CN109885899A - The extracting method of spacecraft heat-control multilayer graph data - Google Patents
The extracting method of spacecraft heat-control multilayer graph data Download PDFInfo
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- CN109885899A CN109885899A CN201910080354.4A CN201910080354A CN109885899A CN 109885899 A CN109885899 A CN 109885899A CN 201910080354 A CN201910080354 A CN 201910080354A CN 109885899 A CN109885899 A CN 109885899A
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Abstract
The present invention relates to a kind of spacecraft heat-control multilayer extracting graphics data methods, this method realizes the rapidly extracting of heat-control multilayer graph data based on the drafting systems secondary development such as AutoCAD, mainly comprise the steps that a. calculates the length of all line segments, including curve and straight line；B. the quantity of all points of multilayer contoured interior is calculated；C. adjust automatically longest straight flange is horizontal, measures the overall length and beam overall of figure under the state；D. all 20mm × 20mm are calculated and by the square quantity of filling processing.The present invention solves the problems, such as spacecraft heat-control multilayer graph data rapidly extracting, is not necessarily to personnel's manual measurement and calculating, improves work efficiency, and makes man-hour calculation for heat-control multilayer and provides data.
Description
Technical field
The present invention relates to a kind of spacecraft heat-control multilayer extracting graphics data method, this method may be directly applied to spacecraft
Heat-control multilayer production field.
Background technique
Spacecraft develops task and increases sharply in recent years, also increasingly increases the demand of heat-control multilayer, the life to heat-control multilayer
It produces efficiency and production capacity is proposed challenge.In order to more accurately carry out technique adjustment, design efficiency promotes target, rational meter
Draw and provide operator and examine reference standard etc., need it is more acurrate heat-control multilayer processing time matrix is effectively performed, calculating work
When need the basic data of heat-control multilayer figure, to guarantee the normal development of subsequent man-hour calculation.Due to carrying out basis by hand
The measurement and calculating of data are excessively cumbersome, and the extraction of data is rapidly completed by the method for area of computer aided graphics process, can have
Effect improves working efficiency.
Summary of the invention
The purpose of the present invention is to provide a kind of spacecraft heat-control multilayer extracting graphics data method, this method is directly applied
In heat-control multilayer processing time matrix.
Spacecraft heat-control multilayer extracting graphics data method, including the following contents:
1) length of all line segments is calculated
Line segment length all on figure is measured, including curve and straight line, closing or non-close line segment, and to institute
There is the length of line segment to sum；
2) quantity of all points of multilayer contoured interior is calculated
In heat-control multilayer figure, the position for the pin hole being arranged in corresponding multilayer is put, is calculated all in graph outline
The quantity of point obtains the pin hole number for needing to process；
3) overall length and beam overall of multi-layer graphical are measured
The longest straight flange of adjust automatically figure is horizontal, measures the overall length and beam overall of figure under the state；
4) all 20mm × 20mm are calculated and by the square quantity of filling processing
In heat-control multilayer figure, 20mm × 20mm simultaneously represents grounding assembly by the square that filling is handled, and calculates the party
The quantity of block obtains grounding assembly quantity.
Method operating procedure of the invention is simple, processing time matrix side when can be made by the extraction of data for multilayer
The basis of method.
Detailed description of the invention
Fig. 1 is the graphical examples for the spacecraft heat-control multilayer being applicable in the method for the present invention.
Specific embodiment
Spacecraft heat-control multilayer extracting graphics data method is further described with reference to the accompanying drawing.The present invention passes through
Following steps are realized:
1) length of all line segments is calculated
Line segment length all on figure is measured, including curve and straight line, straightway AB, BC as shown in figure 1,
The length of DE, EF, FA, HI, JK, the length of circular arc C D and the perimeter of circle G, and sum；Such as straightway AB long 100mm, BC long
50mm, DE long 20mm, EF long 100mm, FA long 150mm, JK long 30mm, HI long 30mm, circular arc C D long 160mm, circle G perimeter
60mm.So multilayer line segment total length is AB+BC+CD+DE+EF+FA+JK+HI+G=700mm.
