Uav flight control system based on three-dimensional circuit

Abstract

The application relates to a three-dimensional circuit-based unmanned aerial vehicle flight control system. The three-dimensional circuit-based unmanned aerial vehicle flight control system comprises an insulating casing, a large-current three-dimensional circuit, a communication three-dimensional circuit, a main control circuit board, a power supply circuit board and a wireless communication circuit board. The large-current three-dimensional circuit is formed on the inner wall of the insulating casing and forms an integral whole with the insulating casing. The communication three-dimensional circuit is formed on the inner wall of the insulating casing and forms an integral whole with the insulating casing. The main control circuit board is detachably installed on the first installation position and electrically contacts the large-current three-dimensional circuit and the communication three-dimensional circuit respectively. The power supply circuit board is detachably installed on the second installation position and electrically contacts the large-current three-dimensional circuit. The wireless communication circuit board is detachably installed on the third installation position and electrically contacts the communication circuit board. The three-dimensional circuit-based unmanned aerial vehicle flight control system is convenient to assemble, solves a series of EMC problems caused by cable winding, and is beneficial to the miniaturization and lightening development of the unmanned aerial vehicle.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, and particularly to an unmanned aerial vehicle flight control system based on a three-dimensional circuit. BACKGROUND

[0002] The flight control system is a core component of the unmanned aerial vehicle, and its functions are to transmit flight hovering, attitude change and other information back to the flight control through various sensors, and to send various instructions through operation and judgment by the flight control, so that the execution mechanism completes the action and flight attitude adjustment. The flight control system has a large number of functional modules, and the integration is difficult due to the rack structure, which causes the power cables and communication cables between the functional modules to be directly exposed to the cabin environment. Thus, the following problems exist:

[0003] 1) The cables, antennas and other connecting components need to have sufficient excess to complete the installation, resulting in excess quality of the product, and the assembly of the whole machine is difficult, which is not conducive to the realization of lightweight and batch production.

[0004] 2) The cables are efficient electromagnetic wave receiving antennas and radiating antennas. Due to the large number of cables between systems and inside the system, coupling, loop differential mode radiation and other problems are easy to occur, which directly affects whether the whole machine system can pass the EMC test. SUMMARY

[0005] Therefore, it is necessary to provide an unmanned aerial vehicle flight control system based on a three-dimensional circuit, which has small volume, simple assembly and can overcome EMC problems.

[0006] An unmanned aerial vehicle flight control system based on a three-dimensional circuit, comprising:

[0007] An insulating shell is a hollow structure having opposite first and second ends; the insulating shell has a first mounting position, a second mounting position and a third mounting position spaced apart in the direction from the first end to the second end;

[0008] A large-current three-dimensional circuit is formed on the inner wall of the insulating shell and forms an integral whole with the insulating shell; two ends of the large-current three-dimensional circuit extend to the first mounting position and the second mounting position, respectively;

[0009] A communication three-dimensional circuit is formed on the inner wall of the insulating shell and forms an integral whole with the insulating shell; the communication three-dimensional circuit is spaced apart from the large-current three-dimensional circuit, and two ends thereof extend to the first end and the second end, respectively;

[0010] The main control circuit board, the power supply circuit board and the wireless communication circuit board are spaced and accommodated in the insulating casing; the main control circuit board is detachably installed on the first installation position and respectively electrically connected with one end of the large-current three-dimensional circuit away from the second installation position and one end of the communication three-dimensional circuit away from the second end; the power supply circuit board is detachably installed on the second installation position and electrically connected with one end of the large-current three-dimensional circuit away from the first installation position; and the wireless communication circuit board is detachably installed on the third installation position and electrically connected with one end of the communication three-dimensional circuit away from the first end.

[0011] The unmanned aerial vehicle flight control system based on the three-dimensional circuit forms the large-current three-dimensional circuit and the communication three-dimensional circuit in the insulating casing and forms an integral whole with the insulating casing, and only needs to install the main control circuit board, the power supply circuit board and the wireless communication circuit board on the first installation position, the second installation position and the third installation position in the insulating casing respectively, so that the electrical connection between the main control circuit board and the power supply circuit board is realized through the large-current three-dimensional circuit, the communication connection between the main control circuit board and the wireless communication circuit board is realized through the communication three-dimensional circuit, and the installation is convenient and fast. The large-current three-dimensional circuit and the communication three-dimensional circuit form an integral whole with the insulating casing, the wiring space is saved, the cable weight is saved, and the miniaturization and light weight development of the unmanned aerial vehicle are facilitated. In addition, compared with the traditional unmanned aerial vehicle flight control system based on the three-dimensional circuit, a large number of cables are removed in the unmanned aerial vehicle flight control system based on the three-dimensional circuit, and the EMC problems such as attenuation, crosstalk, coupling, loop differential mode radiation caused by the winding of the cables can be avoided. BRIEF DESCRIPTION OF DRAWINGS

