Lift wing unmanned aerial vehicle
By designing a blended wing-body lifting wing UAV, which combines the structure of fuselage, wings, struts, and propellers, the UAV achieves high payload capacity and stable flight, solving the problem of insufficient cargo loading capacity of existing UAVs and improving freight efficiency.
Patent Information
- Application Number
- CN202520031089.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-06
- Publication Date
- 2026-02-03
- Estimated Expiration
- 2035-01-06
AI Technical Summary
Existing blended wing-body drones are unable to carry as much cargo as possible in freight applications, resulting in insufficient loading capacity.
The design incorporates a blended wing-body lifting wing drone, comprising a fuselage, wings, struts, and propellers. The blended fuselage and wings provide lift, the underside of the fuselage has a first cargo compartment with an aspect ratio between 1:1 and 2:1, the back has second and third compartments for batteries and flight control systems, the propellers provide vertical takeoff and landing and cruise power, and the struts provide stable landing.
It improves the drone's cargo loading capacity and flight stability, increases payload capacity and flight range, and ensures the safety and flexibility of the flight process.
Smart Images
Figure CN223865113U_ABST
Abstract
Description
Technical Field
[0001] This disclosure relates to a lifting wing unmanned aerial vehicle (UAV), and more specifically, to a blended wing-body lifting wing UAV. Background Technology
[0002] Blended wing-body drones, where the wings and fuselage are integrated into one unit, generate greater lift while reducing drag, thus improving payload capacity and flight range. However, in certain drone applications, especially for cargo drones, there is a desire to carry as much cargo as possible.
[0003] Therefore, it is hoped that a lifting wing UAV can be proposed to further improve its cargo loading capacity. Utility Model Content
[0004] To address the aforementioned problems, this disclosure proposes a lifting-wing unmanned aerial vehicle (UAV), comprising: a blended wing-body fuselage and two wings, the two wings being located on opposite sides of the fuselage, the wings being shaped to provide lift to the lifting-wing UAV; two struts, having a rod-like shape and extending through the respective wings; and a propeller mounted to the end of each strut. The lifting-wing UAV includes a lower belly with a first accommodating space for loading and accommodating cargo. The aspect ratio of the lifting-wing UAV is between 1:1 and 2:1, where the aspect ratio is the ratio of the lateral dimension to the longitudinal dimension of the lifting-wing UAV.
[0005] For example, according to some embodiments of this disclosure, the back of the lifting wing UAV has a second housing space, within which the battery is located.
[0006] For example, according to some embodiments of this disclosure, the second containment space is larger than the battery to allow the battery to change its fixed position in the second containment space to adjust the center of gravity of the drone according to the cargo in the first containment space.
[0007] For example, according to some embodiments of this disclosure, two second accommodating spaces are symmetrically arranged on both sides of the lifting wing UAV.
[0008] For example, according to some embodiments of this disclosure, the back of the lifting wing UAV has a third accommodating space for accommodating the flight control system.
[0009] For example, according to some embodiments of this disclosure, the two second receiving spaces are spaced apart in the lateral direction, and the second receiving space and the third receiving space are spaced apart in the longitudinal direction.
[0010] For example, according to some embodiments of this disclosure, the second accommodating space is located in front of the third accommodating space in the longitudinal direction.
[0011] For example, according to some embodiments of this disclosure, the second receiving space has an elongated and flat shape, with its dimension in the longitudinal direction being greater than its dimension in the transverse direction, and its dimension in the transverse direction being greater than its dimension in the height direction.
[0012] For example, according to some embodiments of this disclosure, the ratio of the lateral dimension of the first receiving cavity to the lateral dimension of the lifting wing UAV is between 0.2 and 0.25, and the ratio of the longitudinal dimension of the first receiving cavity to the longitudinal dimension of the lifting wing UAV is between 0.32 and 0.4.
[0013] For example, according to some embodiments of this disclosure, the first accommodating space includes a pivotally openable hatch. Attached Figure Description
[0014] Figure 1 A schematic diagram of a lifting wing unmanned aerial vehicle according to an embodiment of the present invention is shown, wherein the canopy is closed;
[0015] Figure 2 It shows Figure 1 A schematic diagram of the canopy of a lifting wing unmanned aerial vehicle when it is open;
[0016] Figure 3 A schematic diagram from another perspective of a lifting wing unmanned aerial vehicle according to an embodiment of the present invention is shown;
[0017] Figure 4 A schematic diagram of the back of a lifting wing unmanned aerial vehicle according to an embodiment of the present invention is shown.
