Multi-mode intelligent folding wing mechanism
By using a multimodal intelligent folding wing mechanism, multi-directional folding and height symmetry are achieved, solving the problem of asymmetrical wing stacking in existing rotorcraft, improving flight stability and safety, and adapting to various carrier applications.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHANGHAI ZHANHANG INTELLIGENT TECH CO LTD
- Filing Date
- 2025-05-30
- Publication Date
- 2026-05-12
AI Technical Summary
Most existing rotorcraft folding wing mechanisms can only fold in one direction, resulting in asymmetrical wing stacking, which affects flight stability and parking stability. Furthermore, they are prone to wear during the folding process, and additional mechanisms are difficult to save space effectively.
It adopts a multimodal intelligent folding wing mechanism, which achieves multi-directional folding and height symmetry through components such as active folding arm, driven auxiliary folding arm, fixed support and servo motor. Combined with gyroscope to monitor flight attitude in real time and dynamically adjust wing shape, it is equipped with an intelligent control system.
This technology enables the wings to maintain the same height when folded, improving flight and parking stability, reducing mechanical damage, increasing flight efficiency and safety, adapting to various carriers, and broadening the scope of applications.
Smart Images
Figure CN224225288U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of folding rotor technology, and in particular to a multimodal intelligent folding rotor mechanism. Background Technology
[0002] In existing rotorcraft, most folding wing mechanisms can only support unidirectional folding (such as folding horizontally from a straight line to an inverted V shape). This results in an asymmetrical state when the left and right wings are stacked vertically, creating a height difference between the wings in the horizontal direction. This affects stability during flight and also impacts stability when parked. Furthermore, the wings interact and wear each other during folding, limiting wing size and overall structural design. If additional mechanisms (such as spacers) are used to make the wings the same height, it severely limits the folding effect and makes it difficult to effectively save space.
[0003] To address the aforementioned issues, a multimodal intelligent folding wing mechanism is proposed. Utility Model Content
[0004] The main purpose of this invention is to provide a multimodal intelligent folding wing mechanism that solves the problems mentioned in the background art.
[0005] The objective of this utility model can be achieved by adopting the following technical solution:
[0006] A multimodal intelligent folding wing mechanism includes a fuselage carrier, and a folding wing mechanism is provided on the top of the fuselage carrier;
[0007] The folding wing mechanism includes two sets of symmetrically detachable fixed supports mounted on the top of the fuselage carrier. A horizontally placed rotating shaft is rotatably mounted inside the higher end of the fixed support, and a driving force folding arm is fitted to the outer end of the rotating shaft. A driven auxiliary folding arm is rotatably mounted inside the lower end of the fixed support.
[0008] The active folding arm and the driven auxiliary folding arm are respectively equipped with a first servo motor and a second servo motor at their ends away from the fixed support, and a folding arm is fixed between the first servo motor and the second servo motor.
[0009] Furthermore, a ring structure is fitted in the middle section of the rotating shaft, and a hydraulic cylinder is hinged to the bottom of the ring. A support frame is hinged to the end of the hydraulic cylinder away from the rotating shaft, and the bottom of the support frame is welded to the top of the machine body carrier.
[0010] Furthermore, a locking mechanism is provided inside the end of the active power articulated arm and the driven auxiliary articulated arm near the fixed support, and the locking mechanism adopts a pawl structure.
[0011] Furthermore, a rubber shock-absorbing pad is pressed between the fixed support and the body carrier.
[0012] Furthermore, a gyroscope is embedded in one side of the outer wall of the fixed support.
[0013] Furthermore, a rotor body is fixedly mounted on the upper part of the folding arm.
[0014] The beneficial technical effects of this utility model are as follows:
[0015] This invention, through the design of a multimodal steering folding wing composed of a main power folding arm, a driven auxiliary folding arm, and a fixed support, can achieve:
[0016] 1. Multi-directional folding function and highly symmetrical wing mechanism ensure that the left and right wings are at the same height after folding, thereby improving flight and parking stability;
[0017] 2. Through an intelligent control system, combined with sensors such as gyroscopes, the flight attitude is monitored in real time, and the wing shape is dynamically adjusted through intelligent algorithms to achieve precise matching between the wing and the flight attitude, reduce mechanical damage, and improve flight efficiency and safety.
[0018] 3. Improve the versatility of the folding wing mechanism so that it can be adapted to various carriers such as drones and manned aircraft, integrate the space efficiency advantages of folding wings with the aerodynamic performance advantages of fixed wings, broaden its application range, and meet the needs of multiple application scenarios. Attached Figure Description
[0019] Figure 1 This is a schematic diagram of the front view of the rotor body when it is deployed in a preferred embodiment of a multimodal intelligent folding wing mechanism according to the present invention;
[0020] Figure 2 This is a schematic diagram of the rear view of the rotor body when it is deployed in a preferred embodiment of a multimodal intelligent folding wing mechanism according to the present invention.
[0021] Figure 3 This is a schematic diagram of the rotor body after folding in a preferred embodiment of a multimodal intelligent folding wing mechanism according to the present invention.
