External terminal resistor and aircraft

Abstract

The utility model provides an external terminal resistor and an aircraft, and relates to the technical field of aircrafts. The external terminal resistor comprises a shell and a resistor main body part, wherein the resistor main body part comprises at least two chip grooves, a sliding metal shifting piece, at least two chip resistors, and a first contact terminal and a second contact terminal which are connected with an external data transmission bus; wherein the chip groove is fixed in the shell and is used for placing the chip resistor; the first contact terminal and the second contact terminal are respectively arranged on two sides of the patch groove; the first end of the sliding metal plectrum is exposed outside the shell and is used for enabling the second end of the sliding metal plectrum to be connected with the different chip resistors in the at least two chip grooves under the action of external force so as to adjust the resistance value of the external terminal resistor. According to the external terminal resistor provided by the invention, the resistance value of the terminal resistor is adjustable, and meanwhile, the external terminal resistor is arranged on the data transmission bus, so that the weight of the whole aircraft is reduced by reducing the weight of the data transmission bus.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and particularly to an external terminal resistor and an aircraft. Background Art

[0002] In an aircraft, the terminal resistor plays a crucial role in ensuring the secure and reliable communication data. By matching the characteristic impedance of the data transmission bus, the terminal resistor prevents signal reflection, improves signal integrity, and reduces electromagnetic interference. Therefore, to ensure the reliability and safety performance of the aircraft, the terminal resistor is essential.

[0003] In the related art, the layout of electrical equipment in the aircraft is fixed, and the terminal resistor is built into the electrical equipment located at the end of the data transmission bus to prevent the formation of reflected waves when the signal reaches the end of the data transmission bus and interfere with the original signal. In this case, the layout of the data transmission bus is restricted by conditions and there is a problem of redundant wiring, which in turn leads to an increase in the weight of the aircraft. Summary of the Utility Model

[0004] The external terminal resistor and the aircraft provided by this application are used to solve the problems that when the terminal resistor is built into the electrical equipment located at the end of the data transmission bus, the layout of the data transmission bus is restricted by conditions and there is a problem of redundant wiring, and further leads to an increase in the weight of the aircraft.

[0005] In a first aspect, this application provides an external terminal resistor, which includes a housing and a resistor main body part. The resistor main body part includes at least two patch slots, a sliding metal shifter, at least two patch resistors, and a first contact terminal and a second contact terminal connected to an external data transmission bus;

[0006] Among them, the patch slots are arranged in the housing for placing the patch resistors;

[0007] The first contact terminal and the second contact terminal are respectively arranged on both sides of the patch slot;

[0008] The first end of the sliding metal shifter is exposed outside the housing, and is used to make the second end of the sliding metal shifter connect with different patch resistors in at least two patch slots under the action of an external force, so as to adjust the resistance value of the external terminal resistor.

[0009] In a possible implementation, the housing includes a female housing and a male housing that are hermetically docked; the resistor main body part is arranged at one end of the female housing far from the connection with the male housing to form a female connector;

[0010] In a possible implementation, a third contact terminal connected to the first contact terminal in the female end housing and a fourth contact terminal connected to the second contact terminal are provided in the male end housing; the third contact terminal and the fourth contact terminal are provided at one end of the male end housing away from the connection with the female end housing to form a male end connector; the third contact terminal and the fourth contact terminal are used to connect to an external data transmission bus.

[0011] In a possible implementation, a fixed base is provided inside one end of the female end housing away from the connection with the male end housing, and the fixed base is used to fix the patch slot.

[0012] In a possible implementation, the sliding metal slider includes a metal ring and a sliding handle; metal rings with the same diameter as the first contact terminal or the second contact terminal are respectively provided at both ends of the metal ring in the diameter direction, and the metal rings are respectively sleeved on the first contact terminal and the second contact terminal; the sliding handle is arranged in a groove on the side of the female end housing, and the sliding handle can slide along the direction of the patch slot in the groove.

[0013] In a second aspect, the present application provides an aircraft, which includes an aircraft body and electrical equipment arranged on the aircraft body. The wiring structure of the aircraft includes:

[0014] A data transmission bus for successively connecting electrical equipment in series, and the arrangement of the data transmission bus meets the requirements of the shortest path and / or the minimum weight;

[0015] An external terminal resistor is provided at the end of the data transmission bus, and the external terminal resistor is the external terminal resistor provided in the first aspect above.

[0016] In a possible implementation, the external terminal resistor is fixed on the data transmission bus in a series manner.

[0017] Or, the external terminal resistor is arranged at the outlet of the end electrical equipment in a series structure.

[0018] In a possible implementation, the external terminal resistor is provided at both ends of the data transmission bus.

[0019] In a possible implementation, the arrangement of the electrical equipment in the aircraft enables the aircraft to meet the center of gravity balance requirement.

