A center of gravity modular adjustment device and aircraft model

Abstract

The utility model relates to a kind of gravity modular adjusting device and aircraft model, adjusting device includes storehouse and storehouse cover;Storehouse has storehouse, storehouse cover is detachably arranged at the opening of storehouse, to close storehouse;Storehouse includes multiple counterweight room;Further include counterweight, any counterweight room can be detachably placed counterweight, to change the position of the center of storehouse by placing counterweight.The adjusting device in the utility model has gravity adjustability, to accurately realize the pitch balance adjustment of aircraft, so that aircraft adapts to multiple flight environments, adjusting device detachable design and modular design, to facilitate the adjustment of internal counterweight, facilitate the adjustment of gravity.

Description

Technical Field

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

[0002] Currently, model airplane nose sections commonly suffer from several technical structural problems: Traditional foam model airplanes (such as styroplanes and toy airplanes) typically use adhesive or embedded metal for front-end counterweights. This method has the following drawbacks: ① The counterweight position is fixed, preventing flexible adjustment of the center of gravity; ② Adhesive counterweights are prone to detachment, affecting flight stability; ③ Modification requires damaging the fuselage structure, significantly reducing durability. 2. Some designs use internal counterweight placement, but the lack of a dedicated compartment leads to counterweight movement or swaying after impact, affecting flight attitude. Based on these issues, a modular center of gravity adjustment device is proposed to solve these problems. Utility Model Content

[0003] This utility model provides a modular center of gravity adjustment device and an aircraft model. The adjustment device has an adjustable center of gravity to accurately achieve pitch balance adjustment of the aircraft, enabling the aircraft to adapt to various flight environments. The adjustment device has a detachable and modular design to facilitate the adjustment of the internal counterweights and the adjustment of the center of gravity.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] A modular center of gravity adjustment device is installed on an aircraft. The adjustment device includes a cabin body and a cabin cover.

[0006] The aforementioned storage unit has a storage compartment, and the aforementioned storage cover is detachably provided at the opening of the aforementioned storage compartment to close the aforementioned storage compartment;

[0007] The aforementioned storage compartments include multiple counterweight chambers;

[0008] It also includes a counterweight, and any of the aforementioned counterweight chambers can be disassembled to place the counterweight, so as to change the center position of the aforementioned chamber by placing the counterweight.

[0009] Preferably, any of the aforementioned counterweight chambers can accommodate at least two of the aforementioned counterweight blocks.

[0010] Preferably, the plurality of the aforementioned counterweight chambers are arranged along the length of the aircraft.

[0011] Preferably, each of the above-mentioned counterweight chambers is provided with multiple limiting members to abut against the outer wall of the counterweight block and fix the counterweight block.

[0012] Preferably, the two opposite ends of the above-mentioned compartment body are provided with positioning holes and locking holes, and the two opposite ends of the above-mentioned compartment cover are provided with positioning platforms and elastic clips;

[0013] The aforementioned positioning platform is inserted into the aforementioned positioning hole, and the aforementioned elastic clip is connected to the aforementioned locking hole, so that the aforementioned compartment body and the aforementioned compartment cover are connected.

[0014] Preferably, the end of the elastic clip is provided with a pressure plate. When the pressure plate is pushed by force, the elastic clip is inserted into the locking hole. A pressure groove communicating with the locking hole is provided at the locking hole for placing the pressure plate.

[0015] Preferably, the end of the connection between the pressure plate and the elastic clip has a limiting boss, and the pressure groove is provided with an extension plate extending into the locking hole. When the elastic clip enters the locking hole, the limiting boss is located in the locking hole and abuts against the side wall of the extension plate away from the pressure plate.

[0016] An aircraft model includes a fuselage and the aforementioned modular center of gravity adjustment device, wherein the aforementioned cabin is integrated with the aforementioned fuselage.

[0017] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0018] 1. The adjustment device consists of a detachable hatch cover and a cabin body, and the cabin body is used to place counterweights, realizing a modular design. This allows for easy adjustment of the entire aircraft's center of gravity by the number of counterweights placed, making center of gravity adjustment convenient.

[0019] 2. By setting up multiple counterweight chambers inside the cabin to hold counterweights, the center of gravity of the entire adjustment device and the aircraft can be adjusted more precisely by adjusting the number of counterweights in each chamber, thereby changing the center of gravity torque. It has the advantages of simple structure and adjustable center of gravity. Attached Figure Description

[0020] To more clearly illustrate the specific embodiments of this utility model or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the overall adjustment device in an embodiment of the present invention;

[0022] Figure 2 This is a cross-sectional view of the adjustment device in an embodiment of this utility model;

[0023] Figure 3 This is a schematic diagram of the hopper body in an embodiment of this utility model;

[0024] Figure 4 This is a schematic diagram of the bin cover in an embodiment of the present utility model. Figure 1 ;

[0025] Figure 5 This is a schematic diagram of the bin cover in an embodiment of the present utility model. Figure 2 ;

[0026] Figure 6 This is a schematic diagram of the installation of the counterweight block in an embodiment of this utility model. Figure 1 ;

[0027] Figure 7 This is a schematic diagram of the installation of the counterweight block in an embodiment of this utility model. Figure 2 .

