CN107799895A - A kind of balance beam profile and direction-finder antenna cover - Google Patents
A kind of balance beam profile and direction-finder antenna cover Download PDFInfo
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- CN107799895A CN107799895A CN201710817444.8A CN201710817444A CN107799895A CN 107799895 A CN107799895 A CN 107799895A CN 201710817444 A CN201710817444 A CN 201710817444A CN 107799895 A CN107799895 A CN 107799895A
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- balance beam
- fairing
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/286—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
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- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Details Of Aerials (AREA)
Abstract
The present invention devises a kind of balance beam profile and direction-finder antenna cover, belongs to overall Design of Aerodynamic Configuration field.Because the antenna shapes size of installation is larger, commutating zone fusion transition flow line design method before and after antenna house profile is used in the layout designs of antenna house, is separated when reducing airflow passes antenna house, improves air velocity distribution；Pass through the comparative analysis of low speed aerodynamic characteristic, flow field characteristic and vorticity figure, it is determined that optimization scheme；On the premise of task system requirement is met, reduce the appearance and size of antenna house as far as possible, the aerodynamic characteristic of carrier aircraft is influenceed with reducing attaching antenna cover.The antenna house is calculated using variable element control wheel profile, CFD and the pneumatic Synthetical Optimization measures of multinomial totality such as wind tunnel test is verified, optimizes antenna house appearance and size to greatest extent.Solve existing balance beam profile inner space is small, be not easy to waterproof roof leaking design the problems such as, there is provided a kind of new balance beam profile and direction-finder antenna cover alternative.
Description
Technical field
The invention belongs to aircraft totality Design of Aerodynamic Configuration field, is related to a kind of balance beam profile of aircraft and direction finding day
Irdome.
Background technology
Certain model type requires according to full machine antenna arrangement, task efficacy exertion and full machine EMC Design, through more wheels
Argument and analysis is determined using backpack balance beam form loading commissions system TX/RX primary antennas and installation direction estimation antenna array.By
Larger in the envelope size of the type machine task system antenna array, certain former type machine balance beam antenna house can not meet the task of the model
System equipment is installed and requirement, need to newly design balance beam profile and direction-finder antenna cover profile.
The antenna house is arranged using pneumatic Synthetical Optimizations of multinomial totality such as xyz three-dimensionals optimization variable element control wheel profiles
Apply, optimize balance beam antenna house appearance and size to greatest extent and reduce aerodynamic drag；Before and after having redesigned balance beam
Radome fairing carries out profile, reduces influence of the balance beam tail wind separation to full machine aerodynamic characteristic；New design direction-finder antenna cover
Profile, technological design and installation requirement are considered, experiment proves that choosing optimal profile and aerodynamic arrangement.
Antenna shapes are determined after parameter adjustment is carried out to control wheel profile and is verified using CFD calculating and wind tunnel test
Prioritization scheme.Preferable antenna house had not only met internal task antenna use demand but also had taken into account excellent aerodynamic characteristic.
The content of the invention
(1) goal of the invention：Instant invention overcomes existing balance beam antenna house inner space is small, tail wind separation influences
Greatly, the shortcomings of waterproof ability difference, the influence after reduction increase balance beam antenna house profile to aircraft aerodynamic characteristic, there is provided a kind of
Balance beam antenna house and direction-finder antenna cover profile.
