CN109533392A - A kind of antenna cover inner surface foil gauge patch location determines method - Google Patents
A kind of antenna cover inner surface foil gauge patch location determines method Download PDFInfo
- Publication number
- CN109533392A CN109533392A CN201811502502.9A CN201811502502A CN109533392A CN 109533392 A CN109533392 A CN 109533392A CN 201811502502 A CN201811502502 A CN 201811502502A CN 109533392 A CN109533392 A CN 109533392A
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- Prior art keywords
- antenna house
- antenna
- fuselage
- foil gauge
- line
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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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Details Of Aerials (AREA)
Abstract
The present invention relates to a kind of antenna cover inner surface foil gauge patch locations to determine method, belongs to aircraft test field of measuring technique.It borrows software and draws fuselage frame, long joist axial line, fuselage frame and long joist axial line respectively in the projection line of antenna house model outer surface, the intersection point of projection line is drawn in antenna cover outer surface, foil gauge patch location is drawn in antenna house mold inner surfaces according to coordinate, foil gauge patch location is projected to antenna house model outer surface along normal direction, measures subpoint at a distance from nearest two intersection points；Fuselage frame and long joist axial line are drawn in all projection lines of antenna cover outer surface on fuselage and radome test part by laser level later；Then the specific location of subpoint on testpieces is finally determined according to the distance relation of subpoint in figure and nearest two intersection points with compasses, finally, subpoint inner surface on testpieces is projected and made marks along normal direction with laser pen, institute's mark point is foil gauge patch location.
Description
Technical field
The invention belongs to aircrafts to test field of measuring technique, and in particular to a kind of antenna cover inner surface foil gauge patch location
Determine method.
Background technique
Antenna house is part more commonly used in aircaft configuration, usually by arranging in its inner surface when slow test is verified
A certain number of foil gauges measure its structural stress.More data can be usually collected, the case where experimental condition allows
Under, large number of foil gauge is arranged as far as possible.The quantity of foil gauge and and position distribution and finite Element Stress calculate and tie
Fruit has much relations, usually provides stress envelope by finite element analysis, then in high stress areas and other concern areas
Foil gauge is arranged in domain.
Antenna house generallys use the more cambered shells of composite material, and shape is more complicated, therefore how in testpieces inner surface
The position for accurately finding out foil gauge patch is always the difficult point for perplexing antenna cover structure slow test.All the time, in antenna house
Surface strain piece patch location determination is to draw a plurality of related song in its inner surface according to the ready-made datum mark of antenna house by compasses
Line, such method are suitable for the simple small size antenna cover of shape, curvature antenna houses more for large scale, due to compasses size, day
Many restrictions, the position errors such as the ready-made datum mark of irdome shape, antenna house are larger.
Summary of the invention
The purpose of the present invention is to propose to a kind of on the basis of the airframe structure of antenna house installation, according to fuselage frame and stringer axis
Line is in the positional relationship of antenna cover outer surface projection line intersection point and testpieces foil gauge patch coordinate, the accurately table in antenna house
The method that foil gauge patch location is found in face.
A kind of antenna cover inner surface foil gauge patch location determines method, it is known that the model and foil gauge patch of the antenna house
Position of the position on model, it is known that the connection relationship of the antenna house and airframe characterized by comprising 1) by antenna
Cover model is assembled on airframe models according to positional relationship, and the frame of the airframe of antenna house covering position is projected to antenna
The outer surface of cover model forms wire；
2) by the long joist axial line upright projection of the airframe of antenna house covering position to the outer surface of antenna house model, shape
At stringer line；3) intersection point of above-mentioned wire and stringer line is marked out in the model outer surface of antenna house；4) according to foil gauge patch
Position coordinates illustrate all foil gauge patch locations in the antenna house mold inner surfaces, by antenna house mold inner surfaces
Upper foil gauge patch location projects to form subpoint along normal direction to antenna house model outer surface, records each subpoint away from institute
State the distance d1 and distance d2 of the two nearest intersection points formed in step 3)；5) show in the aircraft fuselage skin of installation antenna house
It anticipates out the position line of fuselage frame and fuselage stringer；6) antenna house is installed to the fuselage outer surface, it will be in the step 5)
The fuselage frame of fuselage outer surface and the position line projection of fuselage stringer are simultaneously indicated on the antenna cover outer surface, outside antenna house
The intersection point of the projection line of multiple fuselage frames and the fuselage stringer position line is formed on surface；7) with antenna house appearance in the step 6)
Intersection point on face corresponds to the intersection point of antenna house model outer surface in the step 3), then by each throwing determined in the step 4)
Shadow point determines practical subpoint on antenna house away from the distance d1 and distance d2 of two nearest projection line intersection points；8) laser pen is used
Subpoint inner surface on testpieces is projected and made marks along normal direction, mark position is the practical patch position of foil gauge
It sets.
