piece, a circular ring is installed on the outer wall of the fixing pin, a spring is sleeved on the outer wall of the fixing pin, and both ends of the spring are respectively installed on the surface of the circular ring and the connecting piece.
[0010] Furthermore, circular grooves are provided on the surfaces of the two connecting members, and the circular rings are slidably mounted on the inner walls of the circular grooves.
[0011] Furthermore, a circular hole is penetrated on the surface of the fixing block, and the diameter specification of the circular hole is matched with the diameter and specification of the fixing pin.
[0012] Furthermore, the materials of the mounting seat, the rotating member stator and the rotating member rotor are all set to be aluminum alloy, and are all hollowed out.
[0013] The beneficial effects of the utility model are as follows:
[0014] The utility model is provided with a circular ring, a fixing pin and a spring, etc., and when in use, the mechanism is assembled to the aircraft structure, and the fixing pin is driven to slide on the sliding hole and the connecting piece by pulling the fixing pin, and the circular ring slides in the connecting piece accordingly and compresses the spring, and the rotor of the rotating piece is turned over and rotated on the pin shaft, so that the fixing block is located between the two connecting blocks, and the fixing pin is released, that is, reset under the reset elastic force of the spring, and the fixing pin can be inserted into the circular hole of the fixing block, and the fixing block is limited and locked, so that the aircraft arm can be tilted and folded oppositely, and vice versa, the aircraft arm can be unfolded, thereby realizing the use of an elastic locking method, which is stable, reliable and easy to use, and can make the aircraft arm tilted and folded oppositely, and the fuselage is more compact up and down, and the size of the equipment after folding is greatly reduced. The size and weight of the same specification are significantly better than other products, and the total weight of the equipment is reduced to improve the endurance, leaving more load space for the mounted equipment. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;
[0016] Figure 2 It is a schematic diagram of a partially exploded structure of the utility model;
[0017] Figure 3 It is a cross-sectional structural schematic diagram of the locking mechanism of the utility model.
[0018] Figure numerals: 1, mounting seat; 2, rotating part stator; 3, rotating part rotor; 4, pin shaft; 5, fixing block; 6, connecting block; 7, locking mechanism; 701, connecting part; 702, circular groove; 703, circular ring; 704, fixing pin; 705, spring. Detailed implementation mode
[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present utility model clearer, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are some, but not all, of the embodiments of the present utility model. Usually, the components of the embodiments of the present utility model described and illustrated in the accompanying drawings here can be arranged and designed in various different configurations.
[0020] Therefore, the following detailed description of the embodiments of the present utility model provided in the accompanying drawings is not intended to limit the scope of the present utility model claimed, but merely represents selected embodiments of the present utility model. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts fall within the scope of protection of the present utility model.
[0021] It should be noted that similar reference numerals and letters indicate similar items in the following drawings. Therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. In addition, terms such as "first" and "second" are only used for descriptive distinction and cannot be understood as indicating or implying relative importance.
[0022] In the description of the implementation mode of the present utility model, it should be noted that the orientation or positional relationship indicated by terms such as "inside", "outside", and "above" is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the utility model product is usually placed during use. It is only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present utility model.
[0023] Such as Figures 1-3As shown in the figure, a folding mechanism includes a mounting base 1. A rotating part stator 2 is provided at the top of the mounting base 1. A pin shaft 4 is provided on the rotating part stator 2. A rotating part rotor 3 is rotatably arranged on the pin shaft 4, and the rotating part stator 2 is in contact with the rotating part rotor 3. A fixed block 5 is provided on the surface of the rotating part rotor 3, and a connecting block 6 is provided on the surface of the rotating part stator 2. The number of the connecting blocks 6 is set to two. A locking mechanism 7 for inserting and limiting the fixed block 5 is provided on one of the connecting blocks 6. In this embodiment, when in use, the mechanism is assembled to the aircraft structure. By flipping the rotating part rotor 3 and rotating it on the pin shaft 4, the fixed block 5 is located between the two connecting blocks 6, and then the fixed block 5 is inserted and fixed by the locking mechanism 7, and the tilting folding work of the aircraft arm in the opposite direction can be completed. Conversely, by releasing the insertion and fixing of the fixed block 5 by the locking mechanism 7, the rotating part rotor 3 can be flipped at this time, and the unfolding work of the aircraft arm can be completed, so as to make the fuselage more compact up and down, greatly reduce the size of the equipment after folding, be stable, reliable and easy to use, and be significantly different from the conventional products on the market.
[0024] As Figures 1-2 shown, a threaded hole penetrates through the rotating part stator 2, and the pin shaft 4 is threadedly installed on the inner wall of the threaded hole. In this embodiment, by the threaded connection between the pin shaft 4 and the rotating part stator 2, it is convenient to assemble between the rotating part stator 2 and the rotating part rotor 3.
