CN110251960A - A method for deploying the wings of an amphibious model aircraft in water, land and air - Google Patents

Abstract

The invention discloses a method for deploying the wings of an amphibious model aircraft amphibious, and belongs to the technical field of model aircraft design. The second bracket in the present invention is a telescopic structure. When the second bracket shrinks, the fourth bracket hinged with the second bracket rotates clockwise; so that the third bracket hinged with both ends of the fourth bracket also rotates. Rotate clockwise; meanwhile, the fifth support hinged with the third support rotates counterclockwise, and the sixth support with the fifth support also rotates counterclockwise simultaneously; the wings are deployed. The invention realizes flexible expansion and contraction of the wings by designing the wings of the model airplane into a retractable structure, thereby increasing the interest of the model airplane.

Description

A method for deploying the wings of an amphibious model aircraft in water, land and air

technical field

The invention relates to the technical field of model aircraft design, and more specifically, relates to a method for deploying wings of an amphibious amphibious model aircraft.

Background technique

In nature, birds have undergone long-term evolution, and their forelimbs have evolved into wings, through which they can fly or glide, making them the overlords of the sky. With the rapid development of science and technology, human beings imitate the flying mode of bird wings and gradually march into the sky. Therefore, airplanes, aircrafts, drones, etc. have emerged as the times require.

Wherein, model airplane is as a kind of small-sized aircraft, can control it by remote control device, makes it fly in the air, is very popular among young people. In order to ensure the normal flight of the model aircraft, the structural design of its wings is particularly important. With the continuous advancement of research technology, in order to realize the flight of the wings of the model aircraft in the prior art, the propeller and the wing cooperate with each other to form a model. The aircraft body provides buoyancy, but most of the wings of the model aircraft are fixedly mounted on the body of the model aircraft, and are always in a fixed and unfolded state, which has poor flexibility and interest and needs further improvement.

After searching, the Chinese patent number: CN 201010138146.4, the name of the invention: the bionic wing of the flapping wing, the application includes that the main wing bone and the aileron bone are movably connected through the main and aileron joint joints, and the main and aileron bone are fixed with Wings, the wings are composed of multiple groups of pinnae, the outer side of the connection between the main and aileron wing bones and the wings is covered with the main and aileron coverts, the main and aileron joints are composed of outer joints, inner joints, connecting shafts and bearings, the outer The joint is fixed under the pterygium of the aileron, the inner joint is fixed under the pterygium of the main wing, and the outer joint and the inner joint are movably connected by connecting shafts and bearings. When the bionic wing of this application is in use, the aileron bone moves up and down, so that the wing flutters up and down to provide buoyancy for the orthopter. However, the bionic wing itself in this application cannot realize the contraction function and needs further improvement.

Another example is the Chinese patent number: ZL 201721376182.8, the name of the invention: a toy with movable wings, the application includes a shell, a wing assembly and an unfolding structure. The structure includes a trigger component, a first elastic component, a second elastic component, a first buckle fixedly arranged on the wing assembly, and a second buckle capable of being engaged with the first buckle, and the second buckle passes through the second elastic component It is arranged on the housing, and the interlocking of the first buckle and the second buckle realizes the contraction of the side wing assembly and attaches it to the housing. The first elastic part and the second elastic part of this application undergo elastic deformation. After the first buckle and the second buckle touch the trigger part to release the fastening state, the wing assembly changes from the contracted state to the expanded state, but the overall contraction or expansion of the wing assembly does not reflect the flexibility of the wing assembly itself, resulting in Toys are less interesting.

Contents of the invention

1. The technical problem to be solved by the invention

The purpose of the present invention is to overcome the problem that the model aircraft in the prior art is less interesting, and provides a method for deploying the wing of an amphibious model aircraft. The present invention designs the wing of the model aircraft into a retractable structure, Realize the flexible expansion and contraction of the wings, and increase the interest of the model aircraft.

2. Technical solution

In order to achieve the above object, the technical scheme provided by the invention is:

A method for deploying the wings of an amphibious model aircraft of the present invention utilizes an amphibious model aircraft, the steps of which are as follows:

a. The second bracket hingedly connected with the body is a telescopic structure. When the second bracket shrinks, the fourth bracket hinged with the second bracket rotates clockwise;

b. When the fourth bracket rotates, since both ends of the fourth bracket are connected to the third bracket through hinges, the third bracket also rotates clockwise;

c. When the third bracket rotates, the fifth bracket hinged with the third bracket rotates counterclockwise, and at the same time, the sixth bracket of the fifth bracket also rotates counterclockwise; unfold the wings;

d. The supporting element works, and the second bracket is pushed away from the body through the supporting element. Under the action of the hinge point, the second bracket rotates counterclockwise, so that the whole wing forms a certain angle with the body.