[0012] Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are for purposes of illustration only and are not intended to be limiting, of the present application. Like reference numerals are used to refer to like elements throughout. In the drawings:

[0013] Figure 1 FIG. 1 is a structural schematic diagram of an unmanned aerial vehicle flight control system based on a three-dimensional circuit according to an embodiment of the present application;

[0014] Figure 2 FIG. 2 is a structural schematic diagram of the unmanned aerial vehicle flight control system based on the three-dimensional circuit according to the embodiment of the present application; Figure 1 FIG. 3 is a sectional view of the communication three-dimensional circuit including conductive lines and components in the unmanned aerial vehicle flight control system based on the three-dimensional circuit shown in FIG. 2;

[0015] Figure 3 FIG. 4 is a sectional view of the communication three-dimensional circuit including conductive lines and self-resetting fuses in the unmanned aerial vehicle flight control system based on the three-dimensional circuit shown in FIG. 2; Figure 1

[0016] ​Figure 4 For Figure 1 Figure 1 shows the position relationship diagram of the large current three-dimensional circuit and the communication three-dimensional circuit in the insulating shell of the unmanned aerial vehicle flight control system based on the three-dimensional circuit.

[0017] The specific embodiment of the drawing reference: 100, the unmanned aerial vehicle flight control system based on the three-dimensional circuit; 110, the insulating shell; 111, the first end; 112, the second end; 113, the first mounting position; 1131, the first connecting hole; 114, the second mounting position; 1141, the second connecting hole; 115, the third mounting position; 1151, the mounting hole; 116, the shell; 117, the first connecting plate; 118, the second connecting plate; 120, the large current three-dimensional circuit; 130, the communication three-dimensional circuit; 131, the conductive circuit; 132, the component; 133, the self-recovery fuse; 140, the main control circuit board; 142, the first data communication pin; 150, the power supply circuit board; 160, the wireless communication circuit board; 162, the second data communication pin; 170, the first connecting piece; 180, the second connecting piece; 190, the third connecting piece. Specific embodiments

[0018] In order to facilitate the understanding of the present application, the present application will be described more fully below with reference to the accompanying drawings. The preferred embodiments of the present application are shown in the drawings. However, the present application can be implemented in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of the present application more thorough and comprehensive.

[0019] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the present application belongs. The terms used in the specification of the present application herein are only for the purpose of describing specific embodiments and are not intended to limit the present application. The term "and / or" used herein includes any and all combinations of one or more of the associated listed items.

[0020] In describing the positional relationship, unless otherwise specified, when an element is referred to as being "on" another element, it can be directly on the other element or there can be an intermediate element. It can also be understood that when an element is referred to as being "between" two elements, it can be the only one between the two elements, or there can be one or more intermediate elements.

[0021] In the case of using "including", "having", and "containing" described herein, unless the explicit limiting term is used, such as "only", "consisting of", etc., another component can also be added. Unless otherwise mentioned, the singular form of the term can include the plural form, and cannot be understood as the number of one.

[0022] In addition, the drawings are not drawn to scale 1:1, and the relative sizes of the elements are only drawn by way of example in the drawings and not necessarily to true scale.

[0023] As described in the background, in the conventional UAV flight control system, not only the number of functional modules is large, but also the functional modules are usually electrically connected through cables exposed in the cabin. A large number of cables exposed in the cabin environment need to have sufficient margins to complete the installation, which not only increases the assembly difficulty of the whole machine, but also increases the weight of the UAV. Moreover, since the cables are efficient electromagnetic wave receiving antennas and radiating antennas, and the cables in the UAV flight control system are multiple and redundant, EMC problems such as coupling, loop differential mode radiation, etc. are prone to occur during use of the UAV. Based on this, the applicant proposes a cable-free UAV flight control system based on a three-dimensional circuit.

[0024] Figures 1 to 3 The structure of the UAV flight control system based on a three-dimensional circuit in an embodiment of the application is shown. For ease of illustration, the drawings only show part of the structure related to the embodiment of the application.

[0025] Please refer to Figures 1 to 3 The UAV flight control system based on a three-dimensional circuit in the preferred embodiment of the application 100 includes an insulating casing 110, a large-current three-dimensional circuit 120, a communication three-dimensional circuit 130, a main control circuit board 140, a power supply circuit board 150, and a wireless communication circuit board 160.

[0026] The insulating casing 110 is a hollow structure with opposite first and second ends 111 and 112. The insulating casing 110 has a first mounting position 113, a second mounting position 114, and a third mounting position 115 arranged in the direction from the first end 111 to the second end 112. Among them, the insulating casing 110 can be part of the UAV casing, or the entire UAV casing. Of course, the insulating casing 110 can be only a hollow shell 116 structure, or a component composed of the shell 116 structure and other structures arranged in the shell 116 structure. When the insulating casing 110 is a component, the components in the insulating casing 110 can be fixed by welding, clamping, etc., or can be integrally formed by 3D printing, injection molding, machining, etc. In this embodiment, the insulating casing 110 is integrally formed by 3D printing, injection molding, or machining.

