Single-layer soft empennage structure of ornithopter

Abstract

The utility model discloses a single layer soft empennage structure of ornithopter relates to ornithopter empennage technical field, the attitude adjustment mechanism includes primary rotation unit and secondary rotation unit, the front end of primary rotation unit is equipped with the rotation shaft of ornithopter axial rotation connection, secondary rotation unit and primary rotation unit hinge joint, secondary rotation unit is equipped with the rotation shaft of ornithopter axial rotation connection, and secondary rotation unit is equipped with the rotation shaft of ornithopter axial rotation connection. The fan-shaped empennage is hinged to the second-stage rotating unit; the fan-shaped empennage comprises an empennage fixing piece and a soft empennage, the empennage fixing piece is hinged to the second-stage rotating unit, and the tail end of the soft empennage extends into the empennage fixing piece and is rotationally connected with the empennage fixing piece so as to be opened and closed. The axial rotation angle and the horizontal rotation angle of the empennage are changed through the posture adjusting mechanism, so that the posture of the aircraft can be better adjusted; the fan-shaped empennage can be unfolded and folded, and the unfolding angle is changed, so that the wingspan size is adjusted, and the attitude of the aircraft is conveniently controlled.

Description

Technical Field

[0001] The utility model relates to the technical field of tail wing of flapping-wing aircraft, in particular to a single-layer soft tail wing structure of a flapping-wing aircraft. Background Art

[0002] Flapping-wing aircraft is a type of bionic flying robot, which can be divided into bird-like, bat-like and insect-like flapping-wing robots. Compared with fixed-wing and multi-rotor aircraft of the same size, flapping-wing aircraft has the advantages of good aerodynamic performance, strong maneuverability, high flight efficiency, and easy bionic concealment, and has broad application prospects in both civil and military fields.

[0003] Among the three types of flapping-wing aircraft mentioned above, the bird-like flapping-wing robot has the most diverse attitude adjustment and stability control mechanisms, so it can complete more complex maneuvers. Specifically, in addition to wing differentials, tail movements also play an important role. The tail design of the current bird-like flapping-wing aircraft can be generally divided into the following three categories: 1. The same inverted T-tail as the fixed-wing aircraft; 2. The V-shaped tail whose two ends can be independently deflected up and down; 3. The feather-shaped tail that can achieve wing roll and offset. However, the existing design still has some defects, such as: the tail has limited degrees of freedom, and cannot generate sufficient torque under certain maneuvers, so it cannot effectively adjust the attitude; the tail area is constant, and the adaptability to different speed flight conditions is not high.

[0004] Therefore, a single-layer soft tail structure of a flapping-wing aircraft has become a problem that needs to be solved urgently. Utility Model Content

[0005] The technical problem to be solved by the utility model is to provide a single-layer soft tail structure of a flapping-wing aircraft which is convenient for adjusting the posture and has an adjustable tail area.

[0006] In order to solve the above technical problems, the technical solution provided by the utility model is as follows: a single-layer soft tail structure of a flapping-wing aircraft, comprising an attitude adjustment mechanism and a fan-shaped tail; the attitude adjustment mechanism comprises a primary rotating unit and a secondary rotating unit, the front end of the primary rotating unit is provided with a rotating shaft connected to the axial rotation of the flapping-wing aircraft, the secondary rotating unit is hinged to the primary rotating unit, and the fan-shaped tail is hinged to the secondary rotating unit;

[0007] The fan-shaped tail wing comprises a tail wing fixing part and a soft tail wing, wherein the tail wing fixing part is hinged to the secondary rotating unit, and the end of the soft tail wing extends into the tail wing fixing part and is rotatably connected thereto so as to be opened and closed.

[0008] Furthermore, the primary rotating unit includes a first rotating seat and a first hinged plate, the rotating shaft is arranged at the front end of the first rotating seat, and the first hinged plate is arranged at the rear end of the first rotating seat.

[0009] Furthermore, the secondary rotating unit includes a first hinge block, a second rotating seat and a second hinge plate, the first hinge block is arranged at the front end of the second rotating seat and is hinged to the first hinge plate, and the second hinge plate is arranged at the rear end of the second rotating seat.

[0010] Furthermore, a second hinge block is provided at the front end of the tail wing fixing member, and the second hinge block is hinged to the second hinge plate.

[0011] Furthermore, a wingspan storage compartment is provided at the rear side of the tail wing fixing member, and the soft tail wing is rotated and folded and stored in the wingspan storage compartment.