[0020] In a possible implementation, the resistance value of the external terminal resistor is determined according to the characteristics of the data transmission bus.

[0021] The present application provides an external terminal resistor and an aircraft. The external terminal resistor includes a housing and a resistor main body part. The resistor main body part includes at least two patch slots, a sliding metal slider, at least two patch resistors, a first contact terminal and a second contact terminal connected to an external data transmission bus; wherein, the patch slots are fixed in the housing for placing the patch resistors; the first contact terminal and the second contact terminal are respectively arranged on both sides of the patch slots; the first end of the sliding metal slider is exposed outside the housing, and is used to make the second end of the sliding metal slider connect with different patch resistors in at least two patch slots under the action of an external force, so as to adjust the resistance value of the external terminal resistor. The external terminal resistor provided by the present application can realize adjustable resistance value of the terminal resistor. At the same time, by arranging the external terminal resistor at the end of the data transmission bus, that is, arranging the external terminal resistor on the data transmission bus, the layout of the data transmission bus is not restricted by conditions. By reasonably planning the wiring path of the data transmission bus, the redundancy of the data transmission bus is avoided, thereby reducing the weight of the data transmission bus and reducing the weight of the entire aircraft. Description of the Drawings

[0022] The drawings here are incorporated into the specification and constitute a part of this specification, showing embodiments consistent with the present application, and are used together with the specification to explain the principles of the present application.

[0023] Figure 1 It is a schematic diagram of the wiring method of electrical equipment in an aircraft in the related art;

[0024] Figure 2 It is a schematic diagram of the application scenario provided by the embodiment of the present application;

[0025] Figure 3 It is a flowchart of the wiring method of an aircraft provided by an embodiment of the present application;

[0026] Figure 4 It is a schematic diagram of the setting of the external terminal resistor at the end of the data transmission bus provided by the embodiment of the present application;

[0027] Figure 5 It is a schematic diagram of the structure of the external terminal resistor provided by an embodiment of the present application;

[0028] Figure 6 It is a schematic diagram of the structure of the external terminal resistor provided by another embodiment of the present application;

[0029] Figure 7 It is a schematic diagram of the structure of the external terminal resistor provided by another embodiment of the present application;

[0030] Figure 8 It is a schematic diagram of the connection mode of the external terminal resistor to the data transmission bus provided by the embodiment of the present application;

[0031] Figure 9 The structural schematic diagram of the aircraft provided by the embodiment of the present application.

[0032] Reference numerals:

[0033] 50: Housing;

[0034] 51: Resistance main body part;

[0035] 510: Female terminal housing;

[0036] 511: SMT groove;

[0037] 512: Sliding metal paddle;

[0038] 5121: Metal ring;

[0039] 5122: Sliding handle;

[0040] 5123: Metal ring;

[0041] 513: SMT resistor;

[0042] 514: First contact terminal;

[0043] 515: Second contact terminal;

[0044] 516: Fixed base;

[0045] 52: Data transmission bus;

[0046] 520: Male terminal housing;

[0047] 521: Third contact terminal;

[0048] 522: Fourth contact terminal;

[0049] 53: Female terminal connector;

[0050] 54: Male terminal connector.

[0051] Through the above-mentioned drawings, the specific embodiments of the present application have been shown, and there will be more detailed descriptions hereinafter. These drawings and textual descriptions are not intended to limit the scope of the concept of the present application in any way, but to illustrate the concept of the present application to those skilled in the art by referring to specific embodiments. Detailed implementation manners

[0052] Exemplary embodiments will be described in detail herein, and examples thereof are shown in the accompanying drawings. When the following description refers to the accompanying drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present application. On the contrary, they are merely examples of devices and methods consistent with some aspects of the present application as detailed in the appended claims.

[0053] In the related art, the arrangement of electrical devices in an aircraft is fixed, and the terminal resistance is built into the electrical device located at the end of the data transmission bus. Figure 1 It is a schematic diagram of the wiring method of electrical devices in an aircraft in the related art. As Figure 1 shown, the electrical devices in the aircraft include A to F, among which, terminal resistors R are provided in electrical device A and electrical device E.

[0054] It can be seen from the figure that when the arrangement of electrical devices A to F in the aircraft is fixed, to ensure that electrical device A and electrical device E containing terminal resistor R are the end electrical devices on the data transmission bus, when arranging the data transmission bus according to the arrangement of electrical devices A to F in the aircraft, the data transmission bus will be subject to conditional constraints, that is, taking electrical device A as the starting point for arranging the data transmission bus and electrical device E as the ending point for arranging the data transmission bus, so that there will be redundant wiring when arranging the data transmission bus, which will in turn lead to an increase in the weight of the entire aircraft.

