Grounding device of low-altitude aircraft

Abstract

The utility model provides a grounding device of a low-altitude aircraft. The grounding device comprises a plurality of square grounding carriers, a plurality of strip-shaped grounding carriers and a plurality of cylindrical grounding carriers, the square grounding carriers are fixedly arranged in different areas in a control system circuit of the aircraft, and the cylindrical grounding carriers are used for connecting all grounding points in the control system circuit of the aircraft to the square grounding carriers in the corresponding areas; each strip-shaped grounding carrier is used for connecting different square grounding carriers, so that the square grounding carriers are mutually conducted; and any one of the plurality of strip-shaped grounding carriers is connected with a shell grounding point of the aircraft to establish a complete grounding system of the aircraft. The independently distributed grounding points are classified and collected in a small range, so that bad hidden dangers caused by EMC (Electro Magnetic Compatibility) can be effectively inhibited or eliminated, and the electromagnetic anti-interference capability of the aircraft, the convenience of wiring harness conduction test and troubleshooting and the assemblability and manufacturability of electrical wiring are improved.

Description

Technical Field

[0001] This utility model relates to the field of electrical technology, and in particular to a grounding device for a low-altitude aircraft. Background Technology

[0002] As the electronic and electrical functions of low-altitude aircraft become increasingly automated and intelligent, their system design (including electrical wiring layout and grounding control system planning) is also gradually developing towards higher integration. As a result, the requirements for the layout and wiring of each electronic and electrical functional module in the control system circuit of the aircraft are becoming more and more stringent, including the design of the grounding control system. This is to avoid the adverse effects of unreasonable wiring layout on electromagnetic compatibility (EMC) and electrical connection reliability, which could affect the flight performance of the aircraft and, in severe cases, interfere with the normal operation of the aircraft.

[0003] The current grounding method for low-altitude aircraft involves converging the ground wires of all electronic and electrical modules in the aircraft's control system circuitry to a single point before connecting it to the aircraft's outer casing grounding point. This method results in extended wiring harnesses, poor electrical connection reliability, and an increased probability of electromagnetic radiation and electromagnetic interference, particularly the adverse effects of radiated and conducted emissions, as well as radiated and conducted immunity. Furthermore, the existing wiring method negatively impacts fault location during wiring harness continuity testing and interference troubleshooting. For example, directly converging all ground wires to the same grounding point hinders the precise fault location method of disconnecting each ground wire individually. Utility Model Content

[0004] This invention provides a grounding device for low-altitude aircraft, which improves the reliability of the electrical connection of the grounding of the aircraft and increases the electromagnetic interference immunity of the aircraft.

[0005] This utility model provides a grounding device for a low-altitude aircraft, comprising: multiple square grounding carriers, multiple strip grounding carriers, and multiple cylindrical grounding carriers;

[0006] Each square grounding carrier is fixedly installed in a different area of ​​the aircraft's control system circuit. The square grounding carrier is a conductor including multiple grounding sockets for connecting to the grounding point in the control system circuit within the area.

[0007] Each cylindrical grounding carrier is a conductor. The first end of the cylindrical grounding carrier is connected to the grounding point in the control system circuit within the area, and the second end of the cylindrical grounding carrier is connected to the grounding socket of the square grounding carrier. Each cylindrical grounding carrier is used to connect all the grounding points in the control system circuit of the aircraft to the square grounding carrier set in the corresponding area.

[0008] Each strip grounding carrier is a conductor, used to connect different square grounding carriers so that the square grounding carriers can conduct to each other;

[0009] Any one of the plurality of strip grounding carriers is connected to the grounding point of the aircraft's outer shell.

[0010] According to the present invention, a grounding device for a low-altitude aircraft is provided, wherein the first end of the cylindrical grounding carrier is a metal connector for connecting to a grounding point in the control system circuit within a region based on a wire.

[0011] The second end of the cylindrical grounding carrier is a terminal block that matches the grounding socket of the square grounding carrier and is used to connect to the grounding socket of the square grounding carrier.

[0012] According to the present invention, a grounding device for a low-altitude aircraft is provided, wherein the terminal block includes a cylindrical metal body and an elastic locking area;

[0013] The cylindrical metal body has a ring of elastic locking area around its circumference for locking after docking with the grounding socket.

[0014] According to the present invention, a grounding device for a low-altitude aircraft is provided, wherein a grounding wire label is provided below each grounding socket in the square grounding carrier, and the grounding wire label is used to record the grounding point information connected to the grounding socket.

