Aircraft negative line board layout design method based on airborne equipment fault current

Abstract

The invention belongs to the technical field of aviation, and particularly relates to an aircraft negative line board layout design method based on airborne equipment fault current, which comprises the following steps: setting a potential limit value, adjusting a negative line board according to a reference potential data result and the potential limit value, and obtaining an adjusted reference potential to-be-evaluated area; and judging whether the adjusted to-be-evaluated area of the reference potential is not smaller than a potential limit value or not, if so, performing structure optimization on the negative wire plate, and repeatedly performing adjustment on the negative wire plate until the potential limit value requirement is met, so as to obtain the evaluated to-be-evaluated area. Normal power utilization and fault power utilization characteristics of airplane airborne equipment are integrated, weak links of airplane negative line board layout design are visually displayed in a three-dimensional mode through reference potential distribution of an airplane electrical loop, and evaluation and iterative optimization design can be rapidly carried out on the electrical characteristics of the airplane electrical loop and the negative line board layout. The efficiency and precision of layout design of the aircraft electrical loop and the negative line board are improved, and the power utilization risk of aircraft airborne equipment is reduced.

Description

Technical Field

[0001] This application belongs to the field of aviation technology, and specifically relates to a method for designing the layout of an aircraft negative line board based on the fault current of airborne equipment. Background Technology

[0002] Negative grounding board layout is a crucial aspect of electrical circuit design, especially in aircraft. Proper negative grounding board layout is essential for ensuring circuit reliability and safety, not only improving equipment performance and safety but also protecting electronic equipment from damage. Furthermore, correct grounding connections help reduce electromagnetic interference and improve system electromagnetic compatibility, which is vital for electronic equipment, especially sensitive devices.

[0003] Therefore, improving the electromagnetic compatibility of the system is a problem that needs to be solved. Summary of the Invention

[0004] The purpose of this application is to provide a method for designing the layout of an aircraft negative line board based on the fault current of airborne equipment, so as to solve the problem of low electromagnetic compatibility of existing systems.

[0005] The technical solution of this application is: a method for designing the layout of an aircraft negative line board based on the fault current of airborne equipment, including:

[0006] Obtain the wiring data of the entire aircraft, construct an electrical circuit simulation prototype, and locate the installation area and position of the negative line board corresponding to high current electrical equipment and critical flight equipment;

[0007] The entire aircraft is divided into multiple sections. The section containing high-current electrical equipment is defined as the area to be evaluated for the reference potential of the aircraft's electrical circuit, and the fault electrical characteristics of the area to be evaluated are obtained.

[0008] Inject the normal operating current of the airborne electrical equipment into all negative line boards. Select an area to be evaluated, collect the various fault currents generated by the operation of the negative line boards, and determine whether the difference between the maximum fault current and the normal operating current is less than the set value. If so, proportionally increase the normal operating current of each negative line board in the area to be evaluated.

[0009] Determine the current value that needs to be injected at each zero potential reference point, perform full-aircraft reference potential distribution simulation and calculation on the aircraft electrical circuit and negative line board, and obtain the reference potential data results for each negative line board of the entire aircraft;

[0010] Set the potential limit, adjust the negative line plate according to the reference potential data and the potential limit, and obtain the adjusted reference potential to be evaluated area. Determine whether the adjusted reference potential to be evaluated area is not less than the potential limit. If so, optimize the structure of the negative line plate and repeat the adjustment of the negative line plate until the potential limit requirement is met, and obtain the evaluated area.

[0011] Obtain all evaluated areas and the reference potential of each negative board in the whole machine when there is a fault current under fault current injection, until the reference potential of each negative board in all evaluated areas is less than the potential limit.

[0012] Preferably, determining whether the difference between the maximum fault current and the normal operating current is less than a set value is as follows:

[0013] Based on the selected area to be evaluated, calculate the total normal operating current T of the area to be evaluated, and extract the maximum fault current I of a single electrical device in the area to be evaluated. max And the normal operating current M of the corresponding equipment, and inject the maximum fault current I into the negative line board of the corresponding equipment. max If I max If M is less than T / 2, the injection current of each negative line in the area to be evaluated is increased proportionally until the total injection current in the area to be evaluated is not less than 1.5*T.

