CN112464361A - Lightning partition dividing method - Google Patents
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- CN112464361A CN112464361A CN202011227871.9A CN202011227871A CN112464361A CN 112464361 A CN112464361 A CN 112464361A CN 202011227871 A CN202011227871 A CN 202011227871A CN 112464361 A CN112464361 A CN 112464361A
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000005192 partition Methods 0.000 title claims abstract description 19
- 238000009826 distribution Methods 0.000 claims abstract description 36
- 238000004088 simulation Methods 0.000 claims abstract description 18
- 238000004458 analytical method Methods 0.000 claims abstract description 7
- 238000005096 rolling process Methods 0.000 claims description 5
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 239000010949 copper Substances 0.000 claims description 3
- 230000006698 induction Effects 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 238000013316 zoning Methods 0.000 claims description 2
- 208000025274 Lightning injury Diseases 0.000 description 8
- 238000004364 calculation method Methods 0.000 description 4
- 238000005094 computer simulation Methods 0.000 description 2
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Abstract
本发明提供一种雷电分区1区(包含1A区和1B区)划分的新方法，所述方法包括：构建飞机和放电云层模型，以俯仰角、偏航角和滚转角都为零度作为基准仿真模型；结合SAE‑ARP‑5414A标准分区理论，经过反复仿真分析得出：基于电荷分布的1区划分由飞机表面感应最大电荷密度的35％左右为阈值，超过这一阈值的区域即被确定为雷电分区1区；分别在不同的俯仰角、偏航角和滚转角下，获取不同角度下飞机表面电荷分布情况；根据所述不同角度下飞机表面电荷分布情况，统计得到飞机各区域1区的雷电划分情况。
The present invention provides a new method for dividing lightning zone 1 (including 1A and 1B), the method includes: constructing a model of an aircraft and a discharge cloud layer, and using the pitch angle, yaw angle and roll angle are all zero degrees as a benchmark for simulation Model; combined with the SAE‑ARP‑5414A standard partition theory, after repeated simulation analysis, it is concluded that the division 1 based on the charge distribution is about 35% of the maximum charge density induced on the surface of the aircraft as the threshold, and the area exceeding this threshold is determined as Lightning division 1 area; under different pitch angles, yaw angles and roll angles, respectively, obtain the distribution of the surface charge of the aircraft at different angles; Lightning division.
Description
Technical Field
The invention belongs to the technical field of aviation, and relates to a lightning partition dividing method.
Background
Lightning protection is an important content of modern airplane design, and the division of the airplane into lightning strike areas is the basis for airplane lightning protection design. After the lightning strike areas are divided, lightning protection design can be carried out on different lightning strike areas and equipment in the areas according to the distribution of the different lightning strike areas.
At present, the lightning stroke area division of the airplane is mainly determined by a lightning stroke area division test of an airplane equal ratio or scaling model. The plane lightning area division test needs to manufacture plane geometric or scaling metal models, formulate a test scheme, finally need professional test sites and equipment, and has the disadvantages of complex whole test process, long time consumption and more capital consumption.
Disclosure of Invention
The invention overcomes the defects of long time consumption and high cost of the existing airplane lightning stroke area division test, and provides a simulation calculation method for obtaining the airplane lightning stroke area division through software simulation.
The invention provides a lightning zoning method, which comprises the following steps:
constructing an airplane and a discharge cloud layer model, and taking a pitch angle, a yaw angle and a roll angle which are all zero as reference simulation models;
combining SAE-ARP-5414A standard partition theory, the method is obtained through repeated simulation analysis: on the basis of the 1-zone division of the charge distribution, about 35% of the maximum charge density induced by the surface of the airplane is taken as a threshold value, and the area exceeding the threshold value is determined as a lightning zone 1 zone;
respectively acquiring the surface charge distribution conditions of the airplane at different angles under different pitch angles, yaw angles and roll angles;
and counting to obtain the thunder and lightning division conditions of each region of the airplane according to the distribution conditions of the surface charges of the airplane at different angles.
Specifically, the constructing of the aircraft and the discharge cloud layer model specifically includes:
the nearest distance between the cloud layer and the airplane in the airplane and the discharge cloud layer model is 60m, and the voltage between the cloud layers is set to be 150 ten thousand volts.
Specifically, the aircraft and the discharge cloud model in the discharge cloud model are two copper plates with the potential difference of 150 ten thousand volts, and the aircraft model is an aluminum model.
Specifically, the acquiring the surface charge distribution of the aircraft at different angles under different pitch angles, yaw angles and roll angles includes:
and acquiring the surface charge distribution conditions of the airplane at different angles by using Ansys Q3D software under different pitch angles, yaw angles and roll angles.
Specifically, according to the distribution situation of the surface charges of the airplane at different angles, the lightning division situation of each area of the airplane is obtained through statistics, and the method specifically comprises the following steps:
comparing SAE-ARP-5414A standard partition theory, about 35% of the maximum charge density of the airplane surface induction is a threshold value, and an area exceeding the threshold value is determined as a lightning partition 1 area;
and obtaining the lightning division conditions of the 1A areas of all parts of the airplane in the typical posture.