[0015] According to the present invention, a grounding device for a low-altitude aircraft is provided, wherein each grounding socket in the square grounding carrier is obtained by opening a threadless through hole in a square metal plate or by installing a standard terminal block in a through hole in a square metal plate.

[0016] According to the present invention, a grounding device for a low-altitude aircraft is provided, wherein the strip grounding carrier further includes multiple fastening points;

[0017] Each fastening point is connected to the square grounding carrier by means of screw fastening.

[0018] According to the present invention, the number of fastening points in the strip grounding carrier is determined based on the docking width between the strip grounding carrier and the square grounding carrier.

[0019] According to the present invention, a grounding device for a low-altitude aircraft is provided, wherein the strip grounding carrier is a copper foil of a predetermined thickness or a copper braided strip of a predetermined thickness.

[0020] According to the present invention, a grounding device for a low-altitude aircraft is provided, wherein the strip grounding carrier is pasted and installed in the aircraft along the gap of the aircraft shell.

[0021] The grounding device for low-altitude aircraft provided by this utility model, by setting square grounding carriers in different areas of the aircraft's control system circuit, and based on the basic design principles of proximity, multi-point, and single-point grounding, gradually extends numerous independently distributed grounding points to a regional grounding convergence point, thereby improving the reliability of electrical connections. Furthermore, based on strip grounding carriers connecting different square grounding carriers, the regional grounding convergence point is connected to the aircraft's outer shell grounding point to form a total grounding convergence point, thus establishing a complete grounding system for the aircraft. Classifying and consolidating independently distributed grounding points within a small area can effectively suppress or eliminate adverse EMC hazards, improve the aircraft's electromagnetic interference immunity, enhance the convenience of wiring harness continuity testing and fault diagnosis, and further improve the assemblability and manufacturability of the aircraft's electrical wiring. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the grounding device for a low-altitude aircraft provided by this utility model.

[0024] Figure 2 This is a schematic diagram of the grounding architecture provided by this utility model.

[0025] Figure 3 This is a schematic diagram of the grounding method provided by this utility model.

[0026] Figure 4 This is a schematic diagram of the connection structure of the metal connector provided by this utility model.

[0027] Figure 5 This is a schematic diagram of the square grounding carrier provided by this utility model.

[0028] Figure 6 This is a schematic diagram of the strip grounding carrier provided by this utility model. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0030] Figure 1 This is a schematic diagram of the grounding device for the low-altitude aircraft provided by this utility model, as shown below. Figure 1 As shown, the device includes multiple square grounding carriers 110, multiple strip grounding carriers 120, and multiple cylindrical grounding carriers 130.

[0031] The area encompassing the aircraft's control system circuitry is divided into multiple regions. Square grounding carriers 110 are fixedly installed in different regions of the aircraft's control system circuitry. Specifically, one square grounding carrier 110 is installed in each region. The square grounding carrier 110 can be connected to the grounding point of the control system circuitry within that region.

[0032] The square grounding carrier 110 is used to establish regional grounding collection points. A certain number of grounding holes can be opened on a square metal plate of a certain thickness. The grounding holes are used to connect with the cylindrical grounding carrier (the grounding wire is installed on the cylindrical grounding carrier). That is, the conductivity of the metal plate is used to gather many independent grounding points together.

[0033] It should be noted that the number of grounding sockets in the square grounding carrier 110 can be determined according to the grounding requirements in the area.

[0034] The cylindrical grounding carrier 130 is used to connect the grounding point in the circuit to the grounding socket in the square grounding carrier 110.

[0035] Specifically, the cylindrical grounding carrier 130 can be a cylindrical metal conductor with two ends, the first end being connected to the grounding point in the control system circuit, and the second end being connected to the grounding socket of the square grounding carrier, so as to connect the grounding point in the control system circuit to the square grounding carrier.

[0036] The strip grounding carrier 120 is mainly used to establish the connection between different square grounding carriers 110, that is, to reconnect the regional grounding convergence points formed by different square grounding carriers 110 to the same grounding point through the strip grounding carrier 120.

[0037] It should be noted that because the outer shell of low-altitude aircraft is generally made of non-metallic materials, different regional grounding collection points must be connected to the outer shell grounding housing via a strip grounding carrier. If the outer shell grounding housing is entirely metal, the strip grounding carrier 120 can be omitted, as the metal shell already connects all regional grounding collection points together.

