A model airplane with an engine unit capable of quick assembly and disassembly

Abstract

The utility model discloses a model airplane that engine group can quick dismounting, include: model airplane body, be provided with a plurality of installation site on the both sides wing of model airplane body, a plurality of power groups are installed on the installation site of both sides wing with detachable installation mode symmetry, with model airplane body electricity is connected, provides the kinetic energy for model airplane, realize when using, can not need to destroy the organism, can directly dismantle the effect of replacement failure power group, avoid the organism damage caused by the non - detachable, reduce maintenance loss, and single - set power group replacement can restore the whole machine operation, save maintenance cost. Moreover, the whole installation structure is efficient, stable, can realize quick dismounting replacement at the same time, realizes the effect that uses stably flies.

Description

Technical Field

[0001] This utility model belongs to the field of model aircraft technology and relates to a model aircraft with a quick-disassembly and assembly engine assembly. Background Technology

[0002] Currently, the installation of power units in multi-engine model aircraft commonly uses an assembly process that relies on adhesive. While this process ensures a strong connection, it has significant drawbacks: the adhesive is for single use only, and once the power unit is attached to the fuselage, disassembly and maintenance can only be performed by damaging the fuselage, making it impossible to quickly replace a faulty power unit.

[0003] For model aircraft equipped with multiple external engine sets, the probability of failure or damage of a single power set is much higher than that of a single-engine aircraft. Traditional processes result in high maintenance costs and low efficiency, making it difficult to meet the needs of rapid repair in actual use. Utility Model Content

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

[0005] A model airplane with a quickly detachable engine assembly, comprising:

[0006] The model airplane body has multiple mounting positions on both wings.

[0007] The multiple power units are symmetrically mounted on the mounting positions on both wings in a detachable manner, and are electrically connected to the model aircraft body to provide kinetic energy to the model aircraft.

[0008] As a further embodiment of this utility model: each power unit includes: a wind duct, a fan blade installed inside the wind duct, and a drive motor that drives the fan blade to move;

[0009] The upper end of the air duct is equipped with a rearward-extending mounting bracket, which is fixedly connected to the wing by a screw assembly;

[0010] The mounting bracket has an electrical probe at the corresponding mounting position, which is electrically connected to the drive motor; and the mounting position has an electrical contact at the corresponding position, which is electrically connected to the power supply of the model aircraft body; when the power unit is installed in the mounting position, the electrical probe and the electrical contact make contact and conduct electricity.

[0011] As a further embodiment of this utility model: the two ends of the mounting bracket are formed with outwardly extending screw connecting pieces; and the mounting position is provided with a corresponding connecting groove.

[0012] As a further embodiment of this utility model: the mounting bracket is provided with a limiting piece for limiting the mounting bracket installation; and the mounting position is provided with a corresponding limiting slot.

[0013] As a further embodiment of this utility model: the mounting position is located at the lower end of the wing; and the end of the mounting bracket is recessed to form a mounting groove corresponding to the mounting position, and the electrical probe and the limiting piece are both set in the mounting groove.

[0014] The beneficial effects of this utility model are: it enables the direct disassembly and replacement of faulty power units without damaging the airframe during use; it avoids airframe damage caused by non-removable components, reduces maintenance losses, and restores the entire aircraft to operation simply by replacing a single power unit, saving maintenance costs. Furthermore, the overall installation structure is efficient and stable; it achieves both rapid disassembly and replacement while maintaining stable flight performance. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of this utility model.

[0016] Figure 2 This is a schematic diagram of the installation structure of this utility model.

[0017] Figure 3 This is a schematic diagram of the mounting position in this utility model.

[0018] Figure 4 This is a schematic diagram of the power unit in this utility model.

[0019] Figure 5 This is another structural schematic diagram of the power unit in this utility model. Detailed Implementation

[0020] 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.

[0021] 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.

[0022] 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.

[0023] 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.

[0024] This utility model provides a reference. Figures 1-5 In this embodiment of the invention, a model airplane with a quickly detachable engine assembly includes:

[0025] The model aircraft body 1 has multiple mounting positions 111 on its two wings 11.

[0026] The multiple power units 2 are symmetrically mounted on the mounting positions 111 of the wings 11 on both sides in a detachable manner, and are electrically connected to the model aircraft body 1 to provide kinetic energy to the model aircraft.

[0027] This technology enables the rapid disassembly and installation of the power unit 2; in actual use, it allows for the quick replacement of faulty power units 2, effectively reducing the overall maintenance and operating costs of the model aircraft.