(2) technical scheme：In order to solve the above-mentioned technical problem, the present invention is achieved by the following technical solutions：
A kind of balance beam profile and direction-finder antenna cover, by air inlet (1), front fairing (2), top cover (3), rear radome fairing
(4), exhaust outlet (5), side antenna house (6), direction-finder antenna cover (7), supporting leg singletree (8), supporting leg (9) composition；The balance beam
Profile and direction-finder antenna cover total length 12869mm, wherein front fairing (2) and air inlet (1) length are 1580mm, principal length is
9640mm, rear radome fairing (4) length are 1649mm；Balance beam main body is using double closed chamber frame structures, by front and back ends frame, H type branch
Upper box section is formed after frame, top cover (3) and side antenna house (6) connection, balance beam bottom part body torsion box is lower box section；It is above-mentioned
Balance beam main body total height is 1200mm, and side antenna house (6) overall width is 862mm, length 9640mm, wetted area 48.298
㎡, each seamed edge of balance beam main body carry out chamfered, and side antenna house (6) uses radius 60mm with balance beam body upper surface
Arc-shaped transition, side antenna house (6) and balance beam body lower surface use radius 30mm arc-shaped transition；Direction-finder antenna cover (7)
Balance beam main body front lower place is installed on, direction-finder antenna cover (7) First Point is according to front fairing (2) and balance beam main body interface
46.87mm, installation direction keep -3 ° of established angle, the unilateral prominent side antenna of direction-finder antenna cover (7) with respect to aircraft horizontal datum
The width for covering (6) be 180mm, be optimizing pneumatic effect by the control of direction-finder antenna cover (7) total length within 4500mm, wait straight section
Long 3775mm, preceding commutating zone and rear commutating zone are separately designed before and after the straight sections such as direction-finder antenna cover (7)；The front fairing (2)
Profile includes air inlet lip, front fairing area, and lip axis be located in the aircraft plane of symmetry and standard of fuselage line is into above returning 3 ° of angles, lip
Mouth axis is described to be docked with lip axis with front fairing (2) with balance beam main body according to balance beam body lower surface 764.55mm
The intersection point in face is origin of coordinates O, and X-axis is along lip axis to inverse course scheme just, in Y-axis to be that just, Z axis is preceding to the left for just
Radome fairing (2) is symmetrical along the aircraft plane of symmetry, and according to the form below coordinate points are chosen, measurement unit mm；
Front fairing (2) profile is formed by above-mentioned data point-rendering curved surface；Radome fairing (4) profile includes rear rectification after described
Cover area, exhaust outlet, lip axis, lip axis be located in the aircraft plane of symmetry and standard of fuselage line is into above returning 3 ° of angles, lip axis
According to balance beam body lower surface 764.55mm, using the intersection point of lip axis and rear radome fairing (4) and balance beam main body interface as
Origin of coordinates O, it just, in Y-axis is being that just, Z axis is just rear radome fairing (4) edge to the left that X-axis is to inverse course scheme along lip axis
The symmetrical according to the form below coordinate points of the aircraft plane of symmetry are chosen, measurement unit mm；
Rear radome fairing (4) profile is formed by above-mentioned data point-rendering curved surface.
Also include 6 sections of the top cover (3) structure point, every section of top cover (3) is independently detachable.
Also including the top cover (3) upper surface along right boundary upwards inclined 1 ° and both sides design gutter.
Also include balance beam main body using the multiple material structure of A interlayers, edge is real sandwich layer glass fibre reinforced plastic structure, with fixed edge strip glue
Rivet after connecing, be connected again by bolt with fuselage after taking watertight measure.
Also A type honeycomb sandwich composite structures, the angle of border and torsion box two sides are used including direction-finder antenna cover (7)
Material uses the detachable connection of bolt, and uses the liquid-tight envelope of silicone adhesive.
Also include the front fairing (2), rear radome fairing (4) uses A interlayer composite material structures, the outer design arrangement of covering
Flow guide bar, flow guide bar are extended at the frame of end, pass through bolt and end frame electrical bonding；Front fairing (2) bosom location arrangements gold
Belong to bulkhead, front fairing (2) bottom and lateral layout safeguard lid；Simultaneously in front fairing (2) bottom rear end and supporting leg (9) phase
Position is handed over, sets cable, conduit to pass through hole；The front fairing (2), rear radome fairing (4) using bolt respectively with front and back ends frame
Connection.