[0038] With the configuration and addition of different electronic and electrical functional modules, aircraft control systems face the dual challenges of increased wiring complexity and compromised EMC performance. The grounding device described in this invention, applied to low-altitude aircraft, can optimize the EMC performance of the flight control system while further improving the convenience of electrical wiring and the efficiency of troubleshooting.

[0039] The architecture of the grounding point can be as follows Figure 2 As shown in the schematic diagram of the grounding architecture provided by this utility model, at the beginning of the wiring, the ground wires corresponding to different electronic and electrical functional modules are all independently distributed grounding points. Combining the electrical functional attributes and the principle of grounding nearby, a number of independently distributed grounding points first gradually form a certain number of regional grounding convergence points. Secondly, the regional grounding convergence points gradually form smaller regional grounding convergence points, and finally converge with the housing grounding point of the low-altitude aircraft to form a total grounding convergence point. Thus, the grounding control system of the entire flight control system is fully constituted.

[0040] Figure 3 This is a schematic diagram of the grounding method provided by this utility model. (Combined with...) Figure 3 The grounding method diagram shown and Figure 2 The grounding control system architecture shown can effectively establish a grounding control system for low-altitude aircraft by simultaneously utilizing different grounding carriers within the grounding device. From Figure 3 It can be seen that the grounding device mainly consists of three modules: square grounding carrier, strip grounding carrier, and column grounding carrier. Synchronous integration. Figure 2 The grounding architecture establishes a conductive connection between independently distributed grounding points and square grounding carriers (which can be understood as the male connector of a connector) through cylindrical grounding carriers (which can be understood as the female connector of a connector). Simultaneously, regional grounding convergence points are formed on the square grounding carriers; that is, n independent grounding points converge to a certain number of square grounding carriers. A conductive connection is then established between different regional grounding convergence points through strip grounding carriers. This process continues until all n regional grounding convergence points are eventually connected together and linked to the housing grounding point on the outer shell of the low-altitude aircraft, forming a complete grounding control system.

[0041] Based on the above grounding methods, ground wires can be converged to the nearest area via the shortest distance, minimizing EMC impacts while improving assembly convenience, including benefits to production costs. Multi-point grounding, in conjunction with the flight control system's grounding system layout, gradually forms multiple regional grounding convergence points based on the principle of proximity, further improving EMC performance and the ease of interference troubleshooting. Single-point grounding connects the regional grounding convergence points formed by multi-point grounding to a single total grounding convergence point, thus forming a complete grounding control system for low-altitude aircraft.

[0042] The grounding system of low-altitude aircraft comprises three main parts: square grounding carriers, strip grounding carriers, and cylindrical grounding carriers. Square grounding carriers focus on classifying and aggregating independently distributed grounding points within a small area, thereby establishing regional grounding aggregation points. This means that, based on system wiring planning and conductor electrical properties, numerous independently distributed ground wires are aggregated into multiple regional grounding aggregation points in stages, avoiding the situation where all ground wires are laid out before final aggregation, which could negatively impact EMC and wiring harness assembly. Strip grounding carriers are used to establish connections between different square grounding carriers; any two square grounding carriers can be connected through a strip grounding carrier to form a common grounding aggregation point. Cylindrical grounding carriers are used in conjunction with square grounding carriers in a connector-like relationship. This facilitates convenient ground wire connections and also aids in interference or fault diagnosis; by disconnecting cylindrical grounding carriers one by one, the source of interference / fault can be gradually located.

[0043] It should be noted that, based on the fundamental design principles of proximity, multi-point, and single-point grounding, numerous independently distributed grounding points are gradually extended to a regional grounding convergence point, ultimately forming a total grounding convergence point, thus establishing a complete inverted triangle grounding control system. This system addresses the complex and numerous grounding signals of flight control systems, while also considering the electrical functional attributes and grounding design principles of various ground lines to establish a standardized and complete grounding control system. It can effectively suppress / eliminate the adverse effects caused by EMC, and also bring certain beneficial effects in terms of Design for Manufacturability (DFM) and Design for Assembly (DFA), as well as improving quality, reducing costs, and increasing efficiency.

