An unmanned aerial vehicle cabin door sealing strip

Abstract

The utility model belongs to the technical field of sealing strip, especially, relate to a kind of unmanned aerial vehicle hatch sealing strip.Solve the technical problems such as the rigidity of conventional sealing strip, leading to hatch difficult to close, deformation, etc.It includes the sealing strip upper body and the sealing strip lower body of the cross section of the integrated molding " cloud " shape, and the cross section of the sealing strip lower body is " horizontal fold " shape;Three arc convex parts are equipped on the sealing strip upper body, and the sealing strip lower body is equipped with a clamping groove.The significant reduction of door force value is realized, and the adaptation contradiction between conventional rigid sealing strip and carbon fiber composite fuselage, hatch is solved from the root.The optimization not only can easily realize the complete closure of hatch, eliminate the hidden danger such as air tightness damage, equipment damp and air pressure failure caused by gap, but also can fundamentally avoid irreversible deformation of hatch caused by long-term rigid extrusion, ensure the cooperation precision of fuselage and hatch, greatly reduce the risk of sealing failure.

Description

Technical Field

[0001] This utility model belongs to the field of sealing strip technology, and in particular relates to a sealing strip for a drone cabin door. Background Technology

[0002] In the field of UAV design and manufacturing, door sealing strips are key components ensuring the airtightness, waterproofing, and dustproofing of the fuselage. Their performance directly affects the flight safety and mission reliability of the UAV. Currently, the commonly used UAV door sealing strips in the industry mainly include classic structures such as Ω-type, P-type, and e-type: Ω-type sealing strips, with their symmetrical cross-section design, have an advantage in sealing contact area and are often used in areas requiring high sealing stability; P-type sealing strips, due to their protruding lip structure on one side, are highly adaptable to dynamic sealing scenarios; e-type sealing strips, characterized by their compact structure and small installation space requirements, are widely used in UAV models with limited door space. Figure 1 .

[0003] However, as drones evolve towards lighter weight and higher strength, the manufacturing materials for fuselages and doors are increasingly shifting towards carbon fiber composites. While this material significantly reduces drone weight and improves structural strength, it also inherently has lower rigidity and a significantly lower elastic modulus compared to traditional metal materials, making it more prone to deformation under external forces. This characteristic creates a significant contradiction with the rigidity of conventional sealing strips: to ensure structural stability and sealing performance, conventional sealing strips typically use high-hardness rubber or elastomer materials. During door closure, the contact between the sealing strip and the door / fuselage generates a substantial reaction force.

[0004] When this reaction force is transmitted to the insufficiently rigid carbon fiber composite door, it triggers a series of problems: First, excessive closing resistance makes it difficult for the door to close completely, creating gaps that compromise the airtightness of the fuselage. This can lead to malfunctions of internal equipment due to air pressure during high-altitude flight, and even moisture damage to internal components in humid environments. Second, long-term, repeated rigid compression can cause irreversible deformation of the door, affecting not only the drone's appearance but also potentially altering the fit between the door and the fuselage, further increasing the risk of seal failure. The cumulative effect of these problems is particularly pronounced in drones performing long-endurance, complex-environment missions, potentially directly impacting mission completion and even causing serious consequences such as drone crashes.

[0005] Therefore, developing a drone sealing strip with low closing force has become a pressing technical challenge for the industry. This new sealing strip needs to significantly reduce the reaction force when in contact with the hatch and fuselage through structural innovation, while ensuring sealing performance. This will allow it to adapt to the characteristics of carbon fiber composite fuselage and avoid problems such as hatches failing to close completely or deformation. Utility Model Content

[0006] To address the shortcomings of existing technologies, this utility model provides a sealing strip for drone cabin doors, solving the technical problems of conventional sealing strips having high rigidity, which leads to difficulties in closing the cabin door and deformation.

[0007] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is as follows: A sealing strip for a drone cabin door includes an upper sealing strip body with a cloud-shaped cross-section and a lower sealing strip body with a horizontal fold cross-section, both integrally formed; the upper sealing strip body has three arc-shaped protrusions, and the lower sealing strip body has a groove.

