Double-landing-wheel-set synchronous retracting and releasing mechanism for model airplane

Abstract

The utility model discloses a double-landing-wheel-set synchronous retracting and releasing mechanism for a model airplane. The double-landing-wheel-set synchronous retracting and releasing mechanism comprises a wheel carrier base installed on the model airplane, a server arranged in the wheel carrier base, a landing wheel base and landing wheel sets installed on the two sides of the landing wheel base. The server is installed in the middle of the front ends of the two landing wheel sets, a push rod of the server moves forwards, a connecting rotating base is installed on the push rod, and the two ends of the connecting rotating base are rotationally matched with the wheel carrier base. A group of wheel carrier pull rods are arranged between the landing wheel seat and the connecting rotary seat; two ends of the wheel carrier pull rods are respectively hinged and matched with the landing wheel seat and the connecting rotary seat; the design structure that one server is installed in the middle is adopted, the two landing wheel sets are controlled to be folded and unfolded at the same time through one server, and compared with a traditional control mode of two servers, the space in the model airplane is remarkably saved; more possibilities are provided for layout of other parts of the model airplane, and the structural compactness and functionality of the whole airplane are effectively improved.

Description

Technical Field

[0001] This utility model belongs to the field of model aircraft technology and relates to a synchronous deployment and retraction mechanism for dual landing wheel sets used in model aircraft. Background Technology

[0002] In the field of model aircraft, the design and performance of the landing gear have a crucial impact on the flight experience and overall functionality. Traditional model aircraft nose landing gear often uses a monotube structure, which consists of a main boom with one or more wheels, and the landing gear retraction and extension are controlled one-to-one by a servo. While this structure is simple and occupies little space, making it suitable for realistic scale models of light-load aircraft, it cannot meet the load requirements of model aircraft that need to carry greater weight and simulate scenarios such as heavy transport aircraft.

[0003] In the design of heavy transport aircraft model airplanes, a twin-tube landing gear is typically used, which is equivalent to having two sets of nose landing gear. According to conventional model airplane design, two sets of servos are needed to control these two sets of landing gear separately. However, this control method has several problems: First, the coordinated operation of the two sets of servos makes it difficult to ensure the synchronicity of the landing gear retraction and extension, easily leading to inconsistent retraction and extension between the two sets of landing gear, affecting the landing safety and stability of the model airplane; second, using two sets of servos increases the internal space occupation and system complexity of the model airplane, not only increasing design and manufacturing costs but also reducing system reliability. Utility Model Content

[0004] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0005] A synchronous deployment and retraction mechanism for dual landing gear sets for a model aircraft includes: a wheel frame base mounted on the model aircraft, a servo unit disposed within the wheel frame base, landing gear seats, and landing gear sets mounted on both sides of the landing gear seats; the outer cylinder of the landing gear sets is fixedly disposed on the landing gear seats.

[0006] The servo is installed at the front center of the two sets of landing wheels. The push rod of the servo moves forward and is equipped with a connecting swivel. The two ends of the connecting swivel are rotatably engaged with the wheel frame base.

[0007] A set of wheel frame tie rods is provided between the landing wheel seat and the connecting swivel, with both ends of the wheel frame tie rods hinged to the landing wheel seat and the connecting swivel respectively.

[0008] As a further embodiment of this utility model: a set of servo motors is also installed on the landing wheel base. The servo motors are located in the center of the landing wheel base, and a set of steering linkages are installed on the steering disk of the servo motors. The two ends of the steering linkages are respectively connected to the wheel axles of the landing wheel assembly.

[0009] The beneficial effects of this utility model are as follows: This utility model adopts a design structure in which a single servo is centrally installed. By using a single servo to control the simultaneous retraction and extension of two sets of landing gear, compared with the traditional two-servo control method, it significantly saves internal space of the model aircraft; it also provides more possibilities for the layout of other components of the model aircraft, effectively improving the overall structural compactness and functionality of the aircraft. Attached Figure Description

[0010] Figure 1 This is a schematic diagram of the structure of this utility model.