[0044] Based on the wiring pattern of the inverted triangle grounding control system, three different grounding carriers—square, strip, and column—are designed. Through the effective connection of these three grounding carriers, a complete grounding control system is formed. This involves planning the architecture and grounding methods of the grounding control system, designing different grounding devices to promote the effective implementation of standardized and reliable grounding. The integrated application of different grounding control systems can improve the convenience of fault diagnosis and identification, and also contribute to the optimization of the system design of DFM, DFA, and flight controllers.

[0045] The grounding device for low-altitude aircraft provided by this utility model, by setting square grounding carriers in different areas of the aircraft's control system circuit, and based on the basic design principles of proximity, multi-point, and single-point grounding, gradually extends numerous independently distributed grounding points to a regional grounding convergence point, thereby improving the reliability of electrical connections. Furthermore, based on strip grounding carriers connecting different square grounding carriers, the regional grounding convergence point is connected to the aircraft's outer shell grounding point to form a total grounding convergence point, thus establishing a complete grounding system for the aircraft. Classifying and consolidating independently distributed grounding points within a small area can effectively suppress or eliminate adverse EMC hazards, improve the aircraft's electromagnetic interference immunity, enhance the convenience of wiring harness continuity testing and fault diagnosis, and further improve the assemblability and manufacturability of the aircraft's electrical wiring.

[0046] In one embodiment, the first end of the cylindrical grounding carrier is a metal connector for connecting to a grounding point in the control system circuit within a certain area via a wire; the second end of the cylindrical grounding carrier is a terminal block that matches the grounding socket of the square grounding carrier for connecting to the grounding socket of the square grounding carrier. The terminal block includes a cylindrical metal body and an elastic locking region; the cylindrical metal body has a circumference with an elastic locking region for locking after mating with the grounding socket.

[0047] The cylindrical grounding carrier, used for docking with the square grounding carrier, mainly consists of three parts: a cylindrical metal body, a metal connector, and a resilient locking area. The cylindrical metal body is slightly smaller than the grounding socket in the square grounding carrier. To further improve connection reliability, a resilient locking area is provided around the circumference of the metal body. This facilitates docking between the cylindrical and square grounding carriers while also enhancing locking reliability. This resilient structural design is particularly important under conditions of vibration during aircraft flight.

[0048] Metal connectors can be like Figure 4 The connection structure diagram of the metal connector provided by this utility model shows that it can specifically include two methods: one is to assemble the ground wire to the cylindrical grounding carrier by welding, such as... Figure 4The metal connector shown in the left image has its welded cavity bounded by the dotted circle shown in the left image. Another method is to use screws for fastening, such as... Figure 4 The ground wire fastening holes shown in the right figure are used to assemble the corresponding ground wire using screws. Both methods have their advantages and disadvantages, and the choice depends on factors such as wire diameter and maintenance requirements. If the ground wire diameter is too small, screw fastening is not suitable; in this case, soldering provides better reliability. Generally, soldering is used for wire diameters below 1mm. Similarly, when the ground wire diameter reaches a certain value, considering factors such as solder penetration control, screw fastening is more convenient and reliable.

[0049] Understandably, based on the cylindrical grounding carrier, the ground wires are converged to the nearest square grounding carrier via the shortest distance, minimizing EMC impacts while improving assembly convenience. Multi-point grounding, in conjunction with the flight control system's grounding system layout, gradually forms multiple regional grounding convergence points based on the principle of proximity, further improving EMC performance and the ease of interference troubleshooting.

[0050] In one embodiment, each grounding socket in the square grounding carrier is obtained by either creating a threadless through hole in the square metal plate or by installing a standard terminal block in a through hole in the square metal plate. A grounding label is provided below each grounding socket in the square grounding carrier, and the grounding label is used to record the grounding point information connected to the grounding socket.

[0051] Grounding labels can be directly affixed with labels that have good adhesion, such as self-adhesive labels, or the characters can be screen-printed directly on the grounding carrier, depending on the ease of operation and processing cost. Grounding labels located below the grounding socket facilitate continuity testing and troubleshooting of the wiring harness.

[0052] The current method of converging all ground wires of electronic and electrical modules to a single point can negatively impact fault location during wiring harness continuity testing and interference troubleshooting. For example, directly converging all ground wires to the same grounding point hinders the precise fault location method of disconnecting each ground wire individually. By using ground wire labels, each ground wire can be clearly identified, allowing maintenance and repair personnel to quickly identify the connection status of each ground wire when faced with complex aircraft electrical systems. This helps avoid misoperation or accidental contact, reducing the risk of safety accidents.