2) quantity of all points of multilayer contoured interior is calculated
In heat-control multilayer figure, point represents pin hole, and the quantity for calculating point all in graph outline obtains needing to add
The pin hole number of work, pin quantity 25, all the points as shown in figure 1；
3) overall length and beam overall of measurement pattern
The longest straight flange of adjust automatically figure is horizontal, measures the overall length and beam overall of figure under the state, and AF is most as shown in figure 1
Long straight line adjusts its level, i.e. the length of line segment AB is beam overall, and line segment AC is overall length；
4) all 20mm × 20mm are calculated and by the square quantity of filling processing
In heat-control multilayer figure, 20mm × 20mm simultaneously represents grounding assembly by the square that filling is handled, and calculates the party
The quantity of block obtains grounding assembly quantity, and grounding assembly quantity is 3 as shown in figure 1.
Although the detailed description and description of the specific embodiments of the present invention are given above, it should be noted that
We can carry out various equivalent changes and modification to above embodiment according to the concept of the present invention, and generated function is made
It, should all be within protection scope of the present invention when with the spirit still covered without departing from specification and attached drawing.
Claims (1)
1. spacecraft heat-control multilayer extracting graphics data method, comprising the following steps:
1) length of all line segments is calculated
Line segment length all on figure is measured, including curve and straight line, closing or non-close line segment, and summed；
2) quantity of all points of multilayer contoured interior is calculated
In heat-control multilayer figure, point represents pin hole, and the quantity for calculating point all in graph outline obtains what needs were processed
Pin hole number；
3) overall length and beam overall of measurement pattern
The longest straight flange of adjust automatically figure is horizontal, measures the overall length and beam overall of figure under the state；
4) all 20mm × 20mm are calculated and by the square quantity of filling processing
In heat-control multilayer figure, 20mm × 20mm simultaneously represents grounding assembly by the square that filling is handled, and calculates the square
Quantity obtains grounding assembly quantity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910080354.4A CN109885899A (en) | 2019-01-28 | 2019-01-28 | The extracting method of spacecraft heat-control multilayer graph data |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910080354.4A CN109885899A (en) | 2019-01-28 | 2019-01-28 | The extracting method of spacecraft heat-control multilayer graph data |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109885899A true CN109885899A (en) | 2019-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910080354.4A Pending CN109885899A (en) | 2019-01-28 | 2019-01-28 | The extracting method of spacecraft heat-control multilayer graph data |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112015139A (en) * | 2020-09-01 | 2020-12-01 | 北京卫星环境工程研究所 | Method, device, equipment and storage medium for automatically manufacturing thermal control multilayer of spacecraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04267484A (en) * | 1991-02-22 | 1992-09-24 | Nec Corp | Cost calculator of sheet metal product |
| JPH07224534A (en) * | 1994-02-14 | 1995-08-22 | Sekisui House Ltd | Manhour estimation device |
| JP2009282803A (en) * | 2008-05-23 | 2009-12-03 | Murata Mach Ltd | Plate processing time estimator and device for generating nesting order |
| JP2010231632A (en) * | 2009-03-27 | 2010-10-14 | Fujitsu Ltd | Man-hour estimation support program, man-hour estimation support device, and man-hour estimation support method |
| US20150127480A1 (en) * | 2013-10-17 | 2015-05-07 | Plethora Corporation | Method for quoting part production |
-
2019
- 2019-01-28 CN CN201910080354.4A patent/CN109885899A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04267484A (en) * | 1991-02-22 | 1992-09-24 | Nec Corp | Cost calculator of sheet metal product |
| JPH07224534A (en) * | 1994-02-14 | 1995-08-22 | Sekisui House Ltd | Manhour estimation device |
| JP2009282803A (en) * | 2008-05-23 | 2009-12-03 | Murata Mach Ltd | Plate processing time estimator and device for generating nesting order |
| JP2010231632A (en) * | 2009-03-27 | 2010-10-14 | Fujitsu Ltd | Man-hour estimation support program, man-hour estimation support device, and man-hour estimation support method |
| US20150127480A1 (en) * | 2013-10-17 | 2015-05-07 | Plethora Corporation | Method for quoting part production |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112015139A (en) * | 2020-09-01 | 2020-12-01 | 北京卫星环境工程研究所 | Method, device, equipment and storage medium for automatically manufacturing thermal control multilayer of spacecraft |
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