CN107063837A - A kind of radome test load(ing) point determines method - Google Patents
A kind of radome test load(ing) point determines method Download PDFInfo
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- CN107063837A CN107063837A CN201710178694.1A CN201710178694A CN107063837A CN 107063837 A CN107063837 A CN 107063837A CN 201710178694 A CN201710178694 A CN 201710178694A CN 107063837 A CN107063837 A CN 107063837A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/0202—Control of the test
- G01N2203/0208—Specific programs of loading, e.g. incremental loading or pre-loading
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Abstract
Method is determined the present invention relates to a kind of radome test load(ing) point, belongs to aircraft test field of measuring technique.Software is borrowed to draw fuselage frame, long joist axial line respectively, projection line in antenna house profile of loading Position, fuselage frame and long joist axial line and cross load(ing) point tangent plane intersection in antenna house profile；All intersections in figure are drawn on fuselage and radome test part by laser level afterwards；Finally, the particular location of load(ing) point on testpieces is finally determined to the position relationship of related intersection according to load(ing) point in figure.The method that the laser level that the present invention is used is combined with software is positioned, and is measured and is rule, and greatly improves the accuracy that the large-scale antenna dome loading Position with complex appearance is determined, and easy to operate, improves operating efficiency.The positioning of all kinds antenna house, radar cover outer surface point that are assembled suitable for aircraft outer surface.
Description
Technical field
The invention belongs to aircraft test field of measuring technique, and in particular to a kind of radome test load(ing) point determines method.
Background technology
Antenna house is the more commonly used part in aircaft configuration, the aerodynamic loading loaded for being mainly derived from its surface,
Generally its structure stress is simulated when slow test is verified by arranging a number of load(ing) point in its outer surface.Usually can
The structure stress of enough more real artificial antenna covers, in the case where experimental condition allows, is arranged large number of as far as possible
Experiment load(ing) point.The quantity of load(ing) point and and position distribution and the distributed load size direction of antenna cover outer surface have very big
Relation, is provided typically by LOAD FOR, and distribution more disperses.
Antenna house generally uses many cambered shells of composite, and profile is more complicated, therefore how accurate on testpieces surface
The position for really finding out load(ing) point is always the difficult point for perplexing antenna cover structure slow test.All the time, the surface of antenna house adds
Loading point position determines it is the method by tensing thin silk thread on antenna house surface on the basis of airframe structure, and such a method is often
Straight skidding due to silk thread along antenna house profile, loading point tolerance is larger；It is such as many especially for the complex curved surface of profile
The large-scale antenna dome of curvature profile, error can be bigger；Another method is that a plurality of related song is drawn on its surface by compasses
Line, it is spherical or almost spherical small size antenna cover that such a method, which is applied to curved surface, for load(ing) point more macrotype spherical day
Irdome, workload is very huge, and the antenna house for many curvature profiles is really at a loss what to do.
The content of the invention
The purpose of the present invention is to propose to a kind of on the basis of the airframe structure that antenna house is installed, according to testpieces load(ing) point
Coordinate, the method for finding loading Position in radar cover outer surface exactly.The technical solution of the present invention includes following several
Individual step：
S1, in the contoured surface of antenna house model all wires are illustrated successively, the wire refers to the frame of airframe
Frame is to projecting resulting line on the antenna house；
S2, by the axis where aircraft stringer to vertical projection is done on the antenna house model, in the antenna house model
On illustrate stringer line；
S3, the coordinate according to load(ing) point, illustrate all load(ing) points on the antenna house model, record any load(ing) point
Away from the wire on nearest antenna house model apart from d1And away from the stringer line on nearest antenna house model apart from d2；
S4, fuselage wire and fuselage stringer line are illustrated in fuselage outer surface；
S5, antenna house is attached to the fuselage outer surface, by the fuselage wire of the fuselage outer surface in the step S4
Illustrate with fuselage stringer line to the antenna house；
S6, by being determined in step S3 apart from d1And apart from d2Actual loaded point is determined on the antenna house.