The beneficial effects of the present invention are: 1) compasses, laser pen, laser level and the CATIA V5 that the present invention use are soft
The method that part combines is positioned, and is measured and is crossed, greatly improves the large-size antennae cover foil gauge with complex appearance
The accuracy that patch location determines, and it is easy to operate, it improves work efficiency.2) present invention is suitable for the assembly of aircraft outer surface
The positioning of various types antenna house, radar cover inner surface point.
Detailed description of the invention
Fig. 1 is antenna house and fuselage positions relation schematic diagram.
Fig. 2 is antenna house, frame, long joist axial line relation schematic diagram.
Fig. 3 is antenna house, wire, the relation schematic diagram of stringer line, subpoint.
Fig. 4 is the structure partial amplification nearby of Fig. 3 subpoint and postrotational schematic diagram.
It numbers and illustrates in figure: 1 antenna house, 2 wires, 3 stringer lines, the intersection point of 4 wires and stringer line, 5 subpoints, 6 fuselages,
7 frames, 8 long joist axial lines.
Specific embodiment
Referring to attached drawing, the purpose of the present invention is to propose to a kind of on the basis of the airframe structure of antenna house installation, according to fuselage
Frame and long joist axial line accurately exist in the positional relationship of antenna cover outer surface projection line intersection point and testpieces foil gauge patch coordinate
The method that radar cover inner surface finds foil gauge patch location.
Position of the model and foil gauge patch location of the known antenna house on model, it is known that the antenna house 1 and aircraft
The connection relationship of fuselage 6, technical solution of the invention comprise the following steps:
1) antenna house model 1 is assembled on airframe models according to positional relationship, by the aircraft machine of antenna house covering position
The frame 7 of body 6 projects to the outer surface of antenna house model, forms wire 2；
2) by the appearance of 8 upright projection of long joist axial line of the airframe 6 of antenna house covering position to antenna house model 1
Face forms stringer line 3；
3) intersection point 4 of above-mentioned wire and stringer line is marked out in the model outer surface of antenna house；
4) according to foil gauge patch location coordinate, all foil gauge patches are illustrated in the antenna house mold inner surfaces
Foil gauge patch location in antenna house mold inner surfaces is projected to form throwing by position along normal direction to antenna house model outer surface
Shadow point 5 records distance d1 and distance d2 of each subpoint 5 away from the two nearest intersection points 4 formed in the step 3)；
5) position line of fuselage ring 7 Yu fuselage long joist axial line 8 is illustrated on 6 surface of airframe of installation antenna house；
6) antenna house is installed to 6 outer surface of airframe, by the fuselage of the fuselage outer surface in the step 5)
The position line projection of frame 7 and fuselage long joist axial line 8 is simultaneously indicated on the antenna cover outer surface, the shape on antenna cover outer surface
At the intersection point 4 of multiple fuselage rings 7 and the projection line of 8 position line of fuselage long joist axial line；
7) antenna house model outer surface in the step 3) is corresponded to the intersection point in the step 6) on antenna cover outer surface
Intersection point, then by distance d1 and distance of each subpoint away from two nearest projection line intersection points 4 determined in the step 4)
D2 determines practical subpoint 5 on antenna house；
8) subpoint inner surface on testpieces is projected and is made marks along normal direction with laser pen, mark position is
The practical patch location of foil gauge.
It should be noted that the aircraft 3 d structure model with antenna house is made first before step 1), for example,
After making structural model using CATIA software, since antenna house is attached to airframe outer surface, other than doing projection line,
Directly the intersection of 1 outer surface of antenna house model and fuselage ring can also be drawn using CATIA software, as antenna house mould
The wire of type outer surface, it is to be understood that antenna cover structure is irregular in the present embodiment and covers multiple fuselage rings, passes through
After step 1), there will be several vertical 2 lines of wire on antenna house model.
It should be noted that the vertical projection referred in step 2) refers to when aircraft is horizontally arranged, by aircraft stringer axis
Line is projected to underface, which falls in just on the antenna house model 1 below airframe, thus in antenna house model
Several stringer lines 3 are obtained on outer surface, after step 2), there will be several on 1 outer surface of antenna house model
Horizontal stringer line 3.It is understood that said reference face is parallel to horizontal plane when aircraft level is parked, above-mentioned plumb cut is
Perpendicular to the face of horizontal plane.
It is understood that frame is horizontal skeleton for airframe, stringer is longitudinal framework, it is above-mentioned respectively
Frame and long joist axial line are projected to antenna house, and several criss-cross latitude and longitude can be made on antenna house model outer surface.
Should be noted that above-mentioned steps 1)~4) in, the operation carried out on model by software is answered for determination
Become the position of piece patch, later the step of for the operation on material object.
Method of the compasses, laser level that the present invention uses in conjunction with CATIA V5 software positions, and measures and draws
Line greatly improves the accuracy that the large-size antennae cover foil gauge patch location with complex appearance determines, and operates letter
Just, it improves work efficiency.
The present invention is suitable for the positioning of the various types antenna house, radar cover outer surface point of aircraft outer surface assembly.
The present invention is that the new antenna cover inner surface foil gauge patch location of one kind determines method, complicated especially for having
The antenna house of shape.
