Flight control structure and unmanned aerial vehicle

Abstract

The utility model discloses a flight control structure and an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the flight control structure comprises a circuit board and a standby bonding pad, the standby bonding pad is arranged on one side of the circuit board, and the standby bonding pad is used for providing additional circuit connection. According to the technical scheme of the utility model, the standby bonding pad is arranged, so that even if the socket is accidentally damaged, the standby bonding pad can continue to work, and the flight control structure can be welded with the standby bonding pad and is matched with the electronic speed regulator for use, thereby ensuring the continuous operation and stability of the unmanned aerial vehicle and improving the fault-tolerant capability of the system.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, especially a flight control structure and unmanned plane. BACKGROUND

[0002] Unmanned plane is the plane of not carrying people with radio remote control equipment and self -provided program control device manipulation. With the development of unmanned plane technology, unmanned plane has been widely applied in military reconnaissance, agricultural monitoring, logistics distribution and many other fields. In the flight control system of unmanned plane, electronic speed controller and flight control structure are two core components, flight control structure is responsible for the adjustment and stabilization of flight attitude, the transmission of control signal, height control, stable control and data storage and other functions, and through the socket and the power supply, signal and data of electronic speed controller docking, and electronic speed controller is responsible for adjusting motor speed to realize the flight attitude adjustment of unmanned plane.

[0003] In the related art, the socket on the flight control structure is easy to be damaged in the unexpected situation such as unmanned plane crash or collision, once damaged, the flight control structure cannot continue to be used, cannot continue to be used with the electronic speed controller, increases the risk of unmanned plane out of control and accident, at the same time increases the maintenance cost, reduces the reliability of unmanned plane. UTILITY MODEL CONTENT

[0004] The main purpose of the utility model is to provide a flight control structure and unmanned plane, which aims to solve the technical problem that the socket on the flight control structure in the related art is damaged and the flight control structure cannot be used.

[0005] To achieve the above purpose, the flight control structure provided by the utility model comprises:

[0006] A circuit board;

[0007] A spare pad, which is arranged on one side of the circuit board, and is used for connecting external circuits.

[0008] In an embodiment, the flight control structure further comprises a socket, which is arranged on the same side as the spare pad, the spare pad is arranged on the side of the circuit board facing the socket, the socket is used for electrically connecting with the electronic speed controller, and the spare pad is used for additional circuit connection.

[0009] In an embodiment, the flight control structure further comprises a power supply protection module, the power supply protection module comprises an external power supply unit and an internal power supply unit, the external power supply unit is connected with an external device, the internal power supply unit is connected with the flight control structure, the external power supply unit is used for supplying power to the external device, and the internal power supply unit is used for supplying power to the flight control structure.

[0010] In an embodiment, the circuit board is provided with a plurality of mounting holes, each of the mounting holes is arranged at the edge of the circuit board, and two of the mounting holes are provided with the socket.

[0011] In an embodiment, the center distance between two adjacent mounting holes is 20 mm.

[0012] In an embodiment, the circuit board further comprises a plurality of shock-absorbing columns, each of the shock-absorbing columns is arranged in each of the mounting holes, one end of the shock-absorbing column is exposed to the circuit board, the other end of the shock-absorbing column is exposed to the other side of the circuit board, and the shock-absorbing column is provided with a through hole.

[0013] In an embodiment, the size of the circuit board ranges from 26*26 mm to 30*30 mm.

[0014] In an embodiment, the side of the circuit board opposite to the socket is integrated with a flight control module.

[0015] The utility model also provides a kind of unmanned aerial vehicle, and the unmanned aerial vehicle comprises:

[0016] Frame;And

[0017] The flight control structure described above, the frame is connected with the flight control structure.

[0018] In an embodiment, the unmanned aerial vehicle further comprises an electronic governor, and the electronic governor is electrically connected with the flight control structure.

[0019] The technical scheme of the utility model sets up spare pad, so that even in the case of accidental damage of socket, spare pad can continue to work, flight control structure can be welded with spare pad, and cooperate with electronic governor, so as to ensure the continuous operation and stability of unmanned aerial vehicle, improve system fault tolerance. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical scheme in the embodiments of the utility model or prior art, the drawings needed in the embodiment or prior art description will be briefly introduced below, and obviously, the drawings in the following description are only some embodiments of the utility model, and for those skilled in the art, other drawings can be obtained from the structure shown in the drawings without creative labor.

[0021] Figure 1 The structural diagram of the flight control structure provided by the utility model is shown in the figure.

[0022] Figure 2 The explosion view of the flight control structure provided by the utility model is shown in the figure.