(3) beneficial effect
It is of the invention compared with existing balance beam form, there is clear advantage and beneficial effect：
1) expand the balance beam body contours after width and increase inside antenna installation free space by meeting that China is new
Radar system installs and uses requirement, and about 25.5% is added compared to the usable space of original；
2) design of profile increase-volume can meet constant with former balance beam installation join domain and reduce internal structure and set
The Curve guide impeller workload of meter form, reduce the structural strength risk that balance beam design is brought；
3) radome fairing profile uses the digital modeling form of xyz three-dimensional curved surface controllable parameter contour lines before and after, to contour line
Carry out multiple parameter adjustment, ensure smoothly transitting for balance beam main body and front and rear radome fairing, it is more preferable to meet process implementing
It is required that understand to carry out profile amendment to front fairing (violet region) by the curvature analysis of CATIA digital-to-analogues, on the original basis
Maximum outer deviator is about that 44mm makes profile more fairing and and is easy to the manufacturing of model；
5) radome fairing profile has not only taken into full account rain-proof problem in design afterwards, and by using CFD calculating and wind
Prioritization scheme is determined after the verification experimental verification of hole, passes through the low velocity pneumatic to new design radome fairing compared to radome fairing profile after original
The comparative analysis of characteristic, flow field characteristic and vorticity figure, prioritization scheme is finally determined (see Fig. 1)：
Radome fairing passes through installation in aircraft stopped status after can changing former balance beam due to rear radome fairing configuration design
The rain-proof water problems that blanking cover is brought, greatly improves maintainability, simultaneously because lower part of the exhaust outlet design in commutating zone
Exhaust port area can moderately be expanded, improve high-altitude ventilation and negative pressure ventilation ability；
Known by low speed aerodynamic characteristic analysis：Simulate comparing calculation by CFD type selectings, it is former after radome fairing configuration lift
Characteristic is relatively low, and new rear radome fairing appearance and size gradually increases, and frictional resistance is influenceed less, but pressure drag drops compared with original configuration
It is low；
Known by stream field specificity analysis：There is air-flow separation after around edge strip at left and right sides of balance beam in air-flow
Phenomenon, concentrated vorticity is formed in afterbody, air-flow preferably can be attached on object plane when passing through new radome fairing profile in upper and lower surface
(see Fig. 2)；
Known by vortex intensity analysis：The spin intensity schematic diagram of original configuration and new tail cup profile (see Fig. 3)
Contrast understands that the whirlpool intensity of new departure is obviously reduced relative to original configuration；
Known by barometric gradient analysis：Original configuration has a low-pressure area in balance beam afterbody upper surface, and new rectification
Cover scheme reduces with the increase of afterbody fairing length, the barometric gradient of balance beam afterbody, and pressure distribution approaches uniformity is (see figure
4)。
Brief description of the drawings：
Radome fairing profile comparison diagram after Fig. 1
During 0 ° of radome fairing flow pattern schematic diagram after Fig. 2 --- the angle of attack
During 0 ° of Fig. 3 spin intensity schematic diagrames --- the angle of attack
During 0 ° of Fig. 4 pressure cloud atlas --- the angle of attack
Fig. 5 direction-finder antenna covers profile contrasts
Fig. 6 antenna house design sketch
Fig. 7 antenna house side views
Fig. 8 antenna house top views
Fig. 9 installation effect figures
Figure 10 installation effect figures
Figure 11 balance beam profile composition schematic diagrams --- 1. air inlets；2. front fairing；3. top cover；Radome fairing after 4.；5.
Exhaust outlet；6. side antenna house；7. direction-finder antenna cover；8. supporting leg singletree；9. supporting leg
Figure 12 balance beam size of main body schematic diagrames
Figure 13 balance beam top design top cover schematic diagrames
Figure 14 direction-finder antenna cover appearance schematic diagrams
Figure 15 front fairing schematic diagrames
Figure 16 front fairing coordinate points Sample point collection schematic diagrames
Radome fairing schematic diagram after Figure 17
Radome fairing coordinate points Sample point collection schematic diagram after Figure 18
4) direction-finder antenna cover
Direction-finder antenna cover (see Fig. 5) is the installation needs for meeting task system antenna, by the prominent balance beam main body side in one side
The 140mm width of antenna house is that increase is 180mm, be optimizing pneumatic effect by the straight sections such as antenna house control to 4500mm with
Interior, relative to primary antenna cover 9000mm length range, local optimization improves the aerodynamic characteristic of full machine to a certain extent, together
When because the compact design of profile simplifies subsequent structural specialty installation safeguard the design efforts would of mouth, improve full machine design
Efficiency；
By the design to balance beam profile, aircraft aerodynamic characteristic is significantly optimized under comprehensive function, can effectively change
Kind China's new system radar antenna array enormous size and caused by design, assembly difficulty, reduce task system antenna house to full machine
The influence of weight, aerodynamic characteristic and flight quality.
