The fuselage of the drone and the drone
By optimizing the continuous smooth curved wall structure design of the drone fuselage, the problem of increased weight due to the fairing was solved, thereby improving the drone's range and smoothness of flight.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- MEITUAN TECH CO LTD
- Filing Date
- 2025-05-28
- Publication Date
- 2026-05-26
AI Technical Summary
Existing technologies reduce the drag of drones by adding fairings, but fairings do not generate lift and increase weight, thus limiting the range of drones.
The design of the drone's fuselage has been optimized, adopting a continuous and smooth curved wall structure to reduce drag and maintain space for internal components, thus avoiding adding extra weight.
By reducing airframe drag, the range of the drone can be increased, while maintaining lightweight design and stability, and enhancing airflow guidance.
Smart Images
Figure CN224277588U_ABST
Abstract
Description
Technical Field
[0001] This disclosure relates to the field of aircraft technology, specifically to a fuselage shell of a drone and the drone itself. Background Technology
[0002] Currently, drones have been widely used in various industries such as aerial photography, sports competitions, logistics and transportation, fire inspection, and security monitoring. As the low-altitude economy gradually prospers, there is an urgent need to improve the range of drones.
[0003] In related technologies, adding a fairing to the outside of a conventional frame fuselage can reduce the drag of a UAV. Although the fairing can reduce drag, it does not generate lift itself and has additional weight. Reducing drag helps increase range, while increasing the weight of the UAV does not increase range. Therefore, the contribution of this solution to increasing the range of UAVs is debatable. Utility Model Content
[0004] The purpose of this disclosure is to provide a fuselage shell for a drone and the drone itself, which optimizes the fuselage shell to reduce drag, thereby at least partially solving the aforementioned technical problems.
[0005] To achieve the above objectives, according to a first aspect of this disclosure, a fuselage shell for an unmanned aerial vehicle (UAV) is provided, including a housing for enclosing a space for accommodating internal components of the UAV. The housing includes a bottom wall and a front wall, a transition wall, and a main body wall sequentially disposed on the bottom wall from front to back along the longitudinal direction of the UAV.
[0006] The orthographic projection area of the front wall along the front-back direction is the first projection area, and the orthographic projection area of the area enclosed by the first connecting line at the connection between the transition wall and the main wall and the bottom wall along the front-back direction is the second projection area.
[0007] The first projection area is completely located within the second projection area, and the transition wall is a continuous smooth curved wall extending backward from the front end wall.
[0008] Optionally, the ratio of the area of the first projection area to the area of the second projection area is 0.25 to 0.8.
[0009] Optionally, along the front-rear direction of the UAV, the length of the transition wall is a first length, the length of the main body wall is a second length, and the ratio of the first length to the second length is 0.25 to 1.
[0010] Optionally, the main body wall includes a top wall, and the top wall forms a first flow guide structure at each end along the left and right directions of the UAV, and the two first flow guide structures extend obliquely from front to back.
[0011] Optionally, the top wall includes a middle top wall surface and side top wall surfaces located on both sides of the middle top wall surface along the left-right direction. The side top wall surfaces are recessed downward in the height direction of the UAV into the middle top wall surface to form the first flow guiding structure.
[0012] Optionally, the main body wall further includes two side walls located on both sides of the top wall in the left-right direction, and the side walls and the transition wall form a transition flow guiding structure connected to the front end of the corresponding first flow guiding structure.
[0013] Optionally, in the left-right direction, the sidewall protrudes beyond the transition wall to form the transition flow guide structure between them.
[0014] Optionally, the middle top wall surface of the top wall extends smoothly from the middle position in the left-right direction to both sides and downwards in a curve.
[0015] Optionally, the front end wall and the transition wall are connected by a rounded corner; and / or,
[0016] The edge contour line at the connection between the front end wall and the transition wall is curved.
[0017] According to a second aspect of this disclosure, a drone is provided, including the fuselage shell of the aforementioned drone.
[0018] The above technical solution optimizes the shape of the shell to reduce the airframe drag and increase the range of the UAV. The bottom wall, front wall, transition wall and main wall of the shell form a space suitable for accommodating the internal components of the airframe. The first projection area is completely located within the second projection area. The transition wall extends from the front wall to the main wall and is constructed as a continuous and smooth curved wall. This makes the area of the shell's orthographic projection area along the forward and backward direction of the UAV gradually increase from front to back, thereby making the shell shape more rounded, which is suitable for guiding airflow during flight, reducing airframe drag and increasing the range of the UAV.