[0014] Preferably, the current value to be injected at each zero-potential reference point is determined as follows:

[0015] A reverse current equal to the total current injected into the entire aircraft is injected at the zero-potential reference point. For multiple zero-potential reference points, the current value to be injected at each zero-potential reference point is determined based on the power supply source of the airborne equipment.

[0016] Preferably, determining whether the adjusted reference potential region to be evaluated is not less than the potential limit is as follows:

[0017] The recorded reference potential results for each negative line plate of the entire machine, and the potential limit V. d For comparison, V d The value is greater than 0; if the reference potential result of the negative line plate is less than V d Then the normal power supply of the corresponding airborne equipment is risk-free, and the layout of the negative line board meets the requirements; if the reference potential data of the negative line board is greater than or equal to V d This would put the normal power supply of the corresponding airborne equipment at risk.

[0018] Preferably, the negative line plate is adjusted based on the reference potential data and the potential limit, as follows:

[0019] Based on the overall reference potential distribution cloud map, the reference potential within the radius limit R around the equipment installation area corresponding to this negative line board is determined to be less than the potential limit V. d The position distribution of the negative line plate was adjusted so that the reference potential was less than V. d The position was then recalculated and the full-machine reference potential distribution was simulated and calculated again until the adjusted reference potential of the negative line plate was less than the potential limit V. d The radius limit R is a value greater than 0 meters.

[0020] Preferably, the negative line plate is structurally optimized as follows:

[0021] Even after multiple adjustments to the position of the negative line plate, its reference potential remains no less than the potential limit value V. d If so, then the reference potential to be evaluated region is supplemented with additional metal structures and parallel paths are added; and supplementary metal structures are added to the electrical circuit simulation prototype.

[0022] Preferably, the installation area and location of the negative line board corresponding to the high-current electrical equipment and critical flight equipment are as follows:

[0023] Compile and summarize the normal electrical characteristics of aircraft onboard electrical equipment, including operating voltage and operating current;

[0024] The preliminary design schemes of the negative line plates for the entire aircraft were compiled and summarized, and the installation area and position of the negative line plates were located in the three-dimensional model of the aircraft.

[0025] Based on the installation area and location of the negative line board, the high-current electrical equipment and critical flight equipment of the aircraft are screened out, and their installation areas and locations are located in the three-dimensional model of the aircraft. Then, the installation areas and locations of the negative line boards corresponding to the high-current electrical equipment and critical flight equipment are located.

[0026] Preferably, the fault power characteristics of the high-current electrical equipment include fault voltage and fault current.

[0027] The aircraft negative line board layout design method based on the fault current of airborne equipment in this application integrates the normal and fault power consumption characteristics of aircraft airborne equipment. It uses the reference potential distribution of the aircraft electrical circuit to visually display the weak links in the aircraft negative line board layout design in three dimensions. It can quickly evaluate and iteratively optimize the electrical characteristics of the aircraft electrical circuit and negative line board layout, improve the efficiency and accuracy of the aircraft electrical circuit and negative line board layout design, and reduce the power consumption risks of aircraft airborne equipment. Attached Figure Description

[0028] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0029] Figure 1 This is a structural diagram of the aircraft negative line plate layout for this application;

[0030] Figure 2 This is a schematic diagram of the negative line plate layout in the wing area of ​​this application;

[0031] Figure 3 This is a schematic diagram showing the aircraft area division and the distribution of zero-potential reference points in this application. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] A method for designing the layout of aircraft negative line boards based on fault currents of airborne equipment, such as... Figure 1 As shown, it includes the following steps:

[0034] Step S100: Obtain the wiring data of the entire aircraft, construct an electrical circuit simulation prototype, and locate the installation area and position of the negative line board corresponding to high current electrical equipment and key flight equipment.

