CN203551699U - Device for plane scaling model lightning direct effect test - Google Patents
Device for plane scaling model lightning direct effect test Download PDFInfo
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- CN203551699U CN203551699U CN201320709284.2U CN201320709284U CN203551699U CN 203551699 U CN203551699 U CN 203551699U CN 201320709284 U CN201320709284 U CN 201320709284U CN 203551699 U CN203551699 U CN 203551699U
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Abstract
The utility model provides a device for a plane scaling model lightning direct effect test. The device comprises a connector, a yaw posture adjustment member, a pitching posture adjustment member, a rolling posture adjustment member, an insulation support member, a strengthening insulation support member, a grounding platform and an insulation box; the connector is arranged on the yaw posture adjustment member; the yaw posture adjustment member, the pitching posture adjustment member, and the rolling posture adjustment member are perpendicular to each other; and the three posture adjustment members can be adjusted to freely adjust a rotation angle of the connector. One end of the insulation support member is connected with the rolling posture adjustment member, and the other end of the insulation support member is connected with the grounding platform in an insulation manner; the grounding platform comprises one lifting grounding plane and one insulation box; and the insulation box is internally provided with a current transformer. One end of the strengthening insulation support member is connected with the rolling posture adjustment member, and the other end of the strengthening insulation support member is connected with the insulation support member. The device for the plane scaling model lightning direct effect test is simple and reasonable in design, convenient in assembly and disassembly, and good in stability, and satisfies the test conditions of the plane scaling model lightning direct effect test.
Description
[technical field]
The utility model relates to a kind of high-voltage test device, especially a kind of aircraft scale model thunder and lightning direct effect test device.
[background technology]
Along with the raising of expanding economy and people's living standard, aircraft becomes the vehicles of people's amusement and travel and travel for commercial purpose first-selection gradually.But in recent years, aircraft is happened occasionally by the event in being struck by lightning, it is said 10,000 li of every flights of aircraft just likely by thunderbolt once.After aircraft is struck by lightning, thunder and lightning produces powerful electric current, forms electromagnetic field, optical radiation, shock wave and electric arc.These phenomenons are the safety of serious threat aircraft all, brings serious consequence, so people require day by day to increase to the shocking preventing technology of aircraft.The technical standard that propose aircraft lightning protection properties today is in the world more and more stricter, especially to modern military aircraft.Aircraft for military struggle does not often have condition as aircarrier aircraft, calm change of flight height, route, and the lightning-arrest rain belt of detouring, so require higher to the shocking preventing technology of military aircraft.Expert and technician, when carrying out airplane design, have proposed lightning Protection Design and the lightning protection device of aircraft.In order to verify correctness and the validity of these lightning Protection Design and lightning protection device, carry out the test of aircraft scale model thunder and lightning direct effect and be very important.Meanwhile, the test of aircraft scale model thunder and lightning direct effect provides strong test basis for the lightning Protection Design of aircraft and the research and development of lightning protection device.
Aircraft is when being struck by lightning, often have two lightning strike spots at least, one for entering a little, one for going out a little, statistics for the in and out point of thunder and lightning attachment point is the important content of aircraft scale model thunder and lightning direct effect test, needs to measure the size of lightning current in the test of aircraft scale model thunder and lightning direct effect simultaneously.Aircraft, when high airflight, possesses three kinds of flight attitudes conventionally, is respectively driftage, pitching and rolling.Therefore in the test of aircraft scale model thunder and lightning direct effect, these three kinds of flight attitudes of simulated aircraft are tested and are very important respectively.When carrying out the test of aircraft scale model thunder and lightning direct effect, the original state of scale model of take is benchmark, be that crab angle, the angle of pitch and roll angle are all 0 °, in 0 ° to 180 ° of crab angles, every 30 °, getting an attitude tests, in 0 ° to 360 ° of the angles of pitch, every 30 °, get an attitude and test, in 0 ° to 180 ° of roll angle, every 30 °, get an attitude and test.When carrying out the test of aircraft scale model thunder and lightning direct effect, scale model fabricated section level by belly when yaw-position is installed on insulating support, existing insulating support is a vertical insulating cylinder without any processing, some is even a conducting metal bar, and is directly installed on ground.When insulating support is a metal conducting bar, thunder and lightning hits after aircraft scale model, and lightning current directly flows into the earth by metal conducting bar, and scale model going out of thunder and lightning attachment point when yaw-position a little cannot add up and lightning current cannot be measured.When insulating support is an insulating cylinder, because ground and insulating cylinder base are in same level, thunder and lightning hits after aircraft scale model, mounting points by scale model and insulating cylinder is along the creepage flashover of insulating cylinder, and then lightning current flows directly into the earth, scale model when yaw-position thunder and lightning attachment point go out a little to be just fixed on all the time the mounting points place of scale model and insulating cylinder, cannot a little add up and lightning current cannot be measured going out of scale model thunder and lightning attachment point.And because scale model will be realized in test the conversion of different angles under driftage, pitching and three kinds of attitudes of rolling, existing insulating support need to leave mounting points on a plurality of installation sites and scale model and need to have various ways and can realize three kinds of conversions under attitude different angles on scale model, but it is unpractical on aircraft scale model, leaving a plurality of installation sites and requiring mounting points on scale model various informative, and cannot reach.In sum, existing device cannot meet the test condition of aircraft scale model thunder and lightning direct effect test.