[0027] It should be noted that the first mounting position 113, the second mounting position 114, and the third mounting position 115 can be virtual mounting positions, or can be protruding structures, plate structures, grooves, holes, etc. formed on the inner wall of the insulating casing 110.

[0028] Please refer to Figure 3The high-current three-dimensional circuit 120 is formed on the inner wall of the insulating casing 110 and integrated with the insulating casing 110. The high-current three-dimensional circuit 120 extends to the first mounting position 113 and the second mounting position 114 respectively. Thus, the high-current three-dimensional circuit 120 is connected between the first mounting position 113 and the second mounting position 114. Specifically, the high-current three-dimensional circuit 120 is formed on the inner wall of the insulating casing 110 by laser processing and chemical plating, so that the high-current three-dimensional circuit 120 is integrated with the insulating casing 110 as a whole structure.

[0029] The communication three-dimensional circuit 130 is formed on the inner wall of the insulating casing 110 and integrated with the insulating casing 110. The communication three-dimensional circuit 130 is spaced apart from the high-current three-dimensional circuit 120 and extends to the first end 111 and the second end 112 respectively. Thus, the communication three-dimensional circuit 130 is used for electrically connecting the components located at the first end 111 and the second end 112 in the insulating casing 110. Specifically, the communication three-dimensional circuit 130 is formed on the inner wall of the insulating casing 110 by laser processing and chemical plating, so that the communication three-dimensional circuit 130 is integrated with the insulating casing 110 as a whole structure.

[0030] The master control circuit board 140, the power supply circuit board 150 and the wireless communication circuit board 160 are spaced apart and accommodated in the insulating casing 110. The master control circuit board 140 is detachably mounted on the first mounting position 113 and electrically contacts with the end of the high-current three-dimensional circuit 120 away from the second mounting position 114 and the end of the communication three-dimensional circuit 130 away from the second end 112. The power supply circuit board 150 is detachably mounted on the second mounting position 114 and electrically contacts with the end of the high-current three-dimensional circuit 120 away from the first mounting position 113. The wireless communication circuit board 160 is detachably mounted on the third mounting position 115 and electrically contacts with the end of the communication circuit board away from the first end 111. Specifically, the master control circuit board 140, the power supply circuit board 150 and the wireless communication circuit board 160 are sequentially and parallelly arranged along the direction from the first end 111 to the second end 112.

[0031] Thus, in the assembling process of the unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit, the main control circuit board 140, the power supply circuit board 150 and the wireless communication circuit board 160 are respectively installed on the first installation position 113, the second installation position 114 and the third installation position 115 in the insulating casing 110, and the main control circuit board 140 can be automatically connected with one end of the large-current three-dimensional circuit 120 and one end of the communication three-dimensional circuit 130, the power supply circuit board 150 can be automatically connected with the other end of the large-current three-dimensional circuit 120, and the wireless communication circuit board 160 can be automatically connected with the other end of the communication three-dimensional circuit 130, so as to realize the electrical connection among the main control circuit board 140, the power supply circuit board 150 and the wireless communication circuit board 160, and the assembling is convenient and fast.

[0032] Moreover, the large-current three-dimensional circuit 120 and the communication three-dimensional circuit 130 are formed on the inner wall of the insulating casing 110, and the three form an integral whole, so that the unmanned aerial vehicle flight control system is cable-free, which saves the wiring space and the weight of the cable, and solves the EMC problems such as attenuation, crosstalk, coupling, loop differential mode radiation caused by the cable winding together. Therefore, the unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit is cable-free, which realizes the convenient and fast assembling, solves a series of EMC problems caused by the cable winding, and is also beneficial to the miniaturization and light weight development of the unmanned aerial vehicle.

[0033] Please refer to Figure 2 In some embodiments, the communication three-dimensional circuit 130 includes a conductive circuit 131 formed on the inner wall of the insulating casing 110 and a component 132 arranged in the conductive circuit 131. The two ends of the conductive circuit 131 are respectively in electrical contact with the main control circuit board 140 and the wireless communication circuit board 160. The component 132 is one or several of a capacitor, a resistor, a connector, a packaged chip and an environmental detection element. Specifically, the component 132 is fixed on the inner wall of the insulating casing 110 by adhesion or the like, and is in electrical connection or contact with the conductive circuit 131.

[0034] Thus, the component 132 is fixed on the inner wall of the insulating casing 110, so as to reduce the number of components 132 on the integrated circuit board (such as the main control circuit board, the wireless communication circuit board, etc.), and thus the volume of the integrated circuit board can be reduced, and the volume of the unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit can be further reduced, which is more beneficial to the miniaturization of the unmanned aerial vehicle.

[0035] The environment detection member can be a temperature sensor, a humidity sensor, a vibration sensor, or other sensor with high sensitivity to the environment. When the environment detection member is fixed to the inner wall of the insulating casing 110, the most suitable position on the inner wall of the insulating casing 110 can be selected for fixation, so as to obtain accurate measurement data. Therefore, the environment detection member arranged on the inner wall of the insulating casing 110 can improve the use performance of the unmanned aerial vehicle.

