Lift wing unmanned aerial vehicle
By designing a strut with a specific angle on the drone and combining it with the propeller tilt angle and aspect ratio, the problem of insufficient payload of blended wing-body drones is solved, achieving higher payload capacity and stability, and supporting flexible flight mode switching.
Patent Information
- Application Number
- CN202520027657.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-06
- Publication Date
- 2026-01-16
- Estimated Expiration
- 2035-01-06
AI Technical Summary
Existing blended wing-body drones have insufficient payload capacity for certain applications, making it difficult to further improve it.
The design incorporates an angle between the strut and the wing plane of 25° to 35°. The propeller is configured to provide power and lift by tilting in cruise mode and by providing lift in parallel during takeoff and landing. Combined with a low aspect ratio and swept-back design, pitch stability is enhanced, and precise control is achieved through control surfaces.
It improves the flight range and payload capacity of drones, enhances flight stability and safety, and enables flexible flight mode switching.
Smart Images
Figure CN223803805U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to a lift wing unmanned plane more specifically, relate to a wing body fusion lift wing unmanned plane. BACKGROUND
[0002] The wing body fusion unmanned plane with the wing and the fuselage integrated into one makes the body be able to generate greater lift while the resistance is reduced, thereby improving the load capacity and flight range of the unmanned plane. But in some application requirements of the unmanned plane, it is expected to further improve the load capacity of the unmanned plane.
[0003] Therefore, it is expected to propose a lift wing unmanned plane to further improve its load capacity. SUMMARY
[0004] According to an aspect of the utility model, a kind of lift wing unmanned plane is provided, comprising: wing body fusion fuselage and two wings, two wings are located at the two sides of fuselage respectively, the shape of wing is designed to provide lift for lift wing unmanned plane;Two struts, with rod shape and extend through corresponding wing respectively;Screw propeller, installed to the end of strut;Wherein, the included angle between strut and wing surface plane is between 25 ° and 35 °.
[0005] According to the scheme, the included angle between strut and wing surface plane is between 25 ° and 35 ° means that when unmanned plane flies in cruising mode, the included angle between the paddle plane of screw propeller and ground is between 25 ° and 35 °, which is particularly advantageous for improving the power (forward) and lifting force (upward) of unmanned plane simultaneously.
[0006] In some schemes, lift wing unmanned plane can be configured to operate at least in cruising mode and take-off and landing mode, when lift wing unmanned plane is in cruising mode, wing surface plane is parallel to ground, when lift wing unmanned plane is in take-off and landing mode, the paddle plane of screw propeller is parallel to ground.
[0007] According to the scheme, when unmanned plane is in cruising mode, the paddle plane of screw propeller is inclined to ground, so that the lift of screw propeller to unmanned plane has both forward power component and upward lifting force component, thereby correspondingly improving the flight range of unmanned plane and the load capacity of unmanned plane. When unmanned plane is in take-off and landing mode, unmanned plane no longer needs forward power component, so the paddle plane of screw propeller is parallel to ground, so that screw propeller only provides upward lifting force component to unmanned plane.
[0008] In some schemes, the included angle between strut and wing surface plane can be 30 °.
[0009] In some embodiments, the aspect ratio of the lift wing unmanned aerial vehicle can be between 1:1 and 2:1, the aspect ratio being the ratio of the dimension of the lift wing unmanned aerial vehicle along the transverse direction to the dimension of the lift wing unmanned aerial vehicle along the longitudinal direction.
[0010] According to the embodiment, the aspect ratio of the unmanned aerial vehicle is designed to be small, so as to achieve the characteristics of the blended wing body.
[0011] In some embodiments, the aspect ratio of the lift wing unmanned aerial vehicle can be between 1:1 and 1.2:1.
[0012] In some embodiments, the wing can include a swept back portion extending outwardly along the transverse direction and rearwardly along the longitudinal direction.
[0013] According to the embodiment, the swept back portion of the wing can function as a horizontal tail to some extent, thereby improving the pitch stability of the unmanned aerial vehicle.
