CN109159917A - A kind of aircraft thunder and lightning partition experiment device of electric field fidelity - Google Patents
A kind of aircraft thunder and lightning partition experiment device of electric field fidelity Download PDFInfo
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- CN109159917A CN109159917A CN201810960190.XA CN201810960190A CN109159917A CN 109159917 A CN109159917 A CN 109159917A CN 201810960190 A CN201810960190 A CN 201810960190A CN 109159917 A CN109159917 A CN 109159917A
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- support rod
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Aviation & Aerospace Engineering (AREA)
- Elimination Of Static Electricity (AREA)
Abstract
The present invention discloses a kind of aircraft thunder and lightning partition experiment device of electric field fidelity, it is one ground connection plate of setting, it is respectively arranged with symmetrical tooling in the two sides of ground connection plate, symmetrical tooling includes: frame plate, main support rod, insulation drawstring, Ifold flange disk, firm support rod, the first support connector, the second support connector and third support connector.Present invention design is simple and direct rationally, and installation and removal are convenient, and stability is good with safety, meets the test requirements document of the aircraft thunder and lightning partition experiment of electric field fidelity.
Description
Technical field
The present invention relates to a kind of high-voltage test devices, especially in the aircraft thunder and lightning partition experiment dress of electric field fidelity
Support fixed dummy vehicle, the high-voltage test device used when being adjusted to attitude of flight vehicle.
Background technique
It is average that about 8,000,000 thunders and lightnings occur daily in earth atmosphere, there is statistical data to show a frame scheduled airline
Business aircraft will be once struck by lightning every year on average, and fighter plane is average in its life cycle to be struck by lightning twice.The civilian boat in China
Empty office's statistics shows aircraft year lightning strike accident about 50 on present China course line, and aircraft accident resulting from happens occasionally,
Some are even catastrophic.Especially modern Advanced Aircraft largely uses modern electronic technology to promote aeroplane performance,
Such as computer flight control system, communication and navigation system, while also largely using advanced composite material, such as carbon fibre composite
Deng, but regrettably, these advanced electronic technology and material technology are more sensitive to thunder and lightning, and loss is bigger, therefore, by atmosphere
Thunder and lightning environment minimizes to the influence of flight safety bring, is always the target that people lay siege to.For flight safety,
In related air worthiness regulation, strict demand is proposed to the lightning protection performance of aircraft, ensures aircraft in thunder and lightning environment with this
Safety.Researcher has carried out thunder and lightning subregion to aircraft surface according to the estimated component of thunder and lightning and the severity of influence,
The aircraft thunder and lightning partition experiment of electric field fidelity is very necessary.
According to SAE-ARP5414 standard, the aircraft thunder and lightning partition experiment of electric field fidelity needs to simulate aircraft yaw, bows
It faces upward, three kinds of flight attitudes of rolling, on the basis of aircraft scale model initial state, changes three kinds of aircraft with 30 ° for increment and fly
Row posture.In the aircraft thunder and lightning partition experiment of electric field fidelity, need for model aircraft to be mounted on insulating support.It is existing exhausted
Edge rack bearing weight is low, stability is poor, can not achieve yaw, pitching, roll attitude are quickly converted, while in supporting structure
There is metal structure more, the accuracy of test result can be had an impact and then influenced on the electric field on thunder and lightning partition experiment, it can not
According to the aircraft thunder and lightning partition experiment of SAEARP standard implementation electric field fidelity.
