CN105277080A - Cantilever operation platform for large-scale carrier rocket all-rocket test - Google Patents
Cantilever operation platform for large-scale carrier rocket all-rocket test Download PDFInfo
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- CN105277080A CN105277080A CN201410274261.2A CN201410274261A CN105277080A CN 105277080 A CN105277080 A CN 105277080A CN 201410274261 A CN201410274261 A CN 201410274261A CN 105277080 A CN105277080 A CN 105277080A
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Abstract
The invention relates to the all-rocket dynamics test technical field, specifically relates to a cantilever operation platform for large-scale carrier rocket all-rocket tests, and aims the solve the technical problems in an all-rocket dynamics test that gaps are formed between the rocket body and a fixed platform, so test personnel cannot operate the rocket body; the cantilever operation platform (10) is arranged between two adjacent boost motors along the outer surface of a core stage (7), and fixed with the fixed platform. The cantilever operation platform is made of hollow aluminium alloy material so as to ensure intensity and light mass, so operation personnel can conveniently operate the platform; square tubes are spliced in different quantity so as to satisfy differentiation requirements of different zones; the cantilever operation platform can cover the gap areas between the fixed platform and the rocket body, so the operation personnel can carry out various works around the rocket body and between surrounding rocket bodies.
Description
Technical field
The present invention relates to whole rocket dynamic test technical field, be specifically related to a kind of cantilevered operating platform for the test of Large Launch Vehicle whole rocket.
Background technology
CZ-5 carrier rocket is the cluster carrier rocket of China at the maximum-norm ground, its SMIS one-level diameter 5m, length 33m, and whole core level highly reaches 63m, single boost motor diameter 3.35m, length 28m.CZ-5 whole rocket modal test is also the cluster rocket body structure modal test of the domestic maximum-norm carried out, this test (the newly-built vibration tower in Tianjin) first time in Fia vibration tower carries out, test can be completed smoothly most important, but rocket enters vibration tower and is erected at after on test station, there is very large gap in rocket and tower internal fixtion platform, particularly between two boostings, define larger space, local operating personnel between boost motor and core level also cannot arrive, as shown in Figure 1, when boost motor and the docking of core level, minimum needs two people uses aid between boost motor and core level and other void area operate simultaneously, and aid also has larger weight.The rocket of small-scale mode of overlap joint plank that adopts when Beijing vibration tower is tested solved more in the past, because rocket size is little, space is apart from short, the method is feasible, but space is larger in this test, distant, operate smoothly if conventionally only overlap joint plank operating personnel are very difficult, its steadiness, security and operability all can not meet the demands.
Summary of the invention
The object of the invention is to solve in whole rocket dynamic test, space is there is between rocket rocket body and fixed platform, testing crew is difficult to the technical problem operated rocket body, provide a kind of space can filled up between rocket rocket body and fixed platform, for testing crew provides the cantilevered operating platform for the test of Large Launch Vehicle whole rocket of firm operating platform.
The present invention is achieved in that
For a cantilevered operating platform for Large Launch Vehicle whole rocket test, comprise cantilevered operating platform, cantilevered operating platform is arranged between adjacent two boost motors of core level outer surface, is fixedly connected with fixed platform.
Cantilevered operating platform as above has four covers, be arranged between No. 1 boost motor and No. 2 boost motors, between No. 2 boost motors and No. 3 boost motors, between No. 3 boost motors and No. 4 boost motors, front two cover cantilevered operating platforms are fixedly connected with eastern fixed platform, and rear two cover cantilevered operating platforms are fixedly connected with western fixed platform.
Cantilevered operating platform as above comprises elongated slot steel, short channel-section steel, wide hollow square tube assembly, narrow hollow square tube assembly, bolt and wedge; Wide hollow square tube assembly and narrow hollow square tube assembly placed side by side on fixed platform upper surface, its length direction and horizontal direction and vertical direction are all in 45 degree of angles; Narrow hollow square tube assembly is positioned at the both sides of wide hollow square tube assembly; Wide hollow square tube assembly passes between adjacent two groups of hanging steel ropes, and narrow hollow square tube assembly passes between two adjacent group hanging steel rope; Elongated slot steel and short channel-section steel are pressed in above wide hollow square tube assembly and narrow hollow square tube assembly, and elongated slot steel is arranged in the outside of short channel-section steel; Elongated slot steel and short channel-section steel two ends are separately fixed in fixed platform, are connected with fixed platform by bolt; Wedge is between channel-section steel and hollow square tube assembly.