[utility model content]
The purpose of this utility model is to provide a kind of aircraft scale model thunder and lightning direct effect test device, to solve the problems of the technologies described above.
To achieve these goals, the utility model adopts following technical scheme:
An aircraft scale model thunder and lightning direct effect test device, comprises web member, yaw-position adjustment part, pitch attitude adjustment part, rolling attitude adjustment part, insulated support, reinforced insulation support member, ground connection platform and insulation booth; Described web member is for being fastenedly connected with aircraft scale model mounting points, and yaw-position adjustment part, pitch attitude adjustment part, rolling attitude adjustment part are vertical mutually, by adjusting three attitude adjustment parts, regulate arbitrarily the anglec of rotation of described web member; Described insulated support one end connects rolling attitude adjustment part, other end insulation connects ground connection platform, this ground connection platform comprises ground plane, is welded in the ground plane base of ground plane bottom, and be arranged on the insulation booth on ground plane base, in this insulation booth, be provided with current transformer, described ground plane base is provided with height adjusting part in order to the height of regulated ground plane, and the height of described ground plane is higher than insulating support base.
Described connecting piece material is steel, which is provided with threaded hole, and surfaces externally and internally is equipped with a layer insulating.
Described yaw-position adjustment part comprises the first insulating cylinder, and described the first insulating cylinder two ends embed respectively in the first cylindrical metal part, the second cylindrical metal part, are provided with one first transmission shaft in the first insulating cylinder; The first transmission shaft is fixedly connected with web member through one end of the first cylindrical metal part; The first transmission shaft stretches in the second cylindrical metal part; Described the first cylindrical metal part and the second cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with the first transmission shaft that is provided with.
Described pitch attitude adjustment part comprises the second insulating cylinder, and described the second insulating cylinder two ends embed respectively in the 3rd cylindrical metal part, the 4th cylindrical metal part, are provided with a second driving shaft in the second insulating cylinder; One end of second driving shaft is fixedly connected with the second cylindrical metal part through one end of the 3rd cylindrical metal part; Described second driving shaft is perpendicular to described the first transmission shaft; The other end of second driving shaft stretches in the 4th cylindrical metal part; Described the 3rd cylindrical metal part and the 4th cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with second driving shaft that is provided with.
Described rolling attitude adjustment part comprises the 3rd insulating cylinder, and described the 3rd insulating cylinder two ends embed respectively in the 5th cylindrical metal part, the 6th cylindrical metal part, are provided with one the 3rd transmission shaft in the 3rd insulating cylinder; One end of the 3rd transmission shaft is fixedly connected with the 4th cylindrical metal part through one end of the 5th cylindrical metal part; Described the 3rd transmission shaft is perpendicular to described the first transmission shaft and second driving shaft; The other end of the 3rd transmission shaft stretches in the 6th cylindrical metal part; Described the 5th cylindrical metal part and the 6th cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with the 3rd transmission shaft that is equipped with.
Described the second cylindrical metal part, the 4th cylindrical metal part and the 6th cylindrical metal part periphery are equipped with two threaded holes; Described aircraft scale model thunder and lightning direct effect test also comprises three web joints with holes with device, and centre is one or six side's screw holes, both sides; On described the first transmission shaft, second driving shaft and the 3rd transmission shaft, be equipped with one or six square thread holes; Six side's screws stretch into through six square thread holes of corresponding web joint with holes in six square thread holes of corresponding transmission shaft and the tired silk connection of six sides for corresponding transmission shaft; Bolt is threaded with corresponding web joint with holes through the threaded hole of corresponding circle tube shape metal piece periphery, and assurance transmission shaft and cylindrical metal part are fixed, and transmission shaft does not rotate.