[0036] Please refer to Figure 3 In some embodiments, the communication stereo circuit 130 includes a conductive circuit 131 formed on the inner wall of the insulating casing 110 and a self-resetting fuse 133 arranged on the conductive circuit 131. The two ends of the conductive circuit 131 are in electrical contact with the main control circuit board 140 and the wireless communication circuit board 160, respectively. The self-resetting fuse 120 is fixed to the inner wall of the insulating casing 110 and is used to make the conductive circuit 131 conductive or non-conductive.

[0037] When there is no large current passing through, when there is no large current passing through the conductive circuit 131, the self-resetting fuse 133 can realize the conduction of the circuit between the main control circuit board 140 and the wireless communication circuit board 160; when a large current occurs in the conductive circuit 131 due to short circuit or overload; the self-resetting fuse 133 forms a high resistance state, and the working current in the conductive circuit 131 rapidly decreases, thereby limiting and protecting the elastic stereo circuit, achieving the purpose of short circuit or overload protection, and improving the use safety of the above-mentioned unmanned aerial vehicle flight control system 100 based on the stereo circuit.

[0038] In the above two embodiments, the conductive circuit 131 is formed on the inner wall of the insulating casing 110 and forms an integral whole with the insulating casing 110.

[0039] Please refer to Figure 4 In some embodiments, the insulating casing 110 includes a shell 116 in the form of a hollow cylindrical structure with two open ends, a first mounting plate as a first mounting site 113, a second mounting plate as a second mounting site 114, and a third mounting plate as a third mounting site 115. The first mounting plate, the second mounting plate, and the third mounting plate are protruded on the inner wall of the shell 116. The first mounting plate, the second mounting plate, and the third mounting plate can be fixedly connected with the shell 116 by welding, bonding, or other methods, or can be integrally formed with the casing by casting, 3D printing, or other methods. In this embodiment, the first mounting plate, the second mounting plate, the third mounting plate, and the shell 116 are integrally formed by 3D printing, injection molding, or mechanical processing.

[0040] The high-current three-dimensional circuit 120 is formed on the inner wall of the shell 116, the surface of the first mounting plate and the surface of the second mounting plate, and forms an integral whole with the shell 116, the first mounting plate and the second mounting plate respectively. Two ends of the high-current three-dimensional circuit 120 are respectively located on the surface of the first mounting plate and the surface of the second mounting plate. The communication three-dimensional circuit 130 is formed on the inner wall of the shell 116 and forms an integral whole with the inner wall of the shell 116.

[0041] The main control circuit board 140 is detachably mounted on the first mounting plate and is in electrical contact with the high-current three-dimensional circuit 120 on the first mounting plate and the communication three-dimensional circuit 130 of the first end 111 respectively. The power supply circuit board 150 is detachably mounted on the second mounting plate and is in electrical contact with the high-current three-dimensional circuit 120 on the second mounting plate. The wireless communication circuit board 160 is detachably mounted on the third mounting plate and is in electrical contact with the communication three-dimensional circuit 130 of the second end 112. Among them, the main control circuit board 140, the power supply circuit board 150 and the wireless communication circuit board 160 can be detachably mounted on the first mounting plate, the second mounting plate and the third mounting plate by screwing, clamping, locking and the like.

[0042] Therefore, compared with directly mounting the main control circuit board 140, the power supply circuit board 150 and the wireless communication circuit board 160 on the inner wall of the shell 116, the setting of the first mounting plate, the second mounting plate and the third mounting plate further simplifies the assembly work of the three-dimensional circuit-based unmanned aerial vehicle flight control system 100.

[0043] Further, in some embodiments, the first mounting plate, the second mounting plate and the second mounting plate are respectively provided with a first connecting hole 1131, a second connecting hole 1141 and a third connecting hole 1151. One end of the high-current three-dimensional circuit 120 extends to the inner wall of the first connecting hole 1131 through the surface of the first mounting plate, and the other end extends to the inner wall of the second connecting hole 1141 through the surface of the second mounting plate. The main control circuit board 140, the power supply circuit board 150 and the wireless communication circuit board 160 are respectively provided with a first conductive hole (not shown), a second conductive hole (not shown) and a mounting hole (not shown).

[0044] The unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit further comprises a first connecting piece 170 having a conductive property, a second connecting piece 180 having a conductive property, and a third connecting piece 190. The first connecting piece 170 is sequentially arranged in the first conductive hole 141 and the first connecting hole 1131 to detachably connect the main control circuit board 140 and the first mounting plate. The second connecting piece 180 is sequentially arranged in the second conductive hole 151 and the second connecting hole 1141 to detachably connect the power supply circuit board 150 and the second mounting plate. The third connecting piece 190 is sequentially arranged in the mounting hole 1151 and the third connecting piece 190 to detachably connect the wireless communication circuit board 160 and the third mounting plate. The first connecting piece 170, the second connecting piece 180, and the third connecting piece 190 can be bolts, screws, latches, pins, or the like.