[0035] Preferably, the installation area and location of the negative line board corresponding to the high-current electrical equipment and critical flight equipment are as follows:

[0036] Compile and summarize the normal electrical characteristics of aircraft onboard electrical equipment, including operating voltage and operating current;

[0037] The preliminary design schemes for the negative line panels of the entire aircraft were compiled and summarized, and the installation areas and positions of the negative line panels were located in the 3D model of the aircraft. The preliminary design schemes for the negative line panels include layout, etc. Figure 2 As shown, it includes zero potential reference point 1, zero potential reference point 2, negative line plate 1, negative line plate 2, negative line plate 3, and electrical circuit.

[0038] Based on the installation area and location of the negative line board, the high-current electrical equipment and critical flight equipment of the aircraft are screened out, and their installation areas and locations are located in the three-dimensional model of the aircraft. Then, the installation areas and locations of the negative line boards corresponding to the high-current electrical equipment and critical flight equipment are located.

[0039] Step S200, as follows Figure 3 The aircraft is divided into multiple compartments, including the radar compartment, forward equipment compartment, wing surface compartment, and tail boom compartment.

[0040] The compartment containing high-current electrical equipment is defined as the area to be evaluated for the reference potential of the aircraft's electrical circuit, and the fault electrical characteristics of the area to be evaluated are obtained.

[0041] The fault characteristics of high-current electrical equipment include fault voltage and fault current.

[0042] Step S300: Inject the normal operating current of the airborne electrical equipment into all negative line boards, select an area to be evaluated, collect the various fault currents generated by the operation of the negative line boards, and determine whether the difference between the maximum fault current and the normal operating current is less than the set value. If so, proportionally increase the normal operating current of each negative line board in the area to be evaluated.

[0043] Preferably, determining whether the difference between the maximum fault current and the normal operating current is less than a set value is as follows:

[0044] Based on the selected area to be evaluated, calculate the total normal operating current T of the area to be evaluated, and extract the maximum fault current I of a single electrical device in the area to be evaluated. max And the normal operating current M of the corresponding equipment, and inject the maximum fault current I into the negative line board of the corresponding equipment. max If I max If M is less than T / 2, the injection current of each negative line in the area to be evaluated is increased proportionally until the total injection current in the area to be evaluated is not less than 1.5*T.

[0045] Step S400: Determine the current value to be injected at each zero potential reference point, perform full-aircraft reference potential distribution simulation and calculation on the aircraft electrical circuit and negative line board, and obtain the reference potential data results for each negative line board of the entire aircraft.

[0046] Preferably, the current value to be injected at each zero-potential reference point is determined as follows:

[0047] A reverse current equal to the total current injected into the entire aircraft is injected at the zero-potential reference point. For multiple zero-potential reference points, the current value to be injected at each zero-potential reference point is determined based on the power supply source of the airborne equipment.

[0048] Preferably, general-purpose electromagnetic simulation software or system-level electrical simulation software is used to simulate and calculate the reference potential distribution of the entire machine.

[0049] Step S500: Set the potential limit value. Adjust the negative line plate according to the reference potential data result and the potential limit value to obtain the adjusted reference potential to be evaluated area. Determine whether the adjusted reference potential to be evaluated area is not less than the potential limit value. If so, optimize the structure of the negative line plate and repeat the adjustment of the negative line plate until the potential limit value requirement is met, and obtain the evaluated area.

[0050] Preferably, the negative line plate is adjusted based on the reference potential data and the potential limit, as follows:

[0051] Based on the overall reference potential distribution cloud map, the reference potential within the radius limit R around the equipment installation area corresponding to this negative line board is determined to be less than the potential limit V. d The position distribution of the negative line plate was adjusted so that the reference potential was less than V. d The position was then recalculated and the full-machine reference potential distribution was simulated and calculated again until the adjusted reference potential of the negative line plate was less than the potential limit V. d The radius limit R is a value greater than 0 meters.

[0052] The radius limit R is a value greater than 0 meters, allowing different potential limit V for different airborne equipment. d .

