Distributed electric propulsion unmanned aerial vehicle

Abstract

The utility model discloses a kind of distributed electric propulsion unmanned aerial vehicle, comprising: fuselage, front pull type main power propulsion device is installed in the nose of fuselage;Wing, including left wing and right wing, a group of front pull type auxiliary power propulsion device is respectively installed on left wing and right wing, the front pull type auxiliary power propulsion device includes power propulsion unit and vector drive unit, the power propulsion unit includes auxiliary propeller and auxiliary motor, the vector drive unit is used to drive power propulsion unit movement, make the thrust line of auxiliary propeller deflection;Tail, including horizontal tail and vertically arranged rudder.Auxiliary power propulsion device uses vector drive unit to drive the thrust axis of auxiliary propeller deflection along pitch, yaw direction, generates the control moment of pitch / yaw direction, improves the ability of wind correction and short take-off and landing of unmanned aerial vehicle, so that unmanned aerial vehicle simultaneously has the characteristics of high-efficiency aerodynamic characteristic and low power consumption.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically relating to a distributed electric propulsion UAV. Background Technology

[0002] Distributed electric propulsion aircraft, leveraging the size independence of their distributed electric propulsion systems, allow for diverse and heterogeneous flight-engine designs tailored to different scenarios, achieving overall parameter balance between the propulsion system and the aircraft. Compared to traditional aircraft, distributed electric propulsion aircraft offer a higher lift coefficient, making them particularly suitable for missions such as loitering monitoring, exploration, and rescue.

[0003] Due to limitations in battery energy density, existing distributed electric propulsion aircraft have relatively short flight time and range. Furthermore, relying on mechanical control surfaces and differential power combinations for control results in insufficient attitude control capabilities, and issues such as long takeoff and landing distances, weak aerial maneuverability, and poor wind resistance still exist, hindering their practical development. Utility Model Content

[0004] The purpose of this invention is to provide a distributed electric propulsion unmanned aerial vehicle (UAV) to solve the aforementioned problems existing in the application of distributed electric propulsion aircraft.

[0005] This utility model is achieved through the following technical solution: Distributed electric propulsion unmanned aerial vehicles, including: The fuselage, with a forward-pull-type main propulsion device installed at the nose of the fuselage; The wings, including the left wing and the right wing, are equipped with a set of forward-pulling auxiliary power propulsion devices, which include a power propulsion unit and a vector drive unit. The power propulsion unit includes an auxiliary propeller and an auxiliary electric motor. The vector drive unit is used to drive the power propulsion unit to move, causing the thrust line of the auxiliary propeller to deflect. The tail section includes a horizontal tail section and a vertically positioned rudder.

[0006] In some embodiments, the vector drive unit includes two sets of actuator units, one set of actuator units for driving the auxiliary propeller to yaw left and right in the horizontal plane, and the other set of actuator units for driving the auxiliary propeller to pitch in the vertical plane.

[0007] In some embodiments, the actuator unit includes two actuators, which are connected to the auxiliary motor via a spherical bearing. The actuators of one set of actuator units are respectively disposed on the left and right sides of the power propulsion unit, and the actuators of the other set of actuator units are respectively disposed on the upper and lower sides of the power propulsion unit.

[0008] In some embodiments, the spherical bearing is a one-way spherical bearing, which can be locked in its initial position.

[0009] In some embodiments, the vector drive unit includes a mounting pod, and the actuators are respectively fixedly mounted on the mounting pod, which is fixedly mounted on the left wing and the right wing.

[0010] In some embodiments, the auxiliary generator is mounted on a fixed mounting plate, and the actuator cylinders are connected to the fixed mounting plate via spherical bearings.

[0011] In some embodiments, the forward-pull auxiliary power propulsion device is located in the middle of the left and right wings.

[0012] In some embodiments, ailerons are provided on the left and right wings.

