Blade type empennage structure of ornithopter
By designing the attitude adjustment mechanism and fan-shaped tail structure in the mock-type flapping aircraft, the problems of constant freedom and area of the tail are solved, more flexible attitude adjustment and adaptability are achieved, and the maneuverability of the aircraft is improved.
Patent Information
- Application Number
- CN202421027514.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-13
- Publication Date
- 2025-01-10
- Estimated Expiration
- 2034-05-13
AI Technical Summary
The existing tail design of the bird-type flapping wing aircraft has the defects of limited tail freedom and constant tail area, which cannot effectively adjust the posture and adapt to flight conditions at different speeds.
A vane-type tail structure including an attitude adjustment mechanism and a fan-shaped tail wing is designed. The axial and horizontal rotation of the tail wing is realized through the primary and secondary rotating units. Combined with the design of the hard blade, it allows the opening, closing and storage of the tail wing. , adjust the wingspan size.
It realizes more flexible attitude adjustment and tail area adjustability, improving the aircraft's adaptability and control accuracy under different flight conditions.
Smart Images
Figure CN222330031U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of flapping-wing aircraft tail wing, in particular to a blade-type 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 blade-type 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 blade-type 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 blade-type 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 includes a tail wing fixing part and a hard tail wing, the tail wing fixing part is hinged to the secondary rotating unit, and the hard tail wing is a plurality of blades arranged up and down, and one end of each blade extends into the tail wing fixing part and is rotatably connected thereto so as to open and close.
[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 hard tail wing is rotated, stacked and stored in the wingspan storage compartment.
[0012] The advantages of the present invention over the prior art are as follows: the present invention 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 can be unfolded and stored, and its unfolding angle can be changed to adjust the wingspan size, and the use of hard feathers ensures the rigidity of the tail wing, making it convenient to control the attitude of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 The utility model is a schematic structural diagram of a blade-type tail structure of a flapping-wing aircraft.
[0014] Figure 2 This is the use state of the blade-type tail wing structure of a flapping-wing aircraft of the utility model. Figure 1 .
[0015] Figure 3 This is the use state of the blade-type tail wing structure of a flapping-wing aircraft of the utility model. Figure 2 .
[0016] Figure 4 This is a schematic diagram of a top view of a blade-type tail structure of a flapping-wing aircraft of the utility model.
[0017] Figure 5 The utility model is a side view structural schematic diagram of a blade-type tail wing structure of a flapping-wing aircraft.
[0018] Figure 6 The utility model is a schematic diagram of the main structure of a blade-type tail wing 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. hard tail wing, 2021. blade. 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 blade-type 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 1-6 The specific implementation process of the blade-type tail wing structure of a flapping-wing aircraft of the utility model is as follows:
[0024] A blade-type 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, the front end of the primary rotating unit 101 is provided with a rotating shaft 103 connected to the axial rotation of the flapping-wing aircraft, through which the flapping-wing aircraft can control the entire tail to achieve 360-degree axial rotation, 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, the three parts are hinged and the rotation angle can be controlled by the control motor inside them, thereby achieving bending adjustment of the tail.
[0025] The fan-shaped tail 2 includes a tail fixing part 201 and a hard tail 202. The tail fixing part 201 is hinged to the secondary rotating unit 102. The hard tail 202 is a plurality of blades 2021 arranged vertically. One end of each blade 2021 extends into the tail fixing part 201 and is rotatably connected thereto so as to open and close. The hard tail 202 can adjust its shape and can stretch and shrink at the same time to adjust the opening angle of the hard tail 202 and be stored in the tail fixing part 201 when not in use to reduce the volume of the entire tail. The hard tail 202 is composed of a plurality of hard blades 2021, has greater strength, is not easy to bend, and has a better diversion effect.
[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 compartment 2012 is provided at the rear side of the tail fixing member 201, and the hard tail 202 is rotated and folded into the wingspan storage compartment 2012, thereby reducing the volume of the tail.
[0030] In one embodiment of the present application, the blades 2021 are arranged from high to low from the middle to both sides. This arrangement allows the blades 2021 to be staggered and stacked when stored without affecting each other.
[0031] 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 blade-type 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 hard tail wing (202), wherein the tail wing fixing member (201) is hinged to the secondary rotating unit (102), and the hard tail wing (202) is a plurality of blades (2021) arranged vertically, and one end of each blade (2021) extends into the tail wing fixing member (201) and is rotatably connected thereto so as to open and close.
2. The blade-type 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 blade-type 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 blade-type 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 blade-type tail structure of a flapping-wing aircraft according to claim 4, characterized in that: A wingspan storage bin (2012) is provided at the rear side of the tail wing fixing member (201), and the hard tail wing (202) is rotated, stacked and stored in the wingspan storage bin (2012).
6. The blade-type tail structure of a flapping-wing aircraft according to claim 5, characterized in that: The blades (2021) are arranged from high to low from the middle to both sides.