It should be further noted that " illustrating " all in the present embodiment include drawn on model lines and point and
Projection signal is carried out by the way of laser projection on material object and draws lines；All " projection line " is referred both on model or is tested
The projection line of fuselage frame and long joist axial line in antenna cover outer surface on part；All " subpoint " refers both to answer on model or on testpieces
Become the point that piece patch location is projected out along normal direction to antenna cover outer surface；All " intersection point " refers both on model or testpieces
The intersection point of upper fuselage frame and long joist axial line in antenna cover outer surface projection line.
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (1)
1. a kind of antenna cover inner surface foil gauge patch location determines method, it is known that the model of the antenna house and foil gauge patch position
Set the position on model, it is known that the connection relationship of the antenna house and airframe characterized by comprising
1) antenna house model is assembled on airframe models according to positional relationship, by the frame of the airframe of antenna house covering position
Frame projects to the outer surface of antenna house model, forms wire；
2) by the long joist axial line upright projection of the airframe of antenna house covering position to the outer surface of antenna house model, length is formed
Purlin line；
3) intersection point of above-mentioned wire and stringer line is marked out in the model outer surface of antenna house；
4) according to foil gauge patch location coordinate, all foil gauge patches position is illustrated in the antenna house mold inner surfaces
It sets, foil gauge patch location in antenna house mold inner surfaces is projected to form projection along normal direction to antenna house model outer surface
Point records distance d1 and distance d2 of each subpoint away from the two nearest intersection points formed in the step 3)；
5) position line of fuselage frame Yu fuselage stringer is illustrated in the aircraft fuselage skin of installation antenna house；
6) antenna house is installed to the fuselage outer surface, the fuselage frame of the fuselage outer surface in the step 5) and fuselage is long
The position line projection of purlin is simultaneously indicated on the antenna cover outer surface, and multiple fuselage frames and fuselage are formed on antenna cover outer surface
The intersection point of the projection line of the stringer position line；
7) friendship of antenna house model outer surface in the step 3) is corresponded to the intersection point in the step 6) on antenna cover outer surface
Point, then the distance d1 and distance d2 by each subpoint determined in the step 4) away from two nearest projection line intersection points are determining
Practical subpoint on antenna house out；
8) subpoint inner surface on testpieces is projected and is made marks along normal direction with laser pen, mark position is to strain
The practical patch location of piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811502502.9A CN109533392A (en) | 2018-12-07 | 2018-12-07 | A kind of antenna cover inner surface foil gauge patch location determines method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811502502.9A CN109533392A (en) | 2018-12-07 | 2018-12-07 | A kind of antenna cover inner surface foil gauge patch location determines method |
Publications (1)
| Publication Number | Publication Date |
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| CN109533392A true CN109533392A (en) | 2019-03-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201811502502.9A Pending CN109533392A (en) | 2018-12-07 | 2018-12-07 | A kind of antenna cover inner surface foil gauge patch location determines method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110254744A (en) * | 2019-05-17 | 2019-09-20 | 陕西飞机工业（集团）有限公司 | A kind of principal and subordinate wheel linkage mechanism method of adjustment |
| CN113983907A (en) * | 2021-10-12 | 2022-01-28 | 江西洪都航空工业集团有限责任公司 | Design, manufacture and use method of complex skin part checking fixture |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104103913A (en) * | 2014-06-18 | 2014-10-15 | 南京信息工程大学 | Small-sized plane reversed F loading array antenna |
| US20170129588A1 (en) * | 2015-09-25 | 2017-05-11 | Howard R. Verillion, JR. | Truss-Reinforced Radome Crown Structure |
| CN107014669A (en) * | 2017-03-30 | 2017-08-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of radome test load(ing) point determines method |
| CN107063837A (en) * | 2017-03-23 | 2017-08-18 | 西安飞机工业（集团）有限责任公司 | A kind of radome test load(ing) point determines method |
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2018
- 2018-12-07 CN CN201811502502.9A patent/CN109533392A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104103913A (en) * | 2014-06-18 | 2014-10-15 | 南京信息工程大学 | Small-sized plane reversed F loading array antenna |
| US20170129588A1 (en) * | 2015-09-25 | 2017-05-11 | Howard R. Verillion, JR. | Truss-Reinforced Radome Crown Structure |
| CN107063837A (en) * | 2017-03-23 | 2017-08-18 | 西安飞机工业（集团）有限责任公司 | A kind of radome test load(ing) point determines method |
| CN107014669A (en) * | 2017-03-30 | 2017-08-04 | 中国航空工业集团公司西安飞机设计研究所 | A kind of radome test load(ing) point determines method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110254744A (en) * | 2019-05-17 | 2019-09-20 | 陕西飞机工业（集团）有限公司 | A kind of principal and subordinate wheel linkage mechanism method of adjustment |
| CN113983907A (en) * | 2021-10-12 | 2022-01-28 | 江西洪都航空工业集团有限责任公司 | Design, manufacture and use method of complex skin part checking fixture |
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Application publication date: 20190329 |
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