Delta wing fuselage integration unmanned aerial vehicle with large capacity fuel tank for flight stabilization
By incorporating a float plate and an inverted "V"-shaped limiting plate inside the fuel tank, the problem of flight instability caused by fuel oscillation in a large-capacity fuel tank was solved, enabling stable flight of the UAV in complex environments.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- ZHONGAN DATA TECHNOLOGY DEVELOPMENT (SHENZHEN) CO LTD
- Filing Date
- 2025-09-22
- Publication Date
- 2026-07-21
AI Technical Summary
With increased capacity, fuel in traditional delta-wing fuselage drones is prone to violent oscillations due to attitude changes, leading to a shift in the center of gravity and affecting flight stability and safety. This can cause fuselage turbulence and loss of attitude, especially in low-altitude, low-speed flight or complex airflow environments.
A fuel tank structure including a float plate and an inverted "V" shaped limiting plate was designed. The float plate slides in contact with the inner wall of the fuel tank, and the limiting plate presses against the side wall of the fuel tank in response to fuel impact, forming a stable triangular area to limit fuel oscillation and ensure the stability of the center of gravity.
It effectively suppresses fuel oscillation, maintains a stable range of fuel movement within the fuel tank, and improves the flight stability of drones, making it suitable for precision operation scenarios.
Smart Images
Figure CN224528989U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of fuel tank technology, specifically a large-capacity fuel tank for a delta wing fuselage integrated UAV that facilitates flight stability. Background Technology
[0002] With the rapid development of drone technology, delta-wing fuselage drones, with their advantages of high aerodynamic efficiency, low drag, and compact structure, are widely used in reconnaissance, surveying, and cargo transport. These drones often have high requirements for endurance, and the fuel tank, as a core component for storing fuel and ensuring endurance, directly affects the drone's operational performance and flight safety.
[0003] Currently, there are key issues with the fuel tank design of traditional delta-wing fuselage hybrid UAVs:
[0004] To improve endurance, a larger fuel tank capacity is needed. However, during drone flight, the fuel inside a large-capacity tank is prone to severe oscillations due to attitude changes (such as starting, braking, and turning). These fuel oscillations cause frequent shifts in the tank's center of gravity, disrupting the drone's aerodynamic balance. This is especially problematic in low-altitude, low-speed flight or complex airflow environments, potentially leading to turbulence, loss of attitude control, and other risks, severely threatening flight stability. When the drone starts, fuel impacts the rear wall of the tank due to inertia; during braking, it impacts the front wall. Long-term, repeated fuel impacts not only accelerate wear on the tank's inner walls, shortening its lifespan, but can also loosen fuel line connections, leading to potential fuel leaks. Furthermore, the additional force generated by these impacts further interferes with the drone's flight attitude control, increasing the difficulty of operation, especially in precision missions (such as low-altitude mapping and targeted delivery), potentially causing a decrease in operational accuracy.
[0005] Therefore, developing a fuel tank structure that is compatible with delta wing fuselage UAVs, can meet the demand for large-capacity fuel storage, and can effectively suppress fuel oscillation and ensure flight stability has become a technical problem that the industry urgently needs to solve. Utility Model Content
[0006] To address the shortcomings of existing technologies, this utility model provides a large-capacity fuel tank for a delta wing fuselage integrated UAV that facilitates flight stability.
[0007] To achieve the above objectives, the technical solution of this utility model is as follows:
[0008] The delta-wing fuselage hybrid UAV uses a large-capacity fuel tank to facilitate flight stability, including:
[0009] The fuel tank body has an internal cavity for holding fuel;
[0010] The float plate is slidably connected to the cavity of the fuel tank body, and the peripheral sidewall of the float plate is always in contact with the inner wall of the fuel tank body as the float plate slides along the height direction of the fuel tank body.
[0011] Stable components, including:
[0012] Limit plate one;
[0013] Limiting plate two, one side of which is fixed to one side of limiting plate one, the two limiting plates are fixed in an inverted "V" shape, and the fixed part of the two limiting plates is rotatably connected to the bottom of the floating plate.
[0014] in:
[0015] When the fuel in the fuel tank body is not agitated, the free ends of limit plate one and limit plate two are both detached from the inner wall of the fuel tank body.
[0016] When the drone brakes, the fuel in the fuel tank impacts the second limiting plate until the free end of the second limiting plate abuts against the side wall of the fuel tank.