[0019] Other features and advantages of this disclosure will be described in detail in the following detailed description section. Attached Figure Description
[0020] The accompanying drawings are provided to further illustrate the present disclosure and form part of the specification. They are used together with the following detailed description to explain the present disclosure, but do not constitute a limitation thereof. In the drawings:
[0021] Figure 1 This is a schematic diagram of the overall structure of the UAV provided in an exemplary embodiment of this disclosure;
[0022] Figure 2This is a schematic diagram of the structure of the housing provided in an exemplary embodiment of this disclosure;
[0023] Figure 3 This is a front view of the housing provided in an exemplary embodiment of this disclosure;
[0024] Figure 4 This is a side view of the housing provided in an exemplary embodiment of this disclosure.
[0025] Explanation of reference numerals in the attached figures
[0026] 100. Drones;
[0027] 10. Shell;
[0028] 1. Bottom wall; 2. Front wall; 3. Transition wall; 4. Main wall; 41. Top wall; 411. Middle top wall surface; 412. Edge top wall surface; 42. Side wall; 5. First guide structure; 6. Transition guide structure;
[0029] a, First projection area; b, Second projection area; m, First connecting line; n, Edge contour line; L1, First length; L2, Second length. Detailed Implementation
[0030] The specific embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.
[0031] In this disclosure, unless otherwise stated, "inner" and "outer" refer to the interior and exterior of the outline of the corresponding component; "far" and "near" refer to the distance of the corresponding component relative to another component in terms of spatial position. Furthermore, the terms "first," "second," etc., used in this disclosure are for distinguishing one element from another and do not have sequential or importance. When the following description relates to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements.
[0032] The inventors discovered through research that adding a fairing to the outside of a conventional frame fuselage can reduce the drag of a drone. Although the fairing can reduce drag, it does not generate lift itself and has additional weight. Reducing drag helps increase range, while increasing the weight of the drone does not increase range. Therefore, the contribution of this solution to increasing the range of drones is debatable.
[0033] To solve the aforementioned technical problems, in accordance with the first aspect of this disclosure, reference is made to... Figures 1 to 4As shown, this disclosure provides a fuselage shell for a drone 100, including a shell 10. The shell 10 is used to enclose a space for accommodating the internal components of the drone 100. The shell 10 includes a bottom wall 1 and a front wall 2, a transition wall 3, and a main body wall 4, which are sequentially arranged on the bottom wall 1 from front to back along the front-rear direction (or the longitudinal axis direction of the drone). The orthographic projection area of the front wall 2 along the front-rear direction is a first projection area a. The orthographic projection area of the area enclosed by the first connecting line m at the connection between the transition wall 3 and the main body wall 4 and the bottom wall 1 along the front-rear direction is a second projection area b. The first projection area a is completely located within the second projection area b. The transition wall 3 is a continuous smooth curved surface wall extending from the front wall 2 to the rear.
[0034] The above technical solution optimizes the shape of the shell 10 to reduce the airframe drag of the UAV 100 and increase its range. The bottom wall 1, front wall 2, transition wall 3, and main wall 4 of the shell 10 form a space suitable for accommodating internal components. The first projection area a is completely located within the second projection area b, meaning the area of the first projection area a is smaller than the area of the second projection area b. The transition wall 3 extends from the front wall 2 to the main wall 4 and is constructed as a continuous, smooth curved wall. This makes the area of the orthographic projection area of the shell 10 along the front-rear direction of the UAV 100 gradually increase from front to back, thereby making the shell 10 more rounded, suitable for guiding airflow during flight, reducing airframe drag, and increasing the range of the UAV 100.
[0035] It is understood that the internal components of the fuselage include components such as controllers and sensors that can be installed inside the housing 10. The bottom wall 1, front wall 2, transition wall 3 and main body wall 4 of the housing 10 can form a space to accommodate the aforementioned components.
[0036] In addition, this disclosure optimizes the shape of the housing 10 that houses the internal components of the fuselage, eliminating the need for a fairing as in related technologies. Thus, without adding extra weight, the range of the UAV can obviously be increased by optimizing the housing 10 to reduce drag.
[0037] In addition, by designing the transition wall 3 as a continuous smooth curved wall extending from the front wall 2 to the main body wall 4, the installation space requirements of the internal components can be guaranteed. The front wall 2 is designed at the front end of the housing 10, which can reduce the unnecessary internal space at the front of the housing body and reduce the weight of the housing 10.