[0008] Furthermore, the three arc-shaped protrusions are respectively an upper arc-shaped protrusion, a left arc-shaped protrusion, and a right arc-shaped protrusion; the upper arc-shaped protrusion is located at the top center of the upper body of the sealing strip, and the left and right arc-shaped protrusions are symmetrically arranged on the left and right sides of the upper body of the sealing strip, respectively.

[0009] Furthermore, an arc-shaped segment is provided between the upper arc protrusion and the left and right arc protrusions respectively; a straight segment is provided between the left and right arc protrusions.

[0010] Furthermore, the arc-shaped segment has an externally concave and internally convex shape.

[0011] Furthermore, the lower body of the sealing strip includes a vertical segment and a horizontal segment; one end of the vertical segment is perpendicular to one end of the horizontal segment, and the other end of the vertical segment is perpendicular to the position where the left arc protrusion and the straight segment meet.

[0012] Furthermore, the slot is located between the horizontal segment, the vertical segment, and the straight segment, and the opening of the slot faces the other side of the vertical segment.

[0013] Furthermore, the left and right circular arc protrusions are semi-circular.

[0014] Furthermore, the upper arc protrusion is one-third of a circle.

[0015] Furthermore, the length of the horizontal segment is the same as the length of the straight segment.

[0016] Compared with the prior art, the beneficial effects of this utility model are as follows: The sealing strip structure design in this application significantly reduces the closing force, fundamentally resolving the compatibility issues between conventional rigid sealing strips and carbon fiber composite fuselages and hatches. This optimization not only easily achieves complete hatch closure, eliminating potential risks such as airtightness damage, equipment moisture damage, and air pressure failure caused by gaps, but also fundamentally avoids irreversible deformation of the hatch caused by long-term rigid compression, ensuring the fitting precision between the fuselage and the hatch, and greatly reducing the risk of seal failure.

[0017] This application innovatively adopts a cloud-shaped structure for its sealing strip, with the stacking of three arc-shaped protrusions on the main body of the sealing strip being a core technological highlight. Unlike the rigid contact modes of conventional structures such as Ω-type, P-type, and e-type, the symmetrical left and right arc-shaped protrusions utilize the physical characteristic of arc structures easily undergoing elastic deformation under stress: during the door closing process, the protrusions deform uniformly with the contact pressure, dispersing the concentrated reaction force into a gradual buffer force, thereby significantly reducing the resistance at the moment of closing. At the same time, the upper arc-shaped protrusion acts as a structural support, ensuring the overall strength of the sealing strip to maintain sealing performance, and also forming a synergistic deformation effect with the protrusions on both sides. While reducing the closing force, the tight fit of multiple arc segments enhances the sealing contact area, achieving a dual technological breakthrough of "low closing force" and "high sealing performance," perfectly meeting the low rigidity requirements of carbon fiber composite fuselages. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the existing e-type sealing strip structure mentioned in the background art of this utility model; Figure 2 This is a schematic diagram of the structure of this utility model; Figure 3 This utility model Figure 2 A schematic diagram of its decomposed structure. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0020] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention.

[0021] Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort prior to the description are within the scope of protection of this utility model.

[0022] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0023] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0024] like Figure 1-3 As shown: A sealing strip for a drone cabin door includes an upper sealing strip body 1 with a cloud-shaped cross-section and a lower sealing strip body 2 with a horizontal fold cross-section; the upper sealing strip body 1 has three arc-shaped protrusions, and the lower sealing strip body 2 has a groove 21.

[0025] The "cloud" shaped structure design of the main body 1 of the sealing strip is not a simple superposition of three arc protrusions, but rather forms an elastic buffer space similar to cloud layers. Compared with the single contact interface of conventional Ω-type and P-type sealing strips, this structural design can achieve step-like transmission and buffering of force through the sequential deformation of multiple arc protrusions, so that the reaction force during the closing process presents a smooth curve rather than a sudden peak, and achieves a substantial reduction in closing force from the perspective of mechanical principles.