[0013] Compared with the prior art, this utility model has the following advantages and beneficial effects: This invention employs a high-thrust main propulsion device and a low-torque, high-speed auxiliary propulsion device, which can meet the thrust requirements of flight. The auxiliary propulsion device uses a vector drive unit to drive the thrust axis of the auxiliary propeller to deflect along the pitch and yaw directions, generating control torque in the pitch / yaw directions, which improves the UAV's ability to resist wind and correct deviation and its short take-off and landing capabilities, enabling the UAV to simultaneously possess efficient aerodynamic characteristics and low power consumption. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the structure of a distributed electric propulsion UAV according to an embodiment of this utility model.

[0016] Figure 2 This is a top view of the structure of a distributed electric propulsion UAV according to an embodiment of this utility model.

[0017] Figure 3 This is a schematic diagram of the auxiliary power propulsion device according to an embodiment of the present invention.

[0018] Figure 4 This is a geometric diagram showing the relationship between the actuator cylinder manipulation and the thrust line deflection angle of the vector drive unit in this embodiment of the present invention.

[0019] Figure 5This is a graph showing the relationship between the actuator cylinder operating distance and the thrust line deflection angle of the vector drive unit in this embodiment of the present invention.

[0020] in: 100. Fuselage; 200. Left wing; 300. Right wing; 1-Main propeller; 2-Main motor; 3-Right wing auxiliary propeller; 4-Right wing auxiliary motor; 5-Right wing aileron; 6-Right wing vector drive unit; 7-Horizontal tail; 8-Rudder; 9-Left wing aileron; 10-Left wing vector drive unit; 11-Left wing auxiliary propeller; 12-Left wing auxiliary motor; 13-Joint bearing; 14-Right actuator; 15-Upper actuator; 16-Lower actuator; 17-Left actuator; 18-Hosting pod. Detailed Implementation

[0021] 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 some embodiments of this utility model, but not all embodiments.

[0022] This invention aims to provide a high aspect ratio, distributed electric propulsion fixed-wing UAV to solve the problems of weak wind resistance and long take-off and landing distance of existing distributed electric propulsion aircraft at low speeds. It can effectively improve the aerodynamic characteristics of UAVs and reduce energy consumption, thereby enhancing the UAV's long-endurance reconnaissance and monitoring capabilities.

[0023] Reference Figure 1 , Figure 2 and Figure 3 In some embodiments of this utility model, the distributed electric propulsion unmanned aerial vehicle includes: The fuselage is 100mm long, and a front-pull main propulsion device is installed at the nose of the fuselage. The wings, including the left wing 200 and the right wing 300, are equipped with a set of forward-pulling auxiliary power propulsion devices. The forward-pulling auxiliary power propulsion device includes a power propulsion unit and a vector drive unit. The power propulsion unit includes an auxiliary propeller and an auxiliary electric motor. The vector drive unit is used to drive the power propulsion unit to move, causing the thrust line of the auxiliary propeller to deflect. The tail section includes a horizontal tail fin 7 and a vertically positioned rudder 8.

[0024] like Figure 1 and Figure 2 As shown, the main propulsion device includes a main propeller 1 and a main motor 2. The main propeller and the main motor adopt a low-torque, high-speed matching combination to generate a greater slipstream speed.

[0025] The main propeller adopts a large-size, high-thrust forward-pull design to provide the main stabilizing thrust for the drone.

[0026] The main propeller is larger than the auxiliary propeller and can provide greater thrust.

[0027] A left-wing auxiliary propulsion device is installed on the left wing, and a right-wing auxiliary propulsion device is installed on the right wing; wherein the left-wing auxiliary propulsion device includes a left-wing vector drive unit 10, a left-wing auxiliary propeller 11, and a left-wing auxiliary electric motor 12, and the right-wing auxiliary propulsion device includes a right-wing vector drive unit 6, a right-wing auxiliary propeller 3, and a right-wing auxiliary electric motor 4.

[0028] Both the left and right wing auxiliary propellers are low-torque, high-speed forward-pulling propellers, which generate a large aerodynamic lift by creating a high-speed slipstream flowing over the wing surface.

