Hydrogen hybrid unmanned aerial vehicle capable of landing stably
By designing the coordination of components such as fixing seats, wing rods, connecting rods, locking seats, slide rods, locking blocks and elastic springs, the folding and fixing of the wings of the hydrogen hybrid drone is achieved, solving the problem of inconvenient wing storage, and improving portability and flight stability.
Patent Information
- Application Number
- CN202422481985.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-14
- Publication Date
- 2025-07-25
- Estimated Expiration
- 2034-10-14
AI Technical Summary
The existing hydrogen hybrid drone wings are inconvenient to fold, resulting in a large lateral volume when stored and carried, which is inconvenient to carry.
The fit of components such as fixing seats, wing rods, connecting rods, locking seats, slide rods, locking blocks and elastic springs is designed to allow the wing rod to flip downward and fit the main body. The fixing of the wing rod is achieved through the action of the locking blocks and elastic springs, and the stability after folding is ensured by using the L-shaped clamp blocks.
It reduces the wing area, facilitates the storage and carrying of the drone, and ensures the stability of the wing during flight to avoid shaking.
Smart Images
Figure CN223148730U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a hydrogen hybrid unmanned aerial vehicle with stable landing. Background Technique
[0002] A hydrogen hybrid unmanned aerial vehicle uses a hydrogen fuel cell as the core power source. The hydrogen carried is used as fuel and reacts with the naturally inhaled oxygen under the action of a platinum catalyst to generate electrical energy to drive the flight of the unmanned aerial vehicle.
[0003] Currently, most existing hydrogen hybrid unmanned aerial vehicles are provided with a support structure at the bottom to ensure their stability during landing. However, when the existing hydrogen hybrid unmanned aerial vehicles are in use, there are still the following deficiencies: their wings are not convenient to fold, resulting in a relatively large lateral volume during storage and transportation, and it is not convenient to store and carry. In view of this, we propose a hydrogen hybrid unmanned aerial vehicle with stable landing to solve the above-mentioned problems. Content of the Utility Model
[0004] The purpose of the utility model is to provide a hydrogen hybrid unmanned aerial vehicle with stable landing to solve the problems raised in the above background technique.
[0005] To achieve the above purpose, the utility model provides the following technical solution: A hydrogen hybrid unmanned aerial vehicle with stable landing, comprising:
[0006] A hydrogen hybrid unmanned aerial vehicle main body, on both side walls of which a pair of fixed seats are fixedly installed. A wing rod is rotatably installed on the fixed seat, and a rotor is installed at the outer end of the wing rod. A connecting rod is fixedly welded between each pair of wing rods. On both side walls of the hydrogen hybrid unmanned aerial vehicle main body, a locking seat is fixedly installed. A sliding rod is slidably connected in the inner cavity of the locking seat. Locking blocks are fixedly welded at both ends of the sliding rod, and the locking blocks are slidably connected to the outer side wall of the locking seat. A elastic spring is arranged in the inner cavity of the locking seat, and both ends of the elastic spring are fixedly connected to the inner side wall of the locking seat and the sliding rod respectively. A pair of locking grooves are formed on the connecting rod, and the locking blocks are movably inserted into the locking grooves.
[0007] Preferably, a through groove is formed in the middle of the top wall of the locking seat. A connecting block is fixedly adhered to the middle of the top wall of the sliding rod, and the connecting block is slidably connected in the through groove. A push block is fixedly adhered to the top end of the connecting block.
[0008] Preferably, bases are fixedly adhered to both side walls of the hydrogen hybrid unmanned aerial vehicle main body. A sliding column is slidably connected to the base. An L-shaped clamping block is fixedly adhered to the top end of the sliding column, and a pulling plate is fixedly adhered to the bottom end of the sliding column. A tension spring is sleeved on the sliding column, and both ends of the tension spring are fixedly connected to the base and the pulling plate respectively.
[0009] Preferably, two support frames are fixedly installed on the bottom wall of the hydrogen hybrid UAV body.
[0010] Preferably, anti-slip patterns are provided on the top wall of the push block.
