Flight control line interface integrated equipment of unmanned aerial vehicle

Abstract

The invention relates to an unmanned aerial vehicle flight control line interface integrated device, and belongs to the technical field of unmanned aerial vehicle line interface integration, the unmanned aerial vehicle flight control line interface integrated device comprises an upper fixing plate, a fixing middle frame, a lower fixing seat, a plurality of function module board cards, a flight control module and a mainboard, the fixing middle frame is located on the upper surface of the lower fixing seat, and the upper fixing plate is located above the fixing middle frame; the upper fixing plate and the lower fixing seat are connected through the supporting columns, the supporting columns are located on the periphery of the upper fixing plate and the periphery of the lower fixing seat and penetrate through the fixing middle frame, the main board is fixedly arranged in the fixing middle frame, the function module boards are arranged between the upper fixing plate and the main board in a clamped mode, and the flight control module is installed on the main board. The multiple functional module board cards are connected with the mainboard, the upper ends and the lower ends of the multiple functional module board cards are detachably connected with the upper fixing plate and the mainboard respectively, through the modular design of the multiple functional module board cards, the whole equipment is easy to maintain and upgrade, production and control are easier, and the system flexibility is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicle (UAV) circuit interface integration, and in particular relates to an UAV flight control circuit interface integration device. Background Art

[0002] With the continuous expansion of the application of drones in military and civilian fields, such as military reconnaissance, agricultural plant protection, logistics distribution, aerial photography and mapping, the performance requirements of drones are increasing day by day. As a core component, the performance improvement of the electronic control system is crucial. It is necessary to develop more advanced electronic control technology to meet the efficient and stable operation of drones in different scenarios. The existing drone electronic control modular integrated equipment has the following problems: 1. Traditional hardware upgrades often require redesigning hardware and software, which is complex to operate and difficult to develop, and may also involve compatibility debugging. 2. Traditional fault location is complex, maintenance requires professional knowledge and tools, and may also affect the entire system, increasing maintenance costs and difficulty. 3. Users have diverse requirements for drone performance. Users focus on wireless transmission performance, and users need to replace wireless transmission modules with stronger transmission capabilities. 4. The internal structure of the traditional host is compact, the heat dissipation airflow is turbulent, and local overheating is prone to occur, affecting the hardware life and performance stability. Based on the above problems, this solution was created. Summary of the invention

[0003] In view of the shortcomings of the prior art, the technical problem to be solved by the present invention is to provide a UAV flight control circuit interface integrated device, which modularizes the functional module board to make the entire device easy to maintain and upgrade, easier to produce and manage, and improve the system flexibility.

[0004] In order to solve the above technical problems, the technical solution adopted by the present invention is: a UAV flight control circuit interface integrated device, including an upper fixed plate, a fixed middle frame, a lower fixed seat, a plurality of functional module boards, a flight control module and a main board, the fixed middle frame is located on the upper surface of the lower fixed seat, the upper fixed plate is located above the fixed middle frame, the upper fixed plate and the lower fixed seat are connected by support columns, the support columns are located around the upper fixed plate and the lower fixed seat and pass through the fixed middle frame, the main board is fixed in the fixed middle frame, the plurality of functional module boards are arranged between the upper fixed plate and the main board, the flight control module is installed on the main board, the plurality of functional module boards are connected to the main board and the upper and lower ends are detachably connected to the upper fixed plate and the main board respectively.

[0005] Furthermore, the main board is provided with an electronic connector, the functional module board is plugged into the electronic connector, and the functional module board is electrically connected to the main board via the electronic connector.

[0006] Furthermore, the electronic connector is a PCIE-36PIN interface, a PCIE-76PIN interface, a DVI interface, a network cable interface or an aviation interface.

[0007] Furthermore, a plurality of connection notches are provided on the upper and lower surfaces of the functional module board, and an H-shaped connection limiter is provided at the connection notch. The plate bodies of the functional module board located on both sides of the connection notch are respectively clamped in the two clamping grooves of the H-shaped connection limiter, and the middle part of the H-shaped connection limiter extends into the connection notch. A through hole penetrating up and down is formed in the middle part of the H-shaped connection limiter. The upper fixed plate and the main board are provided with a first connection hole and a second connection hole corresponding to the through hole. The functional module board is fixed by two connecting parts that are respectively screwed into the first connection hole and the second connection hole and pass through the through holes of the corresponding H-shaped connection limiter and then press against the bottom wall of the connection notch.