Summary of the invention
Place, the aircraft thunder and lightning partition experiment for providing a kind of electric field fidelity fill the present invention in order to overcome the deficiencies of the prior art
It sets, to can solve, existing insulating support metal structure excessively influences test result accuracy and to can not achieve model aircraft inclined
Boat, pitching, the problem of being quickly converted of roll attitude, to improve test accuracy and validity.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of the characteristics of aircraft thunder and lightning partition experiment device of electric field fidelity of the present invention, is:
One ground connection plate of setting is respectively arranged with symmetrical tooling, the symmetrical tooling packet in the two sides of the ground connection plate
It includes: frame plate, main support rod, insulation drawstring, Ifold flange disk, firm support rod, the first support connector, the second support connector
Connector is supported with third；
The frame plate is supported by insulator pillar and is fixed on pedestal；Middle position in the frame plate upper surface is set
It is equipped with the main support rod, the end of the main support rod is equipped with multiple screw holes, the second support connector and third support
The upper and lower part of connector is also equipped with multiple screw holes, and any screw hole of the main support rod end passes through bolt and described the
Two support connectors are connected with any screw hole on third support connector, to form the main support rod in the frame plate
On fixed structure and the main support rod stretch out the frame plate length and the main support rod height on the frame plate
Adjustment structure；
The firm support rod is symmetrically arranged in the two sides of the main support rod, and the firm support rod passes through described the
One support connector is connected on the frame plate, and the firm support rod is connect simultaneously by bolt with the first support connector
Self-view is adjusted, to form the main support rod auxiliary support structure；
The main support rod converges with support rod front end is stablized, and is connect by bolt with one end of Ifold flange disk；
It is clamped with a connecting rod between the Ifold flange disk of the ground connection symmetrical tooling in plate two sides, is passed through in the middle part of the connecting rod
Bolt is equipped with the dummy vehicle of angle adjustable；
One end of the insulation drawstring is fixed on the frame plate edge of the main support rod end, and the other end connects described group
Flange disk interts a screw rod on third support connector top, and the insulation drawstring is supported by the third and connected
The screw rod on part top, which is formed, pulls angle.
Compared with the existing technology, the beneficial effects of the present invention are embodied in:
1, the experimental rig designed by the present invention realizes thunder and lightning environment dummy vehicle thunder and lightning as defined in SAE ARP standard
Partition experiment, dummy vehicle can fast implement yaw, pitching, the conversion of three kinds of postures of rolling, meet SAEARP standard
Defined test requirements document；Relative to the aircraft thunder and lightning partition experiment device more than traditional hardware, test of the invention
As a result more accurate.
2, the present invention uses two groups of symmetrical toolings, and dummy vehicle is placed between symmetrical tooling, and whole device carries energy
Power is strong, and dummy vehicle dimensional weight is not limited.
3, present invention design is simple and direct rationally, and installation and removal are convenient, and stabilized structure is low in cost, operates convenient for personnel, surely
It is qualitative good with safety, it is more humanized, meet the test requirements document of the aircraft thunder and lightning partition experiment of electric field fidelity.
Detailed description of the invention
Fig. 1 is aircraft thunder and lightning partition experiment apparatus structure schematic diagram of the present invention；
Fig. 2 is one of two groups of symmetrical toolings of the invention structural schematic diagram；
Appended drawing reference: 1 ground connection plate；2 pedestals；3 frame plates；4 main support rods；5 insulation drawstrings；6 Ifold flange disks；7 insulation
Sub- pillar；8 firm support rods；9 connecting rods；10 dummy vehicles；11 bar electrodes；A first supports connector；The support connection of b second
Part；C third supports connector.
Specific embodiment
In the present embodiment, as shown in Figure 1, a kind of aircraft thunder and lightning partition experiment device of electric field fidelity is one ground connection of setting
Plate 1 and two groups of symmetrical toolings are respectively arranged with one group of symmetrical tooling in the two sides of ground connection plate 1, which includes: frame
Plate 3, main support rod 4, insulation drawstring 5, Ifold flange disk 6, firm support rod 8, first support connector a, the second support connection
Part b and third support connector c；Wherein, frame plate 3, main support rod 4, stable support rod 8, first support connector a, second
Support connector b and third support connector c is epoxy material, and 3 thickness of frame plate is not less than 20mm.