[0055] Based on the technical problems existing in the related art, in the embodiments of the present application, by externally placing the terminal resistor on the data transmission bus, when the arrangement of electrical devices in the aircraft is fixed, the arrangement of the data transmission bus is not subject to conditional constraints. By reasonably planning the routing path of the data transmission bus, the redundancy of the data transmission bus is avoided, so as to reduce the weight of the entire aircraft by reducing the weight of the data transmission bus.

[0056] First, the application scenario of the embodiments of the present application will be described below.

[0057] Figure 2 It is a schematic diagram of the application scenario provided by the embodiments of the present application. As Figure 2 shown, the aircraft and its wiring method provided by the embodiments of the present application are applicable to the scenario where an external terminal resistor 20 is externally placed on the data transmission bus 52 when arranging the data transmission bus for electrical devices in the aircraft. Specifically, after arranging the data transmission bus for the electrical devices in the aircraft, the external terminal resistor 20 is arranged in series at the outlet of the end electrical device connected to the data transmission bus.

[0058] In the wiring method of the aircraft provided by the embodiments of the present application, the type of the aircraft is not limited. Exemplarily, the aircraft may be a fixed-wing aircraft, a rotary-wing aircraft, a compound-wing aircraft, a tilt-rotor aircraft, a drone, a rocket, a space shuttle, etc.

[0059] Based on the above application scenarios, the following will combine Figure 3 to elaborate in detail on the wiring method of the aircraft provided by the embodiments of the present application.

[0060] Figure 3 is a flowchart of the wiring method of the aircraft provided by an embodiment of the present application. As Figure 3 shown, the implementation manner of the wiring method of the aircraft includes the following steps:

[0061] S301, obtain the arrangement mode of electrical devices in the aircraft.

[0062] Exemplarily, the electrical devices in the aircraft may include a flight control computer, a load box, an inertial navigation system (INS), a power distribution box, a control box, a servo controller, an altimeter, etc. For a rotary-wing aircraft, the electrical devices may further include a pitch-changing mechanism. For a tilt-rotor aircraft, the electrical devices may further include a drive controller for the tilt mechanism, etc.

[0063] It should be noted that in the wiring method of the aircraft provided by the embodiments of the present application, the number and types of electrical devices in the aircraft are not limited, and the types and numbers of specific electrical devices can be determined according to actual application requirements.

[0064] The arrangement mode of electrical devices in the aircraft mainly refers to the arrangement position and installation direction of electrical devices in the aircraft. The electrical devices on the aircraft also need to be arranged according to the internal structure space layout of the aircraft.

[0065] It can be understood that the arrangement mode of electrical devices in the aircraft is determined according to the functions of the electrical devices, the internal structure space layout of the aircraft, and the center-of-gravity requirements of the entire aircraft. The functional constraints of the electrical devices, for example, the pitch-changing mechanism needs to be as close as possible to the propeller, and the flight control computer is preferably located in the center of the aircraft so that its communication distance from each electrical device is approximately the same.

[0066] Exemplarily, the arrangement mode of electrical devices in the aircraft is as shown in the above Figure 1 figure.

[0067] S302, based on the arrangement mode, serially connect the electrical devices in sequence through a data transmission bus.

[0068] In this step, the arrangement mode of the data transmission bus meets the requirements of the shortest path and / or the minimum weight.

[0069] In some embodiments, the arrangement of the data transmission bus meets the requirement of the shortest path; in some embodiments, the arrangement of the data transmission bus meets the requirement of the minimum weight; in some embodiments, the arrangement of the data transmission bus meets both the requirement of the shortest path and the requirement of the minimum weight.

[0070] Exemplarily, the data transmission bus can be an RS-422 bus, an RS-485 bus, or a Controller Area Network (CAN) communication bus. The specific type of the data transmission bus can be determined according to the actual application requirements.

[0071] Exemplarily, the RS-422 bus, the RS-485 bus, and the CAN communication bus are all twisted pairs.

[0072] In a possible implementation, the data transmission bus is arranged based on the arrangement of the electrical devices in the aircraft, that is, the electrical devices are connected in series in turn through the data transmission bus. Among them, the arrangement of the data transmission bus meets the requirement of the shortest arrangement path of the data transmission bus, or the arrangement of the data transmission bus meets the requirement of the minimum weight of the data transmission bus.

[0073] S303, an external terminal resistor is set at the end of the data transmission bus.

[0074] In a possible implementation, based on the center-of-gravity balancing requirement of the whole aircraft's electrical devices, the electrical device located at the end of the data transmission bus is determined, and then the arrangement positions of the external terminal resistors at the two ends of the data transmission bus are determined. Based on this arrangement position, an external terminal resistor is set at each of the two ends of the data transmission bus.

[0075] It can be understood that multiple electrical devices can be connected to the data transmission bus. If the signal wavelength is relatively short compared to the transmission line, a reflected wave will be formed at the end of the transmission line, interfering with the original signal. By setting an external terminal resistor at each of the two ends of the data transmission bus, interference can be effectively suppressed.