Specifically, respectively under different pitch angle, yaw angle and roll angle, acquire aircraft surface charge distribution under the different angles, specifically include:
changing the rolling angle of the airplane, and simulating to obtain the surface charge distribution conditions of the wingtips and the horizontal tails.
Specifically, respectively under different pitch angle, yaw angle and roll angle, acquire aircraft surface charge distribution under the different angles, specifically include:
and changing the rolling angle of the airplane, and simulating to obtain the surface charge distribution condition of the vertical tail.
Specifically, respectively under different pitch angle, yaw angle and roll angle, acquire aircraft surface charge distribution under the different angles, specifically include:
changing the pitching angle of the airplane, and simulating to obtain the surface charge distribution conditions of the nose and the tail.
In conclusion, the invention provides an effective method for obtaining simulation analysis of the airplane lightning partition 1 (including the 1A partition and the 1B partition) through software simulation calculation, compared with a lightning partition test, the method has the advantages of obvious advantages, high speed, low cost and low manpower consumption, the airplane lightning partition 1 is quickly divided through software, the airplane lightning protection capability can be pre-evaluated in a scheme stage in advance, the lightning protection design is carried out on the whole airplane according to the lightning partition result, and the problems of blind design and design lag caused by long test period of the lightning partition after the design are solved.
Drawings
FIG. 1 is a simulation model reference frame provided herein;
FIG. 2 is a Q3D simulation benchmark engineering model provided by the present application;
FIG. 3 is an aircraft wing tip charge distribution provided herein.
Detailed Description
The Ansys Q3D software can give the distribution of the induced charge on the surface of the airframe shortly before lightning strikes the aircraft using a quasi-static method. The lightning voltage is different from several million volts to several hundred million volts, the voltage between layers of clouds in simulation changes, the charge distribution on the surface of the airplane also changes, but under different conditions, the charge distribution trend is the same, the initial lightning strike attachment area is determined by referring to the definition of the initial lightning strike attachment area in SAE-ARP-5414A and combining the induced charge distribution condition, and then the area 1 of each lightning strike area is divided.
The major implementation steps of lightning stroke area division by using Ansys Q3D software comprise: repairing an airplane model (the original structure model of the airplane does not meet the electrical continuity requirement of simulation software), establishing a simulation model (constructing a physical model simulating the airplane and a discharge cloud layer), calculating and dividing a lightning stroke region (obtaining the induced charge distribution of each part of the airplane by a quasi-static calculation method, and determining the position which exceeds the maximum value of the induced charge density by 35 percent as an initial lightning adhesion 1 region).
The method comprises three main contents of simulation modeling, threshold value calibration, simulation setting and calculation analysis for the division of the airplane lightning region 1 through software.
a) Simulation modeling
Constructing a physical model for simulating the airplane and the discharge cloud layer, wherein the shortest distance between the cloud layer and the airplane in the model is 60m, and the minimum distance meets the requirements specified in SAE ARP 5416: the test should simulate a discharge that is 50m away from the nearest aircraft surface. The inter-cloud voltage was set to 150 kilovolts.
Two copper plates with the potential difference of 150 ten thousand volts are used for simulating the charged cloud layer in the model, the material of the airplane model is aluminum, and three angles for determining the airplane attitude in a three-dimensional rectangular coordinate system are as follows: pitch angle, yaw angle, and roll angle. The attitude coordinate system of the pitch angle, the yaw angle and the roll angle of the plane in the simulation is shown in figure 1.
b) Threshold calibration
Combining SAE-ARP-5414A standard partition theory, the method is obtained through repeated simulation analysis: the 1-zone division based on the charge distribution is characterized in that about 35% of the maximum charge density induced by the aircraft surface is used as a threshold value, and the area exceeding the threshold value is determined as a lightning zone 1 zone.
c) Simulation setup
In the simulation, one of the pitch angle, the yaw angle and the roll angle is changed respectively and is changed once every 30 degrees (due to the symmetry of the model, the range of pitch angle to be discussed is [ -90,90] degrees, the range of yaw angle to be discussed is [ -90,90] degrees, and the range of roll angle to be discussed is [ -90,90] degrees. A Q3D simulated reference engineering model with zero pitch, yaw and roll angles is shown in fig. 2.
d) Computational analysis
And analyzing the surface charge distribution condition of the airplane at different angles. The change of the rolling angle of the airplane mainly influences the size of lightning stroke zones of a wingtip, a horizontal tail and a vertical tail. When the roll angle is 90 degrees (same as minus 90 degrees), the region of the droop 1A reaches a maximum. When the roll angle is 0 degrees, namely the wingspan direction of the airplane is opposite to the charged cloud layer, the area 1A of the wingtip reaches the maximum. The change of the pitching angle of the airplane mainly influences the size of the lightning stroke subareas of the nose and the tail of the airplane. When the pitch angle is 0 degree, the area of the machine head 1A and the area of the machine tail 1B reach the maximum value. The airfoil tip charge distribution is shown in figure 3.
