Vibration isolation type flight control box assembly for unmanned aerial vehicle

Abstract

The vibration isolation type flight control box assembly comprises a flight control box connecting plate and a suspension assembly used for installing a flight control box on the flight control box connecting plate, suspension points are distributed on the flight control box in a three-dimensional space, vibration isolators are arranged at the suspension points, and vibration isolation of the flight control box is achieved; according to the vibration isolation type flight control box assembly for the unmanned aerial vehicle, through the arrangement design of the suspension points and the selection of the vibration isolators, rolling, pitching and course shaking of the flight control box are well limited, the stability of the flight attitude of the unmanned aerial vehicle is guaranteed, the vibration isolation efficiency of the overall structure is high, the obvious vibration isolation effect is achieved in the three-dimensional space of the flight control box, and the vibration isolation effect is good. Long-term stability of vibration isolation efficiency is guaranteed, the overall structure is simple, disassembly and assembly are convenient, meanwhile, the size is small, the weight is reduced, and the production cost is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), in particular to a vibration-isolating flight control box assembly for UAVs. Background Art

[0002] The stability and reliability of an unmanned helicopter's flight control system are crucial for performing various missions. However, due to the helicopter's operational characteristics, the flight control box is often strongly affected by factors such as engine vibration, main rotor rotational imbalance, high-speed airflow, and flight maneuvers. These factors can cause the flight control box to vibrate violently, affecting the drone's flight performance and stability, and may even damage the electronic components within the flight control box, reducing its service life and reliability.

[0003] In the prior art, the vibration isolation suspension structure design of the unmanned helicopter flight control box has the following main problems: the vibration isolation system is relatively rigid. Some vibration isolation suspension structure designs are too rigid, with a low vibration isolation rate, and are unable to effectively isolate the vibrations experienced by the flight control box during flight, resulting in poor vibration isolation effect; the vibration isolation system is relatively soft. Other design schemes are too soft. Although they can provide good vibration isolation effect, the static deformation of the structure is large and the stability is insufficient. Especially during high-acceleration flight maneuvers, the flight control box is prone to shaking, affecting the accuracy of flight control; insufficient vibration control. Some vibration isolation suspension structure designs are insufficient in limiting the shaking of the flight control box, especially under inertial effects and aircraft maneuvers. They cannot fully restrain the shaking of the flight control box, affecting the stability of the drone's flight attitude; the vibration isolation direction is single. Many vibration isolation suspension structures only effectively isolate vibrations in the vertical direction (Z direction), but have little effect on vibration isolation in the horizontal directions (X and Y directions). This is a significant defect in multi-axis rotating equipment because, in addition to vertical vibration, horizontal vibration can also affect the flight control box.

[0004] Therefore, in response to the above problems, it is urgent to develop a flight control box suspension vibration isolation structure that can significantly improve the vibration isolation efficiency of the flight control box, ensure the stability of the UAV's flight attitude, enhance the stability of the structure, and have a high overall structural vibration isolation efficiency. At the same time, it can be easily installed and disassembled, simplified in structure, easy to maintain, and has a wide range of applications. Utility Model Content

[0005] In view of this, the purpose of the utility model is to provide a flight control box suspension vibration isolation structure, which can significantly improve the vibration isolation efficiency of the flight control box, ensure the stability of the UAV's flight attitude, enhance the stability of the structure, and the overall structure has a high vibration isolation efficiency. At the same time, it can be easily installed and disassembled, simplified in structure, easy to maintain, and has a wide range of applications.

[0006] The utility model discloses a vibration-isolating flight control box assembly for an unmanned aerial vehicle, comprising a flight control box connecting plate and a suspension assembly for mounting the flight control box on the flight control box connecting plate. The flight control box has suspension points distributed in three-dimensional space, and vibration isolators are provided at the suspension points to achieve vibration isolation of the flight control box.

[0007] Furthermore, the suspension points are distributed diagonally in the three-dimensional space of the flight control box.

[0008] Furthermore, a cover plate and a bottom plate are arranged side by side on the top and bottom of the flight control box, and the cover plate and the bottom plate are respectively provided with the suspension points distributed diagonally.