Frame plate 3 is located on pedestal 2 and insulator pillar 7, and is supported and fixed by insulator pillar 7 on pedestal 2, bottom
Seat 2 is cast iron quality；
Main support rod 4 is placed in 3 upper surface of frame plate, firm support rod 8, first supports connector a, the second support connector b
Connector c is supported with third；Wherein, the first support connector a is an iron plate, the second support connector b and third support connection
Part c is made of two panels epoxy plate.Middle position in 3 upper surface of frame plate is provided with main support rod 4, the end of main support rod 4
End is equipped with multiple screw holes, and the second support connector b and third support the upper and lower part of connector c to be also equipped with multiple screw holes,
The gap across two panels epoxy plate of main support rod 4, and by bolt by any screw hole of end with second support connector b and
Any screw hole of the third support lower part connector c is connected, and forms fixed structure of the main support rod 4 on frame plate 3；
As shown in Fig. 2, the different screw holes of selection main support rod 4 and the second support connector b and third support the lower part connector c
Fixed, adjustable main support rod 4 stretches out 3 length of frame plate, that is, adjusts the horizontal position of main support rod 4；Select main support rod 4 not
It is fixed with screw hole and two support connector b and the third support top connector c, adjustable main support rod 4 is high on frame plate 3
Degree；
After main support rod horizontal position and height determine, firm support rod is symmetrically arranged in the two sides of main support rod 4
8, every firm support rod 8 is connected on frame plate 3 by the first support connector a, is consolidated support rod 8 and is passed through bolt and first
Connector a connection, the angle of the adjustable stable support rod 8 of rotating bolt are supportted, so that main support rod 4 be cooperated to play Auxiliary support work
With.
Main support rod 4 converges with 8 front end of support rod is stablized, and is connect by bolt with one end of Ifold flange disk 6；Combination
Ring flange 6 is phenolic resin material, thickness 20mm.Adjusting angle is applied in combination in ring flange one screw hole of every 30 ° of settings, two ring flanges
Degree, with bolt fixed pose after the completion of adjustment.
As shown in Figure 1, being clamped with a connecting rod 9, connecting rod 9 between the Ifold flange disk 6 of the ground connection symmetrical tooling in 1 two sides of plate
It also is epoxy material, the middle part of connecting rod 9 is equipped with dummy vehicle 10 by bolt, and dummy vehicle 10 is located at ground connection plate 1
Top and between two groups of symmetrical toolings passes through rotating bolt and adjusts adjustable 10 setting angle of dummy vehicle, i.e., initial machine
Head is directed toward, and rotation combination ring flange 6 is joined with bolts posture after reaching required angle to adjust attitude of flight vehicle.Tool
Body says,
When pitch attitude adjusts, it is connected and fixed 10 heading of dummy vehicle is vertical with connecting rod 9 as initial position,
Ifold flange disk 6 is rotated to required angle for stepping with 30 °, and Ifold flange disk 6 is joined with bolts state.
When yaw-position adjusts, Ifold flange disk 6 is joined with bolts state, 10 heading of dummy vehicle with
Connecting rod 9 is vertically connected to initial position, with angle measurement tool with 30 ° of connections between stepping rotating model and connecting rod 9
Screw rod is to required angle.
When roll attitude adjust, 10 heading of dummy vehicle and 9 horizontal connection of connecting rod are fixed and are used as initial position,
Ifold flange disk 6 is rotated to required angle for stepping with 30 °, and Ifold flange disk 6 is joined with bolts state.
One end of insulation drawstring 5 is fixed on 3 edge of frame plate of 4 end of main support rod, and the other end connects Ifold flange disk
6, intert a screw rod on the third support top connector c, insulation drawstring 5 supports the screw rod on the top connector c to be formed by third
Pull angle.Insulation drawstring 5 is nylon material, can load-bearing 500kg.