[0025] As Figures 1-3 shown, the locking mechanism 7 includes a connecting part 701, and the connecting part 701 is installed on the surface of one of the connecting blocks 6. A sliding hole penetrates through the surface of one of the connecting blocks 6. A fixing pin 704 is slidably installed on the inner wall of the sliding hole, and the fixing pin 704 is slidably installed on the connecting part 701. A circular ring 703 is installed on the outer wall of the fixing pin 704. A spring 705 is sleeved on the outer wall of the fixing pin 704, and both ends of the spring 705 are respectively installed on the surfaces of the circular ring 703 and the connecting part 701. In this embodiment, by pulling the fixing pin 704, the fixing pin 704 is driven to slide on the sliding hole and the connecting part 701, and the circular ring 703 slides in the connecting part 701 accordingly and compresses the spring 705. When the fixing pin 704 is released, it will reset under the restoring elastic force of the spring 705.
[0026] As Figure 3 shown, circular grooves 702 are formed on the surfaces of both connecting parts 701, and the circular ring 703 is slidably installed on the inner walls of the circular grooves 702. In this embodiment, through the setting of the circular grooves 702, the sliding space of the circular ring 703 is reduced and the occupied space is reduced.
[0027] As Figures 2-3As shown, a round hole runs through the surface of the fixed block 5, and the diameter specification of the round hole is adapted to the diameter and specification of the fixing pin 704. In this embodiment, when the fixed block 5 is between the two rotating part stators 2, the fixing pin 704 can be inserted into the round hole of the fixed block 5 to limit and lock the fixed block 5.
[0028] As Figures 1-3 shown, the materials of the mounting base 1, the rotating part stator 2, and the rotating part rotor 3 are all set to aluminum alloy and are all hollow. In this embodiment, through the aluminum alloy material and the hollow structure setting, the total weight of the device can be reduced to improve the endurance, leaving more load space for the mounted device.
[0029] In summary, when in use, assemble this mechanism to the aircraft structure. By flipping the rotating part rotor 3 and rotating on the pin shaft 4, the fixed block 5 is located between the two connecting blocks 6. Then, through the locking mechanism 7, the fixing pin 704 is inserted into and fixed to the fixed block 5, and the tilting and folding work of the aircraft arm in the opposite direction can be completed. Conversely, by releasing the insertion and fixation of the fixed block 5 by the locking mechanism 7, at this time, the rotating part rotor 3 can be flipped to complete the unfolding work of the aircraft arm, thereby making the fuselage more compact up and down, greatly reducing the size of the device after folding, being stable, reliable and easy to use, and significantly different from conventional products on the market. By screwing the pin shaft 4 to the rotating part stator 2, it is convenient to assemble between the rotating part stator 2 and the rotating part rotor 3. By pulling the fixing pin 704, the fixing pin 704 is driven to slide on the sliding hole and the connecting part 701, and the circular ring 703 slides in the connecting part 701 accordingly and compresses the spring 705. Release the fixing pin 704, and it will reset under the restoring elastic force of the spring 705. Through the setting of the circular groove 702, the sliding space of the circular ring 703 is reduced and the occupied space is lowered. When the fixed block 5 is between the two rotating part stators 2, the fixing pin 704 can be inserted into the round hole of the fixed block 5 to limit and lock the fixed block 5. Through the aluminum alloy material and the hollow structure setting, the total weight of the device can be reduced to improve the endurance, leaving more load space for the mounted device.
[0030] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. What is described in the above embodiments and the specification is only the principle of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of the present invention claimed. The scope of protection claimed by the present invention is defined by the appended claims and their equivalents.
Claims
1. A folding mechanism, comprising a mounting seat (1), characterized in that: A rotating part stator (2) is arranged on the top of the mounting seat (1), a pin shaft (4) is arranged on the rotating part stator (2), a rotating part rotor (3) is rotatably arranged on the pin shaft (4), and the rotating part stator (2) is in contact with the rotating part rotor (3), a fixing block (5) is arranged on the surface of the rotating part rotor (3), a connecting block (6) is arranged on the surface of the rotating part stator (2), the number of the connecting blocks (6) is set to two, and one of the connecting blocks (6) is provided with a locking mechanism (7) for inserting and limiting the fixing block (5).
2. A folding mechanism according to claim 1, characterized in that: A threaded hole is passed through the stator (2) of the rotating member, and the pin shaft (4) is threadedly mounted on the inner wall of the threaded hole.
3. A folding mechanism according to claim 1, characterized in that: The locking mechanism (7) comprises a connecting member (701), the connecting member (701) being mounted on the surface of one of the connecting blocks (6), a sliding hole penetrating the surface of one of the connecting blocks (6), a fixing pin (704) being slidably mounted on the inner wall of the sliding hole, and the fixing pin (704) being slidably mounted on the connecting member (701), a circular ring (703) being mounted on the outer wall of the fixing pin (704), a spring (705) being sleeved on the outer wall of the fixing pin (704), and two ends of the spring (705) being respectively mounted on the surfaces of the circular ring (703) and the connecting member (701).
4. A folding mechanism according to claim 3, characterized in that: A circular groove (702) is provided on the surface of the connecting member (701), and a circular ring (703) is slidably mounted on the inner wall of the circular groove (702).
5. A folding mechanism according to claim 3, characterized in that: A circular hole is formed on the surface of the fixing block (5), and the diameter of the circular hole matches the diameter and specification of the fixing pin (704).
6. A folding mechanism according to claim 1, characterized in that: The material of the mounting seat (1), the rotating part stator (2) and the rotating part rotor (3) are all set to be aluminum alloy, and are all hollowed out.