[0023] Figure 3 A structure schematic diagram of another perspective of the flight control structure is provided in the utility model.

[0024] Figure 4 A structure schematic diagram of one perspective of the circuit board is provided in the utility model.

[0025] Explanation of the drawing reference number:

[0026] 100, flight control structure; 1, circuit board; 11, mounting hole; 12, shock column; 12a, through hole; 13, flight control module; 131, Flash storage IC; 132, OSDIC; 133, gyroscope; 134, barometer IC; 135, main control chip; 14, power supply protection module; 141, external power supply unit; 142, internal power supply unit; 2, spare solder pad; 3, socket.

[0027] The implementation, functional features and advantages of the utility model will be further described with reference to the accompanying drawings in combination with the embodiments. Specific implementation

[0028] The technical solutions in the embodiments of the utility model will be clearly and completely described in combination with the accompanying drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all the other embodiments obtained by the person skilled in the art without creative labor belong to the protection scope of the utility model.

[0029] It should be noted that if the embodiments of the utility model involve directional indications (such as up, down, left, right, front, back, etc.), the directional indications are only used to explain the relative position relationship, movement condition, etc. between the components in a certain specific posture, and if the specific posture changes, the directional indications also change accordingly.

[0030] In addition, if the description of "first", "second" and the like is involved in the embodiments of the utility model, the description of "first", "second" and the like is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second" can be explicitly or implicitly included at least one of the features. In addition, if "and / or" or "and / or" appears throughout the text, it means that the three parallel schemes are included, for example, "A and / or B" includes A scheme, or B scheme, or A and B scheme. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the realization of ordinary technical personnel in the art, when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the protection scope required by the utility model.

[0031] The utility model provides a flight control structure 100.

[0032] Please refer to Figures 1 to 4 In an embodiment of the utility model, the flight control structure includes circuit board 1 and spare pad 2, spare pad 2 is located at one side of circuit board 1, and spare pad 2 is used to provide additional circuit connection.

[0033] In the embodiment, the flight control structure is used to be responsible for the adjustment and stability of flight attitude, the transmission of control signal, height control, stability control and data storage and other functions. The spare pad 2 is used to provide the interface of additional circuit connection, so as to ensure that the spare pad 2 can take over when the main connection point has a problem, and ensure the continuous operation of the system. Accordingly, the spare pad 2 is arranged at the edge of the circuit board 1, so as to provide additional circuit connection points without occupying the main wiring area; the spare pad 2 can also be arranged beside the main component pad of the circuit board 1, so as to quickly expand the circuit function when needed. Specifically, a plurality of pads are further arranged on the circuit board 1, which can be used for various purposes of the user, and are used for connecting external devices and data transmission of the unmanned aerial vehicle, for example: voltage output, camera signal, image transmission signal, electronic speed regulation signal, LED signal, receiver signal and the like, which are used for external device connection and data transmission. The main component pad of the spare pad 2 and the circuit board 1 can be arranged on the same side, or can not be arranged on the same side, which can be arranged according to the specific circumstances. Further, in order to ensure the docking of the flight control structure and the electronic speed regulation structure, the circuit board 1 further includes a socket 3, and the positional relationship between the socket 3 and the spare pad 2 can be that the two are arranged in a staggered manner, or the two can be arranged on the same side, and the spare pad 2 is arranged on the bottom side of the socket 3. The staggered arrangement of the two helps to ensure that when the socket 3 fails, the spare pad 2 can be welded in time, so that the flight control structure can continue to be used, achieving double insurance.

[0034] The technical scheme of the utility model discloses a spare soldering pad 2, so that even in the event of accidental damage to the socket 3, the spare soldering pad 2 can continue to work, the flight control structure can be welded with the spare soldering pad 2 and used in cooperation with the electronic speed controller, thereby ensuring the continuous operation and stability of the unmanned aerial vehicle and improving the system fault tolerance.

[0035] In an embodiment of the utility model, the flight control structure further comprises a socket 3, the socket 3 is disposed on the same side as the spare soldering pad 2, the spare soldering pad 2 is disposed on the side of the circuit board 1 facing the socket 3, the socket 3 is used for electrically connecting with the electronic speed controller, and the spare soldering pad 2 is used for additional circuit connection.