[0017] When the drone starts, the fuel in the fuel tank impacts the limiting plate one until the free end of the limiting plate one abuts against the side wall of the fuel tank body.
[0018] Preferably, when the free end of the second limiting plate abuts against the side wall of the tank body, a stable triangular region is formed between the bottom of the float plate, the side wall of the tank body, and the second limiting plate.
[0019] Preferably, the included angle between the first limiting plate and the second limiting plate is between 120°C and 150°C.
[0020] Preferably, both the first limiting plate and the second limiting plate are equipped with impact plates on the side closest to the ground, and a fuel impact zone is formed between the impact plates and the limiting plates.
[0021] Preferably, a one-way fuel inlet valve is installed on the side of the fuel tank body closest to the ground. When fuel is filled into the fuel tank body through the one-way fuel inlet valve, the float gradually rises with the fuel filling height.
[0022] Compared with the prior art, the beneficial effects of this utility model are as follows:
[0023] The inverted "V"-shaped limiting plates one and two in the stabilization assembly can accurately respond to fuel impacts according to different operating conditions such as drone start-up and braking. During start-up, fuel impacts limiting plate one, causing its free end to press against the side wall of the fuel tank body; during braking, fuel impacts limiting plate two, similarly achieving side wall pressing. This design triggers the limit by the impact force of the fuel itself, without the need for additional power drive, and can quickly restrict large-scale fuel flow under critical operating conditions, avoiding frequent shifts in the fuel tank's center of gravity, and fundamentally ensuring the stability of the drone's flight attitude.
[0024] When the second limiting plate is pressed against the side wall of the fuel tank, the bottom of the float plate, the side wall of the fuel tank body, and the second limiting plate form a stable triangular area. Due to the non-deformable mechanical properties of the triangular structure, this area can firmly lock the movement range of the fuel. Even in strong airflow or sudden attitude adjustment scenarios, it can effectively prevent fuel oscillation and further improve flight stability, which is especially suitable for the needs of precision operation drones. Attached Figure Description
[0025] The disclosure of this utility model is illustrated with reference to the accompanying drawings. It should be understood that the drawings are for illustrative purposes only and are not intended to limit the scope of protection of this utility model. In the drawings, the same reference numerals are used to refer to the same parts. Wherein:
[0026] Figure 1 This is a schematic diagram of the structure of the oil tank of this utility model when the oil is not agitated;
[0027] Figure 2 This utility model Figure 1 Enlarged view of section A;
[0028] Figure 3 This is a schematic diagram showing the direction of oil movement in the fuel tank during the braking of the UAV of this utility model;
[0029] Figure 4 This utility model Figure 3 Enlarged view of section B;
[0030] Figure 5 This is a schematic diagram showing the direction of oil movement in the fuel tank during the start-up of the UAV of this utility model.
[0031] The diagram shows: 1. Oil tank body; 11. One-way oil inlet valve; 12. Oil outlet valve; 2. Float; 3. Limiting plate one; 4. Limiting plate two. Detailed Implementation
[0032] It is readily understood that, based on the technical solution of this utility model, those skilled in the art can propose various interchangeable structural methods and implementations without altering the essential spirit of this utility model. Therefore, the following detailed embodiments and accompanying drawings are merely illustrative descriptions of the technical solution of this utility model and should not be considered as the entirety of this utility model or as limitations or restrictions on the technical solution of this utility model.
[0033] Example
[0034] like Figure 1-5 As shown, the delta-wing fuselage hybrid UAV uses a large-capacity fuel tank to facilitate flight stability, including:
[0035] The fuel tank body 1 has an internal cavity for holding fuel.
[0036] The float plate 2 is slidably connected to the cavity of the fuel tank body 1. During the process of the float plate 2 sliding along the height direction of the fuel tank body 1, the peripheral side wall of the float plate 2 is always in contact with the inner wall of the fuel tank body 1. The side of the fuel tank body 1 near the ground is equipped with a one-way fuel inlet valve 11 and a fuel outlet valve 12. When fuel is filled into the interior of the fuel tank body 1 through the one-way fuel inlet valve 11, the float plate 2 gradually rises with the fuel filling height.
[0037] Stable components, including:
[0038] Limit plate 13;
[0039] Limiting plate 2 4, one side of which is fixed to one side of limiting plate 1 3. After the limiting plate 2 4 and the limiting plate 1 3 are fixed, they form an inverted "V" shape. The fixing point of the limiting plate 2 4 and the limiting plate 1 3 is rotatably connected to the bottom of the floating plate 2.