Wide hollow square tube assembly as above is formed by connecting by three square tubes, is of a size of 100mm × 300mm × 3000mm, has seven groups; Narrow hollow square tube assembly is formed by connecting by two square tubes, is of a size of 100mm × 200mm × 3000mm, has four groups; Wide hollow square tube assembly and narrow hollow square tube assembly front end distance rocket body 100mm.
Elongated slot steel as above, short channel-section steel and wedge all adopt stainless steel material to make, and wide hollow square tube assembly and narrow hollow square tube assembly all adopt aluminum alloy materials to make.
The invention has the beneficial effects as follows:
The present invention includes cantilevered operating platform, this cantilevered operating platform structural design under the requirement meeting service condition is simple, convenient and flexible installation can not be interfered with the product of test and other system, and the scope of application is wide, and each layer fixed platform of needs operation all can use; Adopt hollow aluminium alloy material not only proof strength but also alleviate quality, enable operating personnel's handled easily; Square tube can be met the differential requirement of zones of different by varying number splicing.The cantilevered operating platform utilizing the present invention to design can cover the void area between fixed platform and rocket body, makes operating personnel carry out various operation around rocket body and between rocket body.
Accompanying drawing explanation
Fig. 1 is the layout of rocket and fixed platform in vibration tower;
Fig. 2 is the cantilevered operating platform structural representation for the test of Large Launch Vehicle whole rocket of the present invention;
Fig. 3 is the cantilevered operating platform list group cantilevered operating platform structural representation for the test of Large Launch Vehicle whole rocket of the present invention.
In figure: 1. eastern fixed platform, 2. western fixed platform, No. 3.1 boost motors, No. 4.2 boost motors, No. 5.3 boost motors, No. 6.4 boost motors, 7. core level, 8. hanging steel rope, the 9. space of rocket body and fixed platform, 10. cantilevered operating platform, 11. elongated slot steel, 12. short channel-section steels, 13. wide hollow square tube assemblys, 14. narrow hollow square tube assemblys, 15. bolts, 16. wedges, 17. planks.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the cantilevered operating platform for the test of Large Launch Vehicle whole rocket of the present invention is described in detail:
As shown in Figure 2, a kind of cantilevered operating platform for the test of Large Launch Vehicle whole rocket, comprises cantilevered operating platform 10, and cantilevered operating platform 10 is arranged between adjacent two boost motors of core level 7 outer surface, is fixedly connected with fixed platform.Cantilevered operating platform for covering the space 9 of rocket body and fixed platform, for testing crew provides firm operating platform.
In the present embodiment, cantilevered operating platform 10 has four covers, be arranged between No. 1 boost motor 3 and No. 2 boost motors 4, between No. 2 boost motors 4 and No. 3 boost motors 5, between No. 3 boost motors 5 and No. 4 boost motors 6, front two cover cantilevered operating platforms 10 are fixedly connected with eastern fixed platform 1, and rear two cover cantilevered operating platforms 10 are fixedly connected with western fixed platform 2.
As shown in Figure 3, cantilevered operating platform 10 comprises elongated slot steel 11, short channel-section steel 12, wide hollow square tube assembly 13, narrow hollow square tube assembly 14, bolt 15 and wedge 16.Hanging steel rope 8 has eight groups, is arranged in No. 1 boost motor 3 both sides, No. 2 boost motor 4 both sides, No. 3 boost motor 5 both sides and No. 4 boost motor 6 both sides.Often organize hanging steel rope 8 and have four, between adjacent two, spacing is equal.Wide hollow square tube assembly 13 and narrow hollow square tube assembly 14 placed side by side on fixed platform upper surface, its length direction and horizontal direction and vertical direction are all in 45 degree of angles.Narrow hollow square tube assembly 14 is positioned at the both sides of wide hollow square tube assembly 13.Wide hollow square tube assembly 13 passes between adjacent two groups of hanging steel ropes 8, and narrow hollow square tube assembly 14 passes between two adjacent group hanging steel rope 8.Wide hollow square tube assembly 13 and narrow hollow square tube assembly 14 are for filling up the space 9 between rocket body and fixed platform.Elongated slot steel 11 and short channel-section steel 12 are pressed in above wide hollow square tube assembly 13 and narrow hollow square tube assembly 14, and elongated slot steel 11 is arranged in the outside of short channel-section steel 12.Elongated slot steel 11 and short channel-section steel 12 two ends are separately fixed in fixed platform, are connected with fixed platform by bolt 15.Elongated slot steel 11 and short channel-section steel 12 are for fixing wide hollow square tube assembly 13 and narrow hollow square tube assembly 14.Wedge 16 between channel-section steel and hollow square tube assembly, for filling up the gap between channel-section steel and hollow square tube assembly.