[0011] Figure 2 This is another structural schematic diagram of this utility model. Detailed Implementation

[0012] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. It should be understood that this application is not limited to the exemplary embodiments disclosed herein. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0013] 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.

[0014] 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.

[0015] 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.

[0016] Please see Figures 1-2 In this embodiment of the present invention, a synchronous retraction and deployment mechanism for dual landing wheel sets for a model aircraft includes: a wheel frame base 7 installed on the model aircraft, a servo 1 (electric push rod) disposed in the wheel frame base 7, a landing wheel seat 4, and landing wheel sets 5 installed on both sides of the landing wheel seat 4; the outer cylinder 51 of the wheel set 5 is fixedly disposed on the landing wheel seat 4.

[0017] Servo 1 is installed at the front center of the two sets of landing wheel sets 5. The push rod of servo 1 moves forward and a connecting rotatable seat 8 is installed on the push rod. The two ends of the connecting rotatable seat 8 are rotatably engaged with the wheel frame base 7.

[0018] A set of wheel frame rods 9 is provided between the landing wheel seat 4 and the connecting rotatable seat 8. Both the landing wheel seat 4 and the connecting rotatable seat 8 are provided with hinge seats. The two ends of the wheel frame rods 9 are respectively hinged to the two sets of hinge seats to achieve hinged cooperation with the landing wheel seat 4 and the connecting rotatable seat 8.

[0019] During operation, the servo 1 is activated, and the push rod moves forward or backward. Because the connecting rotatable seat 8 is mounted on the push rod and rotates with the wheel frame base 7, the push rod cannot directly push the connecting rotatable seat 8 to translate. Instead, it is converted into the work of rotating the connecting rotatable seat 8. When the connecting rotatable seat 8 rotates, since one end of the wheel frame tie rod 9 is hinged to the connecting rotatable seat 8 and the other end is hinged to the landing wheel seat 4, the tension or thrust generated by the rotation of the connecting rotatable seat 8 is transmitted to the landing wheel seat 4 through the wheel frame tie rod 9.

[0020] When retracting the landing gear, the connecting swivel 8 rotates backward to pull the wheel frame lever 9, causing the landing wheel seat 4 to rise, which in turn drives the landing wheel assembly 5 on both sides to retract upward; when lowering the landing gear, the servo 1 controls the push rod to move in the opposite direction, the connecting swivel 8 rotates forward, pushes the wheel frame lever 9, causing the landing wheel seat 4 to fall, and drives the landing wheel assembly 5 to lower downward.

[0021] Furthermore, a set of servo motors 2 are also installed on the landing wheel base 4. The servo motors 2 are located in the center of the landing wheel base 4, and a set of steering connecting plates 3 are installed on the steering disk 21 of the servo motors 2. The two ends of the steering connecting plates 3 are connected to the wheel axles of the landing wheel assembly 5 respectively, so as to realize the steering control of the landing wheel assembly 5.

[0022] 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.

[0023] 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 synchronous retraction and deployment mechanism for dual landing gear sets in a model aircraft, characterized in that, include: The wheel frame base installed on the model airplane, as well as the servo unit, landing wheel mount, and landing wheel assembly installed on both sides of the landing wheel mount, all housed within the wheel frame base. The outer cylinder of the landing gear assembly is fixedly mounted on the landing gear seat; The servo is installed at the front center of the two sets of landing wheels. The push rod of the servo moves forward and is equipped with a connecting swivel. The two ends of the connecting swivel are rotatably engaged with the wheel frame base. A set of wheel frame tie rods is provided between the landing wheel seat and the connecting swivel, with the two ends of the wheel frame tie rods respectively hinged to the landing wheel seat and the connecting swivel.

2. The synchronous deployment and retraction mechanism for dual landing gear sets in a model aircraft according to claim 1, characterized in that, A set of servo motors is also installed on the landing wheel base. The servo motors are located in the center of the landing wheel base, and a set of steering linkages is installed on the steering disk of the servo motors. The two ends of the steering linkages are connected to the wheel axles of the landing wheel assembly.

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