Described insulated support is an insulating cylinder, and one end is fixedly connected with the 6th cylindrical metal part of rolling attitude adjustment part, and the other end is fixedly connected with insulating support base; Described reinforced insulation support member is an insulating cylinder, and one end is fixedly connected with the 3rd insulating cylinder of rolling attitude adjustment part, and the other end is fixedly connected with insulated support.
Described ground plane adopts stainless steel aluminium sheet to make, plating zinc on surface; Described ground plane chassis side is provided with ground stud; Described insulation booth outside surface is zinc-plated, and leader is installed on outside surface, and described handle is by bare copper wire or copper strips ground connection; One conductor one end connects ground stud, ground connection after the current transformer in other end connection insulation booth; Described conductor is enameled wire.
Described ground plane base comprises four supporting legs, and supporting leg bottom is provided with universal wheel, and universal wheel is that insulating material is made; Four height adjusting parts are installed on corresponding supporting leg; On a described supporting leg, right angle insulcrete is installed, described insulation booth is installed on this right angle insulcrete; Described insulating support base connects described ground connection platform by insulating bar.
The forced formation ballast box in rear portion of described insulating support base, for loading counterweight counterweight.
Compared with prior art, the utlity model has following beneficial effect: a kind of aircraft scale model of the utility model thunder and lightning direct effect test device, reasonable in design, its ground plane can pass through the height of height adjusting part regulated ground plane, make the height of ground plane higher than insulating support base, can reduce the insulation distance between ground plane and aircraft scale model.Due to the existence of three attitude adjustment parts, can realize aircraft scale model and take 30 ° as increment, the posture changing of 0 ° to 360 ° simultaneously.By this cooperation of 2, can effectively prevent that the mounting points of thunder and lightning by scale model and insulating support from can realize the conversion of aircraft scale model attitude simultaneously along insulated support flashover.
[accompanying drawing explanation]
Fig. 1 is the structural representation of device for the test of a kind of aircraft scale model of the utility model thunder and lightning direct effect;
Fig. 2 is the local amplification plan view at A-A place shown in Fig. 1;
Fig. 3 is the structural representation of the platform of ground connection shown in Fig. 1;
Fig. 4 is the vertical view of the base of ground plane shown in Fig. 1;
Fig. 5 is the structural representation of web member shown in Fig. 1;
Fig. 6 is the structural representation of the adjustment part of yaw-position shown in Fig. 1.
The explanation of Reference numeral in the utility model Figure of description below:
1-web member; 2-yaw-position adjustment part; 3-pitch attitude adjustment part; 4-rolling attitude adjustment part; 5-insulated support; 6-reinforced insulation support member; 7-ground plane base; 8-ballast box; 9-supporting leg; 10-ground plane; 11-height adjusting part; 12-ground stud; 13-insulation booth; 14-insulating support base.
[embodiment]
Below in conjunction with accompanying drawing, the utility model is described in further detail:
Refer to shown in Fig. 1 to Fig. 5, the test of a kind of aircraft scale model of the utility model thunder and lightning direct effect comprises web member 1, yaw-position adjustment part 2, pitch attitude adjustment part 3, rolling attitude adjustment part 4, insulated support 5, reinforced insulation support member 6, ground plane base 7, ballast box 8, supporting leg 9, ground plane 10, height adjusting part 11, ground stud 12, insulation booth 13 and insulating support base 14 with device.
As shown in Figure 5, material is steel to web member 1, is semicircle shape, above establishes a threaded hole, and surfaces externally and internally comprises that threaded hole all scribbles coatings, by bolt and aircraft scale model mounting points, is fastenedly connected.On the transmission shaft of web member 1 full weld in yaw-position adjustment part 2.Yaw-position adjustment part 2, pitch attitude adjustment part 3 are identical with attitude adjustment part 4 structures of rolling, as shown in Figure 6.Periphery is an insulating cylinder, a built-in transmission shaft, transmission shaft material is steel, insulating cylinder two ends embed respectively in a cylindrical metal part, in cylindrical metal part, be provided with the bearing matching with transmission shaft, can insulating cylinder be embedded in cylindrical metal part securely by epoxy resin adhesion or arch silk, cylindrical metal part is coated with coatings outward, the cylindrical metal part periphery of transmission shaft one end is established an index dial, take 30 ° as lattice, carry out the mark of 0 ° to 360 °, on transmission shaft, there are one or six side's screw holes, cylindrical metal part is provided with two threaded holes, six side's screws and two bolts are inserted in a web joint with holes, insert again in the six side's screw holes and cylindrical metal part threaded hole on transmission shaft, transmission shaft is fixing can not rotation just.Unclamp six side's screws and bolt and pull down web joint, transmission shaft can rotate.