[0028] Furthermore, each power unit 2 includes: a wind tunnel 21, a fan blade 28 disposed inside the wind tunnel 21, and a drive motor 27 that drives the fan blade 28 to move.

[0029] The drive motor 27 drives the fan blade 28 to rotate at high speed. Through the action of the blade on the air, the airflow is accelerated in the fan duct 21, generating thrust to drive the model airplane to fly. In order to ensure the stability of the model airplane, the structural parameters (e.g., the diameter of the fan duct 21, the diameter of the fan blade 28, and the power of the drive motor 27) in each power unit 2 in the wing 11 are the same.

[0030] The upper end of the air duct 21 is provided with a rearwardly extending mounting bracket 22, which is fixedly connected to the wing 11 by a screw assembly 3;

[0031] A power probe 24 is provided at the mounting position 111 on the mounting bracket 22. The power probe 24 is electrically connected to the drive motor 27. A power contact 112 is provided at the corresponding position on the mounting position 111. The power contact 112 is electrically connected to the power supply of the model aircraft body 1. When the power unit 2 is installed on the mounting position 111, the power probe 24 and the power contact 112 make contact and conduct electricity, so as to supply power to the power unit 2.

[0032] Furthermore, the mounting bracket 22 has outwardly extending screw connecting pieces 26 (with screw through holes) at both ends; and the mounting position 111 is provided with a corresponding connecting groove 114.

[0033] The screw hole 115 is located in the connecting groove 114. During installation, the screw assembly 3 passes through the screw through hole and connects with the screw hole 115 to realize the installation of the mounting bracket 22 on the mounting position 111. The outwardly extending screw connecting piece 26 provides more space for screw installation and makes it easier to disassemble and assemble the power unit 2.

[0034] Furthermore, the mounting bracket 22 is provided with a limiting piece 23 for limiting the installation of the mounting bracket 22; and the mounting position 111 is provided with a corresponding limiting slot 113.

[0035] Furthermore, the limiting piece 23 is divided into a horizontal limiting piece 232 and a vertical limiting piece 231 according to its position and orientation. When the power unit 2 is installed, the limiting piece 23 will be embedded in the limiting slot 113 to realize the limiting work of the mounting bracket 22 in the horizontal and vertical directions, and together with the screw assembly 3, the power unit 2 can be stably installed.

[0036] Furthermore, the mounting position 111 is located at the lower end of the wing 11; while the end of the mounting bracket 22 is recessed to form a mounting groove 25 corresponding to the mounting position 111. The electrical probe 24 and the limiting piece 23 are both set in the mounting groove 25. When the mounting bracket 22 is installed on the mounting position 111, the upper edge of the mounting bracket 22 and the upper end of the wing 11 form a smooth transition structure, making the flight of the model aircraft smoother.

[0037] 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.

[0038] 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 model airplane with a quickly detachable engine assembly, characterized in that, include: The model airplane body has multiple mounting positions on both wings. The multiple power units are symmetrically mounted on the mounting positions on both wings in a detachable manner, and are electrically connected to the model aircraft body to provide kinetic energy to the model aircraft.

2. The model airplane with a quickly detachable engine assembly according to claim 1, characterized in that, Each power unit includes: a wind tunnel, fan blades installed inside the wind tunnel, and a drive motor that drives the fan blades to move; The upper end of the air duct is equipped with a rearward-extending mounting bracket, which is fixedly connected to the wing by a screw assembly; The mounting bracket has an electrical probe at the corresponding mounting position, which is electrically connected to the drive motor; and the mounting position has an electrical contact at the corresponding position, which is electrically connected to the power supply of the model aircraft body; when the power unit is installed in the mounting position, the electrical probe and the electrical contact make contact and conduct electricity.

3. A model airplane with a quickly detachable engine assembly according to claim 2, characterized in that, The mounting bracket has outwardly extending screw connecting pieces at both ends; and the mounting position has a corresponding connecting groove.

4. A model airplane with a quickly detachable engine assembly according to claim 2, characterized in that, The mounting bracket is equipped with a limiting piece for limiting the mounting bracket installation; and the mounting position is equipped with a corresponding limiting slot.

5. A model airplane with a quickly detachable engine assembly according to claim 4, characterized in that, The mounting position is located at the lower end of the wing; the end of the mounting bracket is recessed to form a mounting groove corresponding to the mounting position, and the electrical probe and the limiting piece are both set in the mounting groove.

Images