[0009] Furthermore, the suspension assembly includes a bracket I and a bracket II, and the bracket I and the bracket II are respectively arranged on both sides of the flight control box connection plate, and the bracket I and the bracket II are respectively provided with mounting holes for connecting to the drone body.

[0010] Furthermore, the bracket I and bracket II are respectively connected to the suspension points on the top cover of the flight control box through vibration isolators, and the bracket I and bracket II are respectively provided with reinforcing ribs on the inner side for improving the rigidity.

[0011] Furthermore, the bracket I and the bracket II are parallel to each other and perpendicular to the flight control box connecting plate, and the heights of the bracket I and the bracket II are the same.

[0012] Furthermore, the bracket I has a right-angled trapezoidal structure, the long bottom side of the bracket I is connected to the flight control box connecting plate, and the short bottom side of the bracket I extends toward the side of the bracket II to form a support ear I for installing the vibration isolator, and the support ear I is parallel to the flight control box connecting plate.

[0013] Furthermore, the bracket II has a trapezoidal structure, the long bottom side of the bracket II is connected to the flight control box connecting plate, and the short bottom side of the bracket II extends toward the side of the bracket I to form a support ear II for installing the vibration isolator, and the support ear II is parallel to the flight control box connecting plate.

[0014] Furthermore, the flight control box connecting plate is provided with mounting positions arranged in line, the vibration isolators are installed on the mounting positions and are connected to the suspension points on the flight control box, and the flight control box connecting plate is provided with weight reduction holes for reducing its own weight.

[0015] The beneficial effects of the utility model are as follows: the vibration isolation-type flight control box assembly for unmanned aerial vehicles of the utility model effectively limits the roll, pitch and heading shaking of the flight control box through the arrangement design of the suspension points and the selection of vibration isolators, thereby ensuring the stability of the flight attitude of the unmanned aerial vehicle. The overall structure has a high vibration isolation efficiency and has obvious vibration isolation effect in the three-dimensional space of the flight control box, thereby ensuring the long-term stability of the vibration isolation efficiency. The overall structure is simple and easy to disassemble and assemble. At the same time, the volume is small, the weight is reduced, and the production cost is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be further described below with reference to the accompanying drawings and embodiments:

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

[0018] Figure 2 This is a schematic diagram of the structure of the utility model Figure II ;

[0019] Figure 3 This is a schematic diagram of the structure of the utility model Figure III .

[0020] Numbers in the figure: 1. Flight control box; 101. Cover plate; 102. Base plate; 2. Flight control box connecting plate; 3. Bracket I; 301. Support ear I; 4. Bracket II; 401. Support ear II; 5. Vibration isolator; 6. Mounting hole; 7. Reinforcement rib; 8. Weight reduction hole. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0022] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0023] Figure 1 This is a schematic diagram of the structure of the utility model Figure I , Figure 2 This is a schematic diagram of the structure of the utility model Figure II , Figure 3 This is a schematic diagram of the structure of the utility model Figure IIIAs shown in the figure: the vibration isolation-type flight control box assembly for a drone of this embodiment includes a flight control box connecting plate 2 and a suspension assembly for mounting the flight control box 1 on the flight control box connecting plate 2. The flight control box 1 has suspension points distributed in three-dimensional space, and vibration isolators 5 are provided at the suspension points to achieve vibration isolation of the flight control box 1. The vibration isolator 5 is a device for reducing or eliminating vibration transmission. Its core function is to minimize the mechanical impact between the equipment and the foundation by absorbing and attenuating vibration energy. The working principle of the vibration isolator 5 mainly includes two aspects: mass damping and stiffness damping. Mass damping means that the mass of the vibration isolator 5 itself is greater than the mass of the object to be isolated, so that the vibration energy is mainly converted into kinetic energy of the vibration isolator 5 instead of being transmitted to the object to be isolated. Stiffness damping means that the stiffness of the vibration isolator 5 is smaller than the stiffness of the object to be isolated, so that the vibration energy is mainly absorbed and dissipated through the elastic deformation of the vibration isolator 5; there are many types of vibration isolators 5, the most common ones are metal rubber vibration isolators, steel spring vibration isolators, rubber vibration isolators, air spring vibration isolators, etc. Of course, the design and selection of the vibration isolator 5 need to be carried out according to the actual application requirements and environmental conditions to ensure the best vibration isolation effect and equipment protection; metal rubber vibration isolators can work in extreme environments, such as high and low temperatures, large temperature differences, high pressure, high vacuum, strong radiation, etc., and still maintain excellent properties in these environments. Compared with conventional vibration isolators, they have higher stability and can avoid the low vibration isolation efficiency after long-term use. Therefore, this scheme gives priority to the use of metal rubber vibration isolators.