Preferably, the step S3 further comprises：
S301A, successively excessively any load(ing) point do fuselage cross section, and the fuselage cross section is parallel to where fuselage ring
Face, and illustrate on the antenna house model ring intersection in the fuselage cross section and the antenna house model；
S302A, on the ring intersection, measurement load(ing) point thereon is away from the stringer line l on nearest antenna house model2
Apart from d2；
S303A, the measurement nearest stringer line l2With away from stringer line l2The distance of nearest wire, as load(ing) point
Away from the wire l on nearest antenna house model1Apart from d1。
Preferably, the step S3 further comprises：
S301B, successively excessively any load(ing) point do fuselage vertical section, and the fuselage vertical section is where fuselage ring
Face and parallel to fuselage stringer, and illustrate on the antenna house model fuselage vertical section and the antenna house model
Longitudinal intersection；
S302B, on longitudinal intersection, measurement load(ing) point thereon is away from the wire l on nearest antenna house model1's
Apart from d1；
S303B, the measurement nearest wire l1With away from wire l1The distance of nearest stringer line, as load(ing) point away from
Stringer line l on nearest antenna house model2Apart from d2。
Preferably, the step S6 further comprises：
S601A, according on load(ing) point and antenna house model nearest wire apart from d1Illustrate that ring is handed on antenna house
Line, the ring intersection is parallel with the wire；
S602A, on the ring intersection, according to load(ing) point away from the stringer line l on nearest antenna house model2Distance
d2Determine load(ing) point.
Preferably, the step S6 further comprises：
S601B, according on load(ing) point and antenna house model nearest stringer line apart from d2Longitudinal direction is illustrated on antenna house
Intersection, longitudinal intersection is parallel with the stringer line；
S602B, on longitudinal intersection, according to load(ing) point away from the wire l on nearest antenna house model1Apart from d1
Determine load(ing) point.
By Software on Drawing fuselage and antenna house model in step S1-S3 of the present invention, and load(ing) point is carried out on the mold
The determination of position, step S4-S6 is that projective iteration is carried out on antenna house concrete structure according to the defined location.
The method that the laser level that the present invention is used is combined with CATIA V5 softwares is positioned, and is measured and is rule, pole
The accuracy that the big large-scale antenna dome loading Position improved with complex appearance is determined, and it is easy to operate, improve work
Make efficiency.
The present invention is applied to all kinds antenna house, the positioning of radar cover outer surface point that aircraft outer surface is assembled.
Brief description of the drawings
Fig. 1 is that inventive antenna cover tests the flow chart that load(ing) point determines a preferred embodiment of method.
Fig. 2 is the fuselage ring and stringer structural representation of embodiment illustrated in fig. 1 of the present invention.
Fig. 3 is the antenna house load(ing) point and stringer position relationship schematic diagram of embodiment illustrated in fig. 1 of the present invention.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
The purpose of the present invention is to propose to a kind of on the basis of the airframe structure that antenna house is installed, according to testpieces load(ing) point
Coordinate, the method for finding loading Position in radar cover outer surface exactly.Inventive antenna cover experiment load(ing) point determines method
As shown in figure 1, main include following several steps：
S1, in the contoured surface of antenna house model all wires are illustrated successively, the wire refers to the frame of airframe
Frame is to projecting resulting line on the antenna house；
S2, by the axis where aircraft stringer to vertical projection is done on the antenna house model, in the antenna house model
On illustrate stringer line；
S3, the coordinate according to load(ing) point, illustrate all load(ing) points on the antenna house model, record any load(ing) point
Away from the wire on nearest antenna house model apart from d1And away from the stringer line on nearest antenna house model apart from d2；
S4, fuselage wire and fuselage stringer line are illustrated in fuselage outer surface；
S5, antenna house is attached to the fuselage outer surface, by the fuselage wire of the fuselage outer surface in the step S4
Illustrate with fuselage stringer line to the antenna house；
S6, by being determined in step S3 apart from d1And apart from d2Actual loaded point is determined on the antenna house.
It should be noted that before step S1, the aircraft 3 d structure model with antenna house is made first, for example,
Made using CATIA softwares after structural model, because antenna house is attached to airframe outer surface, in addition to doing projection line,
Directly the intersection of the antenna house and fuselage ring can also be drawn using CATIA softwares, can as the wire of antenna house model
With understanding, antenna cover structure is irregular in the present embodiment and typically covers multiple fuselage rings, from the point of view of top view, passes through
After step S1, there will be some vertical lines on antenna house model.
It should be noted that the vertical projection referred in step S2 refers to when aircraft horizontal positioned, by aircraft stringer axle
Line is projected to surface, and the projection falls on the antenna house model above airframe just, so that in antenna house model
On obtain some stringer lines, with step S1 relative to from the point of view of top view, after step S2, on antenna house model
There will be some horizontal lines.In the alternative, doing the mode of vertical projection can also be：With antenna house model
Face on the basis of the plane for the symmetrical long joist axial line being connected with airframe models, crosses long joist axial line and makes vertically cutting for the reference plane
Face, these plumb cuts and the intersection of antenna house profile are stringer line.It is understood that when aircraft level is parked, it is above-mentioned
Reference plane is parallel to horizontal plane, and above-mentioned plumb cut is perpendicular to the face of horizontal plane.