[0045] Specifically, one end of the first connecting piece 170 is arranged in the first conductive hole 141 and electrically contacts the inner wall of the first conductive hole 141, and the other end is connected in the first connecting hole 1131. One end of the second connecting piece 180 is arranged in the second conductive hole 151 and electrically contacts the inner wall of the second conductive hole 151, and the other end is connected in the second connecting hole 1141.

[0046] During the assembly of the unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit, only the first connecting piece 170 is inserted into the aligned first connecting hole 1131 and the first conductive hole 141, the second connecting piece 180 is inserted into the aligned second connecting hole 1141 and the second conductive hole 151, and the third connecting piece 190 is inserted into the aligned third connecting hole 1151 and the third connecting hole. The main control circuit board 140, the power supply circuit board 150, and the wireless communication circuit board 160 can be installed in the insulating shell 110, and the assembly process of the unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit is further simplified.

[0047] Further, in some embodiments, the first connecting member 170, the second connecting member 180 and the third connecting member 190 are all threaded fasteners. The first connecting hole 1131, the second connecting hole 1141 and the third connecting hole 1151 are all threaded holes. One end of the first connecting member 170 is inserted into the first conductive hole 141, and the other end is screwed into the first connecting hole 1131. One end of the second connecting member 180 is inserted into the second conductive hole 151, and the other end is screwed into the second connecting hole 1141. One end of the third connecting member 190 is inserted into the mounting hole, and the other end is screwed into the third connecting hole 1151. Therefore, during processing and use, only the first connecting member 170, the second connecting member 180 and the third connecting member 190 need to be screwed to achieve the disassembly of the main control circuit board 140, the power circuit board 150 and the wireless communication circuit board 160, further improving the convenience of assembling the unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit. Furthermore, threaded fasteners are standard components, so setting the first connecting member 170, the second connecting member 180 and the third connecting member 190 as threaded fasteners is conducive to reducing the cost of unmanned aerial vehicle processing.

[0048] Further, in some embodiments, the insulating casing 110 further comprises a first connecting plate 117 protruding from the inner wall of the first end 111 and a second connecting plate 118 protruding from the inner wall of the second end 112. The first connecting plate 117 and the second connecting plate 118 can be fixed to the inner wall of the casing 116 by welding, bonding or other methods, or can be integrally formed with the casing 116 by injection molding or other methods. One end of the communication three-dimensional circuit 130 extends to the surface of the first connecting plate 117 and forms an integral whole with the first connecting plate 117. The other end of the communication three-dimensional circuit 130 extends to the surface of the second connecting plate 118 and forms an integral whole with the second connecting plate 118. The main control circuit board 140 is in electrical contact with the communication three-dimensional circuit 130 on the first connecting plate 117. The wireless communication circuit board 160 is in electrical contact with the communication three-dimensional circuit 130 on the second connecting plate 118.

[0049] Specifically, when the insulating casing 110 is integrally formed by 3D printing, injection molding or mechanical processing, the first connecting plate 117, the second connecting plate 118 and the casing 116 are integrally formed by 3D printing, injection molding or mechanical processing.

[0050] The first connecting plate 117 and the second connecting plate 118 are provided, so that both ends of the communication three-dimensional circuit 130 can extend towards the direction of the axis of the casing 116, facilitating electrical contact with the main control circuit board 140 mounted on the first mounting plate and the wireless communication circuit board 160 mounted on the third mounting plate, thereby making the assembly of the unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit more convenient.

[0051] Specifically, one end of the communication cuboid circuit 130 has a horizontal projection that partially overlaps with a horizontal projection of the main control circuit board 140; the other end of the communication cuboid circuit 130 has a horizontal projection that partially overlaps with a horizontal projection of the main control circuit board 140. The horizontal plane refers to a plane that is perpendicular to the direction in which the first end 111 points to the second end 112.

[0052] Specifically, when the communication cuboid circuit 130 includes a conductive circuit 131, one end of the conductive circuit 131 extends to the surface of the first connecting plate 117 and forms an integral with the first connecting plate 117, and the other end of the conductive circuit 131 extends to the surface of the second connecting plate 118 and forms an integral with the second connecting plate 118.

[0053] Further, in some embodiments, the main control circuit board 140 is in electrical contact with the communication cuboid circuit 130 on the first connecting plate 117 through the first data communication pin 142. The wireless communication circuit board 160 is in electrical contact with the communication cuboid circuit 130 on the second connecting plate 118 through the second data communication pin 162. Specifically, the first connecting plate 117 partially overlaps with the main control circuit board 140, and the second connecting plate 118 partially overlaps with the wireless communication circuit board 160, so as to facilitate the electrical contact between the communication cuboid circuit 130 and the main control circuit board 140 and the wireless communication circuit board 160, respectively.

