A model airplane with different levels of ducted power units

Abstract

This utility model discloses a model aircraft with selectable ducted motor units of different levels. The model aircraft body is provided with a power cavity for installing the power assembly. The power assembly includes a small-level ducted motor unit and a large-level ducted motor unit, which can be selectively installed in the power cavity of the model aircraft body during assembly. The large-level ducted motor unit corresponds to the inner diameter of the power cavity of the model aircraft body and is tightly installed in the power cavity. A limiting component is pre-installed in the power cavity, and the small-level ducted motor unit is used in conjunction with the limiting component to achieve a tight installation of the small-level ducted motor unit in the power cavity. This allows for the combined application of a 70mm large-level power assembly and a 64mm small-level power assembly, and users can independently change the power assembly according to flight needs (such as conventional flight or aerobatic flight). The power cavity of the model aircraft can be directly adapted to the 70mm power assembly, while the 64mm power assembly can be tightly installed with the limiting component, allowing for the switching of different levels of power assembly without modifying the fuselage body.

Description

Technical Field

[0001] This utility model belongs to the field of model aircraft technology and relates to a model aircraft with selectable ducted power units of different levels. Background Technology

[0002] Currently, the ducted power units of traditional ducted-powered model aircraft typically adopt a fixed matching design, meaning that the power chamber size of the model aircraft body is only compatible with a single specification of ducted power unit.

[0003] When users need to replace the power unit with a different thrust according to flight requirements, they cannot directly replace it with other types of ducted power units due to the limitations of the power chamber size and the fixed installation structure.

[0004] If different levels of power units are required, users often need to purchase multiple model airplanes with different configurations, which not only increases the cost of use, but also makes it impossible to flexibly switch the power of the same airframe, thus significantly limiting the applicability and cost-effectiveness of model airplanes. Utility Model Content

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] A model aircraft with selectable levels of ducted power units, including:

[0007] The model aircraft body has a power chamber for installing power components and a power chamber cover for sealing the power chamber.

[0008] The power unit includes a small-scale ducted power unit and a large-scale ducted power unit. During assembly, one can be selected and installed in the power chamber of the model aircraft body in a detachable manner.

[0009] The large-scale ducted power unit corresponds to the inner diameter of the power cavity of the model aircraft body and is tightly installed in the power cavity;

[0010] Limiting components are pre-installed in the power chamber, and the small-scale ducted power unit works with the limiting components to achieve tight installation of the small-scale ducted power unit in the power chamber.

[0011] As a further embodiment of this utility model: mounting lugs are provided on both sides of the air duct of the small-scale ducted power unit and the large-scale ducted power unit.

[0012] The power chamber is equipped with mounting slots that correspond to the mounting lugs.

[0013] As a further embodiment of this utility model: the limiting component has a ring structure and is composed of a lower fixing plate, an upper pressing plate, and a connecting member;

[0014] The connector is fixed to the mounting slot, and the lower fixing plate is pressed into the power cavity. The mounting lugs, connectors and mounting slots of the small-level ducted power unit are connected and fitted by screw assembly to achieve installation.

[0015] The upper pressure plate is pressed onto the duct of the small-level ducted power unit through the power chamber cover, realizing the surrounding and limiting work of the limiting component on the small-level ducted power unit.

[0016] The beneficial effects of this invention are: it enables the combined application of a 70mm large-class power unit and a 64mm small-class power unit, allowing users to independently switch power units according to flight needs (such as conventional flight or aerobatic flight); the power chamber of the model aircraft can be directly adapted to the 70mm power unit, while the limiting component allows for a tight installation of the 64mm power unit, enabling switching between different power unit levels without modifying the fuselage. It meets conventional needs and is more cost-effective. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of this utility model.

[0018] Figure 2 This is another structural schematic diagram of this utility model.

[0019] Figure 3 This is a structural schematic diagram of the small-scale ducted power unit of this utility model.

[0020] Figure 4 This is a schematic diagram of the limiting component in this utility model. Detailed Implementation

[0021] 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.