[0014] In some embodiments, the lift wing unmanned aerial vehicle can further include two supports fixed to the corresponding struts at the front side of the fuselage, and the two supports and the tail of the fuselage jointly support the ground when the lift wing unmanned aerial vehicle lands.
[0015] In some embodiments, the two propellers are installed at one end of the strut, and the two propellers are located above and below the strut respectively when the lift wing unmanned aerial vehicle is in the take-off and landing mode.
[0016] According to the embodiment, the two propellers can simultaneously provide upward lifting force and / or forward power to the unmanned aerial vehicle, further improving the flight range and / or load capacity of the unmanned aerial vehicle.
[0017] In some embodiments, the wing can include a control surface located at the trailing edge of the wing.
[0018] According to the embodiment, by changing the angle of the control surface, precise control of the flight attitude of the unmanned aerial vehicle can be achieved, ensuring the safety and stability of the flight.
[0019] In some embodiments, the belly of the lift wing unmanned aerial vehicle can have a first accommodation space, and the back of the lift wing unmanned aerial vehicle can have a second accommodation space, the cargo being located in the first accommodation space and the battery being located in the second accommodation space. BRIEF DESCRIPTION OF DRAWINGS
[0020] Figure 1 A schematic view of a lift wing unmanned aerial vehicle according to an embodiment of the present application is shown;
[0021] Figure 2 A schematic view of a lift wing unmanned aerial vehicle according to an embodiment of the present application is shown.
[0022] Reference signs
[0023] 100 lift wing UAV
[0024] 110 fuselage
[0025] 120 wing
[0026] 124 sweepback
[0027] 130 strut
[0028] 140 propeller
[0029] 140-U upper propeller
[0030] 140-L lower propeller
[0031] 142 rotation shaft
[0032] 150 support
[0033] S1 first accommodation space
[0034] S2 second accommodation space DETAILED DESCRIPTION
[0035] In order to make the purpose, scheme and advantages of the technical scheme of the utility model clearer, the technical scheme of the utility model embodiment will be described clearly and completely in the following with reference to the drawings of the specific embodiment of the utility model. Unless otherwise specified, the terms used herein have the usual meanings in the art. The same reference signs in the drawings represent the same components.
[0036] For a clearer description, unless otherwise explicitly stated, the orientation terms appearing in this text have the following meanings: the longitudinal direction refers to the direction parallel to the flight direction of the UAV, the transverse direction is perpendicular to the longitudinal direction and parallel to the wing plane, and the wing plane is parallel to the ground when the UAV is in the cruising mode.
[0037] Figure 1 A schematic diagram of a lift wing UAV 100 according to an embodiment of the utility model is shown, the lift wing UAV 100 is a UAV that relies on both propellers and wings to provide lift, and in this text the lift wing UAV 100 can also be referred to simply as the UAV 100. The UAV 100 mainly comprises a fuselage 110, two wings 120, two struts 130 and a plurality of propellers 140.
[0038] The fuselage 110 is located in the middle region of the UAV 100, and the two wings 120 are respectively located on the left and right sides of the fuselage 110. The wings 120 are designed in a shape capable of providing lift to the UAV 100. The fuselage 110 and the wings 120 are fused together in a wing-body fusion manner, and there is no obvious boundary between the fuselage 110 and the wings 120.
[0039] The two support rods 130 have a rod shape and respectively extend through the corresponding wings 120. A plurality of propellers 140 are installed at the end of the corresponding support rod 130. For example, the propellers 140 are installed at the front left, front right, rear left and rear right of the UAV 100, respectively, so that the action point 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. The rotation axis 142 of the propeller 140 can be perpendicular to the extension direction of the support rod 130, which means that the blade plane of the propeller 140 can be parallel to the extension direction of the support rod 130.
