Speed brake structure suitable for model airplane speed reduction

Abstract

The utility model relates to the field of model airplanes, in particular to a speed brake structure suitable for model airplane speed reduction. Deceleration assemblies are arranged on the left and right sides of the tail of the fuselage respectively; each speed reduction assembly comprises a server arranged at the tail of the fuselage and a mounting frame, speed reduction plates are rotationally arranged at the upper end and the lower end of the side, away from the fuselage, of the mounting frame correspondingly, and gear grooves are formed in the opposite faces of the sides, close to the mounting frame, of the two speed reduction plates. The speed reducing device has the advantages that the speed reducing assemblies are arranged on the left side and the right side of the tail of the machine body respectively, the speed reducing plates at the lower end are driven by the server to be pulled open in the speed reducing process, the two speed reducing plates are opened synchronously through meshing between gear grooves, the upper speed reducing plate and the lower speed reducing plate move synchronously in the whole process, symmetry is achieved, and the unfolding angle is large; the speed reduction effect is obvious, the flight attitude cannot be fluctuated, the tail space of the fuselage is borrowed, large-size control surfaces do not need to be reserved for the wings, and the practicability is improved.

Description

Technical Field

[0001] This utility model relates to the field of model aircraft, and in particular to a speed brake structure suitable for decelerating model aircraft. Background Technology

[0002] The deceleration mechanism of existing model aircraft or drones is achieved by using flaps. The function of flaps is to increase lift and drag. They can maintain low-speed flight in advance during landing. After landing, the increased drag will also significantly reduce the aircraft's gliding speed. At this time, the lift is also changing, and the flight control system needs to continuously control the aircraft's attitude.

[0003] However, this applies to aircraft that can utilize flaps. When there is no space to reserve flap structures, the aircraft's deceleration is particularly important for the safety of model aircraft. Utility Model Content

[0004] To overcome the shortcomings mentioned above, this utility model provides a technical solution that can solve the above problems.

[0005] A speed brake structure suitable for decelerating model aircraft, including a fuselage;

[0006] Speed ​​reduction components are installed on both the left and right sides of the rear of the fuselage;

[0007] The deceleration assembly includes a servo and a mounting frame located at the rear of the fuselage. The upper and lower ends of the mounting frame away from the fuselage are respectively equipped with deceleration plates. The two deceleration plates are provided with gear grooves on their opposite sides near the mounting frame, and the two gear grooves mesh with each other.

[0008] The lower end of the speed reducer is equipped with a first pull rod on the lower end face near the mounting frame, and the working end of the servo is equipped with a second pull rod. The first pull rod and the second pull rod are connected by a connecting belt.

[0009] As a further embodiment of this utility model: when the two speed reducers are combined, they cooperate with each other on both sides of the machine body to form a straight, extended line structure.

[0010] As a further embodiment of this utility model: the mounting frame is provided with limiting grooves for the speed reducer to rotate on the side near the speed reducer.

[0011] As a further embodiment of this utility model, the second pull rod is provided with multiple mounting holes vertically.

[0012] Compared with the prior art, the beneficial effects of this utility model are as follows: by setting deceleration components on the left and right sides of the tail of the fuselage, during deceleration, the servo drives the lower deceleration plate to open, and the meshing between the gear slots makes the two deceleration plates open synchronously. The entire process of the upper and lower deceleration plates moving synchronously and symmetrically, with a large opening angle, obvious deceleration effect, and no fluctuation in flight attitude. It makes use of the space at the tail of the fuselage, eliminating the need for large-sized control surfaces on the wings, thus improving practicality.

[0013] Additional aspects and advantages of this invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in this embodiment or the prior art, the drawings used in the description of the embodiment or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the existing technology.

[0016] Figure 2 This is a schematic diagram of the structure of the present invention.

[0017] Figure 3 This is a flight status diagram of the deceleration component.

[0018] Figure 4 This is a diagram showing the unused state of the deceleration component.

