Tilt rotor unmanned aerial vehicle with optimized power

Abstract

The utility model relates to a tilt-rotor unmanned aerial vehicle with optimized power. The tilt-rotor unmanned aerial vehicle comprises a fuselage, an empennage and a fixed wing, a bearing rod is installed below the fixed wing, a mounting sleeve is arranged on the bearing rod in a sleeving mode, a mounting seat is arranged on the lower surface of the fixed wing, a mounting hole is formed in the mounting seat, the mounting hole is only in an opening shape, and a cavity used for limiting rotation of the locking rod and the center round rod is further formed in the mounting seat. The mounting hole is composed of a middle long-strip-shaped channel and a circular channel. The front rotor and the rear rotor adopt different power configurations, the front rotor focuses on fixed-wing flight and adopts a low-pitch propeller blade II and a high-kv-value motor II to increase the rotating speed and improve the cruising efficiency of the fixed wing, and the rear rotor adopts a large-pitch propeller blade I and a low-kv-value motor I to improve the lift force efficiency in the take-off and landing stages; the rear rotor and the front rotor are different in direction, the front rotor is conventionally upward, and the rear rotor is downward, so that shielding of the rear rotor to the lift force of the empennage is effectively reduced, and the lift force efficiency is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tilt-rotor with optimized power. Background Technique

[0002] An unmanned aerial vehicle, full name unmanned aircraft, is an unpiloted aircraft controlled by radio remote control equipment and self-prepared program control devices, or operated completely or intermittently autonomously by an on-vehicle computer; compared with piloted aircraft, unmanned aerial vehicles are more suitable for performing tasks that are "dull, dirty or dangerous".

[0003] In conventional vertical takeoff and landing fixed-wing unmanned aerial vehicles, there is no distinction between the rotor power and the fixed-wing power during the cruise phase, resulting in low power efficiency, large power consumption, and reduced endurance when the power motor works for a long time during the cruise phase.

[0004] This design is different from the conventional structure where both the front and rear rotors face upward. The rear rotor is located below the fixed-wing wing, further reducing the interference of the wing on the rear rotor airflow and improving the rotor working efficiency. This design optimizes the front and rear power configurations of the unmanned aerial vehicle and better adapts to the working requirements during the cruise phase. Content of the Utility Model

[0005] The purpose of this part is to outline some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Simplifications or omissions may be made in this part, as well as in the abstract and title of the specification of this application, to avoid obscuring the purpose of this part, the abstract, and the title of the utility model, and such simplifications or omissions shall not be used to limit the scope of the utility model.

[0006] In view of the following technical problems in the prior art: in conventional vertical takeoff and landing fixed-wing unmanned aerial vehicles, there is no distinction between the rotor power and the fixed-wing power during the cruise phase, resulting in low power efficiency, large power consumption, and reduced endurance when the power motor works for a long time during the cruise phase.

[0007] To solve the above technical problems, the utility model provides the following technical solution: a tilt-rotor unmanned aerial vehicle with optimized power, including a fuselage, a tail wing, and a fixed wing.

[0008] A bearing rod is installed below the fixed wing. An installation sleeve is sleeved on the bearing rod. An installation seat is arranged on the lower surface of the fixed wing. An installation hole is opened in the installation seat. The installation hole is only in an open shape. There is also a cavity in the installation seat for locking the rod and limiting the rotation of the central circular rod. The installation hole is composed of a middle long strip channel and a circular channel.

[0009] The front end of the bearing rod is hinged with a front rotor, and the rear end of the bearing rod is installed with a rear rotor.

[0010] The bearing rod and the front rotor are hinged through a tilting mechanism. The tilting mechanism mainly includes a double-axis digital rudder and a U-shaped bracket. The double-axis digital rudder is installed on the bearing rod, and the front rotor is installed on the plane of the U-shaped bracket.

[0011] As a preferred technical solution of a tilt-rotor UAV with optimized power, the fixed wings are located on two sides of the fuselage, and the tail wing is located at the rear of the fuselage.

[0012] As a preferred technical solution of a tilt-rotor UAV with optimized power, a screwing member is arranged on the outer side of the mounting sleeve. The screwing member is the hand-screwing position. A central round rod is arranged on the side of the mounting sleeve away from the screwing member. The central round rod penetrates through the mounting sleeve and the bearing rod and is docked with one side of the screwing member. The central round rod is inserted into the mounting hole. A locking rod is arranged on the outer side of the central round rod. First, the locking rod and the central round rod are shaped corresponding to the mounting hole and embedded. After the docking is completed, the screwing member is rotated by 90 degrees. At this time, the locking rod and the central round rod are in the inner cavity of the mounting seat. At this time, the position of the locking rod does not correspond to the long strip channel of the mounting hole. At this time, the mounting sleeve can be positioned and quickly installed.