[0029] The auxiliary power propulsion devices for the left and right wings are installed in the middle sections of the left and right wings, respectively, facing the direction of flight.

[0030] In some embodiments, such as Figure 3 As shown, the vector drive unit includes two sets of actuator units. One set of actuator units is used to drive the auxiliary propeller to yaw left and right in the horizontal plane, and the other set of actuator units is used to drive the auxiliary propeller to pitch in the vertical plane.

[0031] In some embodiments, the actuator unit includes two actuators, which are connected to the auxiliary motor via a spherical bearing. The actuators of one set of actuator units are respectively disposed on the left and right sides of the power propulsion unit, and the actuators of the other set of actuator units are respectively disposed on the upper and lower sides of the power propulsion unit.

[0032] One set of actuator units includes a left actuator 17 and a right actuator 14, which are respectively arranged on the left and right sides of the power propulsion unit; another set of actuator units includes an upper actuator 15 and a lower actuator 16, which are respectively arranged on the upper and lower sides of the power propulsion unit.

[0033] In some embodiments, the spherical bearing 13 is a one-way spherical bearing, which can be locked in the initial position to prevent angular deflection. In the initial position, the lengths of the actuators are consistent, placing the auxiliary propeller in the initial position.

[0034] The unidirectional motion of a one-way spherical bearing is defined as follows: the spherical bearings corresponding to the left and right actuator cylinders can only yaw in the yaw direction as the actuator cylinder extends and retracts; the spherical bearings corresponding to the upper and lower actuator cylinders can only yaw in the pitch direction as the actuator cylinder extends and retracts.

[0035] like Figure 4 As shown in the figure, the geometric relationship between actuator operation and thrust line deflection angle when actuated by the pitch direction vector is illustrated; in the figure, L is the distance between the axis of the lower or upper actuator and the thrust line. 16 L is the actuation distance for the lower actuator to perform the extension operation. 15 The actuation distance for the upper actuator to perform the retraction operation, where L 16 = L 15 α is the deflection angle of the thrust line after vector actuation, which is calculated to be α = arctan(L 16 / L)*(180 / π).

[0036] like Figure 5 As shown in the figure, the relationship between the actuator control distance and the thrust line deflection angle when the pitch direction vector is actuated is illustrated. When the extension and retraction distances of the lower and upper actuators reach 50mm respectively, the thrust line deflection angle will be greater than 25°, generating a larger thrust and pitching moment in the lift direction of the UAV. This can effectively reduce the wing area, lighten the structural weight of the aircraft, and improve short takeoff and climb capabilities.

[0037] In some embodiments, the vector drive unit includes a mounting pod 18, with actuators fixedly mounted on the mounting pod. The mounting pod is fixedly mounted on the left or right wing to facilitate the installation of the auxiliary power propulsion device on the wing and to provide a high-load, multi-degree-of-freedom motion platform for the auxiliary power propulsion device.

[0038] The auxiliary generator is mounted on a fixed mounting plate, and the actuator cylinders are connected to the fixed mounting plate via spherical bearings. Driving the fixed mounting plate through the actuator cylinders facilitates the connection and operation between the actuator cylinder unit and the power propulsion unit.

[0039] A certain gap is set between the fixed mounting plate and the mounting pod to ensure sufficient deflection adjustment space during deflection adjustment.

[0040] The horizontal tail and rudder are in a T-shape. The rudder can deflect left and right to provide yaw control torque for the UAV, and the horizontal tail can deflect up and down to provide pitch control torque for the UAV.

[0041] The left wing and right wing outer sections are respectively equipped with left wing aileron 9 and right wing aileron 5, which can deflect up and down, to provide pitch control aerodynamic torque for the UAV.

[0042] The operation process of adjusting and controlling the deflection of the auxiliary propeller through the vector drive unit in this invention is as follows: When performing a thrust vectoring action in the downward pitch direction, the length L of the upper actuator cylinder 15 is extended. 15 At the same time, shorten the length L of the lower actuator cylinder 16. 16 By keeping the lengths of the right actuator 14 and the left actuator 17 unchanged, the downward thrust vector can be achieved.