[0008] Furthermore, the UAV flight control circuit interface integrated device also includes a PCB fixed connector, which is perpendicular to the main board and installed on the functional module board.

[0009] Furthermore, a notch is provided on the surface of the fixed middle frame, and a front panel debugging interface is provided on the main board, and the front panel debugging interface extends out from the notch.

[0010] Furthermore, the UAV flight control circuit interface integrated device also includes a protective shell, which is sleeved on the upper fixed plate and covers the functional module board, the flight control module and the main board.

[0011] Furthermore, a limiting channel is formed on the lower surface of the upper fixing plate, and the upper end of the functional module board is limited in the limiting channel.

[0012] Furthermore, heat dissipation gaps are provided on both sides of the lower fixing seat.

[0013] Further, the electronic connector uses a PCIE-36PIN interface, the CAN port of the functional module board is connected to the PIN10-CAN_L and P11-CAN-H of the electronic connector; the I2C port of the functional module board is connected to the PIN5-I2C_SCL and PIN6-I2C_SDA of the electronic connector; the Uart port of the functional module board is connected to the PIN19-UART_TX and PIN20-UART_RX of the electronic connector; The CAN port of the flight control module is connected to PIN28-CAN_L and P29-CAN_H of the electronic connector; the I2C port of the flight control module is connected to PIN7-I2C_SCL and PIN8-I2C_SDA of the electronic connector; the Uart port of the flight control module is connected to PIN21-UART_TX and PIN22-UART_RX of the electronic connector; A plurality of the electronic connectors are connected in parallel.

[0014] Compared with the prior art, the present invention has the following beneficial effects: 1. Existing UAV flight control components generally adopt split single components, which are connected to the core flight control through various interfaces and cables. This method has the problems of heavy weight of the split component structure, complex placement layout, troublesome preparation and identification of multiple interfaces and wires, and low interface reliability; an integrated method of designing multiple functional modules on a PCB board is adopted. This method has the problems of mutual interference of signals in the onboard functional areas, the need to replace the entire PCB board when a certain functional area fails, and the high cost and efficiency of maintenance and troubleshooting. Therefore, this solution modularizes multiple functional module boards. When a functional module board fails, it can be directly disassembled and replaced with a new module. There is no need to disassemble the entire shell as complicated as traditional UAVs, and it can also effectively avoid damage to other components during the maintenance process.

[0015] 2. If you need to improve the performance of the drone, you only need to select a high-performance functional module board that meets the interface standards for replacement, without having to replace the entire integrated device.

[0016] 3. Moreover, in this solution, the functional module board is plugged into the electronic connector on the mainboard. Compared with the existing UAV flight control line interface integrated equipment, it reduces the shell and cables of the hardware components, reduces the weight and wire types of the avionics system, and is more conducive to the design of the internal functional layout and routing of the aircraft.

[0017] 4. Improve the reliability of communication between the functional module board, flight control module and main board. The functional module board is connected to the main board by plugging, the flight control module is arranged on the main board, and a limit channel is arranged on the upper shell to limit the upper end of the functional module board. By setting an H-shaped connection limiter, the upper fixed plate, the functional module board and the main board are connected to achieve secondary limit. The reliability in terms of vibration resistance, impact resistance and durability is much higher than the existing wire plug-in method, which reduces the plug-in interface and also reduces the failure rate.

[0018] 5. Since each functional module board is plugged into the main board, different functional module boards can be produced and assembled at the same time during the production process, which greatly shortens the production cycle compared to the traditional UAV production. Just like the assembly line operation in a factory, different groups are responsible for different modules, and then they are combined at the end, which speeds up the overall production speed. Moreover, each functional module board can be used as an independent unit for quality inspection, making it easier to discover and solve potential quality problems. If a functional module board fails the inspection, only the functional module board needs to be reworked without affecting other qualified parts.