[0026] The slot 21 enhances overall assembly stability and operational reliability. This slot 21 precisely matches the pre-set locking parts on the hatch or fuselage, forming a robust mechanical connection and preventing the sealing strip from shifting or falling off under conditions such as drone flight vibrations and repeated hatch opening and closing. Simultaneously, the limiting function of the slot 21 ensures the sealing strip remains in the optimal sealing position. Combined with the "cloud"-shaped structure of the sealing strip body 1, this results in a more stable sealing contact, strengthening the continuity of the "low closing force" advantage and providing structural assurance for "high sealing performance." This ensures the sealing strip maintains consistent performance over long-term use, meeting the durability requirements of drones under complex operating conditions.

[0027] Furthermore, the three arc-shaped protrusions are the upper arc protrusion 3, the left arc protrusion 4, and the right arc protrusion 5, respectively. The upper arc protrusion 3 is located at the top center of the upper body 1 of the sealing strip, and the left arc protrusion 4 and the right arc protrusion 5 are symmetrically arranged on the left and right sides of the upper body 1 of the sealing strip, respectively.

[0028] The cloud-shaped sealing strip's main body 1 ensures that the left and right arc-shaped protrusions 4 and 5 deform at the same rate under pressure, guaranteeing uniform contact between the sealing strip and the hatch / fuselage. This prevents seal failure or hatch deformation due to localized overpressure. The upper arc-shaped protrusion 3, as the primary contact point, absorbs initial pressure through slight deformation during the initial hatch closure. After absorbing pressure, the upper arc-shaped protrusion 3 disperses the force to the left and right arc-shaped protrusions 4 and 5 through its curvature change, preventing localized stress concentration. More importantly, the three arc-shaped protrusions, after deformation, can tightly adhere to the contact surface due to their elasticity. Combined with the multiple sealing interfaces formed by the multiple protrusions, this further enhances the sealing redundancy while maintaining low closing force. Even when the UAV vibrates during flight, continuous elastic compensation maintains a good sealing condition, truly achieving a deep synergy between structural form and functional performance.

[0029] Furthermore, an arc-shaped segment 6 is provided between the upper arc protrusion 3 and the left arc protrusion 4 and the right arc protrusion 5, respectively. The arc-shaped segment 6 is concave on the outside and convex on the inside. A straight segment 7 is provided between the left arc protrusion 4 and the right arc protrusion 5.

[0030] The arc-shaped segment 6 guides the force transmission path, allowing the pressure borne by the upper arc protrusion 3 to be more smoothly distributed to the left arc protrusion 4 and the right arc protrusion 5. The transition design of the arc-shaped segment 6 reduces stress concentration points, making the deformation of each protrusion more coordinated, and further reducing resistance fluctuations when closing the door. A straight segment 7 is provided between the left arc protrusion 4 and the right arc protrusion 5. It provides appropriate support when the sealing strip is deformed under pressure, preventing excessive inward retraction of the protrusions on both sides from affecting the sealing effect. At the same time, it enhances the overall structural stability, making the deformation of the cloud-shaped structure controllable, and balancing low closing force and sealing reliability.

[0031] Furthermore, the lower body 2 of the sealing strip includes a vertical segment 22 and a horizontal segment 23; one end of the vertical segment 22 is perpendicular to one end of the horizontal segment 23, and the other end of the vertical segment 22 is perpendicular to the position where the left arc protrusion 4 and the straight segment 7 meet.

[0032] Furthermore, the slot 21 is located between the horizontal segment 23, the vertical segment 22, and the straight segment 7, and the opening of the slot 21 faces the other side of the vertical segment 22.

[0033] Furthermore, the left circular arc protrusion 4 and the right circular arc protrusion 5 are semicircles; the upper circular arc protrusion 3 is a third circle; the length of the horizontal straight segment 23 is the same as the length of the straight segment 7.

[0034] When using: During the installation of the sealing strip, the slot 21 of the lower body 2 of the sealing strip is precisely aligned with the pre-set snap-fit ​​part of the drone door or fuselage. By pressing, the snap-fit ​​part is fully embedded in the slot 21. The mechanical limiting effect of the slot 21 is used to firmly fix the sealing strip, ensuring that it does not shift or fall off during drone flight vibration and repeated opening and closing of the door, and always remains in the preset sealing position.