[0028] Explanation of reference numerals in the attached figures:

[0029] 1. Bin body; 11. Bin chamber; 111. Counterweight chamber; 12. Positioning hole; 13. Locking hole; 14. Pressure groove; 15. Extension plate; 2. Bin cover; 21. Elastic clip; 22. Positioning platform; 23. Pressure plate; 24. Limiting boss; 3. Limiting component; 4. Machine body; 5. Counterweight block. Detailed Implementation

[0030] The technical solution of this utility model will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0031] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and 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, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0032] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0033] like Figures 1-7 As shown, this utility model embodiment provides a modular center of gravity adjustment device, which is installed on an aircraft. By adjusting the center of gravity of the modular center of gravity adjustment device, the position of the center of gravity of the entire aircraft is adjusted, thereby changing the center of gravity torque and realizing the pitch balance adjustment of the aircraft.

[0034] like Figures 1-2 As shown, the adjustment device specifically includes a cabin body 1 and a cabin cover 2. The cabin body 1 has a chamber 11 with an opening communicating with the outside. The cabin cover 2 is detachably installed at the opening to close the chamber 11. Furthermore, the weight of the entire adjustment device can be changed by adding or removing counterweights 5 within the chamber 11. Therefore, after installation on the aircraft, it can change the center of gravity of the entire aircraft, making the entire adjustment device modular and easier to adjust the center of gravity of the aircraft, thus achieving pitch control during flight. Preferably, as shown... Figures 6-7 As shown, the cabin 11 includes multiple counterweight chambers 111, each containing a detachable counterweight block 5. Operators can adjust the center of gravity of the entire cabin 1 by placing the counterweight block 5 in different chambers 111, thereby adjusting the position of the adjustment device and the aircraft's center of gravity, changing the center of gravity moment, and achieving pitch balance adjustment of the aircraft. The structure is simple and offers advantages such as adjustable center of gravity and easy disassembly. Since pitch control is generally forward and backward pitching, multiple counterweight blocks 5 are positioned along the length of the aircraft to better control its pitch. This length typically extends from the nose to the tail. By adjusting the center of gravity of the cabin 11 along the length of the aircraft, the range of adjustment for the center of gravity along the length of the aircraft is wider, and the change of the center of gravity moment is easier.

[0035] Specifically, any counterweight chamber 111 can accommodate at least two counterweights 5, thereby allowing for a wider range of adjustment of the center of gravity of the entire chamber 1, making adjustment more convenient, and allowing for more precise pitch balance adjustment by adding counterweights 5.

[0036] Specifically, multiple limiting members 3 are provided in the counterweight chamber 111 to limit and fix the counterweight block 5, and to prevent the radial movement of the counterweight block 5 during flight, which could cause the center of gravity of the aircraft to shift and affect the flight performance. Specifically, in this embodiment, four limiting members 3 are provided, all of which are distributed on the inner side wall of the counterweight chamber 111. After the counterweight block 5 is installed in the counterweight chamber 111, the four limiting members 3 will abut against the outer side wall of the counterweight block 5, limiting it to the counterweight. Specifically, the limiting members 3 are made of plastic plates with a small amount of elasticity, and the four plastic plates can completely fix the counterweight block 5.

[0037] Specifically, such as Figures 3-5 As shown, in order to allow the compartment cover 2 to be detachably connected to the opening of the compartment body 1, positioning holes 12 and locking holes 13 are provided at opposite ends of the compartment body 1, and positioning platforms 22 and elastic clips 21 are provided at opposite ends of the compartment cover 2. The positioning platforms 22 are inserted into the positioning holes 12, and the elastic clips 21 are connected into the locking holes 13, thus completing the connection between the compartment body 1 and the compartment cover 2 and enabling their detachability. Specifically, when connecting the compartment body 1 and the compartment cover 2, the positioning platform 22 of the compartment body 1 is first inserted into the positioning holes 12 to limit its circumferential movement, and then the elastic clips 21 are snapped into the locking holes 13. Compared with the traditional structure where replacing the counterweight requires the use of tools to pry or solvents to dissolve the glue, which can easily cause irreversible damage to the machine body 4, this detachable design offers better performance.

[0038] Specifically, the end of the elastic clip 21 furthest from the end is provided with a pressure plate 23. When the pressure plate 23 is pushed by force, the elastic clip 21 enters into the locking hole 13 and is locked into the locking hole 13. A pressure groove 14 is provided at the locking hole 13. When the pressure plate 23 is placed and abuts against the pressure groove 14, the elastic clip 21 is locked into the locking hole 13. Specifically, in this embodiment, the elastic clip 21 is a V-shaped clip. When the elastic clip 21 enters the locking hole 13, the two side plates of the elastic clip 21 will come closer to provide a clamping force to lock it in place. The structure is simple and easy to assemble and disassemble.