As a further improvement of the present invention, the amphibious model aircraft includes a body, wings, propellers, a vertical tail and a horizontal tail, the wings are retractable wings, and the inside of the wings is realized by a second bracket For the expansion and contraction of the wings, the propeller is arranged on the propeller bracket, which is a foldable and retractable bracket; the tail of the body is also provided with a tail propeller; the bottom of the body is provided with a plurality of wheel.

As a further improvement of the present invention, the wing includes a first bracket and a second bracket hingedly installed on one side of the body, the end of the first bracket away from the body is hinged to the end of the third bracket and the fourth bracket close to the body , the end of the second bracket away from the body is also hinged with the end of the fourth bracket close to the body, the end of the third bracket away from the body is hinged with the end of the fifth bracket close to the body; the end of the fourth bracket away from the body is hinged with the first The fifth bracket and the sixth bracket are hinged at one end close to the body, and the end of the sixth bracket away from the body is connected to the fifth bracket; the side wall of the second bracket is hinged with a support element, which is arranged on the body.

As a further improvement of the present invention, the third support and the fourth support are parallel to each other.

As a further improvement of the present invention, one end of the fourth bracket close to the body is curved, and the curved end surface includes a first end surface and a second end surface, the first end surface and the second end surface are arc-shaped, and The concavity direction of the arc is toward the middle of the curved shape, the hinge point of the first bracket and the fourth bracket is located on the first end surface, and the hinge point of the second bracket and the fourth bracket is located on the second end surface.

As a further improvement of the present invention, one end of the fifth bracket close to the body is curved, and the curved end surface includes a third end surface and a fourth end surface, the third end surface and the fourth end surface are arc-shaped, and The concavity direction of the arc is toward the middle of the curved shape, the hinge point of the third bracket and the fifth bracket is located on the third end surface, and the hinge point of the fourth bracket and the fifth bracket is located on the fourth end surface.

As a further improvement of the present invention, the second bracket is meshed with the fourth bracket through gear teeth; the third bracket is meshed with the fifth bracket through gear teeth.

As a further improvement of the present invention, the outside of the bracket is wrapped into a wing shape by a tarpaulin woven from carbon fibers. There are multiple rib placement holes inside the tarpaulin, and the rib placement holes are opened along the length direction of the body. For placing the ribs.

As a further improvement of the present invention, the diameter of the carbon fiber is 0.1-0.5 mm, and the thickness of the woven tarpaulin is 3-5 mm; the diameter of the rib is 20-50 mm.

As a further improvement of the present invention, the bottom edge of the tarpaulin is provided with a protective edge along its circumference, and the protective edge is composed of a columnar body with a diameter of 5-10mm, and the columnar body is made of carbon fiber.

3. Beneficial effects

Compared with the existing known technology, the technical solution provided by the invention has the following remarkable effects:

(1) The unfolding method of a kind of water, land and air amphibious model aircraft wing of the present invention, by controlling the contraction of the second support, the third support and the fourth support are rotated clockwise, and the third support and the fourth support are rotated to drive The fifth bracket and the sixth bracket rotate counterclockwise, so that the wings are unfolded. The whole process is simple and easy to operate. Compared with the fixed wing of the traditional model airplane, its structure is flexible, which enhances the interest of the model airplane.

(2) A kind of amphibious model aircraft of the present invention, by designing the wing of the model aircraft as a retractable wing, the expansion and contraction of the wing is realized by the second retractable support inside the wing as the driving mechanism When the model airplane is flying, the wings are flexible, which increases the fun of the model airplane; in addition, in order to further increase the fun of flying the model, there is a tail propeller at the tail of the body, which is convenient for the model airplane to sail in the water; at the same time, There are wheels at the bottom of the body, which is convenient for the model aircraft to travel on land. The above structure ensures that the model aircraft can be used in three fields of water, land and air, which further increases the interest of the model aircraft.

(3) in a kind of amphibious model aircraft of the present invention, the brackets inside the wings are connected in a hinged form, which makes the rotation between the brackets more flexible. In addition, in order to control the brackets of the wings Expanding or contracting, the second bracket is hinged with a support element, and the second bracket is a retractable structure, and the expansion or contraction of the bracket is realized through the mutual cooperation of the support element and the second bracket. The whole operation process is simple and flexible.

(4) A kind of amphibious model aircraft of the present invention, in order to facilitate the second support to drive other supports to move, the third support and the fourth support are designed to be parallel to each other, and the third support is hingedly connected to the second support, When the second bracket rotates and expands, the fourth bracket moves accordingly, and under the action of each hinge point, it drives the third bracket, causing the fifth bracket and the sixth bracket to also rotate accordingly, so as to realize the expansion or contraction of the wings.