[0054] The first data communication pin 142 and the second data communication pin 162 can ensure the reliability of the contact between the communication cuboid circuit 130 and the main control circuit board 140 and the wireless communication circuit board, respectively, and facilitate the improvement of the connection reliability of the unmanned aerial vehicle flight control system 100 based on the cuboid circuit.

[0055] In some embodiments, the insulating casing 110 is a hollow cylindrical structure. The connection between the first end 111 and the second end 112 coincides with the central axis of the insulating casing 110. Thus, when the insulating casing 110 is placed vertically, the direction in which the first end 111 points to the second end 112 is vertical. The first mounting position 113, the second mounting position 114, and the third mounting position 115 are multiple. The multiple first mounting positions 113, the multiple second mounting positions 114, and the multiple third mounting positions 115 are arranged along the circumference of the insulating casing 110. The number of the first mounting positions 113, the second mounting positions 114, and the third mounting positions 115 can be the same or different.

[0056] The main control circuit board 140 is detachably connected with each first mounting position 113. The power supply circuit board 150 is detachably connected with each second mounting position 114. The wireless communication circuit board 160 is detachably connected with each third mounting position 115. In this way, the main control circuit board 140, the power supply circuit board 150 and the wireless communication circuit board 160 can be fixed at multiple points, so as to improve the structural stability of the stereoscopic circuit-based unmanned aerial vehicle flight control system 100.

[0057] Further, in some embodiments, the plurality of high-current stereoscopic circuits 120 and the plurality of communication stereoscopic circuits 130 are provided. The number of the plurality of high-current stereoscopic circuits 120, the plurality of first mounting positions 113 and the plurality of second mounting positions 114 is the same, and they are arranged one by one. One end of each high-current stereoscopic circuit 120 extends to the corresponding first mounting position 113, and the other end extends to the corresponding second mounting position 114. The plurality of communication stereoscopic circuits 130 are arranged at intervals.

[0058] The main control circuit board 140 is electrically connected with each high-current stereoscopic circuit 120 on each first mounting position 113 and each communication stereoscopic circuit 130 of the first end 111. The power supply circuit board 150 is electrically connected with each high-current stereoscopic circuit 120 on each second mounting position 114. The wireless communication circuit board 160 is electrically connected with each communication stereoscopic circuit 130 of the second end 112. By arranging the high-current stereoscopic circuits 120 and the communication stereoscopic circuits 130 as independent and spaced multiple, the electrical safety distance between adjacent high-current stereoscopic circuits 120 and adjacent communication stereoscopic circuits 130 is increased, which is beneficial to improve the electrical safety of the stereoscopic circuit-based unmanned aerial vehicle flight control system 100.

[0059] Specifically, when the insulating shell 110 includes the shell body 116, the first connecting plate 117 and the second connecting plate 118, one end of each of the plurality of communication stereoscopic circuits 130 is formed on the first connecting plate 117 at intervals, and the other end is formed on the second connecting plate 118 at intervals.

[0060] Further, in some embodiments, the high-current stereoscopic circuit 120 and the communication stereoscopic circuit 130 are both microstrip lines. The inner wall of the insulating casing 110 is formed with a plurality of first grooves (not shown in the figure) and a plurality of second grooves (not shown in the figure) arranged at intervals. The number of the plurality of first grooves, the plurality of first mounting positions 113, and the plurality of second mounting positions 114 is the same, and they are one-to-one corresponding. Each first groove extends from the corresponding first mounting position 113 to the corresponding second mounting position 114. Each second groove extends from the first end 111 to the second end 112. When the insulating casing 110 includes the casing 116, the first mounting plate, the second mounting plate, and the third mounting plate, each first groove is formed in the inner wall of the casing 116, and the two ends are located on the surfaces of the first mounting plate and the second mounting plate, respectively; when the insulating casing 110 further includes the first connecting plate 117 and the second connecting plate 118, each second groove is formed in the inner wall of the casing 116, and the two ends are located on the surfaces of the first connecting plate 117 and the second connecting plate 118, respectively. The first grooves and the second grooves can be formed by 3D printing, mechanical processing, etc. In this embodiment, the first grooves and the second grooves are formed by laser processing.

[0061] Each high-current stereoscopic circuit 120 includes a first conductive layer (not shown in the figure) formed in the corresponding first groove by electroless plating and a first protective layer (not shown in the figure) formed on the first conductive layer by electroless plating. The two ends of each first conductive layer are in electrical contact with the main control circuit board 140 and the power circuit board 150, respectively.

[0062] Each communication stereoscopic circuit 130 includes a second conductive layer (not shown in the figure) formed in the second groove by electroless plating and a second protective layer (not shown in the figure) formed on the second conductive layer by electroless plating. The two ends of each second conductive layer are in electrical contact with the main control circuit board 140 and the wireless communication circuit board 160, respectively.