In the present embodiment, wide hollow square tube assembly 13 is formed by connecting by three square tubes, is of a size of 100mm × 300mm × 3000mm, has seven groups; Narrow hollow square tube assembly 14 is formed by connecting by two square tubes, is of a size of 100mm × 200mm × 3000mm, has four groups; Wide hollow square tube assembly 13 and narrow hollow square tube assembly 14 front end distance rocket body 100mm.
Elongated slot steel 11, short channel-section steel 12 and wedge 16 all adopt stainless steel material to make, and wide hollow square tube assembly 13 and narrow hollow square tube assembly 14 all adopt aluminum alloy materials to make.
During use, wide hollow square tube assembly 13 is placed on central region in fixed platform and piles up neat, wide hollow square tube assembly 13 front end and rocket body keep 100mm safety clearance; Being placed on by narrow hollow square tube assembly 14 between adjacent two steel wire ropes with group hanging steel rope 8 and piling up neat, narrow hollow square tube assembly 14 front end and rocket body keep 100mm safety clearance; Press elongated slot steel 11 and short channel-section steel 12, and fix in two ends bolt 15 and fixed platform; Check whether there is gap between channel-section steel and hollow square tube assembly, fill in if any gap wedge 16 and prevent single sub-assembly from rocking in fact; On the stationary platform four cover cantilevered operating platforms 10 are installed according to the method described above, then an overlap joint plank 17 on adjacent two cover cantilevered operating platforms 10.
The present invention includes cantilevered operating platform 10, this cantilevered operating platform structural design under the requirement meeting service condition is simple, convenient and flexible installation can not be interfered with the product of test and other system, and the scope of application is wide, and each layer fixed platform of needs operation all can use; Adopt hollow aluminium alloy material not only proof strength but also alleviate quality, enable operating personnel's handled easily; Square tube can be met the differential requirement of zones of different by varying number splicing.The cantilevered operating platform utilizing the present invention to design can cover the void area between fixed platform and rocket body, makes operating personnel carry out various operation around rocket body and between rocket body.
Above effect is passed through repeatedly actual use and is verified, uses the carrying situation of middle cantilevered operating platform as follows:
(1) the binding docking in order to carry out boost motor and core level needs the narrowest region between boost motor and core level to operate, and the plank now between adjacent cantilever formula operating platform carries the instrument of 2 staff and 30Kg;
(2) in order to installation test equipment on the rocket body of more than platform 2m aloft needs to use lift, now often organize and cantilevered operating platform needs carry lift, 2 staff and equipment etc. that approximately 20Kg is heavy.
Through the actual weight using the operating platform of this invention design at least can carry 400Kg, and highly stable, make operating personnel can complete the binding docking of boost motor and core level and the installation of testing equipment at short notice.
Implementation method of the present invention is explained in detail above, but the present invention is not limited to above-described embodiment in conjunction with the embodiments, in the ken that those of ordinary skill in the art possess, various change can also be made under the prerequisite not departing from present inventive concept.The content be not described in detail in description of the present invention all can adopt prior art.
Claims (5)
1. the cantilevered operating platform for the test of Large Launch Vehicle whole rocket, it is characterized in that: it comprises cantilevered operating platform (10), cantilevered operating platform (10) is arranged between adjacent two boost motors of core level (7) outer surface, is fixedly connected with fixed platform.