(5) A kind of water, land and air amphibious model airplane of the present invention, by setting the end of the fourth bracket and the fifth bracket close to the body into a curved shape, and designing two arcs on the corresponding curved end faces, the curved concave The degree direction is toward the middle of the curved shape. This structural design makes the bracket more flexible and convenient when shrinking or unfolding. At the same time, it also limits and guides the rotation of the bracket to ensure that the wings can be expanded or retracted.

(6) a kind of water, land and air amphibious model aircraft of the present invention, by adopting the tarpaulin that the carbon fiber of light weight, high elasticity, high tenacity, high modulus is made as the outer surface of wing, is used for guaranteeing the required airfoil of wing. Buoyancy, in addition, there are holes for placing ribs inside the tarpaulin, which are used to place ribs and provide certain support for the inside of the wing.

Description of drawings

Fig. 1 is a kind of water, land and air amphibious model aircraft structural representation of the present invention;

Fig. 2 is a structural representation of a water, land and air amphibious model aircraft traveling on land;

Fig. 3 is a schematic structural view of a water, land and air amphibious model aircraft navigating in water;

Fig. 4 is the internal structure schematic diagram of the amphibious model aircraft wing of water, land and air in the present invention;

Fig. 5 is the schematic diagram of the deployment of the fourth stent in the present invention;

Fig. 6 is a schematic structural view of a fourth bracket in the present invention;

Fig. 7 is a schematic structural view of a fifth bracket in the present invention;

Fig. 8 is a partial sectional structural schematic diagram of wing deployment in the present invention;

Fig. 9 is a schematic diagram of the installation structure of ribs in the present invention.

Explanation of the labels in the schematic diagram:

100, body; 200, supporting element; 300, wing; 310, upper fixed block; 311, first bracket; 312, first rotating shaft joint; 313, second rotating shaft joint; 314, third rotating shaft joint; 320, lower Fixed block; 321, second bracket; 322, fourth shaft joint; 323, fifth shaft joint; 330, third bracket; 331, sixth shaft joint; 340, fourth bracket; 3401, first end surface; 3402, 341, the seventh rotating shaft joint; 342, the eighth rotating shaft joint; 350, the fifth support; 3501, the third end face; 3502, the fourth end face; 360, the sixth support; 370, tarpaulin; 371, protection Side; 372, ribs; 410, propeller support; 411, propeller; 510, vertical tail; 520, horizontal tail; 600, submarine bridge; 710, tail propeller support; 711, tail propeller; 800, machine wheel.

Detailed ways

In order to further understand the content of the present invention, the present invention will be described in detail in conjunction with the accompanying drawings and embodiments.

Example 1

In the prior art, in order to ensure the stable flight of the model aircraft in the air, wings are generally symmetrically arranged on both sides of the model aircraft, the purpose of which is mainly to provide buoyancy for the model aircraft and ensure the stable flight of the model aircraft, but the model aircraft in the prior art The design of the wing structure of the aircraft is fixed, that is, the wings are fixed on the body of the model aircraft. When the model aircraft is flying with obstacles or in a narrow range, due to the fixed structure of the wings, it is easy to be damaged by surrounding obstacles. Collision damages the model aircraft. In addition, this type of aircraft cannot change the shape of the wing 300, which makes it not flexible enough to fly, and model aircraft enthusiasts are less interested in this model, thereby affecting the production and sales of model aircraft. Therefore, the design of model aircraft needs to be further improved.

As shown in Figure 1, a kind of water, land and air amphibious model aircraft of the present embodiment comprises body 100, wing 300, propeller 411, vertical empennage 510 and horizontal empennage 520, wherein, airframe 100 both sides are symmetrically provided with wing 300, the The wing 300 is a retractable wing, which can realize the expansion and contraction of the wing 300, and increase the flexibility of the wing 300 on the basis of ensuring the stable flight of the model aircraft, thereby increasing the interest of the model aircraft. In addition, there are two propellers 411 in this embodiment, and the propellers 411 are arranged on the propeller bracket 410, and the propeller brackets 410 are symmetrically arranged on both sides of the body 100, as shown in FIG. Flight provides propulsion. In addition, the vertical stabilizer 510 and the horizontal stabilizer 520 in this embodiment are arranged at the rear end of the airframe 100, and their design positions are shown in FIG. 1 . This structural design can ensure the flight stability of the model aircraft.