[0063] In the processing of the stereoscopic circuit-based unmanned aerial vehicle flight control system 100, first, a plurality of first grooves and second grooves arranged at intervals are formed in the inner wall of the insulating casing 110 by laser processing or the like; then, copper plating, silver plating, or other electroless plating processes are performed in the first grooves and the second grooves to form first conductive layers and second conductive layers in the first grooves and the second grooves, respectively; then, nickel plating or gold plating processes are performed on the first conductive layers and the second conductive layers to form protective layers on the conductive layers, thus completing the processing of the high-current conductive circuit and the communication stereoscopic circuit 130 on the inner wall of the insulating casing 110.

[0064] Thus, the first conductive layer and the second conductive layer are wrapped by the first protective layer and the second protective layer, which can reduce the probability of oxidation and corrosion of the first conductive layer and the second conductive layer after long-term use, so that the large-current three-dimensional circuit 120 and the communication three-dimensional circuit 130 have high conductive reliability and long service life. Moreover, each large-current three-dimensional circuit 120 and each communication three-dimensional circuit 130 are arranged as microstrip lines, which is conducive to the reduction of the volume of the unmanned aerial vehicle flight control system 100 based on the three-dimensional circuit, and is conducive to the further miniaturization of the unmanned aerial vehicle.

[0065] Furthermore, in some embodiments, the thickness of the first conductive layer is greater than or equal to 35 microns. The width of the first conductive layer is greater than or equal to 5 millimeters. The thickness of the second conductive layer is greater than or equal to 10 microns. The width of the second conductive layer is greater than or equal to 0.2 millimeters. In this way, the large-current three-dimensional circuit 120 and the communication three-dimensional circuit 130 can be ensured to have a smaller volume while still being able to transport larger current signals and data signals.

[0066] The technical features of the above-described embodiments can be combined in any manner. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described, but as long as the combinations of the technical features do not contradict, they should be considered within the scope of the present disclosure.

[0067] The above-described embodiments only express several embodiments of the present application, and the description is more specific and detailed, but it should not be understood as limiting the scope of the patent. It should be pointed out that for ordinary skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are within the scope of the present application. Therefore, the scope of protection of the present application should be subject to the appended claims.

Claims

1. A stereocircuit-based unmanned aerial vehicle flight control system, characterized in that, The application relates to an insulation casing, a hollow structure with opposite first and second ends; a first mounting position, a second mounting position and a third mounting position are arranged in the insulation casing in a direction from the first end to the second end; a large-current three-dimensional circuit is formed on the inner wall of the insulation casing and is integrated with the insulation casing; two ends of the large-current three-dimensional circuit extend to the first mounting position and the second mounting position respectively; a communication three-dimensional circuit is formed on the inner wall of the insulation casing and is integrated with the insulation casing; the communication three-dimensional circuit is arranged between the large-current three-dimensional circuit and is integrated with the insulation casing; two ends of the communication three-dimensional circuit extend to the first end and the second end respectively; the communication three-dimensional circuit comprises a conductive circuit formed on the inner wall of the insulation casing, components arranged in the conductive circuit and self-recovery fuses arranged on the conductive circuit; the self-recovery fuses are fixed on the inner wall of the insulation casing and are used for making the conductive circuit conductive or non-conductive; a main control circuit board, a power circuit board and a wireless communication circuit board are arranged in the insulation casing; the main control circuit board is detachably mounted on the first mounting position and is electrically connected to one end of the large-current three-dimensional circuit away from the second mounting position and one end of the communication three-dimensional circuit away from the second end; the power circuit board is detachably mounted on the second mounting position and is electrically connected to one end of the large-current three-dimensional circuit away from the first mounting position; the wireless communication circuit board is detachably mounted on the third mounting position and is electrically connected to one end of the communication three-dimensional circuit away from the first end; two ends of the conductive circuit are electrically connected to the main control circuit board and the wireless communication circuit board respectively; the components are one or several of capacitors, resistors, connectors, packaged chips and environment detection components. The insulation casing comprises a hollow cylindrical shell with two open ends, a first mounting plate as the first mounting position, a second mounting plate as the second mounting position and a third mounting plate as the third mounting position; the first mounting plate, the second mounting plate and the third mounting plate are arranged on the inner wall of the shell; the large-current three-dimensional circuit is formed on the inner wall of the shell, the surface of the first mounting plate and the surface of the second mounting plate and is integrated with the shell, the first mounting plate and the second mounting plate respectively; two ends of the large-current three-dimensional circuit are arranged on the surface of the first mounting plate and the surface of the second mounting plate respectively; the communication three-dimensional circuit is formed on the inner wall of the shell and is integrated with the inner wall of the shell. ​ ​ ​ ​ ​ 2. The stereocircuit-based UAV flight control system of claim 1, wherein, ​ ​ The main control circuit board is detachably mounted on the first mounting plate and makes electrical contact with the high-current three-dimensional circuit on the first mounting plate and the communication three-dimensional circuit at the first end, respectively; the power supply circuit board is detachably mounted on the second mounting plate and makes electrical contact with the high-current three-dimensional circuit on the second mounting plate; the wireless communication circuit board is detachably mounted on the third mounting plate and makes electrical contact with the communication three-dimensional circuit at the second end.