Claims (1)
1. a kind of aircraft thunder and lightning partition experiment device of electric field fidelity, it is characterised in that:
One ground connection plate (1) of setting is respectively arranged with symmetrical tooling, the symmetrical tooling in the two sides of ground connection plate (1)
It include: frame plate (3), main support rod (4), insulation drawstring (5), Ifold flange disk (6), firm support rod (8), the first support connection
Part (a), the second support connector (b) and third support connector (c)；
The frame plate (3) is supported by insulator pillar (7) and is fixed on pedestal (2)；In the centre of the frame plate (3) upper surface
It is provided at position the main support rod (4), the end of the main support rod (4) is equipped with multiple screw holes, and second support connects
The upper and lower part of fitting (b) and third support connector (c) is also equipped with multiple screw holes, main support rod (4) end
Any screw hole is connected by bolt with any screw hole in second support connector (b) and third support connector (c),
The frame is stretched out to form fixed structure and the main support rod (4) of the main support rod (4) on the frame plate (3)
The adjustment structure of plate (3) length and the main support rod (4) height on the frame plate (3)；
It is symmetrically arranged with the firm support rod (8) in the two sides of the main support rod (4), the firm support rod (8) passes through
First support connector (a) is connected on the frame plate (3), and the firm support rod (8) passes through bolt and described first
Support connector (a) connects and adjusts self-view, to form the main support rod (4) auxiliary support structure；
The main support rod (4) is converged with support rod (8) front end is stablized, and is connected by one end of bolt and Ifold flange disk (6)
It connects；
It is clamped with a connecting rod (9) between the Ifold flange disk (6) of the ground connection symmetrical tooling in plate (1) two sides, the connecting rod (9)
Middle part is equipped with the dummy vehicle (10) of angle adjustable by bolt；
One end of insulation drawstring (5) is fixed on frame plate (3) edge of the main support rod (4) end, other end connection
The Ifold flange disk (6) interts a screw rod on the third support top connector (c), and the insulation drawstring (5) passes through institute
The screw rod for stating third support top connector (c), which is formed, pulls angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810960190.XA CN109159917B (en) | 2018-08-22 | 2018-08-22 | A kind of aircraft thunder and lightning partition experiment device of electric field fidelity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810960190.XA CN109159917B (en) | 2018-08-22 | 2018-08-22 | A kind of aircraft thunder and lightning partition experiment device of electric field fidelity |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109159917A true CN109159917A (en) | 2019-01-08 |
| CN109159917B CN109159917B (en) | 2019-12-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810960190.XA Active CN109159917B (en) | 2018-08-22 | 2018-08-22 | A kind of aircraft thunder and lightning partition experiment device of electric field fidelity |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572828A (en) * | 2019-09-28 | 2021-03-30 | 苏州电器科学研究院股份有限公司 | Movable aircraft lightning test system |
| CN114229030A (en) * | 2022-02-26 | 2022-03-25 | 合肥航太电物理技术有限公司 | Protection design method for eliminating ignition source of lightning B area of oil tank |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202189067U (en) * | 2011-07-25 | 2012-04-11 | 中国西电电气股份有限公司 | Posture adjusting insulation bracket used for plane lightning partition shrinkage ratio model test |
| CN203037808U (en) * | 2013-01-16 | 2013-07-03 | 山东大学 | Artificial lightning stroke damage testing arrangement of carbon-fiber composite |
| US20150212136A1 (en) * | 2014-01-27 | 2015-07-30 | Mitsubishi Aircraft Corporation | Method for determining object of aircraft lightning protection adequacy test and method for verifying lightning protection adequacy |
-
2018
- 2018-08-22 CN CN201810960190.XA patent/CN109159917B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202189067U (en) * | 2011-07-25 | 2012-04-11 | 中国西电电气股份有限公司 | Posture adjusting insulation bracket used for plane lightning partition shrinkage ratio model test |
| CN203037808U (en) * | 2013-01-16 | 2013-07-03 | 山东大学 | Artificial lightning stroke damage testing arrangement of carbon-fiber composite |
| US20150212136A1 (en) * | 2014-01-27 | 2015-07-30 | Mitsubishi Aircraft Corporation | Method for determining object of aircraft lightning protection adequacy test and method for verifying lightning protection adequacy |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572828A (en) * | 2019-09-28 | 2021-03-30 | 苏州电器科学研究院股份有限公司 | Movable aircraft lightning test system |
| CN114229030A (en) * | 2022-02-26 | 2022-03-25 | 合肥航太电物理技术有限公司 | Protection design method for eliminating ignition source of lightning B area of oil tank |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109159917B (en) | 2019-12-03 |
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