[0038] In some embodiments, the ratio of the area of the first projection area a to the area of the second projection area b can be 0.25 to 0.8. In this way, the weight of the housing 10 can be reasonably reduced while meeting the installation space requirements of the internal components and achieving the required drag reduction effect.
[0039] Furthermore, the inventors discovered through research that, given a fixed length of the main body wall 4, the length of the transition wall 3 needs to be maintained within a reasonable range to balance drag reduction requirements and fuselage weight requirements. Therefore, in some embodiments, referring to... Figure 4 As shown, along the front-rear direction of the UAV 100, the length of the transition wall 3 is the first length L1, and the length of the main body wall 4 is the second length L2. The ratio of the first length L1 to the second length L2 is 0.25~1. In this way, while meeting the installation space requirements of the internal components, the length of the transition wall 3 of the shell 10 in the front-rear direction of the UAV 100 can be guaranteed to better guide the airflow, optimize the flow separation during the flight of the UAV 100, and thus improve the range of the UAV 100.
[0040] In some embodiments, reference Figures 2 to 4 As shown, the main body wall 4 includes a top wall 41. The top wall 41 can form a first flow guide structure 5 at both ends along the left and right directions of the UAV 100. The two first flow guide structures 5 extend obliquely from front to back, so that the first flow guide structure 5 can guide the air on the top wall 41 from front to back during the flight of the UAV 100, thereby reducing resistance and increasing the range of the UAV 100.
[0041] The two first airflow guiding structures 5 can be symmetrically arranged on the left and right sides of the drone 100 about its longitudinal axis to ensure the stability of the drone 100 during flight. In addition, the first airflow guiding structures 5 can also improve the aesthetics of the shell 10.
[0042] It is understood that the first flow guiding structure 5 can be formed in any suitable manner; in some embodiments, reference is made to... Figure 2 and Figure 3 As shown, the top wall 41 includes a central top wall surface 411 and side top wall surfaces 412 located on both sides of the central top wall surface 411 in the left-right direction. The side top wall surfaces 412 are recessed downwards into the central top wall surface 411 in the height direction of the UAV 100 to form a first airflow guiding structure 5. Thus, the first airflow guiding structure 5 can be formed by optimizing the shape of the top wall 41 of the housing 10 itself. The first airflow guiding structure 5 can be a groove formed on both sides of the top wall 41 in the left-right direction. In the front-back direction, the two side top wall surfaces 412 extend closer to each other on the side near the central top wall surface 411, so that airflow can be guided through the gradually increasing groove structure.
[0043] In addition, refer to Figure 2 As shown, a portion of the top wall 41 extends from the transition wall 3 to the first flow guiding structure 5. This portion of the top wall 41 conforms to the smooth curved surface of the transition wall 3, so as to have a rounded shape, while facilitating the smooth connection between the transition wall 3 and the first flow guiding structure 5, which is suitable for guiding airflow and reducing resistance.
[0044] In some embodiments, reference Figures 2 to 4 As shown, the main body wall 4 also includes two side walls 42 located on both sides of the top wall 41 in the left-right direction. A transition flow guiding structure 6 can be formed between the side walls 42 and the transition wall 3, connecting to the front end of the corresponding first flow guiding structure 5. It can be understood that the side walls 42 extend in the height direction to cooperate with the top wall 41 to enclose a space for installing internal components. In the left-right direction, the side walls 42 protrude from the transition wall 3. Therefore, the transition flow guiding structure 6 is formed between the side walls 42 and the transition wall 3 to cooperate with the first flow guiding structure 5 to guide the air flow from front to back.
[0045] For example, refer to Figures 2 to 4 As shown, in the left-right direction, the sidewall 42 protrudes outward from the transition wall 3 to form a transition guide structure 6 between the two. This transition guide structure 6 is constructed to extend smoothly in a curved manner from bottom to top and from front to back, so as to smoothly connect the first guide structure 5. In addition, the transition guide structure 6 can extend further between the first guide structure 5 and the sidewall 42 to further improve the air guiding effect.
[0046] In some embodiments, reference Figure 2 and Figure 3 As shown, the middle top wall surface 411 of the top wall 41 extends smoothly from the middle position in the left-right direction to both sides and downwards in a curve. The middle top wall surface 411 gradually decreases in height from the middle to both sides until it connects to the side top wall surface 412. The middle top wall surface 411 is a continuous smooth curved surface to facilitate airflow on both sides.