Claims (8)
1. A lightning zoning method, comprising:
constructing an airplane and a discharge cloud layer model, and taking a pitch angle, a yaw angle and a roll angle which are all zero as reference simulation models;
combining SAE-ARP-5414A standard partition theory, the method is obtained through repeated simulation analysis: on the basis of the 1-zone division of the charge distribution, about 35% of the maximum charge density induced by the surface of the airplane is taken as a threshold value, and the area exceeding the threshold value is determined as a lightning zone 1 zone;
respectively acquiring the surface charge distribution conditions of the airplane at different angles under different pitch angles, yaw angles and roll angles;
and according to the distribution conditions of the surface charges of the airplane at different angles, counting to obtain the partition conditions of the lightning subareas 1 of all the areas of the airplane.
2. The method according to claim 1, wherein the constructing the aircraft and the discharge cloud model specifically comprises:
the nearest distance between the cloud layer and the airplane in the airplane and the discharge cloud layer model is 60m, and the voltage between the cloud layers is set to be 150 ten thousand volts.
3. The method of claim 1, wherein the model of the aircraft and the model of the discharge cloud are two copper plates with a potential difference of 150 ten thousand volts, and the model of the aircraft is a model of aluminum material.
4. The method as claimed in claim 1, wherein the obtaining the surface charge distribution of the aircraft at different angles at different pitch angles, yaw angles and roll angles respectively comprises:
and acquiring the surface charge distribution conditions of the airplane at different angles by using Ansys Q3D extra software under different pitch angles, yaw angles and roll angles.
5. The method according to claim 1, wherein the statistical obtaining of the lightning division conditions of each region of the aircraft according to the distribution conditions of the surface charges of the aircraft at the different angles specifically comprises:
through repeated simulation analysis and referring to SAE-ARP-5414A standard partition theory, about 35% of the maximum charge density of the airplane surface induction is taken as a threshold, and an area exceeding the threshold is determined as a lightning partition 1 area;
and counting to obtain the lightning division conditions of the 1A area of each part of the airplane in the typical attitude.
6. The method of claim 1, wherein obtaining the surface charge distribution of the aircraft at different angles at different pitch angles, yaw angles and roll angles respectively comprises:
changing the rolling angle of the airplane, and simulating to obtain the surface charge distribution conditions of the wingtips and the horizontal tails.
7. The method of claim 1, wherein obtaining the surface charge distribution of the aircraft at different angles at different pitch angles, yaw angles and roll angles respectively comprises:
and changing the rolling angle of the airplane, and simulating to obtain the surface charge distribution condition of the vertical tail.
8. The method of claim 1, wherein obtaining the surface charge distribution of the aircraft at different angles at different pitch angles, yaw angles and roll angles respectively comprises:
changing the pitching angle of the airplane, and simulating to obtain the surface charge distribution conditions of the nose and the tail.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011227871.9A CN112464361A (en) | 2020-11-05 | 2020-11-05 | Lightning partition dividing method |
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| CN202011227871.9A CN112464361A (en) | 2020-11-05 | 2020-11-05 | Lightning partition dividing method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114186454A (en) * | 2021-11-30 | 2022-03-15 | 南京航空航天大学 | A lightning strike division method for helicopters |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102799112A (en) * | 2012-07-30 | 2012-11-28 | 上海无线电设备研究所 | Method for determining aircraft lightning stroke attachment point position |
| FR3073334A1 (en) * | 2017-11-09 | 2019-05-10 | Airbus Sas | ANTI-LIGHTNING DEVICE FOR AN AIRCRAFT AND AN AIRCRAFT COMPRISING SUCH AN ANTI-LIGHTNING DEVICE |
| CN110481805A (en) * | 2019-07-31 | 2019-11-22 | 南京航空航天大学 | A kind of aircraft avoids lightning stroke method |
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- 2020-11-05 CN CN202011227871.9A patent/CN112464361A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102799112A (en) * | 2012-07-30 | 2012-11-28 | 上海无线电设备研究所 | Method for determining aircraft lightning stroke attachment point position |
| FR3073334A1 (en) * | 2017-11-09 | 2019-05-10 | Airbus Sas | ANTI-LIGHTNING DEVICE FOR AN AIRCRAFT AND AN AIRCRAFT COMPRISING SUCH AN ANTI-LIGHTNING DEVICE |
| CN110481805A (en) * | 2019-07-31 | 2019-11-22 | 南京航空航天大学 | A kind of aircraft avoids lightning stroke method |
Non-Patent Citations (3)
| Title |
|---|
| 杨春光: "直升机雷电防护关键技术研究", 中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑, no. 05, pages 031 - 35 * |
| 王恒等: "基于电荷累积效应的飞机雷击分区快速仿真研究", 微波学报, vol. 30, no. 1, pages 80 - 83 * |
| 高成等: "飞机雷击附着区域的划分仿真研究", 电波科学学报, vol. 27, no. 6, pages 1238 - 1243 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114186454A (en) * | 2021-11-30 | 2022-03-15 | 南京航空航天大学 | A lightning strike division method for helicopters |
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Application publication date: 20210309 |