Full-motion horizontal tail V-tail double-tail boom layout unmanned aerial vehicle

Abstract

The utility model discloses a full-motion horizontal tail V-tail double-tail boom layout unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles and comprises a vehicle body, wings are respectively connected to two sides of the vehicle body, backward tail supporting rods are connected and mounted on the rear sides of the two wings, and a fixed horizontal tail is connected between the tail ends of the two tail supporting rods; the outer side of the tail end of the tail supporting rod is provided with a full-motion horizontal tail capable of being rotationally adjusted, and the upper portion of the tail supporting rod is connected with a V tail forming an obtuse angle with the fixed horizontal tail. A double-tail supporting rod structure is adopted, good structural support is provided, the overall stability is improved, a larger wingspan design space is provided, and high adaptability and flexibility are achieved; a V tail is matched with a rotationally adjustable full-motion horizontal tail structure, so that the unmanned aerial vehicle has higher redundancy in control, pitching motion of the unmanned aerial vehicle is effectively controlled, jolt and vibration caused by airflow disturbance are reduced, and flight stability is improved. The overall structure is simple, using is flexible, and practicability is good.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, specifically a fully movable horizontal tail, V-tail, and dual tail boom UAV. Background Technology

[0002] An unmanned aerial vehicle (UAV) is an unmanned aircraft operated via radio remote control or its own programmed control system. UAV technology involves multiple fields, including sensor technology, communication technology, information processing technology, intelligent control technology, and aerospace propulsion technology. UAVs can be categorized into various types, such as fixed-wing UAVs, multi-rotor UAVs, and helicopters.

[0003] Unmanned aerial vehicles (UAVs) have a wide range of applications, from military to civilian sectors. Militarily, UAVs are used for reconnaissance, communications relay, electronic jamming, and attacks. In civilian applications, UAVs are used for agricultural monitoring, weather observation, disaster relief, and construction photography. Furthermore, with technological advancements, UAVs are also being used in the entertainment and consumer markets, such as aerial photography and logistics delivery. A typical UAV system consists of a UAV carrier, ground station equipment (such as radio control and mission control), and a payload. Modern UAVs are also equipped with advanced navigation systems and sensors, enabling them to fly autonomously and perform complex tasks.

[0004] As an important component of modern aviation, unmanned aerial vehicles (UAVs) are increasingly widely designed and applied. Traditional UAV designs often employ a conventional T-tail configuration. However, with rising demands for UAV flight performance, particularly in areas such as long endurance, high maneuverability, high controllability, operational flexibility, and high structural stability, the traditional T-tail configuration is no longer sufficient to meet all requirements. Utility Model Content

[0005] To address the issue that traditional T-tail layouts for drones can no longer fully meet the requirements for long endurance, high maneuverability, high controllability, operational flexibility, and high structural stability, this invention provides a drone with an all-moving horizontal tail, V-tail, and dual tail boom layout.

[0006] This utility model is achieved through the following technical solution:

[0007] A fully movable horizontal tail and V-tail dual-tail-boom UAV includes a fuselage, with wings connected to both sides of the fuselage. Tail booms pointing backward are connected to the rear of the two wings, and a fixed horizontal tail is connected between the tail ends of the two tail booms. A rotatable and adjustable fully movable horizontal tail is installed on the outer side of the tail end of the tail boom, and a V-tail is connected to the upper part of the tail boom, forming an obtuse angle with the fixed horizontal tail.

[0008] A further improvement of this invention is that a three-point landing gear is installed on the lower part of the fuselage.

[0009] A further improvement of this utility model is that the landing gear includes a hydraulically damped double-rocker front landing gear and a carbon fiber molded main landing gear.

[0010] A further improvement of this utility model is that the fuselage and the two wings are connected and installed via quick-release joints.

[0011] A further improvement of this invention is that control surfaces are arranged on the trailing edge of the wing.

[0012] A further improvement of this utility model is that a control surface is provided at the trailing edge of the V-tail.

[0013] A further improvement of this utility model is that the fuselage is provided with a battery compartment, a flight control compartment and a power compartment in sequence from front to back; the battery compartment is equipped with a battery module, the flight control compartment is equipped with a flight control circuit board, and the power compartment is equipped with an electric motor.

