A modular aircraft

Abstract

This utility model discloses a modular aircraft in the field of aircraft technology, including a control fuselage. A support assembly is installed at the bottom of the control fuselage, and propulsion assemblies are distributed around the outer perimeter of the control fuselage. The propulsion assemblies include two sets of first propellers, which are respectively connected to both ends of the control fuselage. Two sets of second propellers are also respectively provided on both sides of the control fuselage. The modular aircraft designed in this scheme, through its unique connection method, makes the process of disassembly, assembly, repair, and replacement more convenient. When the propulsion assembly needs to be maintained or replaced, the staff only needs to use tools to release the magnetic engagement to easily remove the faulty first or second propeller for individual repair or replacement. If the landing gear has a problem, the fixing screw can also be quickly unscrewed to remove it from the bottom of the fuselage. When installing new parts, the operation is carried out in the reverse order, which greatly saves maintenance time and labor costs.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a modular aircraft. Background Technology

[0002] Modular aircraft refer to aircraft designed using a modular approach, dividing their functional components into relatively independent, standardized modular units, such as propulsion modules, control modules, mission payload modules, and energy modules. These modules are interchangeable and independent, allowing for flexible combination, rapid replacement, or upgrades based on different mission requirements. Modular aircraft enhance design and manufacturing flexibility, shorten development cycles, reduce maintenance and modification costs, and adapt to diverse application scenarios, such as reconnaissance, transportation, and communication.

[0003] Currently, aircraft are widely used in various fields such as air transport, aerial reconnaissance, emergency rescue, and scientific exploration. Traditional aircraft mostly adopt an integrated structural design, with fixed functional configurations and high integration. While this provides a certain degree of stability, it also has significant limitations in adapting to diverse mission requirements, reducing maintenance costs, and improving module replacement efficiency. In particular, if a component of an integrated aircraft fails during mission execution, the entire aircraft often needs to be repaired or replaced, resulting in wasted resources and difficulty in rapid deployment. Therefore, these limitations exist in its use.

[0004] Therefore, developing a modular aircraft structure capable of rapid assembly and disassembly of functional components to enhance system flexibility, scalability, and adaptability has become a research hotspot in the field of aircraft design. Based on this, we propose a modular aircraft. Utility Model Content

[0005] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of the present invention, to avoid obscuring the purpose of these documents, and such simplifications or omissions should not be construed as limiting the scope of the present invention.

[0006] Therefore, the purpose of this utility model is to provide a modular aircraft that can solve the problem that traditional aircraft, due to their integrated structure, have fixed functional configurations and high integration, which have significant limitations in adapting to diverse mission requirements, reducing maintenance costs, improving module replacement efficiency, and enabling rapid deployment.

[0007] To solve the above-mentioned technical problems, this utility model provides a modular aircraft, which adopts the following technical solution: it includes a control fuselage, a support assembly is installed at the bottom of the control fuselage, and propulsion assemblies are distributed around the outer perimeter of the control fuselage. The propulsion assembly includes two sets of first thrusters, which are respectively connected to both ends of the control fuselage. Two sets of second thrusters are also respectively provided on both sides of the control fuselage.

[0008] Optionally, a first electromagnetic block is provided at both ends of the control body, and four sets of conductive brackets are respectively connected to the two sides of the control body near the first electromagnetic block. A fixing screw head is also installed at the bottom of the control body.

[0009] Optionally, the support assembly includes a landing gear, the top of which has a fixing screw hole that matches the fixing screw head structure, and the fixing screw hole and the fixing screw head are threaded together.

[0010] Optionally, the first thruster includes a first support frame, with two sets of second electromagnetic blocks installed at one end of the first support frame. The second electromagnetic blocks are structurally matched with the first electromagnetic blocks, and the second electromagnetic blocks and the first electromagnetic blocks are magnetically attracted to each other. Positioning plates are also installed on both sides of the first support frame near the second electromagnetic blocks.

[0011] Optionally, the second thruster includes a second support frame, and a positioning slot is provided on one side of the second support frame. The positioning slot matches the positioning plate structure, and the positioning slot and the positioning plate are engaged in a snap-fit ​​relationship.

[0012] Optionally, two sets of conductive plates are installed on the side of the second support frame near the positioning slot. The conductive plates are matched with the conductive card base structure, and the conductive plates and the conductive card base are engaged by a snap-fit. A strong magnetic layer is also provided on the side of the second support frame near the two sets of conductive plates.

[0013] In summary, this utility model has at least one of the following beneficial effects:

[0014] 1. The modular aircraft designed in this scheme, through its unique connection method, makes the process of disassembly, assembly, repair, and replacement more convenient. When the propulsion components need maintenance or replacement, the staff only needs to use tools to release the magnetic engagement to easily remove the faulty first or second propulsion unit for individual repair or replacement. If the landing gear has a problem, the fixing screw can also be quickly unscrewed and removed from the bottom of the fuselage. When installing new parts, the operation is carried out in the reverse order: first, place the new part in the appropriate position, engage it, and then use magnetic force or threaded connection to fix it to the fuselage. This process does not require large-scale disassembly of the entire aircraft, which greatly saves maintenance time and labor costs.