[0012] Furthermore, the soft tail wing includes a carbon fiber keel and a special high-toughness cloth. The end of the carbon fiber keel extends into the wing span storage compartment and is rotatably connected thereto. The special high-toughness cloth is sequentially connected to each carbon fiber keel and forms a fan shape after being unfolded.

[0013] The advantages of the utility model compared with the prior art are: the utility model changes the axial rotation angle and the horizontal rotation angle of the tail wing through the attitude adjustment mechanism, so as to better adjust the attitude of the aircraft; the fan-shaped tail wing adopts a soft tail wing that can be unfolded and stored, and its unfolding angle can be changed to adjust the wingspan size. During flight, the specific shape can be changed according to the airflow, which is convenient for controlling the attitude of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The utility model is a structural schematic diagram of a single-layer soft tail structure of a flapping-wing aircraft.

[0015] Figure 2 The utility model is a diagram showing the use state of a single-layer soft tail wing structure of a flapping-wing aircraft.

[0016] Figure 3 The utility model is a top view of a single-layer soft tail structure of a flapping-wing aircraft.

[0017] Figure 4 The utility model is a front view of a single-layer soft tail structure of a flapping-wing aircraft.

[0018] Figure 5 The utility model is a left side view of a single-layer soft tail structure of a flapping-wing aircraft.

[0019] As shown in the figure: 1. attitude adjustment mechanism, 101. primary rotating unit, 1011. first rotating seat, 1012. first hinge plate, 102. secondary rotating unit, 1021. first hinge block, 1022. second rotating seat, 1023. second hinge plate, 103. rotating shaft, 2. fan-shaped tail wing, 201. tail wing fixing part, 2011. second hinge block, 2012. wingspan storage compartment, 202. soft tail wing, 2021. carbon fiber keel, 2022. special high-tenacity cloth. DETAILED DESCRIPTION

[0020] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "inside", "outside", "vertical", "circumferential", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0021] In the present invention, unless otherwise clearly specified and limited, the terms "install", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0022] The single-layer soft tail wing structure of a flapping-wing aircraft of the utility model is further described in detail below in conjunction with the accompanying drawings.

[0023] Combined with Figure 1-5 The specific implementation process of the single-layer soft tail structure of a flapping-wing aircraft of the utility model is as follows:

[0024] A single-layer soft tail structure of a flapping-wing aircraft comprises an attitude adjustment mechanism 1 and a fan-shaped tail 2; the attitude adjustment mechanism 1 comprises a primary rotating unit 101 and a secondary rotating unit 102, a rotating shaft 103 connected to the axial rotation of the flapping-wing aircraft is provided at the front end of the primary rotating unit 101, and the flapping-wing aircraft can control the entire tail to realize axial 360-degree rotation through the rotating shaft 103, the secondary rotating unit 102 is hinged to the primary rotating unit 101, and the fan-shaped tail 2 is hinged to the secondary rotating unit 102, and the three parts are hinged and the rotation angle can be controlled by the control motor inside them, thereby realizing the bending adjustment of the tail.

[0025] The fan-shaped tail 2 includes a tail fixing part 201 and a soft tail 202. The tail fixing part 201 is hinged to the secondary rotating unit 102. The end of the soft tail 202 extends into the tail fixing part 201 and is rotatably connected thereto so as to open and close. The soft tail 202 can adjust its shape and can stretch and shrink at the same time to adjust the opening angle of the soft tail 202 and be stored in the tail fixing part 201 when not in use, thereby reducing the volume of the entire tail.

[0026] In one embodiment of the present application, the first-stage rotating unit 101 includes a first rotating seat 1011 and a first hinge plate 1012. The rotating shaft 103 is arranged at the front end of the first rotating seat 1011 and is rotatably connected to the flapping-wing aircraft. The first hinge plate 1012 is arranged at the rear end of the first rotating seat 1011. The first hinge plate 1012 extends outward from the rear of the first rotating seat 1011 to form two mutually symmetrical connecting plates with axial holes.

[0027] In one embodiment of the present application, the secondary rotation unit 102 includes a first hinge block 1021, a second rotating seat 1022 and a second hinge plate 1023. The first hinge block 1021 is arranged at the front end of the second rotating seat 1022 and is hinged to the first hinge plate 1012. The second hinge plate 1023 is arranged at the rear end of the second rotating seat 1022.

[0028] In one embodiment of the present application, a second hinge block 2011 is provided at the front end of the tail wing fixing member 201 , and the second hinge block 2011 is hinged to the second hinge plate 1023 .