[0019] 6. Users can choose different functional module board combinations according to their needs. For example, for rescue users, they can choose a high-performance image transmission module; for ordinary users, they may prefer to choose a small, energy-saving and efficient module combination to better meet the personalized needs of different users. Moreover, the new module can be quickly applied to the UAV flight control line interface integration device in this solution. It only needs to adapt the socket of the functional module board to the socket of the electronic connector. Even if you encounter a functional module board with a special socket, you can adapt it by replacing a single electronic connector. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a three-dimensional structural schematic diagram of a UAV flight control circuit interface integrated device of the present invention; Figure 2 It is a three-dimensional structural schematic diagram of the functional module board and the main board in the present invention; Figure 3 It is a bottom view structural schematic diagram of the upper fixing plate in the present invention; Figure 4 It is a top view structural schematic diagram of a mixed arrangement of a full-board functional module and a half-board functional module in the present invention; Figure 5 It is a top view structural diagram of a full board card with all selected functional modules in the present invention; Figure 6 It is a top view structural diagram of a half-board card with fully selected functional modules in the present invention; Figure 7 It is a cross-sectional structural schematic diagram of the full board of the functional module in the present invention; Figure 8 It is a cross-sectional structural schematic diagram of a functional module half-board in the present invention; Fig. 9 It is a schematic diagram of the three-dimensional structure of the H-shaped connection limiter in the present invention; Fig.10 It is a front view structural diagram of the functional module board in the present invention.

[0021] Markings in the figure: 1. Upper fixed plate; 11. Limit channel; 2. Fixed middle frame; 21. Make way gap; 3. Lower fixed seat; 31. Heat dissipation gap; 4. Functional module board; 41. Connection gap; 5. Flight control module; 6. Main board; 61. Front panel debugging interface; 62. Electronic connector; 7. Support column; 8. H-shaped connection limiter; 81. Through hole. DETAILED DESCRIPTION

[0022] In order to make the above features and advantages of the present invention more obvious and easy to understand, embodiments are given below with reference to the accompanying drawings for detailed description as follows.

[0023] like Figure 1-Figure 10 As shown, this embodiment provides a UAV flight control circuit interface integrated device, including a PCB fixed connector, a protective shell, an upper fixed plate 1, a fixed middle frame 2, a lower fixed seat 3, multiple functional module boards 4, a flight control module 5 and a main board 6.

[0024] The fixed middle frame 2 is located on the upper surface of the lower fixed seat 3, the upper fixed plate 1 is located above the fixed middle frame 2, the upper fixed plate 1 and the lower fixed seat 3 are connected by a support column 7, the support column 7 is located around the upper fixed plate 1 and the lower fixed seat 3 and passes through the fixed middle frame 2, the main board 6 is fixed in the fixed middle frame 2, specifically, an annular limiting step is formed on the circumference of the inner cavity of the lower surface of the fixed middle frame 2, the main board 6 is installed on the lower surface of the fixed middle frame 2 and the upper surface fits with the annular limiting step, the upper surface of the fixed middle frame 2 is provided with guide holes at four diagonal positions, the lower end of the support rod extends into the guide hole and the upper end fits with the upper fixed plate 1, the upper end of the support rod is fixed by passing the upper fixed plate 1 through a screw and screwing into the top of the support rod, and the lower end of the support rod is fixed by passing the main board 6 through a screw and entering the guide hole and screwing into the top of the support rod. The height of the support rod is adjusted according to the height of the functional module board 4. (Connection relationship between the upper fixed plate, the fixed middle frame and the lower fixed seat) A flight control module 5 is installed on the upper surface of the main board 6. A plurality of electronic connectors 62 are arranged on the upper surface of the main board 6. The electronic connector 62 is electrically connected to the main board 6 to realize the transmission of communication signals. The electronic connector 62 uses a PCIE-36PIN interface, a PCIE-76PIN interface (PCIE-M-MKY), a DVI interface, a network cable interface or an aviation interface, etc. As long as it is an interface that can be plugged in with the functional module board 4, the electronic connector 62 in this solution uses a PCIE-36PIN interface.

[0025] The pin definition table of the PCIE-36PIN interface is shown in Table 1: Table 1

[0026] The pin definition table of the PCIE-M-MKY interface (76Pin) is shown in Table 2: Table 2