[0018] Figure Labels
[0019] 100 Lift Wing UAV
[0020] 110 fuselage
[0021] 120 Wing
[0022] 130 support rod
[0023] 140 propeller
[0024] 140-U upper propeller
[0025] 140-L Lower Propeller
[0026] 142 Rotation axis
[0027] 150 support components
[0028] 21 hatch cover
[0029] S1 First Accommodation Space
[0030] S2 Second Accommodation Space
[0031] S3 Third Accommodation Space Detailed Implementation
[0032] To make the objectives, solutions, and advantages 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. Unless otherwise stated, the terms used herein have their ordinary meanings in the art. The same reference numerals in the drawings represent the same parts.
[0033] For clarity, unless otherwise explicitly stated, the directional terms used herein have the following meanings: longitudinal direction refers to the direction parallel to the direction of flight of the UAV; lateral direction is perpendicular to the longitudinal direction and parallel to the wing plane; altitude direction is perpendicular to both the longitudinal and lateral directions; and when the UAV is in cruise mode, the wing plane is parallel to the ground.
[0034] Figure 1 A schematic diagram of a lifting-wing unmanned aerial vehicle (UAV) 100 according to an embodiment of the present invention is shown. The lifting-wing UAV 100 is a UAV that relies on both propellers and wings for lift. In this document, the lifting-wing UAV 100 can also be simply referred to as UAV 100. The UAV 100 mainly includes a fuselage 110, two wings 120, two struts 130, and multiple propellers 140.
[0035] The fuselage 110 is located in the middle of the drone 100, and the two wings 120 are located on the left and right sides of the fuselage 110 respectively. The shape of the wings 120 is designed to provide lift to the drone 100. The fuselage 110 and the wings 120 are integrated together in a blended wing-body manner, and there is no obvious boundary between the fuselage 110 and the wings 120.
[0036] Two struts 130 have a rod-like shape and extend through the corresponding wings 120. Multiple propellers 140 are mounted to the ends of the corresponding struts 130. For example, the plane of rotation of the propellers 140 may be parallel to the support rod 161. For instance, propellers 140 are mounted at the left front, right front, left rear, and right rear of the UAV 100 so that the point of application of the lift generated by the propellers 140 is close to the center of gravity of the UAV 100, thereby increasing the stability of the UAV 100 during flight.
[0037] Furthermore, the angle between the strut 130 and the wing plane is designed to be between 25° and 35°, more specifically, the angle between the strut 130 and the wing plane can be designed to be approximately 30°. An angle of approximately 30° between the strut 130 and the wing plane means that when the UAV 100 is flying in cruise mode, the strut 130 forms an angle of approximately 30° with the ground. With the rotation plane of the propeller 140 parallel to the extension direction of the strut 130, the angle between the rotation plane of the propeller 140 and the ground is approximately 30°, resulting in the direction of the power provided by the propeller 140 to the UAV 100 forming an angle of approximately 30° with the ground. The components of this power parallel to the wing plane and perpendicular to the wing plane determine the flight speed and payload capacity.
[0038] Two propellers can be mounted at one end of the support rod, namely, an upper propeller 140-U and a lower propeller 140-L can be installed at one end of the support rod 130, and the planes of rotation of the upper propeller 140-U and the lower propeller 140-L are parallel to each other; in particular, all propellers 140 are parallel. When the UAV 100 is in take-off and landing mode, the upper propeller 140-U and the lower propeller 140-L are located above and below the support rod, respectively. The upper propeller 140-U and the lower propeller 140-L can simultaneously provide the UAV 100 with upward lift and / or forward thrust, further improving the flight speed and / or payload capacity of the UAV 100. It should be understood that the aforementioned arrangement of the pair of propellers 140-U and 140-L can be simultaneously arranged at the left front, right front, left rear, and right rear of the UAV 100.
[0039] Furthermore, such as Figure 3 As shown, each propeller 140 can be driven by an independent motor 143, enabling individual control of each propeller 140, which facilitates flight control of the UAV 100.
[0040] Preferably, the wing 120 may include control surfaces (not shown) located at the trailing edge of the wing 120. By changing the angle of the control surfaces, precise control of the flight attitude of the UAV 100 can be achieved, ensuring flight safety and stability.