[0013] As a preferred technical solution of a tilt-rotor UAV with optimized power, a socket is arranged between two mounting seats on a single fixed wing. A plug is arranged on the side of the bearing rod facing the locking rod. The plug is inserted into the socket for signal transmission and can also protect the wire.

[0014] As a preferred technical solution of a tilt-rotor UAV with optimized power, the rear rotor includes a first blade and a first motor. The tail end of the first motor is installed on the bearing rod, and the first blade is docked with the output end of the first motor.

[0015] As a preferred technical solution of a tilt-rotor UAV with optimized power, the front rotor includes a second blade and a second motor. The second blade is docked with the output end of the second motor, and the tail end of the second motor is installed on the U-shaped bracket.

[0016] As a preferred technical solution of a tilt-rotor UAV with optimized power, an external gear shaft is arranged at the output end of the double-axis digital rudder. Linkage disks are arranged on the inner edges at both ends of the U-shaped bracket. An internal gear ring is arranged at the center of the linkage disk. The internal gear ring is inserted and installed outside the external gear shaft, and the internal gear ring meshes and drives with the external gear shaft. When the double-axis digital rudder operates, the linkage disk can be rotated through the external gear shaft under the action of meshing transmission, so that the front rotor rotates.

[0017] The beneficial effects of the present utility model:

[0018] 1. The front rotor and the rear rotor adopt different power configurations. The front rotor focuses on fixed-wing flight, using two low-pitch propeller blades and two high-kv motors to increase the rotation speed and improve the efficiency during fixed-wing cruising. The rear rotor uses one large-pitch blade and one low-kv motor to improve the lift efficiency during takeoff and landing.

[0019] 2. The directions of the rear rotor and the front rotor are different. The front rotor is in the conventional upward direction, and the rear rotor is downward, effectively reducing the occlusion of the rear rotor on the lift of the tail wing and improving the lift efficiency.

[0020] 3. The front rotor is designed to be tiltable. During cruising, the front rotor continues to work in a horizontal state with the fuselage, providing forward pull for the fuselage, and the rear rotor stops working. At this time, the drone is converted from a multi-rotor mode to a conventional fixed-wing mode. This design reduces a set of separate front-pull or rear-push power systems compared to conventional vertical takeoff and landing fixed wings, reduces the overall weight of the machine, optimizes the power structure, and enhances the endurance time.

[0021] 4. By using mounting holes, mounting sleeves, screwing parts, locking rods, and central round rods, the quick-disassembly method of the bearing rod, rear rotor, and front rotor is realized, which is convenient for disassembly and assembly.

[0022] Other features and advantages of the present utility model will be described in the subsequent description, and part of them will become obvious from the description or be understood by implementing the present utility model. The objectives and other advantages of the present utility model can be achieved and obtained through the structures specifically pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings required for the description of the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts. Among them:

[0024] Figure 1 is the overall structural schematic diagram of the present utility model.

[0025] Figure 2 is the bottom view schematic diagram of the present utility model.

[0026] Figure 3 is the schematic diagram of the present utility model with the bearing rod not installed on one of the fixed wings.

[0027] Figure 4 is the docking and installation schematic diagram of the bearing rod of the present utility model.

[0028] Figure 5 is the side view schematic of the present utility model Figure 1 。

[0029] Figure 6 Side view schematic of the present utility model Figure 2 。

[0030] Figure 7 Structural schematic of the tilting mechanism of the present utility model Figure 1 。

[0031] Figure 8 Structural schematic of the tilting mechanism of the present utility model Figure 2 。

[0032] Figure 9 Structural schematic of the tilting mechanism of the present utility model Figure 3 。

[0033] Reference numerals:

[0034] 100, fuselage; 101, tail wing; 102, fixed wing; 103, mounting seat; 104, mounting hole; 105, socket; 200, carrier rod; 201, mounting sleeve; 202, turning member; 203, locking rod; 204, central circular rod; 205, plug; 300, rear rotor; 301, blade one; 302, motor one; 400, front rotor; 401, blade two; 402, motor two; 500, tilting mechanism; 501, double-axis digital rudder; 502, U-shaped bracket; 503, external tooth shaft; 504, linkage disk; 505, internal tooth ring. Detailed implementation manners

[0035] To make the above objects, features and advantages of the present utility model more obvious and understandable, the following will describe the detailed implementation manners of the present utility model with reference to the accompanying drawings of the specification.