[0019] Figure 5 This is a diagram showing the usage status of the deceleration component.

[0020] The figure shows: 1. Body; 2. Reduction assembly; 3. Servo; 4. Mounting frame; 5. Reduction plate; 6. Gear groove; 7. First tie rod; 8. Second connecting rod; 9. Limiting groove; 10. Mounting hole. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] In the description of this utility model, it should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0023] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.

[0024] In the embodiments of this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0025] Please see Figure 2-5 A speed brake structure suitable for decelerating model aircraft, comprising a fuselage 1;

[0026] Speed ​​reduction components 2 are respectively installed on the left and right sides of the tail of the fuselage 1;

[0027] The deceleration assembly 2 includes a servo 3 and a mounting frame 4 located at the rear of the body 1. The upper and lower ends of the mounting frame 4 away from the body 1 are respectively rotatably equipped with deceleration plates 5. The two deceleration plates 5 are provided with gear grooves 6 on the opposite sides of the mounting frame 4, and the two gear grooves 6 mesh with each other.

[0028] The lower end of the speed reducer 5, which is located near the mounting frame 4, is provided with a first pull rod 7, and the working end of the servo 3 is provided with a second pull rod 8. The first pull rod 7 and the second pull rod 8 are connected by a connecting belt.

[0029] When deceleration is required, the servo 3 uses the connecting belt on the second lever 8 to pull the first lever 7 back, which drives the speed reduction plate 5 located at the lower end to open. By utilizing the meshing between the gear slots 6, the two speed reduction plates 5 open synchronously to complete the deceleration action.

[0030] A further solution: When the two speed brakes 5 are combined, they cooperate with the two sides of the fuselage 1 to form a straight, extended line structure.

[0031] When not in use, it can avoid affecting the streamlined shape of fuselage 1 and prevent flight fluctuations.

[0032] A further solution: The mounting frame 4 is provided with a limiting groove 9 on the side near the speed reducer 5 to allow the speed reducer 5 to rotate.

[0033] It can limit the opening angle of the speed reducer 5.

[0034] A further solution: The second tie rod 8 has multiple vertical mounting holes 10.

[0035] The angle at which the speed reducer 5 opens can be adjusted by setting the connecting strip on different mounting holes 10.

[0036] It should also be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0037] The above description of the disclosed embodiments enables those skilled in the art to make or use this application. 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 this application. Therefore, this application 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 speed brake structure suitable for decelerating model aircraft, characterized in that: The fuselage (1) is provided with a servo (3) at the tail thereof. The fuselage (1) is provided with a servo (3) at the tail thereof. The servo (3) and a mounting frame (4) are arranged at the tail of the fuselage (1), the upper and lower ends of the side of the mounting frame (4) away from the fuselage (1) are rotatably provided with two speed reduction plates (5), the opposite sides of the two speed reduction plates (5) close to the mounting frame (4) are provided with gear grooves (6), and the two gear grooves (6) are in meshing engagement. The lower end of the speed reduction plate (5) close to the mounting frame (4) is provided with a first pull rod (7), the working end of the servo (3) is provided with a second pull rod (8), and the first pull rod (7) and the second pull rod (8) are connected through a connecting belt.

2. The airfoil-shaped decal structure for use in model aircraft speed reduction according to claim 1, characterized in that: When the two speed reduction plates (5) are combined, the two speed reduction plates (5) and the two sides of the fuselage (1) are in cooperation and form a straight extension line structure.

3. The airfoil-shaped decal structure for use in model aircraft speed reduction according to claim 1, characterized in that: The side of the mounting frame (4) close to the speed reduction plate (5) is provided with a limiting groove (9) for the rotation of the speed reduction plate (5).

4. The airfoil-shaped decal structure for use in model aircraft speed reduction according to claim 1, characterized in that: A plurality of mounting holes (10) are vertically arranged on the second pull rod (8).

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