[0022] Figure 4 This is an exploded view of the folding wing mechanism after separation in a preferred embodiment of a multimodal intelligent folding wing mechanism according to the present invention.
[0023] The annotations in the attached figures are explained as follows:
[0024] 1. Fuselage carrier; 2. Rotor body; 3. Folding wing mechanism; 301. Fixed support; 302. Rubber shock-absorbing pad; 303. Support frame; 304. Hydraulic cylinder; 305. Rotation shaft; 306. Main power folding arm; 307. First servo motor; 308. Second servo motor; 309. Driven auxiliary folding arm; 310. Folding wing arm; 4. Gyroscope. Detailed Implementation
[0025] To enable those skilled in the art to understand the technical solution of this utility model more clearly, the present utility model will be further described in detail below with reference to the embodiments and accompanying drawings, but the implementation of this utility model is not limited thereto.
[0026] like Figures 1-4 As shown, this embodiment provides a multimodal intelligent folding wing mechanism, including a fuselage carrier 1, with a folding wing mechanism 3 disposed on the top of the fuselage carrier 1; the folding wing mechanism 3 includes two sets of symmetrically detachably mounted fixed supports 301 on the top of the fuselage carrier 1, with a horizontally oriented rotating shaft 305 rotatably mounted inside the higher end of the fixed support 301, and a driving force folding arm 306 mounted on the outer end of the rotating shaft 305, and a driven auxiliary folding arm 309 rotatably mounted inside the lower end of the fixed support 301; a first servo motor 307 and a second servo motor 308 are respectively mounted on the ends of the driving force folding arm 306 and the driven auxiliary folding arm 309 away from the fixed support 301, and a folding wing arm 310 is fixed between the first servo motor 307 and the second servo motor 308.
[0027] In the above structure, the fixed support 301 is the base of the entire folding wing mechanism. It is made of high-strength, lightweight aerospace aluminum alloy material to ensure that it has sufficient structural strength and rigidity to withstand various loads generated during flight, while reducing the overall weight and improving the performance of the aircraft.
[0028] The main power folding arm 306 is the core power component of the folding wing mechanism. Made of high-strength alloy steel, it possesses excellent fatigue resistance and wear resistance, enabling it to withstand long-term reciprocating motion and alternating loads. The main power folding arm 306 is connected to the fixed support 301 via high-precision bearings, ensuring smooth and accurate rotational movement. The driven auxiliary folding arm 309 is connected to the main power folding arm 306 via the folding wing arm 310, assisting the main power folding arm 306 in adjusting the folding wing arm 310, ensuring coordinated movement between the two. The driven auxiliary folding arm 309 is also made of high-strength aluminum alloy, possessing good strength and toughness, and capable of withstanding certain loads and stresses. Its main function is to assist in the folding and unfolding process of the wing under the drive of the main power folding arm 306, and simultaneously, in dynamic adjustment mode, to fine-tune the wing to achieve optimal aerodynamic performance. In the linkage mechanism composed of each arm segment, the length and connection angle of the link are precisely calculated and designed to ensure that the motion trajectory of the driven auxiliary folding arm 309 matches the motion requirements of the wing, so that the wing remains stable and smooth during folding and unfolding, avoiding phenomena such as jamming and collision.
[0029] The first servo motor 307 and the second servo motor 308 used in both are brushless DC motors, which have the advantages of small size, light weight, high efficiency and high control precision, and can provide stable power output.
[0030] A ring structure is fitted in the middle section of the rotating shaft 305. A hydraulic cylinder 304 is hinged to the bottom of the ring. A support frame 303 is hinged to the end of the hydraulic cylinder 304 away from the rotating shaft 305. The bottom of the support frame 303 is welded to the top of the fuselage carrier 1. The hydraulic cylinder 304 drives the rotating shaft 305 to rotate by linear push, thereby realizing the flipping of the folding wing body.
[0031] The active folding arm 306 and the passive auxiliary folding arm 309 are equipped with a locking mechanism at one end near the fixed support 301. The locking mechanism adopts a pawl structure, which effectively ensures that the wing will not loosen or fold due to airflow impact or vibration during flight, thus ensuring flight safety.
[0032] A rubber shock-absorbing pad 302 is pressed between the fixed support 301 and the fuselage carrier 1, which serves as a bottom support and connection to the carrier, and can effectively reduce vibration and impact during flight, protecting the stability and reliability of the folding wing mechanism and other equipment on the fuselage.
[0033] A gyroscope 4 is embedded in one side of the outer wall of the fixed support 301 to monitor the aircraft's attitude information in real time, including parameters such as pitch angle, roll angle, and yaw angle. It has a high level of accuracy and can quickly and accurately reflect the aircraft's attitude changes during flight. The gyroscope 4 is connected to the intelligent control system, transmitting the monitored attitude information to the control system in real time. After collecting the monitoring data, the intelligent control system can analyze and process it using algorithms, combining the current flight mission with preset flight parameters. This allows it to quickly determine the aircraft's flight status and promptly adjust the movement of the active power folding arm 306 and the driven auxiliary folding arm 309, achieving dynamic adjustment of the wings and ensuring the aircraft maintains a stable and efficient flight attitude.