[0036] In the following description, many specific details are set forth to fully understand the present utility model. However, the present utility model can also be implemented in other ways different from this description. Those skilled in the art can make similar extensions without departing from the connotation of the present utility model. Therefore, the present utility model is not limited by the specific embodiments disclosed below.

[0037] Secondly, the so-called "one embodiment" or "embodiment" herein refers to specific features, structures or characteristics that can be included in at least one implementation manner of the present utility model. The "in one embodiment" that appears in different places in this specification does not necessarily refer to the same embodiment, nor is it an embodiment that is separate or selectively exclusive of other embodiments.

[0038] Secondly, the present invention is described in detail with reference to the schematic diagram. When describing the embodiments of the present invention, for the sake of convenience, the cross-sectional diagrams showing the device structure will not be partially enlarged according to the general scale, and the schematic diagrams are only examples, which should not limit the scope of protection of the present invention. In addition, in actual production, the three-dimensional dimensions of length, width and depth should be included.

[0039] Example 1

[0040] Reference Figures 1 to 6 , which is the first embodiment of the utility model, and provides a power-optimized tilt-rotor UAV, comprising a fuselage 100, a tail 101 and fixed wings 102, wherein the fixed wings 102 are located at two sides of the fuselage 100, and the tail 101 is located at the rear of the fuselage 100;

[0041] A load-bearing rod 200 is installed below the fixed wing 102, and a mounting sleeve 201 is sleeved on the load-bearing rod 200. A mounting seat 103 is provided on the lower surface of the fixed wing 102, and a mounting hole 104 is opened on the mounting seat 103, wherein the mounting hole 104 is only an opening shape, and there is also a cavity in the mounting seat 103 for rotation limiting of the locking rod 203 and the center round rod 204, and the mounting hole 104 is composed of a middle long channel and a circular channel; a twisting piece 202 is provided on the outside of the mounting sleeve 201, wherein the twisting piece 202 is a hand twisting position, and a center round rod 204 is provided on the side of the mounting sleeve 201 away from the twisting piece 202, and the center round rod 204 passes through the mounting sleeve 201 and the load-bearing rod 200 and is connected to one side of the twisting piece 202, and the center round rod 204 is inserted into the mounting hole 104, and a locking rod 203 is arranged on the outer side of the central round rod 204. First, the locking rod 203 and the central round rod 204 are aligned with the mounting hole 104 and embedded. After the docking is completed, the twisting piece 202 is rotated ninety degrees. At this time, the locking rod 203 and the central round rod 204 are engaged in the inner cavity of the mounting seat 103. At this time, the position of the locking rod 203 does not correspond to the long channel of the mounting hole 104. At this time, the mounting sleeve 201 can be positioned and quickly installed; a socket 105 is arranged between the two mounting seats 103 on a single fixed wing 102, and a plug 205 is arranged on the side of the bearing rod 200 facing the locking rod 203. The plug 205 is plugged into the socket 105 for signal transmission and can also protect the wires.

[0042] The front end of the load-bearing rod 200 is hinged with a front rotor 400, and the rear end of the load-bearing rod 200 is installed with a rear rotor 300: The rear rotor 300 includes a first blade 301 and a first motor 302. The rear end of the first motor 302 is installed on the load-bearing rod 200, and the first blade 301 is docked to the output end of the first motor 302; The front rotor 400 includes a second blade 401 and a second motor 402. The second blade 401 is docked to the output end of the second motor 402, and the rear end of the second motor 402 is installed on the U-shaped bracket 502. Among them, the second motor 402 is of the X3520-8 model, KV: 520, and the first motor 302 is of the X4112S-11 model, KV: 400.