[0024] Three-dimensional space refers to a space with three dimensions. There are three mutually perpendicular coordinate axes in the three-dimensional space, usually called the X-axis, Y-axis and Z-axis. There are suspension points distributed in this space, and the suspension points are not in the same plane or on the same straight line, and multi-point distribution is adopted.

[0025] In this embodiment, the suspension points are distributed diagonally in the three-dimensional space of the flight control box 1; Figure 2 As shown, the vibration isolators 5 are installed at the suspension points. The diagonally distributed suspension points can increase the stability of the structure because they can provide additional support, especially when bearing the gravity of the flight control box 1 and the excitation generated by the operation of the engine, main rotor and main blades. In three-dimensional space, the diagonal distribution helps to disperse the load more evenly, reduce the stress concentration in a single area of ​​the flight control box 1, improve the torsional performance of the structure and resist torsional force. In the dynamic environment where the drone is used, the diagonally distributed suspension points can also improve the dynamic performance of the structure and reduce vibration and swing.

[0026] The diagonally distributed suspension points in three-dimensional space can make the center of gravity of the flight control box 1 within the geometric center of the suspension point range of the vibration isolator 5. While isolating vibration, the flight control box 1 is well constrained and will not shake. The overall structure is simple and easy to assemble and disassemble. The diagonal distribution can make more effective use of space, especially when the flight control box 1 needs to be suspended at multiple points in a limited space. By optimizing the distribution of the suspension points, the required number of vibration isolators 5 can be reduced, the overall weight can be reduced, and the cost can be reduced.

[0027] In this embodiment, the top and bottom of the flight control box 1 are provided with a cover plate 101 and a bottom plate 102 in parallel, and the cover plate 101 and the bottom plate 102 are respectively provided with the suspension points distributed diagonally; Figure 1 As shown, the cover plate 101 and the bottom plate 102 are respectively parallel to the flight control box connecting plate 2, ensuring that the flight control box 1 can be parallel to the flight control box connecting plate 2 when suspended.

[0028] In this embodiment, the suspension assembly includes a bracket I3 and a bracket II4, and the bracket I3 and the bracket II4 are respectively arranged on both sides of the flight control box connecting plate 2, and the bracket I3 and the bracket II4 are respectively provided with a mounting hole 6 connected to the drone body; Figure 1 As shown, the two sides of the flight control box connecting plate 2 refer to the two sides along the width direction. The bracket I3, bracket II4 and flight control box connecting plate 2 are made of aluminum alloy with certain strength and light weight. Aluminum alloy can withstand high loads and has relatively low cost. Aluminum alloy has good impact resistance, can absorb impact energy, and reduce impact damage. It is very beneficial in the vibration isolation structure of the flight control box 1. Of course, other materials with the same properties as aluminum alloy can also be used to make bracket I3, bracket II4 and flight control box connecting plate 2, such as titanium alloy, carbon fiber composite material, etc., which will not be repeated here; bracket I3 and bracket II4 are respectively provided with mounting holes 6 for connection to the drone body. When disassembling, the entire assembly can be disassembled through the mounting holes 6 without removing individual parts. The overall disassembly and assembly is convenient. The mounting holes 6 and the drone body can be connected by bolts or other mechanical connection methods, which will not be repeated here.