In this embodiment, the bottom of the body 100 is provided with a plurality of wheels 800 along its length direction, such as 2, 4, 8... As shown in Figure 2, the wheels 800 in this embodiment are provided with 4 , the four wheels 800 are divided into two groups, located at the front and rear ends of the body 100 respectively. The model airplane can travel on land through the wheel 800 . It is worth noting that the wheels 800 in this embodiment are arranged on the landing gear, which is a retractable structure. When the model aircraft is flying, the landing gear and the wheels 800 are retracted into the body 100 together, reducing the number of flights of the model aircraft. the resistance encountered. The structural design of the landing gear can be designed by adopting the structure of the aircraft landing gear in the prior art.

When the model airplane in this embodiment is running on land, its wings 300 shrink to fit the body 100, so as to reduce the resistance of the model airplane traveling on land and increase the speed of the model airplane. Simultaneously, its vertical tail 510 and horizontal tail 520 are designed into telescopic structure, as, vertical tail 510 is designed into two section structures, and this structure is similar to the structure of telescoping rod, and the last section of vertical tail 510 will Telescoping into the next section reduces the height of the vertical tail 510, thereby reducing the resistance of the model aircraft. Similarly, the horizontal tail 520 can also be designed with the same structure, thereby further reducing the resistance of the model aircraft.

In addition, as shown in FIG. 3 , a tail propeller 711 is provided at the tail of the body 100 in this embodiment, and the design of the tail propeller 711 is to ensure that the model aircraft can navigate in water and provide lift power for it. Preferably, the tail propeller 711 in this embodiment is installed on the tail propeller bracket 710, and the inside of the tail propeller bracket 710 is provided with a cavity, which can be used to store the tail propeller 711. When the model aircraft is flying or driving on land, In order to reduce drag, the tail propeller 711 can be retracted into the cavity of the tail propeller bracket 710 . 1 and 3 , in this embodiment, a submarine bridge 600 is provided above the front end of the body 100 , and a camera may be provided on the submarine bridge 600 to take pictures underwater. Preferably, the submarine bridge 600 in the present embodiment is a retractable structure, and the submarine bridge 600 stretches out from the body 100 when the model aircraft is traveling in water to photograph the underwater driving environment; when the model aircraft is flying or traveling on land, the submarine The bridge 600 shrinks into the inside of the body 100 to reduce the resistance of the model aircraft.

Preferably, the propeller bracket 410 installed on both sides of the body 100 in this embodiment is designed as a foldable retractable bracket. As shown in FIG. It can shrink along its length, which is the shrinking section. The front end of the shrinking section is a propeller 411. The propeller 411 can be shrunk into the shrinking section. The whole propeller bracket 410 can be rotated so that the propeller bracket 410 fits the body 100 , that is, the propeller bracket 410 rotates with the connection of the propeller bracket 410 and the body 100 as the rotation center. This structural design allows the propeller 411 and the propeller support 410 to be shrunk and the propeller support 410 to be folded when the model aircraft is traveling on land or in water, effectively reducing running resistance. The propeller 411 in this embodiment can adopt the propeller structure in the patent publication number CN 106573677A, that is, the propeller 411 can shrink, so as to ensure that the propeller 411 can shrink into the shrinking section.

In this embodiment, the model aircraft is designed with the above-mentioned structure, so that the model aircraft can be applied in the three fields of water, land and air, and the shape change ability of the model aircraft is strong, and the flexibility is high, which greatly improves the interest of the model aircraft and can Attracts model aircraft enthusiasts.

Preferably, the internal structure of the wing 300 in this embodiment is as shown in Figure 4, including a first bracket 311 and a second bracket 321 hingedly mounted on one side of the body 100, and the body 100 is provided with an upper fixing block along its length direction. 310 and the lower fixing block 320 , the first bracket 311 is hinged on the upper fixing block 310 through the first rotating shaft joint 312 , and the second bracket 321 is hinged on the lower fixing block 320 through the fourth rotating shaft joint 322 . In this embodiment, the end of the first bracket 311 away from the body 100 is hinged to the end of the third bracket 330 close to the body 100 through the second shaft joint 313, and at the same time, the end of the first bracket 311 away from the body 100 is also close to the fourth bracket 340 One end of the machine body 100 is hinged through the third pivot joint 314 . In this embodiment, the end of the second bracket 321 away from the body 100 is also hinged with the end of the fourth bracket 340 close to the body 100 through the fifth shaft joint 323, so that the first bracket 311, the second bracket 321, the body 100 and part of the first bracket 311 Four brackets 340 form a quadrilateral structure. In addition, in this embodiment, the end of the third bracket 330 away from the body 100 is hinged to the end of the fifth bracket 350 close to the body 100 through the sixth shaft joint 331; The end of the fifth bracket 350 close to the body 100 is hinged through the seventh shaft joint 341 , and the end of the fourth bracket 340 away from the body 100 is also hinged with the end of the sixth bracket 360 near the body 100 through the eighth shaft joint 342 . An end of the sixth bracket 360 away from the body 100 is connected to the fifth bracket 350 .