[0015] 2. The modular aircraft designed in this scheme offers numerous significant advantages through its convenient assembly and disassembly methods. First, it greatly improves maintenance efficiency. If a component malfunctions, maintenance personnel can disassemble and replace it in the shortest possible time, reducing downtime and increasing equipment availability. Second, it reduces maintenance costs. Since a comprehensive inspection and large-scale disassembly of the entire aircraft is unnecessary, it reduces reliance on specialized equipment and complex procedures during maintenance, while also avoiding wear and damage to other components that might occur during disassembly and reassembly. Finally, it enhances the aircraft's flexibility and adaptability. Modules such as propulsion components can be quickly replaced and adjusted according to different mission requirements, enabling it to better adapt to varying flight environments and mission demands. This provides an efficient, economical, and practical solution in the field of aircraft technology. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

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

[0018] Figure 2 This is a schematic diagram showing the disassembled propulsion assembly of this utility model;

[0019] Figure 3 This is a schematic diagram of the control body structure of this utility model;

[0020] Figure 4 This is a schematic diagram of the first support frame structure of this utility model;

[0021] Figure 5 This is a schematic diagram of the second support frame structure of this utility model.

[0022] Explanation of reference numerals in the attached drawings: 1. Control fuselage; 2. Support assembly; 3. Propulsion assembly; 4. First thruster; 5. Second thruster; 6. First conductive block; 7. Conductive mounting bracket; 8. Fixing screw head; 9. Landing gear; 10. Fixing screw hole; 11. First support frame; 12. Second conductive block; 13. Positioning plate; 14. Second support frame; 15. Positioning slot; 16. Conductive plate; 17. Strong magnetic layer. Detailed Implementation

[0023] 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.

[0024] Example: Refer to Figures 1 to 5 This utility model provides an embodiment of a modular aircraft, including a control fuselage 1. A support assembly 2 is installed at the bottom of the control fuselage 1, and propulsion assemblies 3 are distributed around the outer perimeter of the control fuselage 1. Each propulsion assembly 3 includes two sets of first thrusters 4, which are respectively connected to both ends of the control fuselage 1. Two sets of second thrusters 5 are also respectively provided on both sides of the control fuselage 1. When the aircraft needs functional adjustment or maintenance, the simple connection structure between the modules allows for quick separation or assembly of the corresponding components by the staff. If a thruster malfunctions, it is only necessary to disconnect it from the fuselage. The magnetic attraction and snap-fit ​​mechanism allows for individual repair or replacement without the need for large-scale disassembly of the entire aircraft, enhancing the flexibility and practicality of the equipment in the field of aircraft technology. Both ends of the control fuselage 1 are equipped with first electromagnetic blocks 6, and four sets of conductive brackets 7 are connected to the two sides of the control fuselage 1 near the first electromagnetic blocks 6. The bottom of the control fuselage 1 is also equipped with a fixing screw head 8. Through the cooperation between the first electromagnetic blocks 6 and the conductive brackets 7, the control fuselage 1 can achieve rapid electrical connection between the thruster module and the fuselage module, ensuring stable current transmission after the thruster module is powered on, and realizing modular plug-and-play without cables or tools.

[0025] The support assembly 2 includes a landing gear 9. A fixing screw hole 10 is provided on the top of the landing gear 9. The fixing screw hole 10 matches the structure of the fixing screw head 8, and the fixing screw hole 10 and the fixing screw head 8 are threaded together. Through the threaded connection between the fixing screw hole 10 and the fixing screw head 8, a stable connection and quick assembly / disassembly of the landing gear 9 and the control fuselage 1 can be achieved, providing stable support for the aircraft during takeoff and landing and facilitating convenient maintenance and replacement of the landing gear 9. The first thruster 4 includes a first support frame 11. Two sets of second electromagnetic blocks 12 are installed at one end of the first support frame 11. The second electromagnetic blocks 12 are connected to... The first conductive block 6 is structurally matched, and the second conductive block 12 is magnetically attached to the first conductive block 6. Positioning plates 13 are also installed on both sides of the first support frame 11 near the second conductive block 12. Through the structural design of the magnetic attachment between the second conductive block 12 and the first conductive block 6, a rapid cable-free electrical connection and initial mechanical adsorption between the thruster module and the fuselage module can be achieved, ensuring stable current transmission and stable support of the thruster module. The positioning plates 13 installed on both sides of the first support frame 11 can achieve precise alignment and reliable locking between the two sets of thruster modules.