Specific embodiment
A kind of balance beam profile and direction-finder antenna cover are located between the frame of middle fuselage top 21~49, and its profile is by advancing air
Mouth, front fairing, top cover, side antenna house, direction-finder antenna cover, rear radome fairing, supporting leg and supporting leg singletree etc. form, outside balance beam
Figure 11 is shown in shape composition signal.
Balance beam profile total length 12869mm (wherein front fairing and air inlet 1580mm, main body 9640mm, rear radome fairing
1649mm), wherein balance beam supporting leg and singletree are consistent with former balance beam profile.
Major design embodiment is as follows：
1) balance beam composition design
Balance beam is made up of H-shaped support, top cover, base, front fairing, rear radome fairing and strut, balance beam antenna house,
It is specifically shown in Figure 11；
By the above-mentioned function operational feasibility for forming the balance beam profile designed and ensure that internal structure.Balance beam
Structure design (forms upper box using double closed chamber frame structures after front and back ends frame, H types support, top cover and the connection of side antenna house
Section, balance floor sill (torsion box) is lower box section), aerodynamic force and inertia force in cover body structure are transmitted to down by superstructure
Portion's torsion box, then fuselage is transmitted to by trussing (supporting leg) by bottom torsion box and balanced；
Wherein 6 sections of cap structure point, every section of top cover is independently detachable；
Front fairing, rear radome fairing can be dismounted independently, and forward and backward radome fairing adds honeycomb core knot using glass fibre surface layer
Structure.
2) balance beam main body
Balance beam main body total height and former balance beam systems compliant are 1200mm, and side antenna house overall width is 862mm, long
Spend and see Figure 12 for 9640mm, the ㎡ of wetted area 48.298, the ㎡ of front face area 1.032, the signal of balance beam size of main body, antenna house is
Detachable, using the multiple material structure of " A " interlayer, edge is real sandwich layer glass fibre reinforced plastic structure, rivets, takes after being glued with fixed edge strip for it
It is connected again by bolt with fuselage after watertight measure, Figure 12 is shown in the signal of balance beam size of main body；
Each seamed edge of balance beam carries out chamfered, and both sides antenna house uses radius 60mm arc with balance beam upper surface
Transition, both sides antenna house uses radius 30mm arc-shaped transition with balance beam lower surface, to meet production engineering specifications；
According to Structural Design Requirement in balance beam top design top cover, achievable attended operation, to prevent on balance beam
Surface area water and the risk of leakage brought, by upper surface along inclined 1 ° upwards of right boundary, gutter can be designed around, balance beam
Figure 13 is shown in the signal of top design top cover.
3) direction-finder antenna cover
The width of the unilateral prominent balance beam main body side antenna house of direction-finder antenna cover is 180mm, will for optimizing pneumatic effect
For the control of antenna house total length within 4500mm, Figure 14 is shown in the long 3775mm of the straight section such as antenna house, direction-finder antenna cover profile signal；
Direction-finder antenna cover is installed on balance beam main body front lower place, and antenna house First Point is according to front fairing and balance beam main body
Interface 46.87mm, installation direction keep -3 ° of established angle with respect to aircraft horizontal datum, to ensure that acquisition is preferably pneumatic
Characteristic, preceding commutating zone and rear commutating zone are separately designed before and after the straight sections such as antenna house.
Direction-finder antenna cover is compound using " A " type cellular sandwich to meet intensity and task system antenna electric performance requirement
The angle section of material structure, border and torsion box two sides uses the detachable connection of bolt, and uses the liquid-tight envelope of silicone adhesive.
4) front fairing
Front fairing profile includes air inlet lip, front fairing area, and Figure 15 is shown in the signal of balance beam front fairing.With lip axle
(lip axis is located in the aircraft plane of symmetry with standard of fuselage line into 3 ° of angles are above returned line, and lip axis is according to balance beam body lower surface
It is 764.55mm) origin of coordinates O with the intersection point of front fairing and balance beam main body interface, X-axis is along lip axis to inverse course
It just, in Y-axis is being that just, Z axis is just, to be chosen by following coordinate points, measurement unit mm to the left that scheme, which is,.