[0047] In some embodiments, reference Figures 2 to 4 As shown, the front wall 2 and the transition wall 3 can be connected by rounded corners, thus achieving a smooth connection and reducing resistance. It can be understood that the middle top wall surface 411 and the side top wall surface 412 of the top wall 41 can also be connected by rounded corners, as can the side wall 42 and the first flow guide structure 5, and the side wall 42 and the transition wall 3. The transition flow guide structure 6 can be constructed as a rounded corner connection surface / wall between the side wall 42 and the transition wall 3.
[0048] In some embodiments, reference Figures 2 to 4 As shown, the edge contour line n at the connection between the front wall 2 and the transition wall 3 is curved. In this way, compared with the case in the related art where the edge contour of the front wall 2 is rectangular or polygonal, the edge contour line n of the front wall 2 provided in this disclosure can reduce the occurrence of corners, making the edge contour line n more rounded. This allows the transition wall 3 arranged along the edge contour line n to be designed for a smooth transition, reducing surface pressure and making airflow smoother.
[0049] According to a second aspect of this disclosure, a drone 100 is provided, including the aforementioned fuselage shell. The drone 100 possesses all the beneficial effects of the aforementioned fuselage shell, which will not be elaborated further herein. Furthermore, the drone 100 may be, for example, a multi-rotor drone or a fixed-wing drone, etc., and this disclosure does not specifically limit it in this regard.
[0050] The preferred embodiments of this disclosure have been described in detail above with reference to the accompanying drawings. However, this disclosure is not limited to the specific details of the above embodiments. Within the scope of the technical concept of this disclosure, various simple modifications can be made to the technical solutions of this disclosure, and these simple modifications all fall within the protection scope of this disclosure.
[0051] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. In order to avoid unnecessary repetition, this disclosure will not describe the various possible combinations separately.
[0052] Furthermore, various different embodiments of this disclosure can be combined in any way, as long as they do not violate the spirit of this disclosure, they should also be regarded as the content disclosed in this disclosure.
Claims
1. A fuselage shell for a drone, characterized in that, The device includes a housing for enclosing a space for housing internal components of the drone. The housing includes a bottom wall and a front wall, a transition wall, and a main wall that are sequentially disposed on the bottom wall from front to back along the front-rear direction of the drone. The orthographic projection area of the front wall along the front-back direction is the first projection area, and the orthographic projection area of the area enclosed by the first connecting line at the connection between the transition wall and the main wall and the bottom wall along the front-back direction is the second projection area. The first projection area is completely located within the second projection area, and the transition wall is a continuous smooth curved wall extending backward from the front end wall.
2. The fuselage casing according to claim 1, characterized in that, The ratio of the area of the first projection area to the area of the second projection area is 0.25 to 0.
8.
3. The fuselage casing according to claim 1, characterized in that, Along the front-rear direction of the drone, the length of the transition wall is a first length, the length of the main body wall is a second length, and the ratio of the first length to the second length is 0.25~1.
4. The fuselage casing according to claim 1, characterized in that, The main body wall includes a top wall, and the top wall forms a first flow guide structure at each end along the left and right directions of the UAV. The two first flow guide structures extend obliquely from front to back, gradually converging.
5. The fuselage casing according to claim 4, characterized in that, The top wall includes a middle top wall surface and side top wall surfaces located on both sides of the middle top wall surface along the left-right direction. The side top wall surfaces are recessed downward in the height direction of the UAV into the middle top wall surface to form the first flow guiding structure.
6. The fuselage casing according to claim 5, characterized in that, The main body wall also includes two side walls located on both sides of the top wall in the left-right direction, and a transition flow guiding structure is formed between the side walls and the transition wall, which is connected to the front end of the corresponding first flow guiding structure.
7. The fuselage casing according to claim 6, characterized in that, In the left-right direction, the sidewall protrudes outward from the transition wall to form the transition flow guiding structure between them.
8. The fuselage casing according to claim 4, characterized in that, The middle top wall surface extends smoothly from the middle position in the left-right direction to both sides and downwards in a curve.
9. The fuselage casing according to claim 1, characterized in that, The front end wall and the transition wall are connected by a rounded corner transition; and / or, The edge contour line at the connection between the front end wall and the transition wall is curved.
10. A drone, characterized in that, Includes the fuselage shell of the drone as described in any one of claims 1-9.