[0027] A plurality of functional module boards 4 are arranged between the upper fixed plate 1 and the main board 6. The plurality of functional module boards 4 are connected to the main board 6 and the upper and lower ends are detachably connected to the upper fixed plate 1 and the main board 6, respectively. Specifically, the functional module boards 4 are plugged into the interface of the electronic connector 62, and a plurality of connection notches 41 are arranged on the upper and lower surfaces of the functional module boards 4. An H-shaped connection stopper 8 is arranged at the connection notch 41. The board bodies of the functional module boards 4 located on both sides of the connection notch 41 are respectively arranged in the two card slots of the H-shaped connection stopper 8. The middle part of the H-shaped connection stopper 8 extends into the connection notch 41. A through hole 81 penetrating from top to bottom is formed in the middle part of the H-shaped connection stopper 8. The upper fixed plate 1 and the main board are formed with a first connection hole and a second connection hole corresponding to the through hole 81. The functional module boards 4 are respectively screwed into the first connection hole and the second connection hole by two connecting members and pass through the through hole 81 of the corresponding H-shaped connection stopper 8, and then abut against the bottom wall of the connection notch 41 to achieve fixation. (Connection relationship of functional module boards) Preferably, the functional module board 4 can also be connected to the upper fixing plate 1 and the main board 6 through a snap-fit ​​structure. The snap-fit ​​structure adopts an existing common structure and will not be described in detail here.

[0028] like Figure 4 As shown, according to the area limitation that can be arranged on the main board 6, the functional module board 4 in this solution includes a functional module half board and a functional module full board. The length of the functional module full board is greater than that of the functional module half board, and the sockets of the two are the same. The number of connecting notches 41 at the upper and lower ends of the functional module half board is two, and the number of connecting notches 41 at the upper and lower ends of the functional module full board is three. Only by such an arrangement can the installation stability of the functional module board 4 be ensured and the vibration during operation be reduced.

[0029] Preferably, if Figure 5-Figure 6 As shown, according to the models of the mainboard 6 of different specifications, all functional module full-board cards can be selected for plugging, or all functional module half-board cards can be selected for plugging.

[0030] The function module board 4 is connected to the main board 6 by plugging, the flight control module 5 is arranged on the main board 6, and a limit channel 11 is arranged on the upper shell to limit the upper end of the function module board 4, and by setting an H-shaped connection limiter 8, the upper fixed plate 1, the function module board 4 and the main board 6 are connected to achieve secondary limit. The reliability in terms of vibration resistance, impact resistance and durability is much higher than the existing wire plug-in method, reducing the plug-in interface, and also reducing the failure rate. Moreover, since each function module board 4 is plugged in with the main board 6 in the form of plug-in, different function module boards 4 can be produced and assembled at the same time during the production process, which greatly shortens the production cycle compared with the traditional UAV whole machine production. Just like the assembly line operation of the factory, different groups are responsible for different modules respectively, and finally combined to speed up the overall production speed. Moreover, each function module board 4 can be used as an independent unit for quality inspection, which makes it easier to find and solve potential quality problems. If a function module board 4 fails the inspection, only the function module board 4 needs to be reworked without affecting other parts that have already passed.

[0031] The PCB fixed connector is perpendicular to the main board 6 and is installed on the functional module board 4. The PCB fixed connector is a universal connector.

[0032] Preferably, a limiting channel 11 is formed on the lower surface of the upper fixing plate 1, and the upper end of the functional module board 4 is limited in the limiting channel 11, which further limits the functional module board 4 and facilitates its installation.

[0033] Preferably, a clearance notch 21 is provided on the surface of the fixed middle frame 2 , and a front panel debugging interface 61 is provided on the main board 6 , and the front panel debugging interface 61 extends out from the clearance notch 21 .

[0034] Preferably, heat dissipation notches 31 are provided on both sides of the lower fixing seat 3 , and there are multiple heat dissipation notches 31 on each side and they are arranged at intervals to facilitate heat dissipation.

[0035] The protective shell is mounted on the upper fixing plate 1 and covers the functional module board 4 , the flight control module 5 and the main board 6 .

[0036] The present solution also provides a control method for a software interface, including the following: the electronic connector 62 uses a PCIE-36PIN interface. First, the CAN port of the functional module board 4 is connected to PIN10-CAN_L and P11-CAN-H of the electronic connector 62; the I2C port of the functional module board 4 is connected to PIN5-I2C_SCL and PIN6-I2C_SDA of the electronic connector 62; the Uart port of the functional module board 4 is connected to PIN19-UART_TX and PIN20-UART_RX of the electronic connector 62.

[0037] Secondly, the CAN port of the flight control module 5 is connected to PIN28-CAN_L and P29-CAN_H of the electronic connector 62; the I2C port of the flight control module 5 is connected to PIN7-I2C_SCL and PIN8-I2C_SDA of the electronic connector 62; the Uart port of the flight control module 5 is connected to PIN21-UART_TX and PIN22-UART_RX of the electronic connector 62.