[0036] In combination Figure 1 And Figure 3 In this embodiment, the socket 3 is used for electrically connecting and connecting control signals with the electronic speed controller. It can be understood that the socket 3 is disposed on one side of the circuit board 1 by welding, patching or the like, the socket 3 has a shell, the shell of the socket 3 is a plastic part, a metal pin is arranged in the shell of the socket for electrically connecting with components such as the electronic speed controller, the number of the metal pins is not limited, and the socket 3 is disposed on the edge of the circuit board 1. Further, in order to adapt to a flight control structure of smaller size, the socket 3 and the spare soldering pad 2 are disposed on one side, and the spare soldering pad 2 is disposed on the bottom side of the socket 3. This arrangement not only can adapt to a flight control structure of smaller size, but also can protect the spare soldering pad 2 from impact when the socket 3 is accidentally damaged. The above arrangement not only saves the volume of the circuit board 1, but also protects the socket 3, so that the spare soldering pad 2 can continue to work even in the event of accidental damage to the socket 3, the flight control structure can be welded with the spare soldering pad 2 and used in cooperation with the electronic speed controller, thereby ensuring the continuous operation and stability of the unmanned aerial vehicle and improving the system fault tolerance.

[0037] In an embodiment of the utility model, the flight control structure further comprises a power supply protection module 14, the power supply protection module 14 comprises an external power supply unit 141 and an internal power supply unit 142, the external power supply unit 141 is connected with an external device, the internal power supply unit 142 is connected with the flight control structure, the external power supply unit 141 is used for supplying power to the external device, and the internal power supply unit 142 is used for supplying power to the flight control structure.

[0038] In combination Figure 4 In this embodiment, the power supply protection module 14 is used for protecting the internal power supply from external influence, so that even if the external device is damaged and causes abnormal power supply, the internal power supply of the flight control structure will not be affected, or even if the external device power supply line is short-circuited, the internal power supply will not be short-circuited. The above arrangement maximally protects the important internal circuits of the flight control structure and reduces the probability of circuit damage.

[0039] In an embodiment of the present application, the circuit board 1 is provided with a plurality of mounting holes 11, each mounting hole 11 is arranged at the edge of the circuit board 1, and the two mounting holes 11 are provided with the socket 3.

[0040] In combination Figure 2 In this embodiment, the mounting hole 11 is used to provide a mounting base for the flight control structure. Accordingly, each mounting hole 11 is arranged at the edge of the circuit board 1, and can be fixed with other components through connecting members such as screws, to avoid the circuit board 1 from shaking or displacing during use, thereby enhancing the stability and reliability of the entire flight control structure. At the same time, arranging the mounting hole 11 at the edge of the circuit board 1 can save the internal space of the circuit board 1, so as to adapt to a smaller size flight control structure. The socket 3 is arranged between the two mounting holes 11, which can more effectively utilize the edge space of the circuit board 1.

[0041] In an embodiment of the present application, the center distance between adjacent mounting holes 11 is 20mm.

[0042] In this embodiment, it can be understood that Figure 1 In this embodiment, it can be understood that

[0043] In an embodiment of the present application, the circuit board 1 further comprises a plurality of shock absorbing columns 12, each shock absorbing column 12 is arranged in each mounting hole 11, one end of the shock absorbing column 12 is exposed to the circuit board 1, the other end of the shock absorbing column 12 is exposed to the other side of the circuit board 1, and the shock absorbing column 12 is provided with a through hole 12a.

[0044] In combination Figure 2In the embodiment, in order to reduce the vibration of the unmanned aerial vehicle during flight, the damping column 12 is installed to reduce the vibration between the rack and the circuit board 1. Accordingly, the material of the damping column 12 includes but is not limited to silicone, rubber and the like, and the material of silicone is preferred. The damping column 12 is provided in the mounting hole 11. It can be understood that the damping column 12 is provided with a through hole 12a penetrating the damping column 12, and the outer side of the damping column 12 is formed with a clamping groove which can be limited in the mounting hole 11, so that the damping column 12 can be better fixed and connected with the mounting hole 11. It can be understood that in an embodiment, the hole diameter of the mounting hole 11 is 4mm, and by replacing the damping column 12 with different sizes, the hole diameter of the mounting hole 11 is the hole diameter of the through hole 12a of the actual damping column 12 when the damping column 12 is limited in the mounting hole 11, so as to adapt to different sizes of connecting pieces. This setting mode not only realizes the damping effect, but also can adapt to connecting pieces of various sizes, increases the versatility and flexibility.

[0045] In an embodiment of the utility model, the size range of circuit board 1 is 26*26mm-30*30mm.

[0046] In the embodiment, the size range of the circuit board 1 includes but is not limited to 26*26mm, 27*27mm, 28*28mm, 29*29mm, 30*30mm and the like, which can be set according to specific requirements, and is not limited herein. Further, in order to adapt to smaller size flight control structure, in an embodiment, the size of the circuit board 1 is set to 26*26mm to realize higher integration of electronic components. At the same time, the size reduction of the circuit board 1 makes the components and connections on the circuit board 1 more compact, which helps to reduce power consumption, improve flight time and improve flight experience.