[0039] Of course, the detachable connection structure between the cover 2 and the body 1 is not limited to this one. It can also be connected by bolts or other detachable structures.

[0040] Specifically, to ensure the elastic clip 21 is more stably positioned within the limiting hole, a limiting boss 24 is provided at the end of the connection between the pressure plate 23 and the elastic clip 21. An extension plate 15 is correspondingly provided at the pressure groove 14, extending into the locking hole 13. When the elastic clip 21 is engaged in the locking hole 13, the limiting boss 24 is located within the locking hole 13 and abuts against the extension plate 15. Thus, the extension plate 15 restricts the elastic clip 21 from disengaging from the locking hole 13. Specifically, because the elastic clip 21 is elastic, when it enters the locking hole 13, due to the presence of the extension plate 15, one side wall of the elastic clip 21 will continuously abut against the side wall of the extension plate 15. When the elastic clip 21 is fully engaged in the locking hole 13, the pressure plate 23 is installed in the mounting groove, and the elastic clip 21... The sidewall of the clip 21 no longer abuts against the extension plate 15, but instead abuts against the outer sidewall of the locking hole 13 due to its own elastic reset. Therefore, the protrusion at the connection between the elastic clip 21 and the pressure plate 23 will be located inside the locking hole 13, and will also move outwards with the sidewall of the elastic clip 21, placing it below the extension plate 15. Preferably, the limiting protrusion 24 abuts against the sidewall of the extension plate 15 away from the pressure plate 23, allowing the extension plate 15 to effectively limit the limiting protrusion 24, thus providing secondary limiting for the entire elastic clip 21 and ensuring its stable connection at the locking hole 13. During disassembly, simply move the pressure plate 23 towards the axis of the locking hole 13, causing the limiting protrusion 24 to move inwards, disengaging from the extension plate 15, and then pull it outwards. Specifically, there are two extension plates 15, located on both sides of the pressure groove 14 along the width of the chamber 1, and are part of the upper sidewall of the chamber 1.

[0041] In a specific embodiment of this utility model, an aircraft model is also disclosed, including a fuselage 4 and the aforementioned modular center of gravity adjustment device. The cabin 1 and the fuselage 4 are integrated into one design. Specifically, the lower part of the nose of the fuselage 4 is provided with an installation groove, the cabin 1 is formed entirely in the installation groove, and the cabin cover 2 is placed over the opening of the cabin 1 to close the cabin 1, thereby allowing the center of gravity moment of the entire aircraft to be adjusted at any time to achieve pitch balance adjustment.

[0042] The above embodiments are merely preferred embodiments of this utility model and should not be construed as limiting the scope of protection of this utility model. Any non-substantial changes and substitutions made by those skilled in the art based on this utility model shall fall within the scope of protection claimed by this utility model.

Claims

1. A modular center of gravity adjustment device, installed on an aircraft, characterized in that, Includes the cargo box body and cargo box cover; The silo body has a silo compartment, and the silo cover is detachably provided at the opening of the silo compartment to close the silo compartment; The compartment includes multiple counterweight chambers; It also includes a counterweight, and any of the counterweight chambers can be detached and the counterweight can be placed therein, so as to change the center position of the chamber by placing the counterweight.

2. The modular center of gravity adjustment device according to claim 1, characterized in that, Each of the aforementioned counterweight chambers may accommodate at least two of the aforementioned counterweight blocks.

3. The modular center of gravity adjustment device according to claim 1, characterized in that, Multiple counterweight chambers are arranged along the length of the aircraft.

4. The modular center of gravity adjustment device according to claim 1, characterized in that, Each counterweight chamber is equipped with multiple limiting components to abut against and fix the counterweight block to the outer wall of the counterweight block.

5. The modular center of gravity adjustment device according to claim 1, characterized in that, The two opposite ends of the compartment body are provided with positioning holes and locking holes, and the two opposite ends of the compartment cover are provided with positioning platforms and elastic clips; The positioning platform is inserted into the positioning hole, and the elastic clip is connected to the locking hole so that the compartment body and the compartment cover are connected.

6. The modular center of gravity adjustment device according to claim 5, characterized in that, The end of the elastic clip is provided with a pressure plate. When the pressure plate is pushed by force, the elastic clip is inserted into the locking hole. The locking hole is provided with a pressure groove that communicates with it for placing the pressure plate.

7. The modular center of gravity adjustment device according to claim 6, characterized in that, The end of the connection between the pressure plate and the elastic clip has a limiting boss, and the pressure groove is provided with an extension plate extending into the locking hole. When the elastic clip enters the locking hole, the limiting boss is located in the locking hole and abuts against the side wall of the extension plate away from the pressure plate.

8. An aircraft model, characterized in that, It includes the fuselage and the modular center of gravity adjustment device as described in any one of claims 1-7, wherein the cargo compartment is integrated with the fuselage.

Images