Specifically, described yaw-position adjustment part 2 comprises the first insulating cylinder, described the first insulating cylinder two ends embed respectively in the first cylindrical metal part, the second cylindrical metal part, in the first insulating cylinder, be provided with the first transmission shaft, one end of the first transmission shaft is connected with web member 1 through one end of the first cylindrical metal part; The other end of the first transmission shaft stretches in the second cylindrical metal part; Described the first cylindrical metal part and the second cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with the first transmission shaft that is provided with.
Described pitch attitude adjustment part 3 comprises the second insulating cylinder, and described the second insulating cylinder two ends embed respectively in the 3rd cylindrical metal part, the 4th cylindrical metal part, in the second insulating cylinder, are provided with second driving shaft; One end of second driving shaft is connected with the second cylindrical metal part through one end of the 3rd cylindrical metal part; Described second driving shaft is perpendicular to described the first transmission shaft; The other end of second driving shaft stretches in the 4th cylindrical metal part; Described the 3rd cylindrical metal part and the 4th cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with second driving shaft that is provided with.
Described rolling attitude adjustment part 4 comprises the 3rd insulating cylinder, and described the 3rd insulating cylinder two ends embed respectively in the 5th cylindrical metal part, the 6th cylindrical metal part, are provided with the 3rd transmission shaft in the 3rd insulating cylinder; One end of the 3rd transmission shaft is connected with the 4th cylindrical metal part through one end of the 5th cylindrical metal part; Described the 3rd transmission shaft is perpendicular to described the first transmission shaft and second driving shaft; The other end of the 3rd transmission shaft stretches in the 6th cylindrical metal part; Described the 5th cylindrical metal part and the 6th cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with the 3rd transmission shaft that is equipped with.
Described the second cylindrical metal part, the 4th cylindrical metal part and the 6th cylindrical metal part periphery are equipped with two threaded holes; Described device also comprises three web joints with holes; In the middle of web joint with holes, be one or six square thread holes, both sides are two bolts hole; On described the first transmission shaft, second driving shaft and the 3rd transmission shaft, be equipped with one or six square thread holes; Six side's screws stretch into through six square thread holes of corresponding web joint with holes in six square thread holes of corresponding transmission shaft and connect with six side's screws with corresponding transmission shaft; Bolt connects with bolt with two threaded holes of corresponding web joint with holes through the threaded hole of corresponding circle tube shape metal piece periphery, and assurance transmission shaft and cylindrical metal part are fixed, and transmission shaft does not rotate.
Insulated support 5 is an insulating cylinder, insulating cylinder two ends connect respectively cylindrical metal part by epoxy adhesion or arch silk, cylindrical metal part is coated with coatings outward, the six cylindrical metal part of the vertical full weld in cylindrical metal part one end on rolling attitude adjustment part 4, the vertical full weld of the other end is on insulating support base 14, and insulating support base 14 materials are steel, and four universal wheels are installed, and each universal wheel side is with a supporting leg 9, and supporting leg 9 is firmly secured on ground by rotation.By the forced formation ballast box 8 in the rear portion of insulating support base 14, in ballast box 8, can load counterweight counterweight, firm with assurance device.
Reinforced insulation support member 6 two ends are designed to circular arc, epoxy resin adhesion rolling attitude adjustment part 4 and insulated support 5 outside surfaces are respectively used in two ends, by reinforced insulation support member 6, rolling attitude adjustment part 4 and insulated support 5 are coupled together, make total possess triangle rock-steady structure.
While using the utility model to carry out the test of aircraft scale model thunder and lightning direct effect, first the utility model is pushed away and put to assigned address, then insulating support base 14 is fixing by supporting leg 9, in insulating support base ballast box 8, install counterweight counterweight, according to the indication on angle dial corresponding to pointer by yaw-position adjustment part 2, pitch attitude adjustment part 3 and rolling attitude adjustment part 4 are adjusted to after test attitude, and scale model is installed on to yaw-position adjustment part 2 tops by web member 1.By the height of height adjusting part 11 regulated ground planes 10, make its correct position in test, with bare copper wire or copper strips by connecting enameled wire on ground stud 12, enameled wire is caused to insulation booth 13 places, wide seam through insulation booth 13 upper covers, pull open insulation booth 13 upper covers, the current sensor that connects the placement in insulation booth, by the wide seam on insulation booth and right angle insulcrete, enameled wire and measurement cable are drawn, close insulation booth upper cover, finally, by enameled wire ground connection, measure cable and connect oscillograph, insulation booth handle utilizes bare copper wire or copper strips ground connection.