[0076] An external terminal resistor is a component used in electrical and electronic circuits, mainly used to eliminate signal reflection and match impedance. External terminal resistors are usually applied in high-speed data transmission lines, communication lines, and radio frequency circuits. The main function of the external terminal resistor is to absorb the signal energy at the end of the transmission line, thereby preventing the signal from reflecting back into the line, resulting in signal distortion or data transmission errors.

[0077] Specifically, when transmitting high-frequency signals, the signal wavelength is relatively short compared to the transmission line, and a reflected wave will be formed at the end of the transmission line, interfering with the original signal. Therefore, an external terminal resistor needs to be added at the end of the transmission line to prevent the signal from reflecting when it reaches the end of the transmission line. When transmitting long-line signals, generally, in order to avoid signal reflection and echo, a terminal matching resistor also needs to be connected at the receiving end.

[0078] The following will describe Figure 4 the setting of the external terminal resistor at the end of the data transmission bus in the wiring method of the aircraft provided in the embodiments of the present application.

[0079] Figure 4 FIG. is a schematic diagram of the setting of the external terminal resistor at the end of the data transmission bus provided in the embodiments of the present application. As Figure 4 shown, A to F represent electrical devices in the aircraft, and R represents the external terminal resistor. It can be seen from Figure 4 that the relative positions of the electrical devices A to F in the aircraft are fixed. When the positions of the electrical devices A to F are fixed, optionally, the electrical devices shown in Figure 4 are connected in series through the data transmission bus in the order of A to F. Among them, the electrical devices A and F are the electrical devices connected to the end of the data transmission bus, that is, the end electrical devices.

[0080] It should be noted that the layout method of the data transmission bus shown above Figure 4 is only an example. In the wiring method of the aircraft provided in the embodiments of the present application, when the positions of the electrical devices A to F are fixed, the connection order of connecting each electrical device through the data transmission bus is not limited, as long as the requirement of the shortest data transmission bus for connecting the electrical devices or the minimum weight of the data transmission bus can be achieved.

[0081] Compared with Figure 1 the layout method of the data transmission bus with the terminal resistor built into the electrical device shown in Figure 4 that is, when the positions of the electrical devices are fixed, the layout method of the data transmission bus can only start / end with the electrical device A with the built-in terminal resistor and end / start with the electrical device E with the built-in terminal resistor, which is subject to conditions.

[0082] By comparing Figure 1 and Figure 4, in the wiring method of the aircraft provided by the embodiments of the present application, the arrangement method of the data transmission bus with the terminal resistor externally placed at the outlet of the end electrical device has no conditional constraints on the arrangement of the data transmission bus, so as to ensure that the routing path of the data transmission bus can be the shortest when arranged, that is, there is no redundant wiring, or the weight of the data transmission bus can be the lightest.

[0083] It should be noted that the above Figure 1 and Figure 4 are only examples. Figure 1 In Figure 1 , there is no limitation on the electrical device with an internal terminal resistor. Figure 1 In the wiring method shown in

[0084] , the setting method of the data transmission bus depends on the electrical device with an internal terminal resistor, that is, the electrical device with an internal terminal resistor must be used as the starting point and the ending point of the data transmission bus wiring.

[0084] Next, the structure of the external terminal resistor in the wiring method of the aircraft provided by the embodiments of the present application will be described in detail with reference to Figures 5 to 7 .

[0085] Figure 5 FIG. Figure 5 shows a schematic structural diagram of an external terminal resistor provided by an embodiment of the present application. As Figure 5 shown, the external terminal resistor includes a housing 50 and a resistor main body portion 51. The resistor main body portion 51 includes at least two patch slots 511, a sliding metal dial 512, at least two patch resistors 513, and a first contact terminal 514 and a second contact terminal 515 connected to an external data transmission bus 52.

[0086] Among them, the patch slots 511 are arranged in the housing 50 for placing the patch resistors 513; the first contact terminal 514 and the second contact terminal 515 are respectively arranged on both sides of the patch slot 511; the first end of the sliding metal dial 512 is exposed outside the housing 50, and is used to connect the second end of the sliding metal dial 512 to different patch resistors 513 in at least two patch slots 511 under the action of an external force, so as to adjust the resistance value of the external terminal resistor.

[0087] Exemplarily, patch resistors with different resistance values are placed in the patch slots, and the second end of the sliding metal dial 512 is connected to different patch resistors 513 in at least two patch slots 511 under the action of an external force, so as to realize the adjustment of the resistance value of the external terminal resistor.

[0088] As Figure 5The external terminal resistor shown is configured such that, under the action of an external force, the sliding metal slider 512 is connected to different patch resistors 513 in at least two patch slots 511, thereby achieving adjustment of the resistance value of the external terminal resistor. By providing two pores at one end of the housing 50 close to the resistor main body portion 51, the data transmission bus is connected to the first contact terminal 514 and the second contact terminal 515, thus realizing the connection between the external terminal resistor and the data transmission bus.