[0026] The second thruster 5 includes a second support frame 14. A positioning slot 15 is provided on one side of the second support frame 14. The positioning slot 15 is structurally matched with a positioning plate 13, and the positioning slot 15 and positioning plate 13 are in a snap-fit ​​engagement. This snap-fit ​​structure allows for precise positioning and secure engagement between the second thruster 5 and the first thruster 4, enabling rapid connection and reliable fixation of the propulsion components 3. This ensures the stability of the aircraft during flight and facilitates the disassembly and maintenance of the thruster, improving assembly efficiency and maintenance convenience. The second support frame 14 is located near the positioning slot 15. Two sets of conductive plates 16 are installed on one side. The conductive plates 16 are structurally matched with the conductive card holders 7. The conductive plates 16 and the conductive card holders 7 are engaged by a snap-fit. A strong magnetic layer 17 is also provided on the side of the second support frame 14 near the two sets of conductive plates 16. Through the snap-fit ​​structure between the conductive plates 16 and the conductive card holders 7, the second thruster 5 and the control body 1 can be quickly connected and reliably electrically connected, ensuring that the thruster module can stably receive power and signals. The strong magnetic layer 17 installed on one side of the second support frame 14 can magnetically fix the two sets of second support frames 14 that are snap-fitted to both sides of the control body 1.

[0027] Working principle: The modular aircraft designed in this scheme is mainly composed of a control fuselage 1, a support assembly 2, and a propulsion assembly 3. The propulsion assembly 3 includes a first thruster 4 and a second thruster 5. The second thruster 5 is connected to the control fuselage 1 by two sets of conductive plates 16 installed on one side of the second support frame 14 and four sets of conductive brackets 7 installed on both sides of the control fuselage 1. Since the conductive plates 16 and conductive brackets 7 are structurally matched and are engaged, the four sets of second support frames 14 can be snapped and fixed to both sides of the control fuselage 1. With the help of the strong magnetic layer 17 installed on one side of the second support frame 14, the two sets of second support frames 14 on both sides of the control fuselage 1 are magnetically fixed.

[0028] The modular aircraft designed in this scheme uses positioning plates 13 installed on both sides of the first support frame 11 and positioning slots 15 opened on one side of the second support frame 14. Since the positioning slots 15 and positioning plates 13 are structurally matched and have a snap-fit ​​fit, the first support frame 11 can be snapped and fixed between the two sets of second support frames 14. In addition, with the two sets of second electromagnetic blocks 12 installed on one side of the first support frame 11 and the first electromagnetic blocks 6 installed at both ends of the control fuselage 1, since the second electromagnetic blocks 12 and first electromagnetic blocks 6 are structurally matched and have a magnetic attraction fit, the first support frame 11, which is snapped and fixed between the two sets of second support frames 14, can also be magnetically fixed to the control fuselage 1.

[0029] The modular aircraft designed in this scheme uses a support component 2 installed at the bottom of the control fuselage 1. This support component 2 uses a fixing screw hole 10 opened at the top of the landing gear 9 and a fixing screw head 8 installed at the bottom of the control fuselage 1. Since the fixing screw hole 10 and the fixing screw head 8 are structurally matched and have a threaded fit, the landing gear 9 can be connected and fixed to the bottom of the control fuselage 1. Furthermore, the control fuselage 1 can also disassemble, connect, repair, and replace the landing gear 9 according to its usage.

[0030] Finally, it should be noted that the above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A modular aircraft, comprising a control fuselage (1), characterized in that: The bottom of the control body (1) is equipped with a support assembly (2), and the outer sides of the control body (1) are also equipped with propulsion assemblies (3). The propulsion assembly (3) includes two sets of first propellers (4). The two sets of first propellers (4) are respectively connected to the two ends of the control body (1). Two sets of second propellers (5) are also respectively provided on both sides of the control body (1).

2. A modular aircraft according to claim 1, characterized in that: The control body (1) is provided with a first electromagnetic block (6) at both ends. Four sets of conductive card seats (7) are connected to the two sides of the control body (1) near the first electromagnetic block (6). A fixing screw head (8) is also installed at the bottom of the control body (1).

3. A modular aircraft according to claim 2, characterized in that: The support assembly (2) includes a landing gear (9), and a fixing screw hole (10) is provided on the top of the landing gear (9). The fixing screw hole (10) is structurally matched with the fixing screw head (8), and the fixing screw hole (10) and the fixing screw head (8) are threaded together.

4. A modular aircraft according to claim 3, characterized in that: The first thruster (4) includes a first support frame (11). Two sets of second electromagnetic blocks (12) are installed at one end of the first support frame (11). The second electromagnetic blocks (12) are structurally matched with the first electromagnetic blocks (6). The second electromagnetic blocks (12) and the first electromagnetic blocks (6) are magnetically attracted to each other. Positioning plates (13) are also installed on both sides of the first support frame (11) near the second electromagnetic blocks (12).

5. A modular aircraft according to claim 4, characterized in that: The second thruster (5) includes a second support frame (14), and a positioning slot (15) is provided on one side of the second support frame (14). The positioning slot (15) is structurally matched with the positioning plate (13), and the positioning slot (15) and the positioning plate (13) are engaged.

6. A modular aircraft according to claim 5, characterized in that: Two sets of conductive plates (16) are installed on the side of the second support frame (14) near the positioning slot (15). The conductive plates (16) are structurally matched with the conductive card seat (7). The conductive plates (16) and the conductive card seat (7) are engaged. A strong magnetic layer (17) is also provided on the side of the second support frame (14) near the two sets of conductive plates (16).

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