[0053] A schematic diagram of a square grounding carrier can be shown as follows: Figure 5The schematic diagram of the square grounding carrier provided by this utility model is shown. The size of the square grounding carrier can be determined according to the number of independently distributed grounding points in the current planned area, that is, it depends on the size of n. The number of fastening points is determined by the size / area of ​​the square grounding carrier. The position of the fastening points is determined by the overall structural layout of the low-altitude aircraft and the docking width of the strip grounding carrier. The fastening points can be directly based on the mounting holes with appropriate threads opened in the square metal plate, or they can be achieved by riveting screw holes, or by installing standard terminals in the through holes opened in the square metal plate. The specific method is determined by the thickness of the metal plate, the installation requirements, the processing technology of the threaded holes, and the reliability of the fastening.

[0054] The grounding socket can be made by directly drilling a threadless through hole on the metal plate. This method requires that the thickness h of the metal plate fully meets the reliability requirements after the cylindrical grounding carrier is connected. Based on cost and lightweight design requirements, h1 is generally (3~5) mm to avoid insufficient thickness that prevents complete engagement with the cylindrical grounding carrier. The diameter of the through hole is d1 = (d2-0.5) mm, where d2 is the diameter of the cylindrical grounding carrier (excluding the elastic locking area). Alternatively, a standard terminal can be installed on the through hole. This method requires that the inner diameter φ of the terminal matches the cylindrical grounding carrier. Generally, d2 = (φ-0.5) mm is required to avoid potential problems such as poor grounding contact.

[0055] In one embodiment, the strip grounding carrier further includes multiple fastening points; each fastening point is connected to the square grounding carrier by screw fastening. The number of fastening points in the strip grounding carrier is determined based on the mating width between the strip grounding carrier and the square grounding carrier. The strip grounding carrier is a copper foil or copper braided strip of a predetermined thickness. The strip grounding carrier is pasted and installed in the aircraft along the gaps in the aircraft shell.

[0056] Strip grounding carriers are mainly used to establish connections between different square grounding carriers. That is, through strip grounding carriers, regional grounding convergence points formed by different square grounding carriers are reconnected to a single grounding point. Specifically, this can be done as follows: Figure 6 The schematic diagram of the strip grounding carrier provided by this utility model is shown.

[0057] It should be noted that because the outer shell of low-altitude aircraft is made of non-metallic material, different regional grounding junctions must be connected to the housing grounding point on the outer shell via strip grounding carriers. When used for products with an entirely metallic outer shell, the strip grounding carriers can be omitted, as the metal outer shell already connects all regional grounding junctions together.

[0058] The strip grounding carrier can be made of copper foil or copper braided strip of appropriate thickness. Generally, the thickness of the copper foil or copper braided strip is required to be h2 = (1~3) mm. Based on the shielding of electromagnetic interference signals of different electrical functional modules of the flight control system (focusing on radiated emission RE and radiated immunity RI), copper foil with good adhesion is generally pasted and installed along the gaps of the aircraft shell to seal the gaps and reduce the transmission capability of electromagnetic interference signals as much as possible.

[0059] The strip grounding carrier is connected to the square grounding carrier by screw fastening. The location and number of screw fastening points are determined based on the shape and area of ​​both the strip and square grounding carriers, i.e., according to the joint width between them. To further improve the reliability of copper foil or copper braided strip grounding, especially when the strip grounding carrier exceeds a certain length, additional screw fastening points can be added in the middle of the carrier. The square grounding carrier is not strictly a perfect square compared to circular, strip, or cylindrical grounding carriers.

[0060] Understandably, strip-shaped grounding carriers can further aggregate grounding points from different areas, thereby connecting the ground wires of all electronic and electrical modules in the aircraft's control system circuitry to the aircraft's outer shell grounding point, thus establishing a complete grounding system for the aircraft. Aggregating independently distributed grounding points can effectively suppress or eliminate potential EMC-related problems, improve the aircraft's electromagnetic interference immunity, enhance the convenience of wiring harness continuity testing and fault diagnosis, and further improve the assemblability and manufacturability of the aircraft's electrical wiring.

[0061] In one embodiment, the different regions in the control system circuit are obtained by dividing the control system circuit based on the distribution of grounding points in the control system circuit.

[0062] The partitioning process can be implemented based on the spatial distribution of grounding points, dividing the area according to their physical location. Adjacent or close grounding points can be grouped into one area to facilitate wiring and the setting of grounding convergence points.