[0053] Preferably, determining whether the adjusted reference potential region to be evaluated is not less than the potential limit is as follows:

[0054] The recorded reference potential results for each negative line plate of the entire machine, and the potential limit V. d For comparison, V d The value is greater than 0; if the reference potential result of the negative line plate is less than V d Then the normal power supply of the corresponding airborne equipment is risk-free, and the layout of the negative line board meets the requirements; if the reference potential data of the negative line board is greater than or equal to V d This would put the normal power supply of the corresponding airborne equipment at risk.

[0055] Preferably, the negative line plate is structurally optimized as follows:

[0056] Even after multiple adjustments to the position of the negative line plate, its reference potential remains no less than the potential limit value V. d If so, then the reference potential to be evaluated region is supplemented with additional metal structures and parallel paths are added; and supplementary metal structures are added to the electrical circuit simulation prototype.

[0057] Step S600: Obtain all evaluated areas that have been evaluated, and obtain the reference potential result of each negative board of the whole machine when there is a fault current under the fault current injection, until the reference potential result of each negative board of the whole machine in all evaluated areas under the fault current is less than the potential limit.

[0058] Finally, the layout of the aircraft negative line board was confirmed as the final design scheme.

[0059] In summary, this application has the following advantages:

[0060] By comprehensively considering the normal and fault power consumption characteristics of aircraft avionics, and visually displaying the weak points in the aircraft negative line board layout design in three dimensions through the reference potential distribution of the aircraft electrical circuits, the electrical characteristics of the aircraft electrical circuits and negative line board layout can be quickly evaluated and iteratively optimized, thereby improving the efficiency and accuracy of the aircraft electrical circuits and negative line board layout design and reducing the power consumption risks of aircraft avionics.

[0061] The following is an example to illustrate this:

[0062] 1. Construct a full-fledged electrical circuit simulation prototype for the aircraft. Figure 2 The electrical circuit of the right wing of the aircraft is shown by the dashed line in the figure;

[0063] 2. Compile and summarize the normal electrical characteristics of the aircraft's airborne electrical equipment, including operating voltage and operating current. The operating voltages of wing surface equipment D, B, and C are 28V, 270V, and 28V, respectively, and the corresponding operating currents are 95A, 200A, and 5A, respectively. Equipment C is located on the trailing edge of the wing surface.

[0064] 3. Compile and summarize the preliminary design schemes for the negative line plates of the entire aircraft, and locate the installation area and position of the negative line plates in the 3D model of the aircraft. Figure 2 The right wing surface of the aircraft is equipped with negative line plate 1 and negative line plate 2;

[0065] 4. Based on the data from step 2, identify the high-current electrical equipment and critical flight equipment of the aircraft, and locate their installation areas and positions in the three-dimensional model of the aircraft. Equipment D and equipment B are high-current electrical equipment, and equipment C on the trailing edge of the wing surface is critical flight safety equipment.

[0066] 5. Based on the data from steps 3 and 4, locate the installation areas and positions of the negative line boards corresponding to high-current electrical equipment and critical flight equipment in the three-dimensional model of the aircraft, where equipment D corresponds to negative line board 1, and equipment B and equipment C correspond to negative line board 2.

[0067] 6. Statistically summarize the fault power characteristics of the high current electrical equipment in step 4, including fault voltage and fault current. The fault voltages of equipment D and B are 28V and 270V, respectively, and the fault currents are 300A and 400A, respectively.

[0068] 7. For example Figure 3 The aircraft is divided into multiple sections. The section containing high-current electrical equipment is defined as the area to be evaluated for the reference potential of the aircraft electrical circuit. In this case, the wing deck contains high-current electrical equipment D and equipment B. The wing deck is the area to be evaluated for the reference potential of the aircraft electrical circuit.

[0069] 8. Based on the results of steps 2 and 5, inject the normal operating current of the airborne electrical equipment into all negative line boards. The current injected into negative line board 1 is 95A, and the current injected into negative line board 2 is 200A + 5A = 205A. The total normal operating current of the wing deck is T = 95A + 205A = 300A. The maximum fault current I of a single electrical device in the wing deck is... max The fault current of device B is 400A, I max =400A, the normal operating current of equipment B is M=200A, and the maximum fault current I is injected into the negative line plate 2 of the wing surface compartment. max =400A, I max -M=200A is greater than T / 2=150A, the injected current of negative line plate 1 is 95A, and the injected current of negative line plate 2 is 400A+5A=405A.