It is understood that for airframe, framework is horizontal skeleton, stringer is longitudinal framework, as shown in Fig. 2
It is approximate it is rectangular be airframe models, thereon irregular shape for antenna house model, horizontal dotted line 0-9 represents some stringers
Axis, longitudinal dotted line circle 14- circles 21 represent some wires, above-mentioned to be projected respectively with regard to framework and stringer to antenna house, Neng Gou
Some latitude and longitude wrong from traversed by are made on antenna house model, so, it is possible to carry out irregular antenna house model accurately
Longitude and latitude is positioned.
As shown in figure 3, non-schematic diagram wire in the diagram.Step S3 is determined apart from d1And d2Further comprise：
Step S301A, successively excessively any load(ing) point do fuselage cross section, and the fuselage cross section is parallel to fuselage ring institute
Face, and illustrate on the antenna house model ring intersection in the fuselage cross section and the antenna house model；
Step S302A, on the ring intersection, measurement load(ing) point thereon is away from the stringer on nearest antenna house model
Line l2Apart from d2；
Step S303A, the measurement nearest stringer line l2With away from stringer line l2The distance of nearest wire, as adds
Loading point is away from the wire l on nearest antenna house model1Apart from d1。
It is appreciated that, above-mentioned steps S301A~S303A is in order to which more accurate measurement load(ing) point is away from described nearest
The distance of wire and nearest stringer line, by do one cross load(ing) point and parallel to the ring intersection of wire after, Ke Yiyan
The ring intersection accurately measures d2, afterwards, along the nearest stringer line l2D can be accurately measured again1。
Further, step S3 also derives another alternative embodiment, as follows：
Step S301B, successively excessively any load(ing) point do fuselage vertical section, and the fuselage vertical section is perpendicular to fuselage ring institute
Face and parallel to fuselage stringer, and illustrate on the antenna house model fuselage vertical section and the antenna house mould
Longitudinal intersection of type；
Step S302B, on longitudinal intersection, measurement load(ing) point thereon is away from the wire on nearest antenna house model
l1Apart from d1；
Step S303B, the measurement nearest wire l1With away from wire l1The distance of nearest stringer line, is as loaded
Point is away from the stringer line l on nearest antenna house model2Apart from d2。
Above-mentioned steps are consistent with the rapid S301A~S303A principles of step, first determine apart from d1, then determine apart from d2。
It should be noted that in above-mentioned steps S1~S3, the operation carried out by software on model, for determining to add
The position of loading point, afterwards the step of for the operation on material object.
First, fuselage wire and fuselage stringer line are being illustrated in fuselage outer surface, and antenna house is attached to the machine
Body outer surface, also, fuselage testpieces regulation level is prevented from causing load(ing) point to be determined because putting deviation to be subsequently accurately positioned
Position is inaccurate.
Afterwards, in the step S5, on the basis of frame and long joist axial line on fuselage testpieces, using laser level
Draw respectively such as the wire and stringer line in step S1 and S2.
Before step S6, further comprise measuring in step S3 apart from d1And apart from d2By model and practical structures
Ratio zoom in and out, it is to be understood that the step can also be completed in step s3, by step S3 determine apart from d1And
Apart from d2Size as in practical structures.
For step S3 two embodiments, step S6 equally includes two kinds of embodiments, as follows respectively：
Embodiment one：
Step S601A, according on load(ing) point and antenna house model nearest wire apart from d1Ring is illustrated on antenna house
To intersection, the ring intersection is parallel with the wire；
Step S602A, on the ring intersection, according to load(ing) point away from the stringer line l on nearest antenna house model2's
Apart from d2Determine load(ing) point.
Embodiment two：
Step S601B, according on load(ing) point and antenna house model nearest stringer line apart from d2Illustrated on antenna house
Longitudinal intersection, longitudinal intersection is parallel with the stringer line；
Step S602B, on longitudinal intersection, according to load(ing) point away from the wire l on nearest antenna house model1Away from
From d1Determine load(ing) point.
It is understood that above-mentioned embodiment and embodiment in step S3 are just the opposite, by doing plus
The lines of loading point determine a dimension of load(ing) point, and another dimension for obtaining load(ing) point is measured on the lines,
And then it is capable of determining that the two-dimensional coordinate of load(ing) point.
The present invention determines method for a kind of new radome test load(ing) point, especially for the antenna with complex appearance
Cover.