[0041] Furthermore, the drone 100 may include a lower abdomen, which may have a first receiving space S1, such as... Figure 2 and 3 As shown, it is used to load and accommodate goods. In order to enable the transfer of more goods, the first accommodating space S1 needs to be as large as possible.
[0042] Therefore, the aspect ratio of the UAV 100 can be set between 1:1 and 2:1, where the aspect ratio is the ratio of the UAV 100's dimension in the lateral direction to its dimension in the longitudinal direction. More preferably, the aspect ratio of the UAV 100 can be between 1:1 and 1.2:1. For example, the UAV 100's dimension in the lateral direction can be approximately 1.6m, and its dimension in the longitudinal direction can be approximately 1.5m, resulting in an aspect ratio of approximately 1.07. By designing a smaller aspect ratio for the UAV 100, the characteristics of a blended wing-body lifting body are achieved, thereby increasing the first accommodating space S1.
[0043] Furthermore, the drone 100 may also include an upper back, such as Figure 4 As shown, the back can have a second accommodating space S2, and the battery can be placed in the second accommodating space S2. By placing the second accommodating space S2 and the first accommodating space S1 on the abdomen and back respectively, the second accommodating space S2 is separated from the first accommodating space S1, which optimizes the spatial layout and can further increase the size of the first accommodating space S1.
[0044] In particular, the second accommodating space S2 can be configured to have a volume larger than the battery to allow the battery to change its fixed position within the second accommodating space. Thus, the fixed position of the battery can be changed according to the weight and / or stacking shape of the cargo within the first accommodating space, which adjusts the center of gravity of the drone 100, specifically aligning the center of gravity of the drone 100 with that of the first accommodating space S1, which is beneficial for flight stability.
[0045] like Figure 4 As shown, the second accommodating space S2 can be set to two, and these two second accommodating spaces S2 can be symmetrically arranged on both sides of the UAV 100, which further optimizes the spatial layout and can further increase the first accommodating space S1.
[0046] Furthermore, the second accommodating space S2 can also be configured as a long and flat shape, such as... Figure 4 As shown. Specifically, the second receiving space S2 has a larger dimension in the longitudinal direction than in the lateral direction, and the lateral dimension can be larger than the dimension in the height direction. This allows for as much space as possible to be provided for the first receiving space S1 in the height direction, and the battery can be adjusted and fixed in the second receiving space S2 in the longitudinal direction to change the aircraft's center of gravity.
[0047] The back of the drone 100 can also be equipped with a third storage space S3, such as... Figure 4As shown. The third accommodating space S3 can, for example, accommodate a flight control system. In particular, the two second accommodating spaces S2 can be spaced apart in the lateral direction, and the second accommodating space S2 and the third accommodating space S3 can be spaced apart in the longitudinal direction. The spatial layout is further optimized, and the first accommodating space S1 can be further increased.
[0048] Furthermore, the third accommodating space S3 can be positioned close to the tail of the UAV, so that the second accommodating space is located in front of the third accommodating space in the longitudinal direction. This further optimizes the spatial layout and can further increase the size of the first accommodating space S1.
[0049] Therefore, the ratio of the lateral dimension of the first receiving cavity S1 to the lateral dimension of the lifting wing UAV 100 can be between 0.2 and 0.25, and the ratio of the longitudinal dimension of the first receiving cavity S1 to the longitudinal dimension of the lifting wing UAV 100 can be between 0.32 and 0.4.
[0050] like Figure 2 and Figure 3 As shown, the first accommodating space S1 may include a hatch, thereby facilitating the loading and unloading of cargo. In particular, the hatch has a streamlined design, and when closed, the drone has a fully sealed, streamlined shell, which is beneficial for the drone's flight. Furthermore, the hatch may be pivotable to facilitate the rapid opening and closing of the first accommodating space S1; particularly, the hatch can be electrically controlled to save manpower and facilitate use.
[0051] Preferably, such as Figure 2 As shown, the drone 100 may also include two support members 150, which are respectively fixed to corresponding struts 130 on the front side of the fuselage 110. When the drone 100 lands, the two support members 150 and the tail of the fuselage 110 jointly support the ground. In other words, the two support members 150 and the tail of the fuselage 110 form a relatively stable three-point support for the drone 100, which plays a role similar to the landing gear of an aircraft.