[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] This utility model provides a reference. Figures 1-4 In this embodiment of the invention, a model aircraft with selectable ducted power units of different levels includes:

[0026] The model aircraft body 1 has a cylindrical power cavity 11 for installing the power unit 2. Its inner diameter is designed to match the outer diameter of the 70mm large-scale ducted power unit 21 to achieve a tight installation. The power cavity 11 is also equipped with a power cavity cover 12 for sealing the power cavity 11, so as to facilitate the disassembly, installation and replacement of the power unit 2.

[0027] Power unit 2 includes a 64mm small-scale ducted power unit 22 and a 70mm large-scale ducted power unit 21. During assembly, either can be selected and installed in the power cavity 11 of the model aircraft body 1 in a detachable manner. In actual use, users can choose to install and use the small-scale ducted power unit 22 or the large-scale ducted power unit 21 according to their own needs (the power unit is electrically connected to the internal power supply of the model aircraft body 1 through a freely pluggable connector wire).

[0028] Mounting lugs 221 are provided on both sides of the air duct of the small-level ducted power unit 22 and the large-level ducted power unit 21.

[0029] The power chamber 11 is provided with a mounting groove (not shown) corresponding to the mounting lug 221; during installation, the mounting lug 221 of the small-level ducted power unit 22 or the large-level ducted power unit 21 is placed in the mounting groove and connected by a screw assembly.

[0030] The inner diameter of the power chamber 11 of the model aircraft body 1 corresponds to the outer diameter of the wind tunnel of the large-scale ducted power unit 21 (70mm). In use, the large-scale ducted power unit 21 can be directly and tightly installed in the power chamber 11.

[0031] In order to ensure that the small-scale ducted power unit 22 can be tightly installed in the power cavity 11, a limiting component 3 is pre-installed in the power cavity 11. The small-scale ducted power unit 22, together with the limiting component 3, achieves tight installation of the small-scale ducted power unit in the power cavity 11.

[0032] The limiting component 3 has a ring structure and is composed of a lower fixing piece 32, an upper pressing piece 31, and a connecting piece 33.

[0033] The connector 33 is fixed to the mounting slot and the lower fixing piece 32 is pressed into the power chamber 11. The mounting lug 221, connector 33 and mounting slot of the small-level ducted power are connected and fitted by screw assembly to achieve installation.

[0034] The upper pressure plate 31 is pressed onto the air duct of the small-level ducted power unit 22 by the power cavity cover 12, realizing the surrounding and limiting work of the limiting component 3 on the small-level ducted power unit 22; the thickness of the lower fixing plate 32 and the upper pressure plate 31 in the limiting component 3 is the radius difference between the small-level ducted power unit 22 and the large-level ducted power unit 21, so that the small-level ducted power unit 22 can be tightly installed in the power cavity 11.

[0035] 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.

[0036] 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 having a ducted power unit of selectable levels, characterized in that, include: The model aircraft body has a power chamber for installing power components and a power chamber cover for sealing the power chamber. The power unit includes a small-scale ducted power unit and a large-scale ducted power unit. During assembly, one can be selected and installed in the power chamber of the model aircraft body in a detachable manner. The large-scale ducted power unit corresponds to the inner diameter of the power cavity of the model aircraft body and is tightly installed in the power cavity; Limiting components are pre-installed in the power chamber, and the small-scale ducted power unit works with the limiting components to achieve tight installation of the small-scale ducted power unit in the power chamber.

2. A model aircraft according to claim 1, wherein, Both small-scale and large-scale ducted power units have mounting lugs on both sides of the air duct. The power chamber is equipped with mounting slots that correspond to the mounting lugs.

3. A model aircraft having a selectable level of ducted propulsion assembly according to claim 2, wherein, The limiting component has a ring structure and consists of a lower fixing plate, an upper pressure plate, and connecting parts. The connector is fixed to the mounting slot, and the lower fixing plate is pressed into the power cavity. The mounting lugs, connectors and mounting slots of the small-level ducted power unit are connected and fitted by screw assembly to achieve installation. The upper pressure plate is pressed onto the duct of the small-level ducted power unit through the power chamber cover, realizing the surrounding and limiting work of the limiting component on the small-level ducted power unit.

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