Preferably, each bracket in this embodiment is made of directional solidified TMD-5 alloy material with excellent performance, which has the characteristics of high specific strength and high specific stiffness, making the wing 300 more durable.

In this embodiment, the connections between the brackets are hinged. Under the action of the joints, the brackets can be rotated at the center of the joints, which is beneficial to the contraction and deployment of the wing 300 . In addition, due to the existence of the rotating shaft joints, the structure of the entire wing 300 tends to be that of a bird's wing, that is, the rotating shaft joints are equivalent to the parts between the joints of the bones, which facilitate the rotation of the bracket.

It is worth noting that the second support 321 in this embodiment is a retractable structure, which can be controlled by an air cylinder or an oil cylinder, so that the first support 311, the second support 321, the body 100 and part of the fourth support 340 surround The formed quadrilateral is a movable quadrilateral, which is convenient for driving the fourth bracket 340 to move when the second bracket 321 expands and contracts.

In the amphibious model aircraft of this embodiment, as shown in Figure 4, when the wings 300 need to be deployed, the second support 321 begins to shrink, and under the contraction force and hinged joint, the fourth support 340 is articulated with the fifth rotating shaft. 323 is the center of rotation, which rotates clockwise. Due to the limitation of the joints of the rotating shafts, the third bracket 330 rotates with the fourth bracket 340. When the third bracket 330 rotates to a certain degree, the third bracket 330 drives the fifth bracket 350 to The sixth rotating shaft joint 331 is the center of rotation, and rotates counterclockwise to unfold the wing 300 . Similarly, the second bracket 321 is elongated, and under the action of thrust and hinge, the fourth bracket 340 rotates counterclockwise, and then the fifth bracket 350 rotates clockwise to realize the contraction of the wing 300 . The entire wing 300 has a simple structural design and flexible operation, and the entire wing 300 can be contracted or expanded only by controlling the contraction of the second bracket 321 .

To further illustrate, the distance between the third pivot joint 314 and the fifth pivot joint 323 in this embodiment is fixed, so that the telescopic length of the second bracket 321 is limited, that is, the second bracket 321 and the first bracket The rotation range of 311 is limited. As shown in FIG. 5 , the circular dotted line in the figure is a circle formed by taking the third rotating shaft joint 314 as the center and the distance between the third rotating shaft joint 314 and the fifth rotating shaft joint 323 as the radius. Assuming that the first bracket 311 is fixed, the second bracket 321 changes from the solid line in the figure to the dotted line in the figure, that is, the second bracket 321 shrinks, and the third rotation axis joint 314, the fifth rotation axis joint 323 and the fourth rotation axis joint Under the action of 322, the fourth bracket 340 is rotated clockwise, that is, the position of the solid line in the figure is moved to the position of the dotted line in the figure, and the fourth bracket 340 of the solid line is deployed.

In addition, the designed positions of the second rotating shaft joint 313 and the third rotating shaft joint 314 in this embodiment are shown in FIG. The joint 313 is arranged on the side wall close to the third rotating shaft joint 314. When the fourth support 340 and the third support 330 rotate, because the lengths of the third support 330 and the fourth support 340 are fixed, when the fourth support 340 and the third support 340 are fixed, When the third bracket 330 rotates clockwise, and the third bracket 330 and the fourth bracket 340 rotate at a height lower than the fifth shaft joint 323, the end of the third bracket 330 away from the body 100 starts to be higher than the fourth bracket 340 away from the body 100 At one end, the third bracket 330 provides a certain pulling force for the fifth bracket 350 , so that the fifth bracket 350 rotates counterclockwise, so that each bracket is stretched apart, that is, the wing 300 is unfolded.

It is worth noting that in this embodiment, in order to ensure that the entire wing 300 is in the unfolded state, there is a relatively large angle between the wing 300 and the body 100, so that the wing 300 can effectively provide buoyancy, so that the model aircraft can Flying, as shown in Figure 4, since the length of the first bracket 311 is a fixed value, and the length of the expansion and contraction of the second bracket 321 is limited, the longer the length of the second bracket 321, the folder between the wing 300 and the body 100 in the unfolded state. The larger the angle, therefore, the distance between the upper fixed block 310 and the lower fixed block 320 is not easy to be too large. In this embodiment, the distance between the upper fixed block 310 and the lower fixed block 320 is the third rotating shaft joint 314 and the fifth rotating shaft 1.0-1.6 times the distance between joints 323 .

Preferably, the distance between the upper fixing block 310 and the lower fixing block 320 in this embodiment is 1.5 times the distance between the third rotating shaft joint 314 and the fifth rotating shaft joint 323 .