[0014] A further improvement of this utility model is that a fully movable horizontal tail actuator is installed at the tail end of the tail support; the fully movable horizontal tail actuator includes a servo motor and a base positioned and installed inside the tail support; a first rocker arm is connected to the output shaft of the servo motor, a rotating rod connected to the fully movable horizontal tail is rotatably installed on the base, and a second rocker arm is vertically connected and installed on the rotating rod, and the first rocker arm and the second rocker arm are rotatably connected and installed through a connecting rod.

[0015] A further improvement of this utility model is that a connecting seat is mounted on the second rocker arm, and the connecting seat is rotatably connected to one end of the connecting rod.

[0016] A further improvement of this utility model is that a fully movable horizontal tail fixing seat is vertically connected and installed on the rotating rod and connected to the fully movable horizontal tail.

[0017] As can be seen from the above technical solutions, the beneficial effects of this utility model are:

[0018] The dual-tail strut structure provides excellent structural support for the UAV, increasing its overall stability and aiding in stability during high-speed and maneuvering flight, thus improving flight safety. It also provides greater wingspan design space, allowing the UAV to carry more equipment and payloads to meet diverse mission requirements. This results in strong adaptability and flexibility, enabling modification and adjustment to meet various military and civilian needs. Furthermore, it offers more spatial layout possibilities, such as accommodating engines or other equipment on the tail boom, optimizing the overall aircraft layout and endurance. The V-tail configuration, combined with a fixed horizontal stabilizer and a rotatable, adjustable all-moving horizontal stabilizer, provides greater redundancy in control. Even when some control surfaces are damaged, the UAV can still maintain normal flight and control through other control surfaces, significantly improving flight safety and reliability. It also effectively controls the UAV's pitch motion, reducing turbulence and vibration caused by airflow disturbances and enhancing flight stability. The overall structure is simple, flexible, and highly practical. Attached Figure Description

[0019] To more clearly illustrate the technical solution of this utility model, the drawings used in the description will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a first-view structural diagram of a specific embodiment of the present invention.

[0021] Figure 2 This is a second-view structural diagram of a specific embodiment of the present invention.

[0022] Figure 3 This is a rear view schematic diagram of a specific embodiment of the present utility model.

[0023] Figure 4 This is a first-view structural diagram of the fully movable flat-tail actuator according to a specific embodiment of the present invention.

[0024] Figure 5 This is a second-view structural diagram of the fully movable flat-tail actuator according to a specific embodiment of the present invention.

[0025] In the attached diagram: 1. Fuselage, 2. Wing, 21. Control surface, 3. Tail strut, 4. V-tail, 5. All-moving horizontal stabilizer, 6. Landing gear, 7. Fixed horizontal stabilizer, 8. All-moving horizontal stabilizer actuator, 81. Servo, 82. First rocker arm, 83. Linkage rod, 84. Connecting seat, 85. Second rocker arm, 86. Base, 87. Rotating rod, 88. All-moving horizontal stabilizer fixed seat. Detailed Implementation

[0026] To make the objectives, features, and advantages of this utility model more apparent and understandable, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings of the specific embodiments. Obviously, the embodiments described below are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this patent, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this patent.

[0027] like Figure 1-3 As shown, this utility model discloses an all-moving horizontal tail and V-tail dual-tail-bearing layout UAV, including a fuselage 1, with wings 2 connected and installed on the left and right sides of the fuselage 1 respectively, and tail support rods 3 extending backward connected and installed on the rear side of the two wings 2, with a fixed horizontal tail 7 connected between the tail ends of the two tail support rods 3; an all-moving horizontal tail 5 that can be rotated and adjusted is installed on the outer side of the tail end of the tail support rod 3, and a V-tail 4 that forms an obtuse angle with the fixed horizontal tail 7 is connected to the upper part of the tail support rod 3.