[0040] in:
[0041] When the fuel in the fuel tank body 1 is not agitated, the free ends of the limiting plate 3 and the limiting plate 4 are both detached from the inner wall of the fuel tank body 1.
[0042] When the drone brakes, the fuel in the fuel tank body 1 impacts the limiting plate 2 4 until the free end of the limiting plate 2 4 abuts against the side wall of the fuel tank body 1.
[0043] When the drone starts, the fuel in the fuel tank body 1 impacts the limiting plate 3 until the free end of the limiting plate 3 abuts against the side wall of the fuel tank body 1.
[0044] Specifically, in this utility model, the fuel tank body 1 is used to store fuel, and its shape is integrated with the delta wing fuselage of the UAV. When fuel is added to the fuel tank body 1, the float 2 rises due to the compression of the fuel as fuel is continuously added. During the fuel consumption process, the float 2 will descend due to gravity. In short, the lower surface of the float 2 will always be in contact with the top of the fuel tank. As the fuel is continuously added and the float 2 rises, when the fuel in the fuel tank body 1 is not agitated, the force exerted by the fuel on the limiting plate 3 and the limiting plate 4 is approximately the same, which will prevent the limiting plate 3 and the limiting plate 4 from causing a rupture. When the drone rotates, the free ends of limit plates 3 and 4 detach from the inner wall of the fuel tank body 1. When these free ends detach, they will no longer restrict movement. The fuel tank's center of gravity is approximately at the center, maintaining the drone's stability. When the drone brakes, the fuel inside the fuel tank body 1 continues to move forward, causing it to impact the side of limit plate 4 closest to the ground. Before the fuel impacts limit plate 4, the free ends of limit plate 4... Since the fuel tank body 1 is not in contact with the interior, when fuel impacts the limiting plate 4, because the fixing point of the limiting plate 4 and the first limiting plate 3 is rotatably connected to the bottom of the float 2, the limiting plate 4 will rotate until its free end abuts against the side wall of the fuel tank body 1. After the free end of the limiting plate 4 abuts against the side wall of the fuel tank body 1, when the fuel continues to impact the limiting plate 4, since its free end is already against the side wall of the fuel tank body 1, the limiting plate 4 will not move. At this time, the float 2 will also not move. At this time, the fuel tank body 1 and the float 2 are assembled. The combined fuel storage space will be fixed. No matter how the fuel impacts the limiting plate 24, it will not change the fuel storage space formed by the combination of the fuel tank body 1 and the float plate 2. Therefore, the center of gravity of the entire fuel tank will not change and will always be in a roughly central position. The change in the center of gravity will not cause the drone to become unstable. Similarly, when the drone starts, the fuel in the fuel tank body 1 impacts the limiting plate 3 until the free end of the limiting plate 3 abuts against the side wall of the fuel tank body 1. At this time, the center of gravity will not change and will be in a roughly central position. The change in the center of gravity will not cause the drone to become unstable.
[0045] Furthermore, when the free end of the limiting plate 2 4 abuts against the side wall of the tank body 1, a stable triangular region is formed between the bottom of the float plate 2, the side wall of the tank body 1, and the limiting plate 2 4.
[0046] Specifically, when the fuel does not impact the limiting plate 2 4, the free end of the limiting plate 2 4 detaches from the side wall of the fuel tank body 1. When the fuel impacts the limiting plate 2 4, since the fixed part of the limiting plate 2 4 and the limiting plate 1 3 is rotatably connected to the bottom of the float plate 2, the end of the limiting plate 2 4 away from the limiting plate 1 3 will be impacted and pressed against the side wall of the fuel tank body 1. As long as the impact force continues, the end of the limiting plate 2 4 away from the limiting plate 1 3 will always press against the side wall of the fuel tank body 1. At this time, the float plate 2, the fuel tank body 1 and the limiting plate 2 4 form a stable triangular area. Due to the obstruction of the side wall of the fuel tank body 1, even if the fuel continues to impact the limiting plate 2 4, the limiting plate 2 4 will no longer rotate. At this time, the fuel will be limited between the fuel tank body 1 and the float plate 2, and will not oscillate significantly, keeping the center of gravity always roughly in the center position, thereby maintaining the stability inside the fuel tank.
[0047] Furthermore, the included angle between the first limiting plate 3 and the second limiting plate 4 is between 120°C and 150°C.