During the flight of the model airplane, when encountering an obstacle, the wing 300 can be controlled to shrink properly, so that the model airplane can pass through the obstacle. In addition, during the flight, the flying speed of the model aircraft can be controlled by changing the size of the wing 300 to open, and the buoyancy provided by the wing 300, so that the model aircraft can fly more flexibly.

It is worth noting that, in this embodiment, the wing 300 may cause the second bracket 321 to be fully attached to the body 100 in the process of unfolding. Therefore, in order to avoid this phenomenon, in this embodiment, the body 100 is provided with a support element 200, the support element 200 is hinged with the second bracket 321, the purpose of the support element 200 is to support the second bracket 321, so that the second bracket 321 rotates counterclockwise, to ensure that the wings 300 and the body 100 Forming a certain angle facilitates the deployment of the wings 300, which is beneficial to the flight of the model airplane and effectively ensures the stability of the flight of the model airplane.

Example 2

A kind of water, land and air amphibious model aircraft of this embodiment is basically the same as Embodiment 1, further: in conjunction with Fig. 4, in this embodiment, the third support 330 and the fourth support 340 are designed to be parallel to each other, the second support 321 drives the fourth bracket 340 to move during the expansion and contraction process. Since the two ends of the fourth bracket 340 are connected to the two ends of the third bracket 330 through the joint of the rotating shaft, the third bracket 330 also moves together with the fourth bracket 340, and at the same time The fifth bracket 350 and the sixth bracket 360 are driven to move together to realize the expansion or contraction of the wing 300 .

In this embodiment, the end of the fourth bracket 340 close to the body 100 is curved, and the curved end surface includes a first end surface 3401 and a second end surface 3402. Referring to FIG. 4 and FIG. 6, the first end surface 3401 and the second end surface 3402 is arc-shaped, and the concavity direction of the arc is toward the middle of the curved shape. The third pivot joint 314 is located on the first end surface 3401 , and the fifth pivot joint 323 is located on the second end surface 3402 .

In addition, the end of the fifth bracket 350 in this embodiment close to the body 100 is curved, and the curved end surface includes a third end surface 3501 and a fourth end surface 3502. Referring to FIGS. 4 and 7, the third end surface 3501 and the fourth end surface The four end surfaces 3502 are arc-shaped, and the concavity direction of the arc is toward the middle of the curved shape. The sixth rotating shaft joint 331 is located on the third end surface 3501 , and the seventh rotating shaft joint 341 is located on the fourth end surface 3502 .

In this embodiment, the fourth bracket 340 and the fifth bracket 350 are designed into the above-mentioned shapes. When each bracket in the wing 300 rotates, due to the existence of the arc-shaped end face, the rotation of the bracket is limited and guided, so that the bracket The rotation is more flexible, ensuring that the wing 300 can be normally deployed or retracted.

Example 3

A kind of water, land and air amphibious model aircraft of the present embodiment is basically the same as embodiment 2, further: in the present embodiment, on the contacting surface between the second bracket 321 and the fourth bracket 340, the wheels that mesh with each other are correspondingly provided. teeth, when the second bracket 321 moves, the fourth bracket 340 rotates, and under the effect of gear teeth meshing, both the second bracket 321 and the fourth bracket 340 rotate synchronously, that is, the two rotate relatively. On the one hand, this structure can Improve the expansion or contraction efficiency of the wing 300. On the other hand, when the gear teeth mesh and rotate, the second bracket 321 will receive the force transmitted by the fourth bracket 340 through the gear teeth, so that the second bracket 321 will rotate, especially when the wing 300 is unfolded. , further avoiding the occurrence of the situation that the second bracket 321 is attached to the body 100 .

In this embodiment, the gear teeth provided between the supporting element 200 and the second bracket 321 and the fourth bracket 340 cooperate together to effectively avoid the occurrence of the second bracket 321 being attached to the body 100 .

In the same way, in this embodiment, the contacting surfaces between the third bracket 330 and the fifth bracket 350 are also provided with gear teeth that mesh with each other, and cooperate with each other between the second bracket 321 and the fourth bracket 340 to facilitate the machine. Contraction and deployment of wings 300 .

Example 4

A kind of water, land and air amphibious model aircraft of this embodiment is basically the same as embodiment 3, and further: in combination with Fig. 8 and Fig. 9, since the wings 300 are installed on both sides of the model aircraft, certain buoyancy is provided for the model aircraft, through The buoyancy counteracts the gravity of the model aircraft itself, suspending the model aircraft in the air. Preferably, in this embodiment, in order to reduce the gravity of the model aircraft itself, the outside of the wing 300 is wrapped by a tarpaulin 370, and it is wrapped into a wing shape. It is worth noting that the tarpaulin 370 in this embodiment is made of M60G carbon fibers with a diameter of 0.1-0.5 mm are woven, and the woven tarpaulin 370 has a thickness of 3-5 mm. As a new type of material, M60G carbon fiber is light in weight and can effectively reduce the overall weight of the model aircraft, so that the buoyancy to be provided by the wing 300 is small, so the requirements for each bracket inside the wing 300 are small, which is beneficial to the airfoil. 300 in production. In addition, the M60G carbon fiber also has the properties of high elasticity, high toughness, and high modulus, which play an important role in the manufacture and use of the wing 300 .