[0089] Figure 6 FIG. [X] is a schematic structural diagram of an external terminal resistor provided by another embodiment of the present application. As Figure 6 shown, the housing 50 of the external terminal resistor includes a female terminal housing 510 and a male terminal housing 520 that are hermetically docked; the resistor main body portion 51 is disposed at one end of the female terminal housing 510 away from the connection with the male terminal housing 520, forming a female terminal connector 53.

[0090] Optionally, a third contact terminal 521 connected to the first contact terminal 514 in the female terminal housing 510 and a fourth contact terminal 522 connected to the second contact terminal 515 are provided in the male terminal housing 520; the third contact terminal 521 and the fourth contact terminal 522 are disposed at one end of the male terminal housing 520 away from the connection with the female terminal housing 510, forming a male terminal connector 54; the third contact terminal 521 and the fourth contact terminal 522 are used to connect to the data transmission bus 52.

[0091] As Figure 6 shown, for the external terminal resistor, under the action of an external force, the sliding metal slider 512 is connected to different patch resistors 513 in at least two patch slots 511, thereby achieving adjustment of the resistance value of the external terminal resistor. By providing two pores at one end of the male terminal housing away from the connection with the female terminal housing, the data transmission bus is connected to the third contact terminal and the fourth contact terminal, thus realizing the connection between the external terminal resistor and the data transmission bus.

[0092] Figure 7 FIG. [X] is a schematic structural diagram of an external terminal resistor provided by another embodiment of the present application. As Figure 7 shown, the external terminal resistor includes a female terminal connector 53 and a male terminal connector 54. Among them, the female terminal connector 53 includes patch slots 511, a female terminal housing 510, a first contact terminal 514, a second contact terminal 515, a sliding metal slider 512, and patch resistors 513; the male terminal connector 54 includes a male terminal housing 520, a third contact terminal 521, and a fourth contact terminal 522.

[0093] Among them, the female terminal connector 53 and the male terminal connector 54 are connected by a screwing and plugging method.

[0094] As Figure 7As shown, the female end housing 510 can be frustum-shaped. Among them, the upper bottom surface of the female end housing is sealed, and the lower bottom surface is open. A fixed base 516 is provided inside the upper bottom surface of the female end housing 510, and the fixed base 516 is used to fix the patch slot 511.

[0095] There can be multiple patch slots 511, and a patch resistor 513 can be placed in each patch slot 511. That is, a patch resistor is inserted into one patch slot.

[0096] The sliding metal slider 512 includes a metal ring 5121 and a sliding handle 5122. Among them, metal rings 5123 with the same diameter as the first contact terminal 514 or the second contact terminal 515 are respectively provided at both ends of the metal ring 5121 in the diameter direction. The metal rings 5123 are respectively sleeved on the first contact terminal 514 and the second contact terminal 515. The sliding handle 5122 is arranged in the groove on the side of the female end housing 510, and the sliding handle 5122 can slide up and down or left and right along the direction of the patch slot in the groove.

[0097] As Figure 7 shown in the external terminal resistor, under the action of an external force, it is connected to different patch resistors 513 in at least two patch slots 511 through the sliding metal slider 512 to realize the adjustment of the resistance value of the external terminal resistor; by providing two pores at one end of the male end housing far from the connection with the female end housing, the data transmission bus is connected to the third contact terminal and the fourth contact terminal, or by providing two pores at one end of the female end housing far from the connection with the male end housing, the data transmission bus is connected to the first contact terminal and the second contact terminal to realize the connection between the external terminal resistor and the data transmission bus.

[0098] Figure 7 As shown in the cross-sectional view of the male end connector 54 in

[0099] Exemplarily, the first contact terminal 514 and the second contact terminal 515 in the female end connector 53 can be hollow cylinders, and the third contact terminal 521 and the fourth contact terminal 522 in the male end connector 54 can be solid cylinders. By inserting the third contact terminal 521 into the first contact terminal 514 and inserting the fourth contact terminal 522 into the second contact terminal 515, the sealed connection of the external terminal resistor can be realized.

[0100] Exemplarily, the female end housing and the male end housing can adopt carbon fiber composite materials to reduce the weight of the external terminal resistor.

[0101] Exemplarily, the number of patch resistors can be 6. The resistance values corresponding to different patch resistors are different. In the wiring method of the aircraft provided in this application, the number of patch resistors is not limited and can be determined according to actual needs.

[0102] For the external terminal resistor provided in the embodiment of the present application, by means of the sliding handle of the sliding metal piece, the sliding metal piece can be slid to the patch resistor contact surfaces with different resistance values, so as to realize the adjustable resistance value of the external terminal resistor.