2. the cantilevered operating platform for the test of Large Launch Vehicle whole rocket according to claim 1, it is characterized in that: described cantilevered operating platform (10) has four covers, be arranged between No. 1 boost motor (3) and No. 2 boost motors (4), between No. 2 boost motors (4) and No. 3 boost motors (5), between No. 3 boost motors (5) and No. 4 boost motors (6), front two covers cantilevered operating platform (10) are fixedly connected with eastern fixed platform (1), rear two covers cantilevered operating platform (10) are fixedly connected with western fixed platform (2).
3. the cantilevered operating platform for the test of Large Launch Vehicle whole rocket according to claim 1, is characterized in that: described cantilevered operating platform (10) comprises elongated slot steel (11), short channel-section steel (12), wide hollow square tube assembly (13), narrow hollow square tube assembly (14), bolt (15) and wedge (16); Wide hollow square tube assembly (13) and narrow hollow square tube assembly (14) placed side by side on fixed platform upper surface, its length direction and horizontal direction and vertical direction are all in 45 degree of angles; Narrow hollow square tube assembly (14) is positioned at the both sides of wide hollow square tube assembly (13); Wide hollow square tube assembly (13) is passed between adjacent two groups of hanging steel ropes (8), and narrow hollow square tube assembly (14) is passed from organizing between two adjacent hanging steel rope (8); Elongated slot steel (11) and short channel-section steel (12) are pressed in wide hollow square tube assembly (13) and narrow hollow square tube assembly (14) top, and elongated slot steel (11) is arranged in the outside of short channel-section steel (12); Elongated slot steel (11) and short channel-section steel (12) two ends are separately fixed in fixed platform, are connected with fixed platform by bolt (15); Wedge (16) is between channel-section steel and hollow square tube assembly.
4. the cantilevered operating platform for the test of Large Launch Vehicle whole rocket according to claim 3, it is characterized in that: described wide hollow square tube assembly (13) is formed by connecting by three square tubes, be of a size of 100mm × 300mm × 3000mm, have seven groups; Narrow hollow square tube assembly (14) is formed by connecting by two square tubes, is of a size of 100mm × 200mm × 3000mm, has four groups; Wide hollow square tube assembly (13) and narrow hollow square tube assembly (14) front end distance rocket body 100mm.
5. the cantilevered operating platform for the test of Large Launch Vehicle whole rocket according to claim 3, it is characterized in that: described elongated slot steel (11), short channel-section steel (12) and wedge (16) all adopt stainless steel material to make, wide hollow square tube assembly (13) and narrow hollow square tube assembly (14) all adopt aluminum alloy materials to make.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410274261.2A CN105277080B (en) | 2014-06-19 | Cantilevered operating platform for the test of Large Launch Vehicle whole rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410274261.2A CN105277080B (en) | 2014-06-19 | Cantilevered operating platform for the test of Large Launch Vehicle whole rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105277080A true CN105277080A (en) | 2016-01-27 |
| CN105277080B CN105277080B (en) | 2016-11-30 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2395059C1 (en) * | 2009-02-16 | 2010-07-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Method of bench testing of rocket catapult device in vertical launching |
| CN101941531A (en) * | 2010-09-03 | 2011-01-12 | 航天东方红卫星有限公司 | Micro-satellite assembly and disassembly method based on large-span hanging |
| CN102717900A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Micro satellite platform suitable for low orbit satellite constellation networking application |
| CN203568807U (en) * | 2013-11-25 | 2014-04-30 | 北京强度环境研究所 | Hanging type high-altitude operation platform |
| CN204008166U (en) * | 2014-06-19 | 2014-12-10 | 北京强度环境研究所 | Cantilever operating platform for the test of Large Launch Vehicle whole rocket |
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2395059C1 (en) * | 2009-02-16 | 2010-07-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Method of bench testing of rocket catapult device in vertical launching |
| CN101941531A (en) * | 2010-09-03 | 2011-01-12 | 航天东方红卫星有限公司 | Micro-satellite assembly and disassembly method based on large-span hanging |
| CN102717900A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Micro satellite platform suitable for low orbit satellite constellation networking application |
| CN203568807U (en) * | 2013-11-25 | 2014-04-30 | 北京强度环境研究所 | Hanging type high-altitude operation platform |
| CN204008166U (en) * | 2014-06-19 | 2014-12-10 | 北京强度环境研究所 | Cantilever operating platform for the test of Large Launch Vehicle whole rocket |
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