[0028] This all-moving horizontal stabilizer, V-tail, and twin-boom UAV utilizes a twin-boom structure, providing robust structural support and enhancing overall stability. This contributes to stability during high-speed and maneuvering flight, improving flight safety. It also offers greater wingspan, allowing the UAV to carry more equipment and payloads to meet diverse mission requirements. Its strong adaptability and flexibility allow for modification and adjustment to meet various military and civilian needs. Furthermore, it provides more spatial layout possibilities, such as mounting engines or other equipment on the tail booms to optimize overall layout and endurance. The V-tail (4) combined with a fixed horizontal stabilizer (7) and a rotatable, adjustable all-moving horizontal stabilizer (5) provides greater redundancy in control. Even with some control surfaces damaged, the UAV can still maintain normal flight and control through other control surfaces, significantly improving flight safety and reliability. It also effectively controls pitch motion, reducing turbulence and vibration caused by airflow disturbances and enhancing flight stability. The overall structure is simple, flexible, and highly practical.

[0029] Furthermore, the angle between the V-tail 4 and the fixed flat tail 7 is 120 degrees.

[0030] Among them, such as Figure 2-5As shown, a fully movable horizontal stabilizer actuator 8, capable of rotating the fully movable horizontal stabilizer 5, is installed at the tail of the tail support 3. The fully movable horizontal stabilizer actuator 8 includes a servo motor 81 and a base 86 positioned within the tail support 3. A first rocker arm 82 is connected to the output shaft of the servo motor 81. A rotating rod 87, connected to the fully movable horizontal stabilizer 5, is rotatably mounted on the base 86. A second rocker arm 85 is vertically connected to the rotating rod 87. The first rocker arm 82 and the second rocker arm 85 are rotatably connected via a connecting rod 83. By driving the first rocker arm 82 to swing through the servo motor 81, and by driving the second rocker arm 85 and the rotating rod 87 (along the base 86) to rotate through the connecting rod 83, the rotation angle of the fully movable horizontal stabilizer 5 can be flexibly adjusted. This effectively controls the pitch motion of the UAV, reduces turbulence and vibration caused by airflow disturbances, and improves flight stability. The fully movable horizontal stabilizer actuator 8 has a simple structure, low development cost, and reliable operation.

[0031] Furthermore, a connecting seat 84 is positioned and mounted on the second rocker arm 85, and the connecting seat 84 is rotatably connected to one end of the connecting rod 83. The connecting seat 84 is mounted on the second rocker arm 85 and is fixed by a set screw, which allows for flexible adjustment of the position of the connecting seat 84 on the second rocker arm 85, improving the flexibility of use.

[0032] Furthermore, the first rocker arm 82 is provided with several mounting holes that are rotatably connected to the connecting rod 83. Selecting different mounting holes for installation can improve the flexibility of use.

[0033] Furthermore, a fully movable horizontal stabilizer fixing seat 88, which is connected and installed vertically on the rotating rod 87, is also installed to connect with the fully movable horizontal stabilizer 5. This forms a T-shaped connection structure, achieving a reliable fixed connection to the fully movable horizontal stabilizer 5.

[0034] The lower part of the fuselage 1 is equipped with a three-point landing gear 6. The landing gear 6 includes a hydraulically damped double-rocker nose landing gear and a carbon fiber molded main landing gear. This effectively ensures the stability and safety of the UAV's takeoff and landing.

[0035] The fuselage 1 and the two wings 2 are connected and installed via quick-release joints. This modular design facilitates disassembly, assembly, and maintenance.

[0036] The trailing edge of wing 2 is equipped with control surfaces 21. Each wing 2 has an outer control surface and an inner control surface, used to control the tilt of the UAV.

[0037] The V-tail 4 has control surfaces on its trailing edge, used to control the UAV's heading.

[0038] The fuselage 1 is arranged from front to back as follows: battery compartment, flight control compartment, and power compartment. The battery compartment contains battery modules that supply power to all electrical equipment in the aircraft via cables. The flight control compartment contains flight control circuit boards that are used to calculate flight missions and maintain the normal flight of the UAV. The power compartment contains electric motors that draw power from the battery modules via cables to generate driving force.