[0038] Finally, multiple electronic connectors 62 are connected in parallel to support multiple functional module boards 4 to be connected to the same flight control module 5 .

[0039] The control method of the software interface realizes modularization by parallel connection between the electronic connectors 62, so that flexible expansion can be achieved and maintenance costs can be reduced. In addition, the functional module boards 4 are not related to each other. It is particularly suitable for scenarios with strict requirements on real-time performance, reliability and multi-tasking capabilities, and the simplification and enhancement of complex systems can be achieved through standardized interfaces.

[0040] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for illustrating the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which shall fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A UAV flight control circuit interface integration device, characterized by: It includes an upper fixed plate, a fixed middle frame, a lower fixed seat, multiple functional module boards, a flight control module and a main board. The fixed middle frame is located on the upper surface of the lower fixed seat, the upper fixed plate is located above the fixed middle frame, the upper fixed plate and the lower fixed seat are connected by support columns, the support columns are located around the upper fixed plate and the lower fixed seat and pass through the fixed middle frame, the main board is fixed in the fixed middle frame, the multiple functional module boards are arranged between the upper fixed plate and the main board, the flight control module is installed on the main board, the multiple functional module boards are connected to the main board, and the upper and lower ends are respectively detachably connected to the upper fixed plate and the main board.

2. The UAV flight control circuit interface integrated device according to claim 1, characterized in that: The main board is provided with an electronic connector, the functional module board is plugged into the electronic connector, and the functional module board is electrically connected to the main board via the electronic connector.

3. The UAV flight control circuit interface integrated device according to claim 2, characterized in that: The electronic connector is selected from a PCIE-36PIN interface, a PCIE-76PIN interface, a DVI interface, a network cable interface or an aviation interface.

4. The UAV flight control circuit interface integrated device according to claim 1, characterized in that: The upper and lower surfaces of the functional module board are provided with a plurality of connection notches, and an H-shaped connection limiter is provided at the connection notch. The plate bodies of the functional module board located on both sides of the connection notch are respectively clamped in the two clamping grooves of the H-shaped connection limiter, and the middle part of the H-shaped connection limiter extends into the connection notch. A through hole penetrating up and down is formed in the middle part of the H-shaped connection limiter. The upper fixed plate and the main board are provided with a first connection hole and a second connection hole corresponding to the through hole. The functional module board is fixed by two connecting pieces that are respectively screwed into the first connection hole and the second connection hole and pass through the through holes of the corresponding H-shaped connection limiter and then abut against the bottom wall of the connection notch.

5. The UAV flight control circuit interface integrated device according to claim 1, characterized in that: The UAV flight control circuit interface integrated device also includes a PCB fixed connector, which is perpendicular to the main board and installed on the functional module board.

6. The UAV flight control circuit interface integrated device according to claim 1, characterized in that: A clearance notch is arranged on the surface of the fixed middle frame, and a front panel debugging interface is provided on the mainboard, and the front panel debugging interface extends out from the clearance notch.

7. The UAV flight control circuit interface integrated device according to claim 1, characterized in that: The UAV flight control circuit interface integrated device also includes a protective shell, which is sleeved on the upper fixed plate and covers the functional module board, the flight control module and the main board.

8. The UAV flight control circuit interface integrated device according to claim 1, characterized in that: A limiting channel is formed on the lower surface of the upper fixing plate, and the upper end of the functional module board is limited in the limiting channel.

9. The UAV flight control circuit interface integrated device according to claim 1, characterized in that: Heat dissipation gaps are arranged on both sides of the lower fixing seat.

10. The UAV flight control circuit interface integrated device according to claim 3, characterized in that: The electronic connector uses a PCIE-36PIN interface, the CAN port of the functional module board is connected to the PIN10-CAN_L and P11-CAN-H of the electronic connector; the I2C port of the functional module board is connected to the PIN5-I2C_SCL and PIN6-I2C_SDA of the electronic connector; the Uart port of the functional module board is connected to the PIN19-UART_TX and PIN20-UART_RX of the electronic connector; The CAN port of the flight control module is connected to PIN28-CAN_L and P29-CAN_H of the electronic connector; the I2C port of the flight control module is connected to PIN7-I2C_SCL and PIN8-I2C_SDA of the electronic connector; the Uart port of the flight control module is connected to PIN21-UART_TX and PIN22-UART_RX of the electronic connector; A plurality of the electronic connectors are connected in parallel.

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