The tarpaulin 370 in this embodiment can be woven into a tarpaulin 370 with a thickness of 3 mm by using M60G carbon fibers with a diameter of 0.1 mm. M60G carbon fibers with a diameter of 0.5 mm can also be used to weave the tarpaulin 370 with a thickness of 5 mm.

As a preference, in this embodiment, M60G carbon fibers with a diameter of 0.2 mm are used to weave a tarpaulin 370 with a thickness of 4 mm.

In addition, when the model airplane in this embodiment is flying, its wings 300 are in the unfolded state, but because the quality of the tarpaulin 370 is relatively light, it is easy to cause the phenomenon that the tarpaulin 370 turns upwards, or the tarpaulin 370 shakes in a wave shape, resulting in Model airplanes cannot fly smoothly in the air. Therefore, in order to avoid the occurrence of this phenomenon, as shown in FIG. The opening direction is the same as the length direction of the body 100. The rib placement holes are used to place ribs 372, and the tarpaulin 370 of the wing 300 is supported by a plurality of ribs 372 to ensure the flight stability of the model aircraft. The ribs 372 in this embodiment have a diameter of 20-50mm. Such as 20mm, 25mm, 40mm, 50mm.

Preferably, ribs 372 with a diameter of 25 mm are used in this embodiment.

As shown in Figure 8, in the present embodiment, the bottom edge of the tarpaulin 370 is provided with a protective edge 371 along its circumference. Under normal circumstances, its bottom turns upwards, and the weight of the bottom of the wing 300 is increased by providing the protective edge 371, so as to avoid the turning of the tarpaulin 370. As a preference, the protective edge 371 in this embodiment is made of M60G carbon fiber, and the protective edge 371 is a column with a diameter of 5-10mm, such as 5mm, 6mm, 8mm, 10mm. As a preference, the diameter of the columnar body in this embodiment is 8 mm.

It should be noted that during the flight of the model aircraft in this embodiment, the tarpaulin 370 provides upward force for the wing 300 under the action of the flowing air. At the rear portion of the wing 300, i.e. the bottom, when the wing 300 is subjected to a force, its tarpaulin 370 will bulge upwards in the middle, and its wing 300 is bowed from front to back, which is conducive to the flow of air and can be The model aircraft provides effective buoyancy to ensure the flight stability of the model aircraft.

A method for deploying the wing of an amphibious amphibious model aircraft of the present embodiment, the steps are:

a. The second bracket 321 hingedly connected to the body 100 is a telescopic structure. When the second bracket 321 shrinks, the fourth bracket 340 hinged to the second bracket 321 rotates clockwise;

b. When the fourth bracket 340 rotates, since both ends of the fourth bracket 340 are connected to the third bracket 330 through hinges, the third bracket 330 also rotates clockwise;

c. While the third bracket 330 rotates, the fifth bracket 350 hinged with the third bracket 330 rotates counterclockwise, and at the same time, the sixth bracket 360 of the fifth bracket 350 also rotates counterclockwise; unfold the wing 300 ;

d. The supporting element 200 works, and the supporting element 200 pushes the second bracket 321 away from the body 100 . Under the action of the hinge point, the second bracket 321 rotates counterclockwise, so that the wing 300 as a whole forms a certain angle with the body 100 .

It is worth noting that, in the method of shrinking the wing 300 in this embodiment, it is only necessary to control the extension of the second bracket 321 so that the rotation direction of each bracket is opposite, and the shrinking can be realized. In addition, the order of step d in this embodiment can be arbitrary, that is, it can be performed in any one of steps a to c, as long as it is ensured that the wing 300 as a whole forms a certain angle with the body 100 .

The above schematically describes the present invention and its implementation, which is not restrictive, and what is shown in the drawings is only one of the implementations of the present invention, and the actual structure is not limited thereto. Therefore, if a person of ordinary skill in the art is inspired by it, without departing from the inventive concept of the present invention, without creatively designing a structural mode and embodiment similar to the technical solution, it shall all belong to the protection scope of the present invention .