[0070] 9. Inject a reverse current at the aircraft's zero-potential reference point, equal to the total current injected into the entire aircraft. Figure 2 The zero potential reference point for 28V electrical equipment is zero potential reference point 1, and the injected current is the total reverse current corresponding to equipment D and equipment C, which is -95A-5A=-100A. The zero potential reference point for 270V electrical equipment is zero potential reference point 2, and the injected current is the reverse current corresponding to equipment B, which is -400A.

[0071] 10. Perform full-aircraft reference potential distribution simulation and calculation on the aircraft electrical circuit and negative line board, and obtain the reference potential data of each negative line board in the whole aircraft. The reference potential of negative line board 1 relative to zero potential reference point 1 is 1.6V, the reference potential of negative line board 2 relative to zero potential reference point 2 is 3.8V, and the reference potential of negative line board 2 relative to zero potential reference point 1 is 2.5V.

[0072] 11. Compare the reference potential data of each negative line plate of the wing surface recorded in step 10, and the potential limit value V of the 270V electrical equipment. d1 The voltage limit V is set for 10V and 28V electrical equipment. d2 The voltage is set to 2V. The corresponding operating voltages for wing surface devices D, B, and C are 28V, 270V, and 28V, respectively. According to the data from step 10, the reference potential of wing surface device D is 1.6V, which is less than the potential limit V of the 28V electrical equipment. d2 =2V, the reference potential of wing-shaped device B is 3.8V, which is less than the potential limit V of the electrical equipment (270V). d1 =10V, the reference potential of the wing-shaped device C is 2.5V, which is greater than the potential limit V of the electrical equipment. d2=2V, then there is no risk in the power supply of devices D and B, but there is a risk in the power supply of device C. For device C, it is recommended that the negative line plate connected to device C be adjusted to negative line plate 3 on the wing surface closer to the fuselage, with a radius limit R set to 2 meters. The distance between negative line plate 3 and device C should be 1.5 meters, which is less than the radius limit R = 2 meters. The placement of negative line plate 3 meets the requirements. After re-simulation evaluation, the reference potential of negative line plate 3 relative to the zero potential reference point 1 is 1.8V, which is less than the potential limit V for 28V electrical equipment. d2 =2V, the arrangement of negative line board 3 meets the requirements;

[0073] 13. Confirm the layout of the aircraft negative line board as the final design scheme. Figure 2 The device D in the wing deck shown is connected to the negative line plate 1, with a corresponding reference potential of 1.6V; the device B is connected to the negative line plate 2, with a corresponding reference potential of 3.8V; and the device C is connected to the negative line plate 3, with a corresponding reference potential of 1.8V.

[0074] Finally, it should be noted that the accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0075] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for designing the layout of an aircraft negative line board based on the fault current of airborne equipment, characterized in that, include: Obtain the wiring data of the entire aircraft, construct an electrical circuit simulation prototype, and locate the installation area and position of the negative line board corresponding to high current electrical equipment and critical flight equipment; The entire aircraft is divided into multiple sections. The section containing high-current electrical equipment is defined as the area to be evaluated for the reference potential of the aircraft's electrical circuit, and the fault electrical characteristics of the area to be evaluated are obtained. Inject the normal operating current of the airborne electrical equipment into all negative line boards. Select an area to be evaluated, collect the various fault currents generated by the operation of the negative line boards, and determine whether the difference between the maximum fault current and the normal operating current is less than the set value. If so, proportionally increase the normal operating current of each negative line board in the area to be evaluated. Determine the current value that needs to be injected at each zero potential reference point, perform full-aircraft reference potential distribution simulation and calculation on the aircraft electrical circuit and negative line board, and obtain the reference potential data results for each negative line board of the entire aircraft; Set the potential limit, adjust the negative line plate according to the reference potential data and the potential limit, and obtain the adjusted reference potential to be evaluated area. Determine whether the adjusted reference potential to be evaluated area is not less than the potential limit. If so, optimize the structure of the negative line plate and repeat the adjustment of the negative line plate until the potential limit requirement is met, and obtain the evaluated area. Obtain all evaluated areas and the reference potential of each negative board in the whole machine when there is a fault current under fault current injection, until the reference potential of each negative board in all evaluated areas is less than the potential limit.