[0043] Embodiment 2

[0044] Refer to Figures 5 to 9 As shown, this is the second embodiment of the present utility model. The difference between this embodiment and the previous one is that: The load-bearing rod 200 and the front rotor 400 are hinged through a tilting mechanism 500. The tilting mechanism 500 mainly includes a double-axis digital rudder 501 and a U-shaped bracket 502. The double-axis digital rudder 501 is installed on the load-bearing rod 200, and the front rotor 400 is installed on the plane of the U-shaped bracket 502; External gear shafts 503 are provided at the output ends (i.e., both sides) of the double-axis digital rudder 501. Linkage disks 504 are provided along the inner edges at both ends of the U-shaped bracket 502. An internal gear ring 505 is provided at the center of the linkage disk 504. The internal gear ring 505 is inserted and installed outside the external gear shaft 503, and the internal gear ring 505 meshes and drives with the external gear shaft 503. When the double-axis digital rudder 501 operates, the linkage disk 504 can be rotated through the meshing drive of the external gear shaft 503, so that the front rotor 400 rotates. Among them, the double-axis digital rudder 501 is of the large-torque RDS15kg type.

[0045] Multi-rotor mode: When the front rotor 400 is vertical, it is used in cooperation with the rear rotor 300 for the takeoff and landing of the unmanned aerial vehicle;

[0046] Fixed-wing 102 mode: When the front rotor 400 is horizontal and the rear rotor 300 stops working, it is used for the cruise work of the unmanned aerial vehicle.

[0047] It should be understood that in the development process of any actual implementation, in any engineering or design project, a large number of specific implementation decisions can be made. Such development efforts may be complex and time-consuming, but for those of ordinary skill in the art who benefit from this disclosure, without excessive experimentation, the development efforts will be a routine task of design, manufacturing, and production.

[0048] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit them. Although the present invention has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present invention can be modified or equivalently replaced without departing from the spirit and scope of the technical solutions of the present invention, and they should all be covered within the scope of the claims of the present invention.

Claims

1. A power-optimized tilt-rotor UAV, characterized in that: It comprises a fuselage (100), a tail wing (101) and a fixed wing (102); A bearing rod (200) is installed below the fixed wing (102), a mounting sleeve (201) is sleeved on the bearing rod (200), a mounting seat (103) is arranged on the lower surface of the fixed wing (102), a mounting hole (104) is opened on the mounting seat (103), and the mounting hole (104) is composed of a middle long channel and a circular channel; A front rotor (400) is hingedly connected to the front end of the load-bearing rod (200), and a rear rotor (300) is installed at the rear end of the load-bearing rod (200); The bearing rod (200) and the front rotor (400) are hingedly connected via a tilt mechanism (500), wherein the tilt mechanism (500) mainly comprises a dual-axis digital rudder (501) and a U-shaped bracket (502), wherein the dual-axis digital rudder (501) is mounted on the bearing rod (200), and the front rotor (400) is mounted on a plane of the U-shaped bracket (502).

2. The drone according to claim 1, characterized in that: The fixed wings (102) are located at two sides of the fuselage (100), and the tail wing (101) is located at the rear of the fuselage (100).

3. The drone according to claim 1, characterized in that: A screwing piece (202) is arranged on the outside of the installation sleeve (201), a central round rod (204) is arranged on the side of the installation sleeve (201) away from the screwing piece (202), and the central round rod (204) passes through the installation sleeve (201) and the bearing rod (200) and butts with one side of the screwing piece (202), the central round rod (204) is inserted into the installation hole (104), and a locking rod (203) is arranged on the outside of the central round rod (204).

4. The drone according to claim 1, characterized in that: A socket (105) is arranged between the two mounting seats (103) on a single fixed wing (102), and a plug (205) is arranged on the side of the bearing rod (200) facing the locking rod (203), and the plug (205) is plugged into the socket (105).

5. The drone according to claim 1, characterized in that: The rear rotor (300) comprises a blade one (301) and a motor one (302), wherein the tail end of the motor one (302) is mounted on the bearing rod (200), and the blade one (301) is connected to the output end of the motor one (302).

6. The drone according to claim 1, characterized in that: The front rotor (400) includes blade 2 (401) and motor 2 (402), wherein blade 2 (401) is connected to the output end of motor 2 (402), and the tail end of motor 2 (402) is installed on a U-shaped bracket (502).

7. The drone according to claim 1, characterized in that: The output end of the dual-axis digital rudder (501) is provided with an external gear shaft (503), the inner edges of both ends of the U-shaped bracket (502) are provided with linkage disks (504), the center of the linkage disk (504) is provided with an internal gear ring (505), the internal gear ring (505) is plugged and installed outside the external gear shaft (503), and the internal gear ring (505) is meshed with the external gear shaft (503) for transmission.

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