[0103] Those skilled in the art can understand that the method of disposing the external terminal resistor outside the data transmission bus is liable to be affected by the outside world, such as human touch, vibration during aircraft operation, and humid environment, etc. In the wiring method of the aircraft provided in the embodiment of the present application, by directly fixing the external terminal resistor on the data transmission bus and docking and sealing it in the form of the male connector and the female connector as shown above Figure 7 the external terminal resistor is made more secure, can better resist vibration, prevent human accidental touch, and is simple to plug and unplug. At the same time, it can prevent signal interference caused by the failure of the external terminal resistor and affect the safe operation of the aircraft.

[0104] In the embodiment of the present application, by obtaining the layout mode of the electrical equipment in the aircraft and, based on the layout mode, successively connecting the electrical equipment in series through the data transmission bus, and further disposing an external terminal resistor at the end of the data transmission bus. In the embodiment of the present application, by disposing the external terminal resistor at the end of the data transmission bus, that is, disposing the external terminal resistor on the data transmission bus, the layout of the data transmission bus is realized without being restricted by conditions. By reasonably planning the wiring path of the data transmission bus, the redundancy of the data transmission bus is avoided, so as to reduce the weight of the data transmission bus and thus reduce the weight of the entire aircraft.

[0105] It can be understood that adding an external terminal resistor on the data transmission bus greatly facilitates the overall layout of the electrical equipment in the aircraft. The adjustable external terminal resistor can also greatly meet the requirements of the aircraft for different resistance values, which is convenient for unified management of parts. The way of docking the external terminal resistor with a connector improves the reliability of the external terminal resistor and ensures the safe operation of the aircraft.

[0106] Optionally, in a possible implementation manner of step S303 of disposing an external terminal resistor at the end of the data transmission bus, the external terminal resistor is fixed on the data transmission bus in a series manner.

[0107] Figure 8 It is a schematic diagram of the connection mode of the external terminal resistor provided in the embodiment of the present application on the data transmission bus. As Figure 8 shown, A to D represent the electrical equipment in the aircraft, and R represents the external terminal resistor. It can be seen from the figure that the electrical equipment A and the electrical equipment D are the terminal electrical equipment on the data transmission bus. Therefore, the external terminal resistor is fixed on the outlet of the electrical equipment A and the outlet of the electrical equipment E in a series manner respectively.

[0108] like Figure 8 As shown in the figure, the data transmission bus is a twisted pair, with external terminal resistors. Figure 8 The connection mode shown in is set on the data transmission bus, that is, one end of the external terminal resistor is connected to a twisted wire in the data transmission bus, and the other end of the external terminal resistor is connected to another twisted wire in the data transmission bus.

[0109] Optionally, in another possible implementation of step S303 of setting an external terminal resistor at the end of the data transmission bus, the external terminal resistor is set in series at an outlet of the terminal electrical device.

[0110] For example, the terminal electrical device is the electrical device connected at both ends of the data transmission bus, as described above. Figure 8 Electrical equipment A and electrical equipment D shown in the figure.

[0111] Optionally, in another possible implementation of step S303 of setting an external terminal resistor at the end of the data transmission bus, external terminal resistors are set at both ends of the data transmission bus.

[0112] It can be understood that the number of external terminal resistors arranged on the data transmission bus is two.

[0113] Optionally, in the wiring method of an aircraft provided in an embodiment of the present application, before obtaining the arrangement of electrical equipment in the aircraft, the method further includes: arranging the electrical equipment on the aircraft so that the aircraft meets the center of gravity balancing requirements.

[0114] Illustratively, the electrical equipment is similar to that described above and will not be described in detail here.

[0115] The external terminal resistor in the wiring method for an aircraft provided in an embodiment of the present application may, optionally, be sealed and docked in the form of a connector, and / or the resistance value of the external terminal resistor may be adjustable.

[0116] As mentioned above Figure 6 or Figure 7 As shown, exemplarily, the external terminal resistor is sealed in the form of a female connector and a male connector that are rotated and plugged together.

[0117] As mentioned above Figures 5 to 7 As shown, for example, when the sliding metal paddle in the external terminal resistor slides to different chip resistors, the corresponding resistance value is different, that is, the resistance value of the external terminal resistor is adjustable. The adjustable resistance value range of the external terminal resistor can be 100Ω-150Ω.

[0118] Exemplarily, the resistance value of the external terminal resistor is determined according to the characteristics of the data transmission bus. The characteristics of the data transmission bus can be one or more of the transmission rate, the number of nodes, and the transmission length.

[0119] Exemplarily, the resistance value of the external terminal resistor can be 100 Ω, 120 Ω, or 150 Ω.

[0120] Optionally, a possible implementation of step S302 for sequentially connecting electrical devices in series through the data transmission bus based on the layout can be: based on the layout, adopting a wiring harness laying method to sequentially connect electrical devices in series through the data transmission bus.