2. The aircraft negative line board layout design method based on airborne equipment fault current as described in claim 1, characterized in that, To determine whether the difference between the maximum fault current and the normal operating current is less than a set value: Based on the selected area to be evaluated, calculate the total normal operating current T of the area to be evaluated, and extract the maximum fault current I of a single electrical device in the area to be evaluated. max And the normal operating current M of the corresponding equipment, and inject the maximum fault current I into the negative line board of the corresponding equipment. max If I max If M is less than T / 2, the injection current of each negative line in the area to be evaluated is increased proportionally until the total injection current in the area to be evaluated is not less than 1.5*T.

3. The aircraft negative line board layout design method based on airborne equipment fault current as described in claim 1, characterized in that, The required current value to be injected at each zero-potential reference point is determined as follows: A reverse current equal to the total current injected into the entire aircraft is injected at the zero-potential reference point. For multiple zero-potential reference points, the current value to be injected at each zero-potential reference point is determined based on the power supply source of the airborne equipment.

4. The aircraft negative line board layout design method based on airborne equipment fault current as described in claim 1, characterized in that, To determine whether the adjusted reference potential in the region to be evaluated is not less than the potential limit, the following steps are taken: The recorded reference potential results for each negative line plate of the entire machine, and the potential limit V. d For comparison, V d The value is greater than 0; if the reference potential result of the negative line plate is less than V d Then the normal power supply of the corresponding airborne equipment is risk-free, and the layout of the negative line board meets the requirements; if the reference potential data of the negative line board is greater than or equal to V d This would put the normal power supply of the corresponding airborne equipment at risk.

5. The aircraft negative line board layout design method based on airborne equipment fault current as described in claim 4, characterized in that, The negative line plate is adjusted based on the reference potential data and potential limits as follows: Based on the overall reference potential distribution cloud map, the reference potential within the radius limit R around the equipment installation area corresponding to this negative line board is determined to be less than the potential limit V. d The position distribution of the negative line plate was adjusted so that the reference potential was less than V. d The position was then recalculated and the full-machine reference potential distribution was simulated and calculated again until the adjusted reference potential of the negative line plate was less than the potential limit V. d The radius limit R is a value greater than 0 meters.

6. The aircraft negative line board layout design method based on airborne equipment fault current as described in claim 4, characterized in that, The negative line board is structurally optimized as follows: Even after multiple adjustments to the position of the negative line plate, its reference potential remains no less than the potential limit value V. d If so, then the reference potential to be evaluated region is supplemented with additional metal structures and parallel paths are added; and supplementary metal structures are added to the electrical circuit simulation prototype.

7. The aircraft negative line board layout design method based on airborne equipment fault current as described in claim 1, characterized in that, The installation areas and locations of the negative line boards for high-current electrical equipment and critical flight equipment are as follows: Compile and summarize the normal electrical characteristics of aircraft onboard electrical equipment, including operating voltage and operating current; The preliminary design schemes of the negative line plates for the entire aircraft were compiled and summarized, and the installation area and position of the negative line plates were located in the three-dimensional model of the aircraft. Based on the installation area and location of the negative line board, the high-current electrical equipment and critical flight equipment of the aircraft are screened out, and their installation areas and locations are located in the three-dimensional model of the aircraft. Then, the installation areas and locations of the negative line boards corresponding to the high-current electrical equipment and critical flight equipment are located.

8. The aircraft negative line board layout design method based on airborne equipment fault current as described in claim 1, characterized in that, The fault power characteristics of the high-current electrical equipment include fault voltage and fault current.

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