[0063] Specifically, the range of grounding points in the control system circuit can be determined based on the distribution of grounding points in the control system circuit. Then, the control system circuit can be divided into multiple different regions based on the number of grounding points in different areas within the range.

[0064] For example, the area containing five adjacent grounding points in the control system circuit can be considered as one region. By dividing all grounding points in the control system circuit, multiple different regions can be obtained within the control system circuit.

[0065] Alternatively, the circuit can be divided based on its functional modules, such as power supply modules, signal processing modules, and control modules. The grounding points within each functional module can be grouped into one area.

[0066] Within each designated area, select a suitable location as the grounding convergence point and install a square grounding carrier at that location. This location should facilitate the connection and convergence of wires while avoiding interference with other electrical equipment.

[0067] Based on the system cabling plan and the electrical properties of the conductors, numerous independently distributed ground wires are aggregated in stages into multiple regional grounding convergence points, which are then connected to square grounding carriers. This ensures that the ground wires do not interfere with each other during installation, while also improving grounding efficiency.

[0068] The grounding device for low-altitude aircraft provided by this utility model divides the control system circuit into regions based on the distribution of grounding points and establishes regional grounding aggregation points. Adhering to the basic design principles of proximity, multi-point, and single-point grounding, it gradually extends numerous independently distributed grounding points to regional grounding aggregation points, optimizing the ground wire layout and improving the stability and reliability of electrical connections. Classifying and aggregating independently distributed grounding points within a small area can effectively suppress or eliminate potential EMC problems, improve the aircraft's electromagnetic interference immunity, enhance the convenience of wiring harness continuity testing and fault diagnosis, and further improve the assemblability and manufacturability of the aircraft's electrical wiring.

[0069] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0070] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments or some parts of the embodiments.

[0071] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A landing gear for a low altitude aircraft, comprising: The utility model relates to a kind of square ground carrier, strip ground carrier and column ground carrier for aircraft control system circuit. Each square ground carrier is fixedly arranged in different regions of the control system circuit of the aircraft, and is a conductor including a plurality of grounding jacks for accessing the grounding points in the control system circuit in the region. Each column ground carrier is a conductor, and a first end of the column ground carrier is connected to the grounding points in the control system circuit in the region, and a second end of the column ground carrier is connected to the grounding jacks of the square ground carrier. Each column ground carrier is used to access all the grounding points in the control system circuit of the aircraft to the square ground carrier arranged in the corresponding region. Each strip ground carrier is a conductor used to connect between different square ground carriers to make each square ground carrier conductive to each other. Any one of the plurality of strip ground carriers is connected to the shell grounding point of the aircraft.

2. The landing gear of a low altitude aircraft according to claim 1, characterized in that, The first end of the column ground carrier is a metal connector used to connect to the grounding points in the control system circuit in the region based on a wire. The second end of the column ground carrier is a terminal post matched with the grounding jacks of the square ground carrier used to connect the grounding jacks of the square ground carrier.

3. The landing gear of a low altitude aircraft according to claim 2, wherein, The terminal post includes a cylindrical metal body and an elastic locking area. The circumference of the cylindrical metal body is provided with a ring of elastic locking areas used for locking after the grounding jacks are connected.

4. The landing gear for a low altitude aircraft of claim 1, wherein, Each grounding jack in the square ground carrier is provided with a ground wire label below, and the ground wire label is used to record the information of the grounding points connected to the grounding jacks.

5. The landing gear for a low altitude aircraft of claim 1, wherein, Each grounding jack in the square ground carrier is obtained based on a threaded hole formed in a square metal plate or based on a terminal post installed in a threaded hole formed in a square metal plate.

6. The landing gear for a low altitude aircraft of claim 1, wherein, The strip ground carrier further includes a plurality of fastening points. Each fastening point is connected to the square ground carrier by screw fastening.

7. The landing gear of a low altitude aircraft according to claim 6, wherein The number of fastening points in the strip ground carrier is determined based on the width of the interface between the strip ground carrier and the square ground carrier.

8. The landing gear for a low altitude aircraft of claim 1, wherein, The strip ground carrier is a copper foil with a predetermined thickness or a copper braid with a predetermined thickness.

9. The landing gear of a low altitude aircraft according to claim 8, wherein, The strip ground carrier is installed in the aircraft by being pasted along the gap of the shell of the aircraft.

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