[0121] Exemplarily, the wiring harness laying method can be a cable tie fixing method, a cable tray and conduit method, a flexible cable chain, etc. The specific wiring harness laying method can be determined according to the actual application requirements, and the present application does not limit this.

[0122] The specific implementation method is similar to the above and will not be elaborated here.

[0123] In summary, in some embodiments, the implementation method of the wiring method for the aircraft provided by the present application includes the following steps:

[0124] S1: Obtain the layout of electrical devices in the aircraft;

[0125] S2: Based on the layout, adopt a wiring harness laying method to sequentially connect electrical devices in series through the data transmission bus;

[0126] S3: Set the external terminal resistor in series on the data transmission bus.

[0127] In some embodiments, the implementation method of the wiring method for the aircraft provided by the present application includes the following steps:

[0128] S1: Obtain the layout of electrical devices in the aircraft;

[0129] S2: Based on the layout, adopt a wiring harness laying method to sequentially connect electrical devices in series through the data transmission bus;

[0130] S3: Set the external terminal resistor in series at the outlet of the terminal electrical device.

[0131] In some embodiments, the implementation method of the wiring method for the aircraft provided by the present application includes the following steps:

[0132] S1: Obtain the layout of electrical devices in the aircraft;

[0133] S2: Based on the layout, adopt a wiring harness laying method to sequentially connect electrical devices in series through the data transmission bus;

[0134] S3: Set external terminal resistors at both ends of the data transmission bus.

[0135] The specific implementation methods of the above steps are similar to those of the above embodiments and will not be elaborated here.

[0136] In summary, the beneficial effects that can be achieved by the wiring method of the aircraft provided in the embodiments of the present application are summarized as follows:

[0137] 1. By externally placing the external terminal resistor at the outlet of the electrical equipment at the end of the data transmission bus, the flexibility of the overall electrical equipment layout of the aircraft is improved, the arrangement of electrical equipment is not restricted, the layout space of the aircraft is effectively utilized, and at the same time, the wiring path of the data transmission bus can be reasonably planned, the cable weight of the data transmission bus is reduced, the overall electrical equipment layout is facilitated, and the weight and center of gravity of the entire aircraft are controlled.

[0138] 2. By directly fixing the external terminal resistor on the data transmission bus and docking and sealing it in the form of a connector, the external terminal resistor is made more secure, preventing signal interference caused by the failure of the external terminal resistor and affecting the safe operation of the aircraft.

[0139] 3. The external terminal resistor is connected in series at the outlet of the electrical equipment at the end of the data transmission bus, which is beneficial to monitoring and analyzing the power quality of data transmission, is flexible to use, does not damage the state of the cable, and has no cost of later maintenance and risk of use.

[0140] 4. The resistance value of the external terminal resistor can be freely adjusted to meet the anti-interference requirements of different frequency signals on the aircraft.

[0141] 5. Since the entire data transmission bus can bear a limited number of load communications, when the cable is laid to a certain length, the signal quality transmitted reaches the limit. According to the actual usage situation, the external terminal resistor can be flexibly arranged at the electrical equipment at the end.

[0142] Next, in combination with Figure 9 The aircraft provided in the embodiments of the present application will be described in detail.

[0143] Figure 9 It is a schematic structural diagram of the aircraft provided in the embodiments of the present application. As Figure 9 shown, the aircraft includes an aircraft body 90, electrical equipment 91, a data transmission bus (not shown in the figure), and an external terminal resistor 92.

[0144] Among them, the electrical equipment 91, the data transmission bus, and the external terminal resistor 92 are arranged on the aircraft body 90 by the wiring method of the aircraft provided in the above embodiments.

[0145] It should be noted that Figure 9This is only a schematic diagram, and the types, numbers, and layout positions of electrical devices in the aircraft are not limited in this application and can be determined according to actual application requirements. The layout position of the external terminal resistor can be determined according to the implementation method of the aircraft wiring method provided in the above embodiments.

[0146] Exemplarily, the electrical devices in the aircraft may include a flight control computer, a load box, an inertial navigation system (INS), a power distribution box, a control box, a servo controller, an altimeter, etc. For rotorcraft, the electrical devices may further include a pitch change mechanism. For tiltrotor aircraft, the electrical devices may further include a drive controller for the tilt mechanism, etc.

[0147] Among them, the pitch change mechanism is used to adjust the angle of the aircraft propeller or rotor blade. By adjusting the angle of the blade, the performance of the aircraft under different flight conditions, such as takeoff, cruise, and landing, can be optimized.

[0148] The flight control computer is the core component of the flight control system, responsible for processing the sensor data of the aircraft, executing control algorithms, and sending commands to the actuators to achieve the stability and control of the aircraft.

[0149] It can be understood that the layout of the geometric centers of gravity of the pitch change mechanism and the flight control computer in the aircraft has an important impact on the performance, stability, and controllability of the aircraft.