[0029] In one embodiment of the present application, a wingspan storage bin 2012 is provided at the rear side of the tail fixing member 201, and the soft tail 202 is rotated and folded and stored in the wingspan storage bin 2012, thereby reducing the volume of the tail.

[0030] In one embodiment of the present application, the soft tail 202 includes a carbon fiber keel 2021 and a special high-toughness cloth 2022. The carbon fiber keel 2021 has higher strength, better supporting effect, and is not easy to be damaged. The special high-toughness cloth 2022 has better toughness and strength, is not easy to deform during high-speed flight, and has stronger pressure resistance. The end of the carbon fiber keel 2021 extends into the wingspan storage compartment 212 and is rotatably connected to it, thereby being able to adjust the wingspan of the tail wing. The special high-toughness cloth 2022 is connected to each carbon fiber keel 221 in turn and is fan-shaped after unfolding. The fan-shaped structure has a better adjustment effect.

[0031] Preferably, the end of the carbon fiber keel 2021 is longer than the special high-tenacity cloth 2022 .

[0032] Preferably, the edge of the special high-tenacity cloth 2022 between every two carbon fiber keels 2021 is concave to form an arc-shaped edge.

[0033] The above description of the utility model and its implementation methods is not restrictive. The drawings show only one implementation method of the utility model, and the actual structure is not limited thereto. In short, if ordinary technicians in this field are inspired by it and design structural methods and embodiments similar to the technical solution without creativity without departing from the purpose of the invention of the utility model, they should all fall within the protection scope of the utility model.

Claims

1. A single-layer soft tail structure for a flapping-wing aircraft, characterized in that: The invention comprises a posture adjustment mechanism (1) and a fan-shaped tail wing (2); the posture adjustment mechanism (1) comprises a primary rotating unit (101) and a secondary rotating unit (102); a rotating shaft (103) connected to the axial rotation of the flapping-wing aircraft is provided at the front end of the primary rotating unit (101); the secondary rotating unit (102) is hingedly connected to the primary rotating unit (101); and the fan-shaped tail wing (2) is hingedly connected to the secondary rotating unit (102); The fan-shaped tail wing (2) comprises a tail wing fixing member (201) and a soft tail wing (202), wherein the tail wing fixing member (201) is hinged to the secondary rotating unit (102), and the end of the soft tail wing (202) extends into the tail wing fixing member (201) and is rotatably connected thereto so as to open and close.

2. The single-layer soft tail structure of a flapping-wing aircraft according to claim 1, characterized in that: The primary rotating unit (101) comprises a first rotating seat (1011) and a first hinged plate (1012); the rotating shaft (103) is arranged at the front end of the first rotating seat (1011); and the first hinged plate (1012) is arranged at the rear end of the first rotating seat (1011).

3. The single-layer soft tail structure of a flapping-wing aircraft according to claim 2, characterized in that: The secondary rotating unit (102) comprises a first hinge block (1021), a second rotating seat (1022) and a second hinge plate (1023), wherein the first hinge block (1021) is arranged at the front end of the second rotating seat (1022) and is hinged to the first hinge plate (1012), and the second hinge plate (1023) is arranged at the rear end of the second rotating seat (1022).

4. The single-layer soft tail structure of a flapping-wing aircraft according to claim 3, characterized in that: A second hinge block (2011) is provided at the front end of the tail wing fixing member (201), and the second hinge block (2011) is hinged to the second hinge plate (1023).

5. The single-layer soft tail structure of a flapping-wing aircraft according to claim 4, characterized in that: A wingspan storage compartment (2012) is provided at the rear side of the tail wing fixing member (201), and the soft tail wing (202) is rotated, folded and stored in the wingspan storage compartment (2012).

6. The single-layer soft tail structure of a flapping-wing aircraft according to claim 5, characterized in that: The soft tail wing (202) comprises a carbon fiber keel (2021) and a special high-toughness cloth (2022), wherein the end of the carbon fiber keel (2021) extends into the wing span storage bin (212) and is rotatably connected thereto, and the special high-toughness cloth (2022) is sequentially connected to each carbon fiber keel (221) and forms a fan shape after being unfolded.

7. The single-layer soft tail structure of a flapping-wing aircraft according to claim 6, characterized in that: The end of the carbon fiber keel (2021) is longer than the special high-tenacity cloth (2022).

8. The single-layer soft tail structure of a flapping-wing aircraft according to claim 7, characterized in that: The edge of the special high-toughness cloth (222) between every two carbon fiber keels (2021) is concave to form an arc-shaped edge.

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