[0043] When performing thrust vectoring actuation in the upward pitch direction, it is only necessary to retract the length L of the upper actuator cylinder 15. 15 At the same time, the length L of the lower actuator cylinder 16 is extended. 16 That is, the lengths of other actuators remain unchanged.

[0044] When performing a thrust vectoring actuation in the left yaw direction, the length L of the right-side actuator cylinder 14 is extended. 14 At the same time, shorten the length L of the left actuator cylinder 17. 17 By keeping the lengths of the upper actuator 15 and the lower actuator 16 unchanged, the thrust vector for yaw to the left can be achieved.

[0045] When performing a thrust vectoring actuation in the right yaw direction, it is only necessary to retract the length L of the right-side actuator cylinder 14. 14 At the same time, the length L of the left actuator cylinder 17 is extended. 17 That is, the lengths of other actuators remain unchanged.

[0046] When vectoring is not performed, the aerodynamic lift of the UAV wing surface is increased by relying solely on the high-speed slipstream generated by the auxiliary propeller. It is only necessary to keep the lengths of the right actuator 14, the upper actuator 15, the lower actuator 16, and the left actuator 17 consistent, and the bearings of each unidirectional motion joint in the initial horizontal locking position to lock the power propulsion unit in the initial state.

[0047] In the description of this utility model, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", and "outer" used to indicate the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship that the utility model product is usually placed in during use. They are only used to facilitate the description of this utility model and to simplify the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0048] Furthermore, the use of terms such as "horizontal" or "vertical" in the description of this utility model does not imply that the component is required to be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0049] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0050] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present utility model shall fall within the protection scope of the present utility model.

Claims

1. A distributed electric propulsion unmanned aerial vehicle, characterized in that, include: The fuselage, with a forward-pull-type main propulsion device installed at the nose of the fuselage; The wings, including the left wing and the right wing, are equipped with a set of forward-pulling auxiliary power propulsion devices. The forward-pulling auxiliary power propulsion device includes a power propulsion unit and a vector drive unit. The power propulsion unit includes an auxiliary propeller and an auxiliary electric motor. The vector drive unit is used to drive the power propulsion unit to move, causing the thrust line of the auxiliary propeller to deflect. The tail section includes a horizontal tail section and a vertically positioned rudder.

2. The distributed electric propulsion UAV according to claim 1, characterized in that, The vector drive unit includes two sets of actuator units, one set of actuator units is used to drive the auxiliary propeller to yaw left and right in the horizontal plane, and the other set of actuator units is used to drive the auxiliary propeller to pitch in the vertical plane.

3. The distributed electric propulsion UAV according to claim 2, characterized in that, The actuator unit includes two actuators, which are connected to the auxiliary motor via a spherical bearing. The actuators of one set of actuator units are respectively located on the left and right sides of the power propulsion unit, while the actuators of the other set of actuator units are respectively located on the upper and lower sides of the power propulsion unit.

4. The distributed electric propulsion UAV according to claim 3, characterized in that, The spherical bearing is a one-way spherical bearing, which can be locked in its initial position.

5. The distributed electric propulsion UAV according to claim 3, characterized in that, The vector drive unit includes a mounting pod, and the actuators are respectively fixedly mounted on the mounting pod. The mounting pod is fixedly mounted on the left wing and the right wing.

6. The distributed electric propulsion UAV according to claim 4, characterized in that, The auxiliary motor is mounted on the fixed mounting plate, and the actuator cylinder is connected to the fixed mounting plate through spherical bearings.

7. The distributed electric propulsion UAV according to any one of claims 1-6, characterized in that, The forward-pull auxiliary power propulsion device is located in the middle of the left and right wings.

8. The distributed electric propulsion UAV according to claim 1, characterized in that, Ailerons are located on the left and right wings.

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