[0150] Exemplarily, the layout positions of the pitch change mechanism and the flight control computer in the aircraft should be as close as possible to the design center of gravity of the aircraft to avoid excessive deviation of the overall center of gravity of the aircraft. At the same time, the pitch change mechanism and the flight control computer should be symmetrically arranged left and right in the aircraft to avoid lateral imbalance of the aircraft.

[0151] Optionally, the pitch change communication signal sent by the pitch change mechanism uses a 485 bus for signal transmission.

[0152] It can be understood that the pitch change communication is a control signal sent by the pitch change mechanism for controlling the pitch change angle. Among them, the pitch change angle is the angle between the blade and the rotation plane.

[0153] Optionally, the resistance value of the external terminal resistor 92 is determined according to the characteristics of the data transmission bus.

[0154] Exemplarily, the characteristics of the data transmission bus can be one or more of the transmission rate, the number of nodes, and the transmission length.

[0155] Exemplarily, the resistance value of the external terminal resistor 92 is determined according to the operating frequency of the data transmission bus.

[0156] The operating frequencies of different types of data transmission buses are different, and the corresponding resistance values of the external terminal resistors are also different.

[0157] Finally, it should be noted that those skilled in the art will readily conceive of other embodiments of the present invention after considering the specification and practicing the invention disclosed herein. The present invention is intended to cover any variations, uses, or adaptations of the present invention, which follow the general principles of the present invention and include known common knowledge or conventional technical means in the technical field not disclosed in the present invention. It is not limited to the exact structures described above and shown in the drawings, and various modifications and changes can be made without departing from its scope. The scope of the present invention is only limited by the appended claims.

Claims

1. An external terminal resistor, characterized in that: include: A housing (50) and a resistor main body (51), wherein the resistor main body (51) comprises at least two patch slots (511), a sliding metal paddle (512), at least two patch resistors (513), and a first contact terminal (514) and a second contact terminal (515) connected to an external data transmission bus (52); The chip slot (511) is arranged in the housing (50) and is used to place the chip resistor (513); The first contact terminal (514) and the second contact terminal (515) are respectively arranged on two sides of the patch slot (511); The first end of the sliding metal paddle (512) is exposed outside the housing (50), and is used to connect the second end of the sliding metal paddle (512) to different chip resistors (513) in the at least two chip slots (511) under the action of an external force, so as to adjust the resistance value of the external terminal resistor.

2. The external terminal resistor according to claim 1, characterized in that: The housing (50) comprises a female housing (510) and a male housing (520) that are sealed and butted together; The resistor main body (51) is arranged in the female end housing (510) to form a female end connector (53).

3. The external terminal resistor according to claim 2, characterized in that: The male end housing (520) is provided with a third contact terminal (521) connected to the first contact terminal (514) in the female end housing (510), and a fourth contact terminal (522) connected to the second contact terminal (515), so as to form a male end connector (54); The third contact terminal (521) and the fourth contact terminal (522) are used to connect to an external data transmission bus (52).

4. The external terminal resistor according to claim 2, characterized in that: A fixing base (516) is provided inside the end of the female end housing (510) away from the connection with the male end housing (520), and the fixing base (516) is used to fix the patch slot (511).

5. The external terminal resistor according to any one of claims 2 to 4, characterized in that: The sliding metal pick (512) comprises a metal ring (5121) and a sliding handle (5122); The metal ring (5121) is provided with metal rings (5123) having the same diameter as the first contact terminal (514) or the second contact terminal (515) at both ends along the diameter direction, respectively, and the metal rings (5123) are respectively sleeved on the first contact terminal (514) and the second contact terminal (515); The sliding handle (5122) is arranged in a groove on the side of the female end housing (510), and the sliding handle (5122) can slide in the groove along the direction of the patch slot (511).

6. An aircraft, characterized in that: The aircraft comprises an aircraft body and electrical equipment arranged on the aircraft body, and the wiring structure of the aircraft comprises: A data transmission bus, used to sequentially connect the electrical devices in series, wherein the arrangement of the data transmission bus satisfies the requirements of shortest path and / or minimum weight; An external terminal resistor is arranged at the end of the data transmission bus, and the external terminal resistor is the external terminal resistor described in any one of claims 1 to 5.

7. The aircraft according to claim 6, characterized in that The external terminal resistor is fixed in series on the data transmission bus; Alternatively, the external terminal resistor is arranged in a series structure at the outlet of the terminal electrical equipment.

8. The aircraft according to claim 7, characterized in that The external terminal resistors are arranged at two ends of the data transmission bus.

9. An aircraft according to any one of claims 6 to 8, characterized in that The arrangement of the electrical equipment in the aircraft enables the aircraft to meet the center of gravity trim requirement.

10. An aircraft according to any one of claims 6 to 8, characterized in that The resistance value of the external terminal resistor is determined according to the characteristics of the data transmission bus.

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