Front fairing coordinate points Sample point collection schematic diagram is shown in Figure 16, and front fairing is symmetrical along the aircraft plane of symmetry, preceding whole
Stream cover coordinate points are shown in Table 1.
The front fairing coordinate points of table 1
5) radome fairing afterwards
Radome fairing profile includes front fairing area, exhaust outlet afterwards, and Figure 17 is shown in rear radome fairing signal.With lip axis (lip
Axis is located in the aircraft plane of symmetry with standard of fuselage line into 3 ° of angles are above returned, and lip axis is according to balance beam body lower surface
It is 764.55mm) origin of coordinates O with the intersection point of rear radome fairing and balance beam main body interface, X-axis is along lip axis to inverse course
It just, in Y-axis is being that just, Z axis is just, to be chosen by following coordinate points, measurement unit mm to the left that scheme, which is,.
Radome fairing coordinate points Sample point collection schematic diagram is shown in Figure 18 afterwards, and radome fairing is symmetrical along the aircraft plane of symmetry, rear rectification
Cover coordinate points are shown in Table 2.
Radome fairing coordinate points after table 2
6) the forward and backward radome fairing of balance beam and the connection of main body and other designs
Forward and backward radome fairing covering uses A interlayer composite material structures, to meet anti-lightning strike requirement, the outer design arrangement of covering
Flow guide bar, flow guide bar are extended at the frame of end, pass through bolt and end frame electrical bonding.Arrangement metal in centre position inside front fairing body
Bulkhead, to maintain radome fairing profile, covering rigidity is improved, lid is safeguarded in front fairing bottom and lateral layout increase, to ensure
The maintenance and installation of its internal air feed flow control equipment；Simultaneously in bottom rear end and front leg strut intersection location, cable, conduit is set to lead to
Via.Forward and backward radome fairing is connected with front and back ends frame respectively using bolt.
Claims (7)
1. a kind of balance beam profile and direction-finder antenna cover, by air inlet (1), front fairing (2), top cover (3), rear radome fairing (4),
Exhaust outlet (5), side antenna house (6), direction-finder antenna cover (7), supporting leg singletree (8), supporting leg (9) composition；It is characterized in that：It is described
Balance beam profile and direction-finder antenna cover total length 12869mm, wherein front fairing (2) and air inlet (1) length are 1580mm, main body
Length is 9640mm, rear radome fairing (4) length is 1649mm；Balance beam main body is using double closed chamber frame structures, by front and back ends
Upper box section is formed after frame, H types support, top cover (3) and side antenna house (6) connection, balance beam bottom part body torsion box is bottom
Box section；Above-mentioned balance beam main body total height is 1200mm, and side antenna house (6) overall width is 862mm, length 9640mm, is infiltrated
The ㎡ of area 48.298, each seamed edge of balance beam main body carry out chamfered, and side antenna house (6) is adopted with balance beam body upper surface
With radius 60mm arc-shaped transition, side antenna house (6) uses radius 30mm arc-shaped transition with balance beam body lower surface；Direction finding
Antenna house (7) is installed on balance beam main body front lower place, and direction-finder antenna cover (7) First Point is according to front fairing (2) and balance beam main body
Interface 46.87mm, installation direction keep -3 ° of established angle with respect to aircraft horizontal datum, and direction-finder antenna cover (7) is unilateral to be protruded
The width of side antenna house (6) is 180mm, and being optimizing pneumatic effect controls direction-finder antenna cover (7) total length within 4500mm,
Deng the long 3775mm of straight section, preceding commutating zone and rear commutating zone are separately designed before and after the straight sections such as direction-finder antenna cover (7)；The preceding rectification
Covering (2) profile includes air inlet lip, front fairing area, and lip axis be located in the aircraft plane of symmetry and standard of fuselage line is into above returning 3 °
Angle, lip axis are described with lip axis and front fairing (2) and balance beam main body according to balance beam body lower surface 764.55mm
The intersection point of interface is origin of coordinates O, and it just, in Y-axis is being that just, Z axis is to the left that X-axis is to inverse course scheme along lip axis
Just, front fairing (2) is symmetrical along the aircraft plane of symmetry, and according to the form below coordinate points are chosen, measurement unit mm；
Front fairing (2) profile is formed by above-mentioned data point-rendering curved surface；Radome fairing (4) profile includes rear radome fairing after described
Area, exhaust outlet, lip axis, lip axis are located in the aircraft plane of symmetry with standard of fuselage line into above returning 3 ° of angles, lip axis evidence
Balance beam body lower surface 764.55mm, using the intersection point of lip axis and rear radome fairing (4) and balance beam main body interface as seat
Mark origin O, X-axis is along lip axis to inverse course scheme just, in Y-axis to be that just, Z axis is to the left for just, and rear radome fairing (4) is along flying
The symmetrical according to the form below coordinate points of the machine plane of symmetry are chosen, measurement unit mm；
Rear radome fairing (4) profile is formed by above-mentioned data point-rendering curved surface.