[0039] This all-moving horizontal stabilizer / V-tail dual-boom UAV employs a dual-boom structure, providing robust structural support and enhancing overall stability. This contributes to stability during high-speed and maneuvering flight, improving flight safety. It also offers greater wingspan, allowing the UAV to carry more equipment and payloads to meet diverse mission requirements. Its strong adaptability and flexibility allow for modification and adjustment to meet various military and civilian needs. Furthermore, it provides more spatial layout possibilities, such as mounting engines or other equipment on the tail booms to optimize overall layout and endurance. The V-tail (4) combined with a rotatable and adjustable all-moving horizontal stabilizer (5) structure provides greater redundancy in control. Even with some control surfaces damaged, the UAV can still maintain normal flight and control through other control surfaces, significantly improving flight safety and reliability. It also effectively controls pitch motion, reducing turbulence and vibration caused by airflow disturbances and enhancing flight stability. The overall structure is simple, flexible, and highly practical.

[0040] The various embodiments in this specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0041] The terms "upper," "lower," "outer," "inner," etc., used in the specification, claims, and accompanying drawings of this utility model, are used to distinguish relative positional relationships and are not necessarily qualitative. It should be understood that such data can be interchanged where appropriate so that embodiments of the utility model described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion.

[0042] The above description of the disclosed embodiments enables those skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A fully movable horizontal tail, V-tail, dual-tail boom unmanned aerial vehicle (UAV) with a unique configuration, characterized in that... The fuselage (1) is connected to wings (2) on both sides of the fuselage (1). A tail boom (3) is connected to the rear side of the two wings (2) and a fixed horizontal stabilizer (7) is connected between the tail ends of the two tail booms (3). A fully movable horizontal stabilizer (5) that can be rotated and adjusted is installed on the outer side of the tail end of the tail boom (3). A V-tail (4) that forms an obtuse angle with the fixed horizontal stabilizer (7) is connected to the upper part of the tail boom (3).

2. The UAV with all-moving horizontal tail, V-tail, and dual tail boom layout according to claim 1, characterized in that, The fuselage (1) is equipped with a three-point landing gear (6) at the bottom.

3. The UAV with all-moving horizontal tail, V-tail, and dual tail boom layout according to claim 2, characterized in that, The landing gear (6) includes a hydraulically damped double-rocker front landing gear and a carbon fiber molded main landing gear.

4. The UAV with all-moving horizontal tail, V-tail, and twin-boom layout according to claim 1, characterized in that, The fuselage (1) and the two wings (2) are connected and installed via quick-release joints.

5. The UAV with all-moving horizontal tail, V-tail, and dual tail boom layout according to claim 1, characterized in that, The trailing edge of the wing (2) is equipped with control surfaces (21).

6. The UAV with all-moving horizontal tail, V-tail, and twin-boom layout according to claim 1, characterized in that, The trailing edge of the V-tail (4) is provided with control surfaces.

7. The UAV with all-moving horizontal tail, V-tail, and twin-tail boom layout according to claim 1, characterized in that, The fuselage (1) is arranged from front to back with a battery compartment, a flight control compartment and a power compartment; the battery compartment contains battery modules, the flight control compartment contains flight control circuit boards, and the power compartment contains electric motors.

8. The UAV with all-moving horizontal tail, V-tail, and twin-tail boom layout according to claim 1, characterized in that, The tail support (3) is equipped with a fully movable horizontal tail actuator (8); the fully movable horizontal tail actuator (8) includes a servo motor (81) and a base (86) positioned and installed in the tail support (3); a first rocker arm (82) is connected to the output shaft of the servo motor (81), and a rotating rod (87) connected to the fully movable horizontal tail (5) is rotatably installed on the base (86), and a second rocker arm (85) is vertically connected to the rotating rod (87). The first rocker arm (82) and the second rocker arm (85) are rotatably connected and installed through a connecting rod (83).

9. The UAV with all-moving horizontal tail, V-tail, and twin-tail boom layout according to claim 8, characterized in that, The second rocker arm (85) is fitted with a connecting seat (84), which is rotatably connected to one end of the connecting rod (83).

10. The UAV with all-moving horizontal tail, V-tail, and twin-tail boom configuration according to claim 8, characterized in that, A fully movable horizontal tail fixing seat (88) that is connected and installed on the rotating rod (87) is vertically connected to the fully movable horizontal tail (5).

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