A kind of aircraft scale model of the utility model thunder and lightning direct effect test device, reasonable in design, its ground plane can pass through the height of height adjusting part regulated ground plane, make the height of ground plane higher than insulating support base, can reduce the insulation distance between ground plane and aircraft scale model.Due to the existence of three attitude adjustment parts, can realize aircraft scale model and take 30 ° as increment, the posture changing of 0 ° to 360 ° simultaneously.By this cooperation of 2, can effectively prevent that the mounting points of thunder and lightning by scale model and insulating support from can realize the conversion of aircraft scale model attitude simultaneously along insulated support flashover.
Ground plane is owing to being installed on the universal wheel that insulating material makes, and ground plane is connected by insulating bar with support member, therefore to only have a place be the ground stud that ground plane side is installed to the earth point of ground plane, ground plane one supporting leg side welds a right angle insulcrete, on right angle insulcrete, place an insulation booth, insulation booth outside surface is zinc-plated, the inner current sensor of placing, outside surface is by handle ground connection, with the sense of shielding external electromagnetic, disturb the impact on current measurement, utilize enameled wire, ground stud is connected with current sensor, thereby realized the measurement function to lightning current.The utility model simplicity of design, easy installation and removal, good stability, has met the test condition that aircraft scale model thunder and lightning direct effect is tested.
Although by reference to the accompanying drawings the utility model is described above; but the utility model is not limited to above-mentioned embodiment; above-mentioned embodiment is only schematic; rather than restrictive; those of ordinary skill in the art is under enlightenment of the present utility model; not departing from the scope situation that the utility model aim and claim protect, can also make a lot of forms, within these all belong to protection of the present utility model.
Claims (10)
1. an aircraft scale model thunder and lightning direct effect test device, it is characterized in that, comprise web member (1), yaw-position adjustment part (2), pitch attitude adjustment part (3), rolling attitude adjustment part (4), insulated support (5), reinforced insulation support member (6), ground connection platform and insulation booth (13); Described web member (1) is for being fastenedly connected with aircraft scale model mounting points, yaw-position adjustment part (2), pitch attitude adjustment part (3), rolling attitude adjustment part (4) are vertical mutually, by adjusting three attitude adjustment parts, regulate arbitrarily the anglec of rotation of described web members (1); Described insulated support (5) one end connects rolling attitude adjustment part (4), other end insulation connects ground connection platform, this ground connection platform comprises ground plane (10), is welded in the ground plane base of ground plane (10) bottom, and be arranged on the insulation booth (13) on ground plane base (7), this insulation booth is provided with current transformer in (13), described ground plane base (7) is provided with height adjusting part (11) in order to the height of regulated ground plane (10), and the height of described ground plane (10) is higher than insulating support base (14).
2. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 1, is characterized in that, described web member (1) material is steel, which is provided with threaded hole, and surfaces externally and internally is equipped with a layer insulating.
3. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 1, it is characterized in that, described yaw-position adjustment part (2) comprises the first insulating cylinder, described the first insulating cylinder two ends embed respectively in the first cylindrical metal part, the second cylindrical metal part, in the first insulating cylinder, be provided with the first transmission shaft, one end of the first transmission shaft is connected with web member (1) through one end of the first cylindrical metal part; The other end of the first transmission shaft stretches in the second cylindrical metal part; Described the first cylindrical metal part and the second cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with the first transmission shaft that is provided with.
4. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 3, it is characterized in that, described pitch attitude adjustment part (3) comprises the second insulating cylinder, described the second insulating cylinder two ends embed respectively in the 3rd cylindrical metal part, the 4th cylindrical metal part, in the second insulating cylinder, are provided with second driving shaft; One end of second driving shaft is connected with the second cylindrical metal part through one end of the 3rd cylindrical metal part; Described second driving shaft is perpendicular to described the first transmission shaft; The other end of second driving shaft stretches in the 4th cylindrical metal part; Described the 3rd cylindrical metal part and the 4th cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with second driving shaft that is provided with.
5. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 4, it is characterized in that, described rolling attitude adjustment part (4) comprises the 3rd insulating cylinder, described the 3rd insulating cylinder two ends embed respectively in the 5th cylindrical metal part, the 6th cylindrical metal part, are provided with the 3rd transmission shaft in the 3rd insulating cylinder; One end of the 3rd transmission shaft is connected with the 4th cylindrical metal part through one end of the 5th cylindrical metal part; Described the 3rd transmission shaft is perpendicular to described the first transmission shaft and second driving shaft; The other end of the 3rd transmission shaft stretches in the 6th cylindrical metal part; Described the 5th cylindrical metal part and the 6th cylindrical metal part skin are provided with one deck insulating coating, and the inner bearing matching with the 3rd transmission shaft that is equipped with.
6. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 5, is characterized in that, described the second cylindrical metal part, the 4th cylindrical metal part and the 6th cylindrical metal part periphery are equipped with two threaded holes; Described device also comprises three web joints with holes; In the middle of web joint with holes, be one or six square thread holes, both sides are two bolts hole; On described the first transmission shaft, second driving shaft and the 3rd transmission shaft, be equipped with one or six square thread holes; Six side's screws stretch into through six square thread holes of corresponding web joint with holes in six square thread holes of corresponding transmission shaft and connect with six side's screws with corresponding transmission shaft; Bolt connects with bolt with two threaded holes of corresponding web joint with holes through the threaded hole of corresponding circle tube shape metal piece periphery, and assurance transmission shaft and cylindrical metal part are fixed, and transmission shaft does not rotate.
7. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 5, it is characterized in that, described insulated support (5) is an insulating cylinder, one end is fixedly connected with the 6th cylindrical metal part of rolling attitude adjustment part (4), and the other end is fixedly connected with insulating support base (14); Described reinforced insulation support member (6) is an insulating cylinder, and one end is fixedly connected with the 3rd insulating cylinder of rolling attitude adjustment part (4), and the other end is fixedly connected with insulated support (5).
8. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 1, is characterized in that, described ground plane (10) adopts stainless steel aluminium sheet to make, plating zinc on surface; Described ground plane base (7) side is provided with ground stud (12); Described insulation booth (13) outside surface is zinc-plated, and leader is installed on outside surface, and described handle is by bare copper wire or copper strips ground connection; One conductor one end connects ground stud (12), ground connection after the current transformer in other end connection insulation booth (13); Described conductor is enameled wire.
9. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 1, is characterized in that, described ground plane base (7) comprises four supporting legs, and supporting leg bottom is provided with universal wheel, and universal wheel is that insulating material is made; Four height adjusting parts (11) are installed on corresponding supporting leg; On a described supporting leg, right angle insulcrete is installed, described insulation booth (13) is installed on this right angle insulcrete; Described insulating support base (14) connects described ground connection platform by insulating bar.
10. a kind of aircraft scale model thunder and lightning direct effect test device as claimed in claim 7, is characterized in that, the forced formation ballast box in rear portion (8) of described insulating support base (14), for loading counterweight counterweight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320709284.2U CN203551699U (en) | 2013-11-08 | 2013-11-08 | Device for plane scaling model lightning direct effect test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320709284.2U CN203551699U (en) | 2013-11-08 | 2013-11-08 | Device for plane scaling model lightning direct effect test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203551699U true CN203551699U (en) | 2014-04-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320709284.2U Expired - Lifetime CN203551699U (en) | 2013-11-08 | 2013-11-08 | Device for plane scaling model lightning direct effect test |
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| Country | Link |
|---|---|
| CN (1) | CN203551699U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112730906A (en) * | 2020-12-18 | 2021-04-30 | 北京航空航天大学 | Thunder and lightning test device for simulating dynamic aircraft |
| CN114236300A (en) * | 2022-02-26 | 2022-03-25 | 合肥航太电物理技术有限公司 | Method for testing lightning attachment characteristics of scaled model of motorized ground radar equipment |
-
2013
- 2013-11-08 CN CN201320709284.2U patent/CN203551699U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112730906A (en) * | 2020-12-18 | 2021-04-30 | 北京航空航天大学 | Thunder and lightning test device for simulating dynamic aircraft |
| CN112730906B (en) * | 2020-12-18 | 2021-12-03 | 北京航空航天大学 | Thunder and lightning test device for simulating dynamic aircraft |
| CN114236300A (en) * | 2022-02-26 | 2022-03-25 | 合肥航太电物理技术有限公司 | Method for testing lightning attachment characteristics of scaled model of motorized ground radar equipment |
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