[0040] The UAV 100 can be configured to operate at least in a cruising mode and a take-off and landing mode. When the UAV 100 is in the cruising mode, the wing plane is parallel to the ground (i.e., the nose points to the horizontal direction, the left wing 120 and the right wing 120 are at the same horizontal height, and the UAV 100 is in a level flight state). When the UAV 100 is in the take-off and landing mode, the support rod 130 can be parallel to the ground. The support rod 130 is designed to be inclined to the wing plane, so that when the UAV 100 is in the cruising mode, the support rod 130 can be inclined to the ground, causing the blade plane of the propeller 140 to be inclined to the ground, so that the lift provided by the propeller 140 to the UAV 100 is inclined to the ground. The lift inclined to the ground has a forward dynamic component, thereby correspondingly increasing the flight range of the UAV 100 and reducing the power consumption of the UAV 100. At the same time, the lift inclined to the ground also has an upward lifting component, thereby correspondingly increasing the load capacity of the UAV 100. When the UAV 100 is in the take-off and landing mode (including the states of vertical take-off and vertical landing), the UAV 100 no longer needs the forward dynamic component, so the attitude of the UAV 100 is set so that the support rod 130 can be parallel to the ground, causing the blade plane of the propeller 140 to be parallel to the ground, so that the propeller 140 only provides an upward lift component to the UAV. It should be understood that although the above describes the process of the UAV 100 taking off and landing vertically to the ground, the present application does not intend to limit the take-off and landing attitude of the UAV 100, and the UAV 100 can also take off and land obliquely to the ground.
[0041] Specifically, the angle between the strut 130 and the wing plane is designed to be between 25° and 35°, and 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 can form an angle of approximately 30° with the ground, resulting in an angle of approximately 30° between the propeller plane of the propeller 140 and the ground, and causing the direction of the lift provided by the propeller 140 to the UAV 100 to form an angle of approximately 30° with the ground. Under certain commonly used airspeed conditions, this is particularly advantageous for simultaneously increasing the power (forward) and lift (upward) of the UAV 100.
[0042] Preferably, the aspect ratio of the UAV 100 can be 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.
[0043] Preferably, the wing 120 may include a swept portion 124, which extends outward in the lateral direction and backward in the longitudinal direction. The swept portion 124 of the wing 120 can function as a horizontal tail to a certain extent, thereby improving the pitch stability of the UAV 100 and preventing the nose of the UAV 100 from being excessively raised or lowered, thus increasing the safety of the UAV 100.
[0044] 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.
[0045] Preferably, the upper propeller 140-U and the lower propeller 140-L are mounted to one end of the strut 130, and when the UAV 100 is in the take-off mode, the upper propeller 140-U and the lower propeller 140-L are located above and below the strut 130, respectively. The upper propeller 140-U and the lower propeller 140-L can simultaneously provide the UAV 100 with upward lift and / or forward power, further improving the flight range and / or load capacity of the UAV 100. It should be understood that the above-mentioned pair of propellers 140-U, 140-L can be arranged at the front left, front right, back left and back right of the UAV 100 at the same time.
[0046] Preferably, the wing 120 can include a control surface (not shown) located at the trailing edge of the wing 120. By changing the angle of the control surface, precise control of the flight attitude of the UAV 100 can be achieved, ensuring the safety and stability of flight.
[0047] Optionally, the belly (lower part in the cruising mode) of the UAV 100 can have a first accommodation space S1, and the back (upper part in the cruising mode) of the UAV 100 can have a second accommodation space S2, the cargo can be loaded in the first accommodation space S1, and the battery and control system, etc. can be located in the second accommodation space S2.
[0048] The general flight process of the UAV 100 is described as follows:
[0049] (1) Vertical take-off from the ground
[0050] When the UAV 100 is placed on the ground, the plane of the propeller 140 can be parallel to the ground, at this time the nose of the UAV 100 is lifted upward relative to the ground. The support 150 is perpendicular to the ground, and its lower end is in contact with the ground. The control system of the UAV 100 is turned on, and the propeller 140 is rotated to provide the UAV 100 with vertical upward lift, and the UAV 100 is vertically taken off from the ground under the action of the lift provided by the propeller 140.