[0048] Specifically, by setting the included angle between the first limiting plate 3 and the second limiting plate 4 between 120° and 150°, the free ends of the first limiting plate 3 and the second limiting plate 4 can be kept as far away from the bottom of the fuel tank body 1 as possible. Since the impact force of the fuel has a certain duration, if the free ends of the first limiting plate 3 and the second limiting plate 4 are close to the bottom of the fuel tank body 1 during this process, the impact segment will be reduced, making it difficult for the free end of the second limiting plate 4 to impact the side wall of the fuel tank body 1. This makes it difficult for the second limiting plate 4 to limit the float 2, allowing the float 2 to continue to rise and fall when the fuel oscillates, resulting in instability in the flight of the UAV. By setting the included angle between the first limiting plate 3 and the second limiting plate 4 between 120° and 150°, this invention can increase the stroke of the impact segment on the one hand, and reduce the distance between the free end of the second limiting plate 4 and the inner wall of the fuel tank body 1 on the other hand. When there is only a slight impact, the free end of the second limiting plate 4 can still abut against the side wall of the fuel tank body 1.
[0049] Furthermore, impact plates are installed on the side of the limiting plate 3 and the limiting plate 4 that are close to the ground, and a fuel impact area is formed between the impact plate and the limiting plate.
[0050] Specifically, since a fuel impact zone is formed between the impact plate and the limiting plate, when the fuel impacts the limiting plate 4, it will impact the fuel impact zone formed between the impact plate and the limiting plate. At this time, the impact force on the limiting plate 4 will increase. Even a small impact from the fuel can push the free end of the limiting plate 4 to the side wall of the fuel tank body 1, thereby forming a pressure against the side wall of the fuel tank body 1, forming a limit, and preventing the fuel from oscillating inside the fuel tank body 1, causing the center of gravity to shift, and affecting the stability of the UAV flight.
[0051] The technical scope of this utility model is not limited to the content described above. Those skilled in the art can make various modifications and variations to the above embodiments without departing from the technical concept of this utility model, and all such modifications and variations should fall within the protection scope of this utility model.
Claims
1. A delta-wing fuselage hybrid UAV uses a large-capacity fuel tank that facilitates flight stability, characterized by: include: The fuel tank body (1) has a cavity inside that can hold fuel; The float (2) is slidably connected to the cavity of the tank body (1), and the circumferential sidewall of the float (2) is always in contact with the inner wall of the tank body (1) during the process of sliding along the height direction of the tank body (1). Stable components, including: Limiting plate 1 (3); Limiting plate two (4), one side of which is fixed to one side of limiting plate one (3), the limiting plate two (4) and limiting plate one (3) are fixed in an inverted "V" shape, and the fixed part of the limiting plate two (4) and limiting plate one (3) is rotatably connected to the bottom of the floating plate (2); in: When the fuel in the fuel tank body (1) does not vibrate, the free ends of the limiting plate one (3) and the limiting plate two (4) are both separated from the inner wall of the fuel tank body (1); When the drone brakes, the fuel in the fuel tank body (1) impacts the limiting plate two (4) until the free end of the limiting plate two (4) abuts against the side wall of the fuel tank body (1); When the drone starts, the fuel in the fuel tank body (1) impacts the limiting plate (3) until the free end of the limiting plate (3) abuts against the side wall of the fuel tank body (1).
2. The large-capacity fuel tank for flight stability of the delta-wing fuselage integrated UAV according to claim 1, characterized in that: When the free end of the limiting plate 2 (4) abuts against the side wall of the tank body (1), a stable triangular region is formed between the bottom of the float plate (2), the side wall of the tank body (1) and the limiting plate 2 (4).
3. The large-capacity fuel tank for flight stability of the delta-wing fuselage integrated UAV according to claim 2, characterized in that: The included angle between the first limiting plate (3) and the second limiting plate (4) is between 120°C and 150°C.
4. The large-capacity fuel tank for flight stability of the delta-wing fuselage integrated UAV according to claim 3, characterized in that: Both the first limiting plate (3) and the second limiting plate (4) are equipped with impact plates on the side closest to the ground, and a fuel impact zone is formed between the impact plates and the limiting plates.
5. The large-capacity fuel tank for flight stability of the delta-wing fuselage integrated UAV according to claim 4, characterized in that: The fuel tank body (1) is equipped with a one-way fuel inlet valve (11) on the side closest to the ground. When fuel is filled into the fuel tank body (1) through the one-way fuel inlet valve (11), the float (2) gradually rises with the fuel filling height.