[0011] Compared with the prior art, the beneficial effects of the present utility model are as follows:
[0012] Through the cooperation of components such as the fixed seat, wing rod, connecting rod, locking seat, sliding rod, locking block and elastic spring provided in the present utility model, when the hydrogen hybrid UAV is in use, the two pairs of wing rods can be turned downward to fit with the hydrogen hybrid UAV body, reducing the occupied area of the wing rods and facilitating the storage and carrying of the hydrogen hybrid UAV. The locking block is inserted into the locking groove under the elastic force of the elastic spring, which can facilitate the locking and fixing after the wing rods are unfolded, ensuring that the wing rods will not shake during the flight of the UAV. By providing the L-shaped clamping block, it can be clamped on the connecting rod after the wing rod is turned over, thus facilitating the locking and fixing of the connecting rod and ensuring the stability of the wing rod after folding, avoiding the wing rod from shaking easily after folding. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 FIG. 1 is a schematic three-dimensional structure diagram of a hydrogen hybrid UAV with stable landing proposed by the present utility model;
[0014] Figure 2 FIG. 2 is a front view structural diagram of the whole in a hydrogen hybrid UAV with stable landing proposed by the present utility model;
[0015] Figure 3 FIG. 3 is a schematic three-dimensional structure diagram of the connection between the locking seat and the connecting rod in a hydrogen hybrid UAV with stable landing proposed by the present utility model;
[0016] Figure 4 FIG. 4 is a schematic cross-sectional top view of the locking seat in a hydrogen hybrid UAV with stable landing proposed by the present utility model.
[0017] In the figure: 1, hydrogen hybrid UAV body; 2, fixed seat; 3, wing rod; 4, rotor; 5, connecting rod; 6, locking seat; 7, sliding rod; 8, locking block; 9, elastic spring; 10, locking groove; 11, through groove; 12, connecting block; 13, push block; 14, base; 15, sliding column; 16, L-shaped clamping block; 17, pull plate; 18, tension spring; 19, support frame. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0018] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without creative efforts shall fall within the protection scope of the present utility model.
[0019] Please refer to Figures 1-4 , the present utility model provides a technical solution: a hydrogen hybrid drone with stable landing, including:
[0020] The hydrogen hybrid drone main body 1, on both side walls of the hydrogen hybrid drone main body 1, a pair of fixed seats 2 are fixedly installed. On the fixed seats 2, wing rods 3 are rotatably installed. At the outer ends of the wing rods 3, rotors 4 are installed. Between each pair of the wing rods 3, a connecting rod 5 is fixedly welded. On both side walls of the hydrogen hybrid drone main body 1, locking seats 6 are fixedly installed. In the inner cavity of the locking seats 6, sliding rods 7 are slidably connected. At both ends of the sliding rods 7, locking blocks 8 are fixedly welded. The locking blocks 8 are slidably connected to the outer side walls of the locking seats 6. In the inner cavity of the locking seats 6, a elastic spring 9 is arranged. The two ends of the elastic spring 9 are respectively fixedly connected to the inner side wall of the locking seat 6 and the sliding rod 7. On the connecting rod 5, a pair of locking grooves 10 are opened. The locking blocks 8 are movably inserted into the locking grooves 10.
[0021] In the middle of the top wall of the locking seat 6, a through groove 11 is opened. In the middle of the top wall of the sliding rod 7, a connecting block 12 is fixedly adhered. The connecting block 12 is slidably connected in the through groove 11. At the top end of the connecting block 12, a pushing block 13 is fixedly adhered. The pushing block 13 can facilitate pushing the connecting block 12 to move in the through groove 11 to drive the sliding rod 7 to slide in the inner cavity of the locking seat 6, so as to drive the two locking blocks 8 to contract on the locking seat 6.
[0022] On both side walls of the hydrogen hybrid drone main body 1, bases 14 are fixedly adhered. On the bases 14, sliding columns 15 are slidably connected. At the top end of the sliding columns 15, L-shaped clamping blocks 16 are fixedly adhered. At the bottom end of the sliding columns 15, pulling plates 17 are fixedly adhered. On the sliding columns 15, tension springs 18 are sleeved. The two ends of the tension springs 18 are respectively fixedly connected to the bases 14 and the pulling plates 17. The L-shaped clamping blocks 16 can be clamped on the connecting rod 5 after the wing rods 3 are turned over, so as to facilitate locking and fixing the connecting rod 5 and ensure the stability of the wing rods 3 after folding.