[0051] (2) Cruising in the air
[0052] After the UAV 100 is vertically taken off from the ground to a certain height, it can be switched from the take-off mode to the cruising mode to fly towards the destination. Specifically, the flight attitude of the UAV 100 is adjusted, and the nose of the UAV 100 is pressed downward until the nose is substantially parallel to the ground. In this case, the plane of the propeller 140 is inclined to the ground at an angle of about 30°, and the orientation of the propeller 140 enables the propeller 140 to simultaneously provide the UAV 100 with forward power and upward lift. At the same time, when the UAV 100 flies forward, the wing 120 can also provide the UAV 100 with upward lift, thereby further increasing the load capacity of the UAV 100.
[0053] (3) Vertical landing to the ground
[0054] When the UAV 100 flies over the destination, it can be switched from the cruising mode to the landing mode to complete the landing process. Specifically, the flight attitude of the UAV 100 is adjusted so that the nose of the UAV 100 is raised upward until the plane of the propeller 140 is substantially parallel to the ground. In this case, the propeller 140 no longer provides forward power to the UAV 100, but only provides upward lifting force, which is conducive to the vertical landing of the UAV 100. In this attitude of the UAV 100, the lower ends of the two supports 150 and the tail of the fuselage 110 are in the same horizontal plane, so that the three points of the lower ends of the two supports 150 and the tail of the fuselage contact the ground at the same time to provide three-point support for the UAV 100, so that the UAV 100 lands smoothly.
[0055] The various exemplary embodiments of the present application are described in detail herein with reference to the preferred embodiments, however, it is understood by those skilled in the art that various modifications and changes can be made to the above specific embodiments without departing from the concept of the present application, and various technical features and structures proposed by the present application can also be combined without exceeding the protection scope of the present application, and the protection scope of the present application is determined by the appended claims.
Claims
1. A lift wing drone, characterized by, Comprising: a fuselage and two wings, the two wings being located on two sides of the fuselage respectively, the wings being shaped to provide lift for the lift-wing UAV; two struts, having a rod shape and extending through the corresponding wings respectively; propellers, mounted to the end of the struts; wherein the angle between the struts and the wing plane is between 25° and 35°.
2. The lift wing drone of claim 1, wherein, The lift-wing UAV is configured to operate in at least a cruising mode and a take-off and landing mode, when the lift-wing UAV is in the cruising mode, the wing plane is parallel to the ground, when the lift-wing UAV is in the take-off and landing mode, the propeller plane is parallel to the ground.
3. The lift wing drone of claim 2, wherein, The angle between the struts and the wing plane is 30°.
4. The lift wing drone of claim 1, wherein, The lift-wing UAV has a span ratio between 1:1 and 2:1, the span ratio being the ratio of the size of the lift-wing UAV in the lateral direction to the size of the lift-wing UAV in the longitudinal direction.
5. The lift wing drone of claim 4, wherein, The lift-wing UAV has a span ratio between 1:1 and 1.2:
1.
6. The lift wing drone of claim 1, wherein, The wings include a sweepback portion, the sweepback portion extending outwardly in the lateral direction and rearwardly in the longitudinal direction.
7. The lift wing drone of claim 1, wherein, Further comprising two supports, the two supports being fixed to the corresponding struts at the front side of the fuselage respectively, the two supports and the tail of the fuselage collectively supporting on the ground when the lift-wing UAV lands.
8. The lift wing drone of claim 1, wherein, Two propellers are mounted to one end of the struts, the two propellers being located above and below the struts respectively when the lift-wing UAV is in the take-off and landing mode.
9. The lift wing drone of claim 1, wherein, The wings include control surfaces, the control surfaces being located at the trailing edge of the wings.
10. The lift wing drone of claim 1, wherein, The belly of the lift-wing UAV has a first accommodating space, the back of the lift-wing UAV has a second accommodating space, the cargo being located in the first accommodating space, the battery being located in the second accommodating space.