[0029] In this embodiment, the bracket I3 and the bracket II4 are connected to the suspension point on the top cover 101 of the flight control box 1 through the vibration isolator 5, and the bracket I3 and the bracket II4 are respectively provided with reinforcing ribs 7 on the inner side for improving the rigidity; Figure 1As shown, the top of the vibration isolator 5 is connected to the suspension point on the cover plate 101, and the top of the bottom of the vibration isolator 5 is connected to the bottom of the bracket I3 and the bracket II4. In this solution, the connection between the vibration isolator 5 and the suspension point, the bracket I3 and the bracket II4, and the connection between the bracket I3 and the bracket II4 and the flight control box connecting plate 2 are all installed and fixed using hexagonal cylindrical head bolts. The hexagonal cylindrical head bolts are usually made of high-strength materials (such as alloy steel) and can withstand large tensile and shear forces to ensure the firmness of the connection. The hexagonal cylindrical head bolts make installation and disassembly very convenient, especially when space is limited, and can be better operated. The hexagon socket head bolt can evenly distribute the applied force, reduce stress concentration, and reduce the risk of material damage. In applications that require regular maintenance or replacement, the removal and reinstallation of the hexagon socket head bolt is relatively simple, saving time and labor costs and improving work efficiency. The connection method described above can also adopt other mechanical connection methods, which will not be repeated here; bracket I3 and bracket II4 are respectively provided with reinforcing ribs 7 on the inner side for increasing the rigidity, and the reinforcing ribs 7 are provided along the length direction of bracket I3 and bracket II4. The number and length of the reinforcing ribs 7 can be determined according to the actual dimensions of bracket I3 and bracket II4, and are not limited here.

[0030] In this embodiment, the bracket I3 and the bracket II4 are parallel to each other and perpendicular to the flight control box connecting plate 2, and the bracket I3 and the bracket II4 have the same height; the bracket I3 and the bracket II4 have the same height, are parallel to each other and perpendicular to the flight control box connecting plate 2, which can ensure that the vibration isolators 5 on the bracket I3 and the bracket II4 are at the same height and the top of the vibration isolator 5 is at the same height as the suspension point on the flight control box cover 101, so that when suspended, the flight control box 1 can be parallel to the flight control box connecting plate 2.

[0031] In this embodiment, the bracket I3 is a right-angled trapezoidal structure, the long bottom side of the bracket I3 is connected to the flight control box connecting plate 2, and the short bottom side of the bracket I3 extends to one side of the bracket II4 to form a support ear I301 for mounting the vibration isolator 5, and the support ear I301 is parallel to the flight control box connecting plate 2; the bracket I3 is a right-angled trapezoidal structure, which provides good stability. The asymmetric shape of the trapezoid can provide additional support, reduce the shaking or tilting of the structure, and further improve the vibration isolation effect of the flight control box 1. The right-angled trapezoidal structure can more effectively utilize the space where the flight control box 1 is located, especially in In situations where additional support is provided in a limited space, the bottom side and height of the right-angled trapezoidal structure can provide a larger bearing area, thereby enhancing the bearing capacity of bracket I3. The asymmetry of the right-angled trapezoidal structure can provide better torsional resistance and reduce torsion caused by external forces. The short bottom side of bracket I3 extends toward one side of bracket II4 to form a support ear II401 for installing the vibration isolator 5. The support ear I301 is parallel to the flight control box connecting plate 2. The support ear I301 is used to provide a mounting point for the vibration isolator 5 for bracket I3, so that bracket I3 can be suspended at the suspension point on the cover plate 101 of the flight control box 1.

[0032] In this embodiment, the bracket II4 has a trapezoidal structure, the long bottom side of the bracket II4 is connected to the flight control box connecting plate 2, and the short bottom side of the bracket II4 extends toward the side of the bracket I3 to form a support ear II401 for mounting the vibration isolator 5, and the support ear II401 is parallel to the flight control box connecting plate 2; the bracket II4 has a trapezoidal structure, and the short bottom side of the bracket II4 and the short bottom side of the bracket I3 are also diagonally distributed relative to the flight control box connecting plate 2, so that the support ears I301 and the support ears II401 are also diagonally distributed; the principle of the trapezoidal structure of the bracket II4 and the function of the support ears I301 are the same as the principle of the right-angled trapezoidal structure of the bracket I3 and the function of the support ears II401 described above, and will not be repeated here.