[0023] On the bottom wall of the hydrogen hybrid drone main body 1, two support frames 19 are fixedly installed. The support frames 19 are used to stably support the drone.
[0024] The top wall of the push block 13 is provided with anti-slip lines, which can improve the friction between the push block 13 and the fingers and facilitate the pushing of the push block 13.
[0025] Working principle: Through the cooperation of components such as the fixed seat 2, wing rods 3, connecting rods 5, locking seats 6, sliding rods 7, locking blocks 8 and elastic springs 9 provided in this utility model, when the hydrogen hybrid unmanned aerial vehicle is in use, the two pairs of wing rods 3 can be turned downward to fit with the main body 1 of the hydrogen hybrid unmanned aerial vehicle, reducing the occupied area of the wing rods 3 and facilitating the storage and carrying of the hydrogen hybrid unmanned aerial vehicle. The locking block 8 inserted into the locking groove 10 under the elastic force of the elastic spring 9 can facilitate the locking and fixing after the wing rods 3 are unfolded, ensuring that the wing rods 3 will not shake during the flight of the unmanned aerial vehicle. By setting the L-shaped clamping block 16, it can be clamped on the connecting rod 5 after the wing rods 3 are turned over, thus facilitating the locking and fixing of the connecting rod 5 and ensuring the stability of the wing rods 3 after folding.
[0026] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such process, method, article or device.
[0027] Although the embodiments of the present utility model have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principle and spirit of the present utility model. The scope of the present utility model is defined by the appended claims and their equivalents.
Claims
1. A hydrogen hybrid drone with stable landing, characterized in that, Including: A hydrogen hybrid UAV body (1), on both side walls of the hydrogen hybrid UAV body (1), a pair of fixed seats (2) are fixedly installed, on the fixed seats (2), wing rods (3) are rotatably installed, at the outer ends of the wing rods (3), rotors (4) are installed, between each pair of the wing rods (3), connecting rods (5) are fixedly welded, on both side walls of the hydrogen hybrid UAV body (1), locking seats (6) are fixedly installed, in the inner cavity of the locking seats (6), sliding rods (7) are slidably connected, at both end positions of the sliding rods (7), locking blocks (8) are fixedly welded, the locking blocks (8) are slidably connected on the outer side walls of the locking seats (6), in the inner cavity of the locking seats (6), elastic springs (9) are arranged, both ends of the elastic springs (9) are respectively fixedly connected with the inner side walls of the locking seats (6) and the sliding rods (7), on the connecting rods (5), a pair of locking grooves (10) are opened, and the locking blocks (8) are movably inserted into the locking grooves (10).
2. The landing-stable hydrogen hybrid drone according to claim 1, characterized in that: In the middle of the top wall of the locking seat (6), a through groove (11) is opened, in the middle of the top wall of the sliding rod (7), a connecting block (12) is fixedly adhered, the connecting block (12) is slidably connected in the through groove (11), and at the top end of the connecting block (12), a pushing block (13) is fixedly adhered.
3. The stable landing hydrogen hybrid drone according to claim 1, characterized in that: On both side walls of the hydrogen hybrid UAV body (1), bases (14) are fixedly adhered, on the bases (14), sliding columns (15) are slidably connected, at the top ends of the sliding columns (15), L-shaped clamping blocks (16) are fixedly adhered, at the bottom ends of the sliding columns (15), pulling plates (17) are fixedly adhered, on the sliding columns (15), tension springs (18) are sleeved, and both ends of the tension springs (18) are respectively fixedly connected with the bases (14) and the pulling plates (17).
4. A hydrogen hybrid drone with stable landing according to claim 1, characterized in that: On the bottom wall of the hydrogen hybrid UAV body (1), two support frames (19) are fixedly installed.
5. The landing-stable hydrogen hybrid drone according to claim 2, wherein: On the top wall of the pushing block (13), anti-slip lines are opened.