[0047] In an embodiment of the utility model, flight control module 13 is integrated on the side of circuit board 1 away from socket 3.

[0048] In the embodiment, it can be understood that the flight control module 13 includes but is not limited to MCU, gyroscope 133, OSDIC 132, Flash storage IC 131, barometer IC 134, USB, power IC, inductor, main control chip 135 and the like. In an embodiment, the flight control module 13 is arranged on the front and back surfaces of the circuit board 1, and the gyroscope 133, OSDIC 132, Flash storage IC 131, barometer IC 134 and the like are arranged on the front and back surfaces of the circuit board 1 respectively. It can be understood that the circuit board 1 is also provided with pads for analog image transmission and digital image transmission. The above setting mode can maximize the volume and space, adapt to smaller size flight control structure, improve flight time and improve flight experience.

[0049] The utility model discloses still provide a kind of unmanned aerial vehicle, the unmanned aerial vehicle includes rack and the flight control structure 100 described above, the specific structure of the flight control structure 100 refers to above embodiment, since the present unmanned aerial vehicle has adopted all technical solutions of above all embodiments, therefore at least have all beneficial effects brought by the technical solution of above embodiment, here no longer one by one elaboration.In this embodiment, flight control structure 100 is installed on rack, the connecting relationship of two includes but is not limited to bolt connection, clamping, riveting and so on, not limited here.

[0050] In an embodiment of the utility model, the unmanned aerial vehicle further comprises an electronic speed regulator, and the electronic speed regulator is electrically connected with the flight control structure.

[0051] In this embodiment, the electronic speed regulator is used to adjust the motor speed to realize the flight attitude adjustment of the unmanned aerial vehicle. Correspondingly, the electronic speed regulator is plugged into the socket 3 of the flight control structure to realize electrical connection and control signal connection.

[0052] The above-mentioned is only the exemplary embodiment of the utility model, and does not limit the patent range of the utility model, and any equivalent structural transformation made by using the utility model specification and drawings contents, or direct / indirect application in other related technical fields is included in the patent protection range of the utility model.

Claims

1. A flight control structure, characterized by, The flight control structure comprises: a circuit board (1); a spare pad (2) provided on one side of the circuit board (1), the spare pad (2) being used for connecting external circuits.

2. The flight control structure of claim 1, wherein, The flight control structure further comprises a socket (3) provided on the same side as the spare pad (2), the spare pad (2) being provided on the side of the circuit board (1) facing the socket (3), the socket (3) being used for electrical connection with an electronic speed controller, and the spare pad (2) being used for additional circuit connection.

3. The flight control structure of claim 1, wherein, The flight control structure further comprises a power supply protection module (14) comprising an external power supply unit (141) and an internal power supply unit (142), the external power supply unit (141) being connected with external equipment, the internal power supply unit (142) being connected with the flight control structure, the external power supply unit (141) being used for supplying power to external equipment, and the internal power supply unit (142) being used for supplying power to the flight control structure.

4. The flight control structure of claim 2, wherein, The circuit board (1) is provided with a plurality of mounting holes (11), each of the mounting holes (11) being provided on the edge of the circuit board (1), and two of the mounting holes (11) being provided with the socket (3) therebetween.

5. The flight control structure of claim 4, wherein, The center distance between adjacent mounting holes (11) is 20 mm.

6. The flight control structure of claim 5, wherein, The circuit board (1) further comprises a plurality of shock-absorbing columns (12), each of the shock-absorbing columns (12) being provided in each of the mounting holes (11), one end of each of the shock-absorbing columns (12) being exposed to the circuit board (1), the other end of each of the shock-absorbing columns (12) being exposed to the other side of the circuit board (1), and each of the shock-absorbing columns (12) being provided with a through hole (12a).

7. The flight control structure of claim 1, wherein, The size of the circuit board (1) ranges from 26*26 mm to 30*30 mm.

8. The flight control structure of claim 2, wherein, The side of the circuit board (1) opposite to the socket (3) is integrated with a flight control module (13).

9. A drone, characterized in that, The unmanned aerial vehicle comprises: a frame; and The flight control structure according to any one of claims 1 to 8, the frame being connected with the flight control structure.

10. The drone of claim 9, wherein, The unmanned aerial vehicle further comprises an electronic speed controller, the electronic speed controller being electrically connected with the flight control structure. The unmanned aerial vehicle further comprises an electronic speed controller, the electronic speed controller being electrically connected with the flight control structure.

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