Claims (10)

1. a method for deploying the wing of an amphibious model airplane in water, land and air, characterized in that: a kind of amphibious model airplane in water, land and air is utilized, and its steps are, a. The second bracket (321) hinged to the body (100) is a telescopic structure. When the second bracket (321) shrinks, the fourth bracket (340) hinged with the second bracket (321) moves clockwise. turn; b. When the fourth bracket (340) rotates, since both ends of the fourth bracket (340) are hinged to the third bracket (330), the third bracket (330) also rotates clockwise; c. While the third bracket (330) rotates, the fifth bracket (350) hinged with the third bracket (330) rotates counterclockwise, and the sixth bracket (360) of the fifth bracket (350) also rotates counterclockwise. Rotate counterclockwise together; Wing (300) is launched; d. The support element (200) works, and the second bracket (321) is pushed away from the body (100) through the support element (200). Under the action of the hinge point, the second bracket (321) rotates counterclockwise, so that the body The wing (300) as a whole forms a certain angle with the body (100). 2. The method for deploying the wing of an amphibious model aircraft according to claim 1, wherein the amphibious model aircraft comprises a body (100), a wing (300), and a propeller (411) , a vertical empennage (510) and a horizontal empennage (520), the wing (300) is a retractable wing, and the inside of the wing (300) realizes the expansion of the wing (300) and the Shrink; the propeller (411) is arranged on the propeller support (410), and the propeller support (410) is a foldable retractable support; the tail of the body (100) is also provided with a tail propeller (711); the body ( 100) The bottom is provided with a plurality of wheels (800) along its length. 3. The method for deploying the wing of an amphibious amphibious model aircraft according to claim 2, characterized in that: the wing (300) comprises a first bracket (311) hingedly mounted on one side of the body (100) and the second support (321), the end of the first support (311) away from the body (100) is hinged to the end of the third support (330) and the fourth support (340) close to the body (100), the second The end of the bracket (321) away from the body (100) is also hinged with the end of the fourth bracket (340) close to the body (100), and the end of the third bracket (330) away from the body (100) is hinged with the fifth bracket (350) One end close to the body (100) is hinged; the end of the fourth bracket (340) away from the body (100) is hinged to the end of the fifth bracket (350) and the sixth bracket (360) close to the body (100), and the sixth The end of the bracket (360) away from the body (100) is connected to the fifth bracket (350); the side wall of the second bracket (321) is hinged to a support element (200), and the support element (200) is arranged on the body (100) up. 4. The method for deploying wings of an amphibious amphibious model aircraft according to claim 3, characterized in that: the third support (330) and the fourth support (340) are parallel to each other. 5. The method for deploying the wing of an amphibious amphibious model aircraft according to claim 4, characterized in that: the end of the fourth bracket (340) close to the body (100) is curved, and the curved The end surface includes a first end surface (3401) and a second end surface (3402), the first end surface and the second end surface (3402) are arc-shaped, and the concavity direction of the arc is toward the middle of the curved shape, the first bracket The hinge point between (311) and the fourth bracket (340) is located on the first end surface (3401), and the hinge point between the second bracket (321) and the fourth bracket (340) is located on the second end surface (3402). 6. The method for deploying the wing of an amphibious amphibious model aircraft according to claim 5, characterized in that: the end of the fifth bracket (350) close to the body (100) is curved, and the curved The end surface includes a third end surface (3501) and a fourth end surface (3502), the third end surface (3501) and the fourth end surface (3502) are arc-shaped, and the concavity direction of the arc is toward the middle of the curved shape, the The hinge point of the third bracket (330) and the fifth bracket (350) is located at the third end surface (3501), and the hinge point of the fourth bracket (340) and the fifth bracket (350) is located at the fourth end surface (3502). 7. The method for deploying the wing of an amphibious amphibious model aircraft according to claim 4 or 6, characterized in that: the second support (321) and the fourth support (340) are also carried out through gear teeth. Engagement: The third bracket (330) and the fifth bracket (350) are also engaged through gear teeth. 8. The method for deploying the wing of an amphibious amphibious model aircraft according to claim 7, characterized in that: the outside of the bracket is wrapped into a wing shape by a tarpaulin (370) woven from carbon fibers, and the tarpaulin (370) A plurality of rib placement holes are arranged inside, and the rib placement holes are opened along the length direction of the body (100) for placing ribs (372). 9. The method for deploying wings of an amphibious amphibious model aircraft according to claim 8, characterized in that: the diameter of the M60G carbon fiber is 0.1-0.5mm, and the thickness of the woven tarpaulin (370) is 3 -5mm; the diameter of the rib (372) is 20-50mm. 10. The method for deploying the wing of an amphibious amphibious model aircraft according to claim 8, characterized in that: the bottom edge of the tarpaulin (370) is provided with a protective edge (371) along its circumference, and the protective edge (371) It consists of a cylindrical body with a diameter of 5-10mm, which is made of carbon fiber.