2. a kind of balance beam profile according to claim 1 and direction-finder antenna cover, it is characterised in that：Top cover (3) knot
6 sections of structure point, every section of top cover (3) is independently detachable.
3. a kind of balance beam profile according to claim 2 and direction-finder antenna cover, it is characterised in that：The top cover (3)
Upper surface along right boundary upwards inclined 1 ° and both sides design gutter.
4. a kind of balance beam profile according to claim 1 and direction-finder antenna cover, it is characterised in that：Balance beam main body uses
The multiple material structure of A interlayers, edge is real sandwich layer glass fibre reinforced plastic structure, rivets after being glued with fixed edge strip, leads to again after taking watertight measure
Bolt is crossed to be connected with fuselage.
5. a kind of balance beam profile according to claim 1 and direction-finder antenna cover, it is characterised in that：Direction-finder antenna cover (7)
Using A type honeycomb sandwich composite structures, the angle section of border and torsion box two sides uses the detachable connection of bolt, and uses silicon
Ketone glue seals.
6. a kind of balance beam profile according to claim 1 and direction-finder antenna cover, it is characterised in that：The front fairing
(2), rear radome fairing (4) uses A interlayer composite material structures, the outer design arrangement flow guide bar of covering, and flow guide bar is extended at the frame of end,
Pass through bolt and end frame electrical bonding.
7. a kind of balance beam profile according to claim 6 and direction-finder antenna cover, it is characterised in that：The front fairing
(2) bosom location arrangements metal bulkhead, front fairing (2) bottom and lateral layout safeguard lid；Simultaneously in front fairing
(2) bottom rear end and supporting leg (9) intersection location, set cable, conduit to pass through hole；The front fairing (2), rear radome fairing (4)
It is connected respectively with front and back ends frame using bolt.
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| CN201710817444.8A CN107799895A (en) | 2017-09-12 | 2017-09-12 | A kind of balance beam profile and direction-finder antenna cover |
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| CN201710817444.8A CN107799895A (en) | 2017-09-12 | 2017-09-12 | A kind of balance beam profile and direction-finder antenna cover |
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| CN109484620A (en) * | 2018-03-16 | 2019-03-19 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
| CN109490841A (en) * | 2018-07-13 | 2019-03-19 | 中国航空工业集团公司济南特种结构研究所 | A kind of radome electrical bonding structure |
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| CN109484620A (en) * | 2018-03-16 | 2019-03-19 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
| CN109484620B (en) * | 2018-03-16 | 2022-05-13 | 陕西飞机工业（集团）有限公司 | Overlapped disc radome on back of body |
| CN108417981A (en) * | 2018-04-25 | 2018-08-17 | 西安飞机工业（集团）有限责任公司 | A kind of segmented airborne radome |
| CN109490841A (en) * | 2018-07-13 | 2019-03-19 | 中国航空工业集团公司济南特种结构研究所 | A kind of radome electrical bonding structure |
| CN109490841B (en) * | 2018-07-13 | 2023-07-21 | 中国航空工业集团公司济南特种结构研究所 | Electric lap joint structure of radar antenna housing |
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