3. The stereocircuit-based UAV flight control system of claim 2, wherein, The first mounting plate, the second mounting plate, and the third mounting plate are respectively provided with a first connecting hole, a second connecting hole, and a third connecting hole; one end of the high-current three-dimensional circuit extends through the surface of the first mounting plate to the inner wall of the first connecting hole, and the other end extends through the surface of the second mounting plate to the inner wall of the second connecting hole; The main control circuit board, the power supply circuit board and the wireless communication circuit board are respectively provided with a first conductive hole, a second conductive hole and a mounting hole; The UAV flight control system based on 3D circuitry further includes a first connector with conductive properties, a second connector with conductive properties, and a third connector. The first connector is sequentially disposed through the first conductive hole and the first connecting hole to detachably connect the main control circuit board to the first mounting plate. The second connector is sequentially disposed through the second conductive hole and the second connecting hole to detachably connect the power circuit board to the second mounting plate. The third connector is sequentially disposed through the mounting hole and the third connector to detachably connect the wireless communication circuit board to the third mounting plate.

4. The stereocircuit-based UAV flight control system of claim 3, wherein, The first connector, the second connector, and the third connector are all threaded fasteners; the first connecting hole, the second connecting hole, and the third connecting hole are all threaded holes; one end of the first connector passes through the first conductive hole, and the other end is screwed into the first connecting hole; one end of the second connector passes through the second conductive hole, and the other end is screwed into the second connecting hole; one end of the third connector passes through the mounting hole, and the other end is screwed into the third connecting hole.

5. The stereocircuit-based UAV flight control system of claim 2, wherein, The insulating housing further includes a first connecting plate protruding from the inner wall of the first end and a second connecting plate protruding from the inner wall of the second end; one end of the communication three-dimensional circuit extends to the surface of the first connecting plate and forms an integral part with the first connecting plate; the other end of the communication three-dimensional circuit extends to the surface of the second connecting plate and forms an integral part with the second connecting plate. The main control circuit board is electrically connected to the communication three-dimensional circuit on the first connecting board; the wireless communication circuit board is electrically connected to the communication three-dimensional circuit on the second connecting board.

6. The stereocircuit-based UAV flight control system of claim 5, wherein, The main control circuit board is electrically connected to the communication three-dimensional circuit on the first connection board via a first data communication pin; the wireless communication circuit board is electrically connected to the communication three-dimensional circuit on the second connection board via a second data communication pin.

7. The stereocircuit-based UAV flight control system of claim 1, wherein, The insulation shell is a hollow cylindrical structure; the line between the first end and the second end coincides with the central axis of the insulation shell; The first mounting position, the second mounting position, and the second mounting position are multiple; multiple first mounting positions, multiple second mounting positions, and multiple third mounting positions are spaced along the circumference of the insulation shell; The main control circuit board is detachably connected with each first mounting position; the power supply circuit board is detachably connected with each second mounting position; and the wireless communication circuit board is detachably connected with each third mounting position.

8. The stereocircuit-based UAV flight control system of claim 7, wherein, The large-current three-dimensional circuit and the communication three-dimensional circuit are multiple; the number of large-current three-dimensional circuits, the number of first mounting positions, and the number of second mounting positions are the same and one-to-one corresponding; one end of the large-current three-dimensional circuit one-to-one corresponds to the first mounting position, and the other end one-to-one corresponds to the second mounting position; multiple communication three-dimensional circuits are spaced apart; The main control circuit board is in electrical contact with the large-current three-dimensional circuit on each first mounting position and each communication three-dimensional circuit at the first end; the power supply circuit board is in electrical contact with the large-current three-dimensional circuit on each second mounting position; and the wireless communication circuit board is in electrical contact with each communication three-dimensional circuit at the second end.

9. The stereocircuit-based UAV flight control system of claim 8, wherein, The large-current three-dimensional circuit and the communication three-dimensional circuit are microstrip lines; the inner wall of the insulation shell forms multiple first grooves and multiple second grooves; the number of multiple first grooves, multiple first mounting positions, and multiple second mounting positions is the same and one-to-one corresponding; each first groove extends from the corresponding first mounting position to the corresponding second mounting position; and each second groove extends from the first end to the second end; Each large-current three-dimensional circuit includes a first conductive layer formed in the corresponding first groove by chemical plating and a first protective layer formed on the first conductive layer by chemical plating; and two ends of each first conductive layer are in electrical contact with the main control circuit board and the power supply circuit board, respectively; Each communication three-dimensional circuit includes a second conductive layer formed in the second groove by chemical plating and a second protective layer formed on the second conductive layer by chemical plating; and two ends of each second conductive layer are in electrical contact with the main control circuit board and the wireless communication circuit board, respectively.

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