The method that the laser level that the present invention is used is combined with CATIA V5 softwares is positioned, and is measured and is rule, pole
The accuracy that the big large-scale antenna dome loading Position improved with complex appearance is determined, and it is easy to operate, improve work
Make efficiency.
The present invention is applied to all kinds antenna house, the positioning of radar cover outer surface point that aircraft outer surface is assembled.
It should be further stated that, " illustrating " every in the present embodiment, which is included on model, draws lines and in reality
Projection signal is carried out on thing by the way of laser projection.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (5)
1. a kind of radome test load(ing) point determines method, it is characterised in that including：
S1, in the contoured surface of antenna house model illustrate all wires successively, the wire refer to by the framework of airframe to
Resulting line is projected on the antenna house；
S2, by the axis where aircraft stringer to vertical projection is done on the antenna house model, show on the antenna house model
Stringer of anticipating out line；
S3, the coordinate according to load(ing) point, all load(ing) points are illustrated on the antenna house model, record any load(ing) point away from most
Wire near antenna house model apart from d1And away from the stringer line on nearest antenna house model apart from d2；
S4, fuselage wire and fuselage stringer line are illustrated in fuselage outer surface；
S5, antenna house is attached to the fuselage outer surface, by the fuselage wire and machine of the fuselage outer surface in the step S4
Height purlin line is illustrated to the antenna house；
S6, by being determined in step S3 apart from d1And apart from d2Actual loaded point is determined on the antenna house.
2. radome test load(ing) point as claimed in claim 1 determines method, it is characterised in that：The step S3 is further wrapped
Include：
S301A, successively excessively any load(ing) point do fuselage cross section, the fuselage cross section parallel to the face where fuselage ring,
And the ring intersection in the fuselage cross section and the antenna house model is illustrated on the antenna house model；
S302A, on the ring intersection, measurement load(ing) point thereon is away from the stringer line l on nearest antenna house model2Away from
From d2；
S303A, the measurement nearest stringer line l2With away from stringer line l2The distance of nearest wire, as load(ing) point is away from most
Wire l near antenna house model1Apart from d1。
3. radome test load(ing) point as claimed in claim 1 determines method, it is characterised in that：The step S3 is further wrapped
Include：
S301B, successively excessively any load(ing) point do fuselage vertical section, the fuselage vertical section perpendicular to the face where fuselage ring and
Parallel to fuselage stringer, and illustrate on the antenna house model longitudinal direction of the fuselage vertical section and the antenna house model
Intersection；
S302B, on longitudinal intersection, measurement load(ing) point thereon is away from the wire l on nearest antenna house model1Distance
d1；
S303B, the measurement nearest wire l1With away from wire l1The distance of nearest stringer line, as load(ing) point is away from nearest
Antenna house model on stringer line l2Apart from d2。
4. radome test load(ing) point as claimed in claim 1 determines method, it is characterised in that：The step S6 is further wrapped
Include：
S601A, according on load(ing) point and antenna house model nearest wire apart from d1Ring intersection, institute are illustrated on antenna house
State ring intersection parallel with the wire；
S602A, on the ring intersection, according to load(ing) point away from the stringer line l on nearest antenna house model2Apart from d2Really
Make load(ing) point.
5. radome test load(ing) point as claimed in claim 1 determines method, it is characterised in that：The step S6 is further wrapped
Include：
S601B, according on load(ing) point and antenna house model nearest stringer line apart from d2Longitudinal intersection is illustrated on antenna house,
Longitudinal intersection is parallel with the stringer line；
S602B, on longitudinal intersection, according to load(ing) point away from the wire l on nearest antenna house model1Apart from d1It is determined that
Go out load(ing) point.
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| CN201710178694.1A CN107063837A (en) | 2017-03-23 | 2017-03-23 | A kind of radome test load(ing) point determines method |
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| CN201710178694.1A CN107063837A (en) | 2017-03-23 | 2017-03-23 | A kind of radome test load(ing) point determines method |
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Cited By (4)
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| 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 |
| CN107917703A (en) * | 2017-11-30 | 2018-04-17 | 江西洪都航空工业集团有限责任公司 | A kind of radome localization method of no special tooling |
| CN109533392A (en) * | 2018-12-07 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of antenna cover inner surface foil gauge patch location determines method |
| CN109649683A (en) * | 2018-12-07 | 2019-04-19 | 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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| 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 |
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| CN109533392A (en) * | 2018-12-07 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of antenna cover inner surface foil gauge patch location determines method |
| CN109649683A (en) * | 2018-12-07 | 2019-04-19 | 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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