[0052] The following describes the general flight process of the UAV 100:
[0053] (1) Take off vertically from the ground
[0054] When the drone 100 is placed on the ground, the plane of rotation of the propeller 140 is parallel to the ground, and the nose of the drone 100 is raised relative to the ground. The support 150 is perpendicular to the ground, and its lower end is in contact with the ground. Activating the control system of the drone 100 causes the propeller 140 to rotate, thereby providing the drone 100 with vertical upward lift. Under the lift provided by the propeller 140, the drone 100 takes off vertically from the ground.
[0055] (2) Cruise in the air
[0056] Once the drone 100 takes off vertically from the ground and reaches a certain altitude, it can switch from takeoff mode to cruise mode to fly towards its destination. Specifically, the drone 100's flight attitude is adjusted so that its nose is tilted downwards until it is approximately parallel to the ground. In this state, the strut 130 is no longer parallel to the ground but at a certain angle, causing the rotor plane of the propeller 140 to also be at an angle to the ground. This orientation of the propeller 140 allows it to simultaneously provide forward thrust and upward lift to the drone 100. At the same time, as the drone 100 flies forward, the wing 120 also provides upward lift, further increasing the drone 100's payload capacity.
[0057] (3) Descending vertically to the ground
[0058] When the drone 100 reaches its destination, it can switch from cruise mode to landing mode to complete the landing process. Specifically, the drone 100's flight attitude is adjusted so that its nose is raised until the plane of rotation of the propeller 140 is approximately parallel to the ground. In this state, the propeller 140 no longer provides forward thrust to the drone 100, but only upward lift, which facilitates a vertical landing. In this attitude, the lower ends of the two support members 150 and the tail of the fuselage 110 are on the same horizontal plane, ensuring that these three points simultaneously contact the ground, providing three-point support for the drone 100 and enabling a smooth landing.
[0059] This document describes in detail several exemplary embodiments of the present invention with reference to preferred embodiments. However, those skilled in the art will understand that various modifications and alterations can be made to the above specific embodiments without departing from the concept of the present invention, and various technical features and structures proposed in the present invention can be combined without exceeding the protection scope of the present invention, which is determined by the appended claims.
Claims
1. A lifting-wing unmanned aerial vehicle, characterized in that, include: The fuselage is a blended wing-body structure with two wings, which are located on either side of the fuselage. The wings are designed to provide lift to the lifting wing UAV. Two struts, each having a rod-like shape, extend through the corresponding wing; A propeller is mounted to the end of the support rod; The lifting wing UAV includes a lower abdomen with a first accommodating space for loading and accommodating cargo. The aspect ratio of the lifting wing UAV is between 1:1 and 2:1, where the aspect ratio is the ratio of the lateral dimension of the lifting wing UAV to its longitudinal dimension.
2. The lifting wing UAV according to claim 1, characterized in that, The lifting wing UAV has a second housing space on its back, and the battery is located in the second housing space.
3. The lifting wing UAV according to claim 2, characterized in that, The second containment space is larger than the battery to allow the battery to move in a fixed position within the second containment space to adjust the drone's center of gravity according to the cargo in the first containment space.
4. The lifting wing UAV according to claim 2, characterized in that, The two second containment spaces are symmetrically arranged on both sides of the lifting wing UAV.
5. The lifting wing UAV according to claim 4, characterized in that, The lifting wing UAV has a third storage space on its back to house the flight control system.
6. The lifting wing UAV according to claim 5, characterized in that, The two second accommodating spaces are spaced apart in the lateral direction, and the second accommodating space and the third accommodating space are spaced apart in the longitudinal direction.
7. The lifting wing UAV according to claim 5, characterized in that, The second accommodating space is located in front of the third accommodating space in the longitudinal direction.
8. The lifting wing UAV according to claim 4, characterized in that, The second accommodating space has an elongated and flat shape, with its dimension in the longitudinal direction being greater than its dimension in the transverse direction, and its dimension in the transverse direction being greater than its dimension in the height direction.
9. The lifting wing UAV according to claim 1, characterized in that, The ratio of the lateral dimension of the first receiving cavity to the lateral dimension of the lifting wing UAV is between 0.2 and 0.25, and the ratio of the longitudinal dimension of the first receiving cavity to the longitudinal dimension of the lifting wing UAV is between 0.32 and 0.
4.
10. The lifting wing UAV according to claim 1, characterized in that, The first accommodating space includes a pivotally openable hatch.