[0035] When the drone's hatch closes, it first contacts and applies pressure to the upper arc-shaped protrusion 3 on the main body 1 of the sealing strip. Upon receiving this pressure, the upper arc-shaped protrusion 3 begins to undergo elastic deformation, simultaneously transmitting the pressure smoothly to the left arc-shaped protrusion 4 and the right arc-shaped protrusion 5 through the arc-shaped segments 6 on both sides. The transition design of the arc-shaped segments 6 ensures more even force transmission, avoiding deformation jamming caused by localized stress concentration.

[0036] As the hatch continues to close, the pressure gradually increases. The left and right arc-shaped protrusions 4 and 5 deform outwards under pressure, absorbing some of the pressure and gradually releasing the reaction force during the closing process, effectively reducing the closing force. At this time, the straight section 7 between the left and right arc-shaped protrusions 4 and 5 provides support, limiting excessive inward retraction of the protrusions on both sides and ensuring that the deformation remains within a controllable range.

[0037] After the hatch is fully closed, the upper arc protrusion 3, the left arc protrusion 4, and the right arc protrusion 5 fit tightly against the contact surface between the hatch and the fuselage under their own elasticity. The multiple arcs forming a multi-seal interface enhances airtightness and waterproofness.

[0038] This application is in contrast to the E-shaped sealing strip (see...). Figure 1 In comparison, with a compression of 10mm, the force per meter of the E-shaped sealing strip is 625N, while the force per meter of the sealing strip of this application is 125N. The force of the sealing strip of this application is only one-fifth of that of the E-shaped sealing strip.

[0039] The present invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited to the above embodiments. Those skilled in the art can make various modifications or variations to the present invention without departing from the technical concept of the present invention, and such modifications or variations naturally fall within the protection scope of the present invention.

Claims

1. A sealing strip for an unmanned aerial vehicle (UAV) cabin door, characterized in that: It includes an upper body (1) of a sealing strip with a cloud-shaped cross section and a lower body (2) of a sealing strip with a horizontal fold cross section. The upper body (1) of the sealing strip is provided with three arc-shaped protrusions, and the lower body (2) of the sealing strip is provided with a slot (21).

2. The unmanned aerial vehicle (UAV) cabin door sealing strip according to claim 1, characterized in that: The three arc protrusions are the upper arc protrusion (3), the left arc protrusion (4), and the right arc protrusion (5); The upper arc protrusion (3) is located at the top center of the upper body (1) of the sealing strip, and the left arc protrusion (4) and the right arc protrusion (5) are symmetrically arranged on the left and right sides of the upper body (1) of the sealing strip, respectively.

3. The unmanned aerial vehicle (UAV) cabin door sealing strip according to claim 2, characterized in that: Arc-shaped segments (6) are provided between the upper arc protrusion (3) and the left arc protrusion (4) and the right arc protrusion (5). A straight segment (7) is provided between the left circular arc protrusion (4) and the right circular arc protrusion (5).

4. The unmanned aerial vehicle (UAV) cabin door sealing strip according to claim 3, characterized in that: The arc segment (6) has an externally concave and internally convex shape.

5. A sealing strip for an unmanned aerial vehicle (UAV) cabin door according to claim 4, characterized in that: The lower body (2) of the sealing strip includes a vertical section (22) and a horizontal section (23); One end of the vertical segment (22) is perpendicular to one end of the horizontal segment (23), and the other end of the vertical segment (22) is perpendicular to the position where the left arc protrusion (4) and the straight segment (7) meet.

6. A UAV cabin door sealing strip according to claim 5, characterized in that: The slot (21) is located between the horizontal segment (23), the vertical segment (22), and the straight segment (7), and the opening of the slot (21) faces the other side of the vertical segment (22).

7. A sealing strip for an unmanned aerial vehicle (UAV) cabin door according to claim 2, characterized in that: The left circular arc protrusion (4) and the right circular arc protrusion (5) are semicircular.

8. A sealing strip for an unmanned aerial vehicle (UAV) cabin door according to claim 2, characterized in that: The upper arc protrusion (3) is one-third of a circle.

9. A sealing strip for an unmanned aerial vehicle (UAV) cabin door according to claim 5, characterized in that: The length of the horizontal segment (23) is the same as the length of the straight segment (7).

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