[0034] The rotor body 2 is fixedly mounted on the upper part of the folding arm 310.
[0035] The working principle of this device is as follows:
[0036] When the aircraft needs to take off or is in the cruise phase, the folding wing mechanism is in the unfolded state. The rotor body 2 is fixed to the fixed support 301 by the locking mechanism of the active folding arm 306 and the driven auxiliary folding arm 309, forming a stable airfoil structure, providing maximum aerodynamic lift and flight stability. The locking mechanism effectively ensures that the wing will not loosen or fold due to airflow impact or vibration during flight, ensuring flight safety. A good aerodynamic shape is formed between the wing and the fuselage, and the airflow can flow smoothly over the wing surface, generating sufficient lift, so that the aircraft can fly stably in the air.
[0037] During flight, when the aircraft's attitude changes, such as during turns, climbs, or dives, the gyroscope 4 monitors these attitude changes in real time and transmits the information to the intelligent control system. Based on the aircraft's current attitude and flight mission requirements, the intelligent control system precisely adjusts the angle and position of the wing arm 310 by controlling the motors of the main power wing arm 306 and the driven auxiliary wing arm 309. This allows parameters such as the wing's angle of attack and twist angle to dynamically match the flight attitude, optimizing aerodynamic performance, improving the aircraft's maneuverability and flight efficiency, reducing mechanical damage, and extending the aircraft's service life. In manned aircraft applications, the intelligent control system can transmit real-time monitoring data to the aircraft's control panel and selectively display control adjustment schemes, helping the pilot to control the aircraft more quickly and reliably.
[0038] When the aircraft completes its flight mission and needs to land, or for transport or storage, the folding wing mechanism switches to a compact folding mode. The intelligent control system controls the motors of the main folding arm 306 and the driven auxiliary folding arm 309, driving the folding arm 310 to fold the wings. The folded wings fit tightly against both sides of the fuselage, forming a compact shape that minimizes the space occupied by the aircraft, facilitating storage and transport in confined spaces, and also helps protect the wings from damage by the external environment.
[0039] By adopting the above structure, the space efficiency of folding wings and the aerodynamic advantages of fixed wings are combined, making it suitable for multiple application scenarios. It is easy to transport and store in complex environments and confined spaces, enabling the aircraft to be used in various scenarios, such as urban air traffic, logistics transportation, and military reconnaissance, and has broad adaptability and practicality.
[0040] The above are merely further embodiments of this utility model, but the protection scope of this utility model is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope disclosed by this utility model, based on the technical solution and concept of this utility model, shall fall within the protection scope of this utility model.
[0041] All standard parts used in this application can be purchased from the market, and can be customized according to the description and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts and equipment adopt conventional models in the prior art. The control method is automatic control through a controller. The control circuit of the controller can be implemented by simple programming by those skilled in the art and is common knowledge in the field. Since this application is mainly used to protect mechanical devices, the control method and circuit connection will not be explained in detail in this application.
Claims
1. A multimodal intelligent folding wing mechanism, comprising a fuselage carrier (1), characterized in that: The top of the fuselage carrier (1) is provided with a folding wing mechanism (3); The folding wing mechanism (3) includes two sets of symmetrically detachable fixed supports (301) installed on the top of the fuselage carrier (1). A horizontally placed rotating shaft (305) is rotatably installed inside the higher end of the fixed support (301). A driving force folding arm (306) is installed on the outer end of the rotating shaft (305). A driven auxiliary folding arm (309) is rotatably installed inside the lower end of the fixed support (301). The active power folding arm (306) and the driven auxiliary folding arm (309) are respectively equipped with a first servo motor (307) and a second servo motor (308) at the ends away from the fixed support (301), and a folding arm (310) is fixed between the first servo motor (307) and the second servo motor (308).
2. The multimodal intelligent folding wing mechanism according to claim 1, characterized in that: The middle section of the rotating shaft (305) is fitted with a ring structure, and a hydraulic cylinder (304) is hinged to the bottom of the ring. A support frame (303) is hinged to the end of the hydraulic cylinder (304) away from the rotating shaft (305). The bottom of the support frame (303) is welded to the top of the body carrier (1).
3. The multimodal intelligent folding wing mechanism according to claim 2, characterized in that: The active power articulated arm (306) and the driven auxiliary articulated arm (309) are provided with a locking mechanism at the end near the fixed support (301), and the locking mechanism adopts a pawl structure.
4. The multimodal intelligent folding wing mechanism according to claim 3, characterized in that: A rubber shock-absorbing pad (302) is pressed between the fixed support (301) and the fuselage carrier (1).
5. A multimodal intelligent folding wing mechanism according to claim 4, characterized in that: A gyroscope (4) is embedded in one side of the outer wall of the fixed support (301).
6. A multimodal intelligent folding wing mechanism according to claim 5, characterized in that: The rotor body (2) is fixedly mounted on the upper part of the folding arm (310).