[0033] The flight control box connecting plate 2 is provided with mounting positions arranged in line, the vibration isolator 5 is installed on the mounting position and is connected to the suspension point on the flight control box 1, and the flight control box connecting plate 2 is provided with a weight reduction hole 8 for reducing its own weight; Figure 2 As shown, the vibration isolator 5 is also connected to the flight control box connecting plate 2 by means of hexagon socket head bolts at the installation position. The reason for using hexagon socket head bolts is the same as above and will not be repeated here. Figure 3 As shown, the flight control box connecting plate 2 is provided with a weight-reducing hole 8 for reducing its own weight. The size and shape of the weight-reducing hole 8 can be determined according to the size, material, strength, etc. of the flight control box connecting plate 2, and are not limited here. The use of the weight-reducing hole 8 reduces the weight of the flight control box connecting plate 2 itself and reduces the production cost.

[0034] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model and are not limiting. Although the utility model is described in detail with reference to the preferred embodiments, ordinary technicians in this field should understand that the technical solution of the utility model can be modified or replaced by equivalents without departing from the purpose and scope of the technical solution of the utility model, which should be included in the scope of the claims of the utility model.

Claims

1. A vibration-isolating flight control box assembly for a drone, characterized by: The invention comprises a flight control box connecting plate and a suspension assembly for mounting the flight control box on the flight control box connecting plate. The flight control box has suspension points distributed in three-dimensional space, and vibration isolators are provided at the suspension points to achieve vibration isolation of the flight control box.

2. The vibration-isolating flight control box assembly for a UAV according to claim 1, characterized in that: The suspension points are distributed diagonally in the three-dimensional space of the flight control box.

3. The vibration-isolating flight control box assembly for a UAV according to claim 2, characterized in that: A cover plate and a bottom plate are arranged side by side on the top and bottom of the flight control box, and the cover plate and the bottom plate are respectively provided with the suspension points distributed diagonally.

4. The vibration-isolating flight control box assembly for a UAV according to claim 1, characterized in that: The suspension assembly includes a bracket I and a bracket II, which are respectively arranged on both sides of the flight control box connection plate, and are respectively provided with mounting holes for connecting with the drone body.

5. The vibration-isolating flight control box assembly for a UAV according to claim 4, characterized in that: The bracket I and bracket II are respectively connected to the suspension points on the top cover of the flight control box through vibration isolators, and the bracket I and bracket II are respectively provided with reinforcing ribs on the inner side for improving the rigidity.

6. The vibration-isolating flight control box assembly for a UAV according to claim 4, characterized in that: The bracket I and the bracket II are parallel to each other and perpendicular to the flight control box connecting plate, and the heights of the bracket I and the bracket II are the same.

7. The vibration-isolating flight control box assembly for a UAV according to claim 4, characterized in that: The bracket I is a right-angled trapezoidal structure, the long bottom side of the bracket I is connected to the flight control box connecting plate, and the short bottom side of the bracket I extends toward the side of the bracket II to form a support ear I for installing the vibration isolator, and the support ear I is parallel to the flight control box connecting plate.

8. The vibration-isolating flight control box assembly for a UAV according to claim 4, characterized in that: The bracket II has a trapezoidal structure, the long bottom side of the bracket II is connected to the flight control box connecting plate, and the short bottom side of the bracket II extends toward one side of the bracket I to form a support ear II for installing the vibration isolator, and the support ear II is parallel to the flight control box connecting plate.

9. The vibration-isolating flight control box assembly for a UAV according to claim 1, characterized in that: The flight control box connecting plate is provided with mounting positions arranged in line, the vibration isolator is installed on the mounting position and is connected to the suspension point on the flight control box, and the flight control box connecting plate is provided with weight reduction holes for reducing its own weight.

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