CN105223003A - Bundle some top load inclined push type chargers more - Google Patents
Bundle some top load inclined push type chargers more Download PDFInfo
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- CN105223003A CN105223003A CN201410264700.1A CN201410264700A CN105223003A CN 105223003 A CN105223003 A CN 105223003A CN 201410264700 A CN201410264700 A CN 201410264700A CN 105223003 A CN105223003 A CN 105223003A
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- load
- loading equipemtn
- frock
- test
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Abstract
The present invention relates to finite element analysis technology, be specifically related to one and bundle some top load inclined push type chargers more.Comprise: step power transmission frock (20), oblique column (23), P
1~ P
8loading equipemtn (24), test platform (25), ground (29), P
13~ P
16loading equipemtn (22), P
9~ P
12loading equipemtn (21), load base (30), wedge shaped support (31), 400 tons of pressure type dynamometers (32), power transmission depression bar (33), high-mechanic ball head nest combination (35), loads frock (34); P
1~ P
8loading equipemtn (24), provides axial load up; Load frock (34) joint test part, provide oblique load upwards to testpieces.Adopt and of the present inventionly bundle some top load inclined push type chargers more and complete binding low temperature associating slow test before core level smoothly, for the slow test of subsequent models low temperature enforcement and carry out and established firmly experimental technique deposit.
Description
Technical field
The present invention relates to finite element analysis technology, be specifically related to one and bundle some top load inclined push type chargers more.
Technical background
Along with continuous progress and the development of Models For Space Science And Technology, large-scale and even the heavy launcher of each scientific and technological power development is an inexorable trend of world's rocket development, low temp fuel is the propelling energy of contemporary advanced space vehicle, these fuel are contained in the tank of supercharging, and tank is in production, storage, lifting, park, transport and flight course will bear axial compression, moment of flexure, shearing, the load such as interior pressure and temperature, so tank structural strength in use, rigidity and low temperature combination property are to design and manufacture extremely important, need the checking by low temperature slow test.
At present, carrier rocket of new generation large-scale tank low temperature slow test method is applicable to the tank low temperature slow test method of routine.Usually carrying out in low temperature slow test examination Rocket tank, the force transferring structure of the load such as the axial compression that tank bears, moment of flexure, shearing is boundary condition simulation part, and non-genuine power transmission border structure part; The applying that test requirement lower end, border is clamped, upper end realizes the load such as axial compression, moment of flexure, shearing by general static loading equipment; Interior pressure realizes the applying of inner pressuring load by spirit pillow supercharging before tank, and the bearing frame building gantry frame type can meet test loading demand.
For bundling low temperature associating slow test project before core level, except the applying of inner pressuring load is substantially identical with Normal practice, but technology and the experience of just low temperature slow test in the past can not be indiscriminately imitated completely, more not having can the external similar experimental technique of reference and method, therefore must according to the structure of the Long March No. five rockets self, load, the feature such as environment and border, and the actual conditions such as field condition and auxiliary facility are implemented in the test of large delivery test site, Tianjin, strictly carry out many-side to consider, and around the accuracy that test load applies, experimental scale, difficulty is implemented in test, test period, test funds etc., design studies goes out a set ofly to meet this Project R&D stage, the large-scale tank suspension type low temperature slow test method that in low temperature slow test project, difficulty is maximum.
Testpieces installation situation before core level required by binding low temperature associating slow test task is shown in Fig. 1, multi-section section associating assembly in low temperature Combined Trials, bundlees brevicone 2 before brevicone 4 after bearing 5, one-level oxygen case, one-level oxygen case 3, one-level oxygen case before brevicone 7, one-level inter-tank section 6,4 before comprising one-level hydrogen case.Apply connected load and comprise the rear end face sectional axis compressive load of brevicone 7 and the inner pressuring load of one-level oxygen case 3 before centre-point load on 4 binding bearings 5, one-level hydrogen case.Before test border requires, the upper surface on transition rings border 1 is connected with test built-in boundary 8.Structure of participating in the experiment required by this project is multi-section section associating assembly, and test setting height(from bottom) also can increase a lot naturally thereupon; In order to make one-level oxygen case 3 be in low temperature environment near the regional area of front binding 4, then testpieces just must put installation, and test requirement upper end, border is clamped simultaneously; The comparatively near and single-point load of binding bearing 5 concentrated force load applying point distance test (DT) part reaches 300 tons; Add the sectional axis compressive load of brevicone 7 before one-level hydrogen case, the axial load that test installation frame need balance is more than 1240 tons; Consider the degree of difficulty of the field conditions such as the test platform size of test site limits, ground hard point tonnage is little simultaneously, all bring huge challenge to plan design and test implementation process.
Summary of the invention
Goal of the invention
The object of the present invention is to provide one to bundle some top load inclined push type chargers, for the loading in low temperature slow test more.
Technical scheme
One bundlees some top load inclined push type chargers more, wherein: comprising: step power transmission frock, oblique column, P
1~ P
8loading equipemtn, test platform, ground, P
13~ P
16loading equipemtn, P
9~ P
12loading equipemtn, load base, wedge shaped support, 400 tons of pressure type dynamometers, power transmission depression bar, high-mechanic ball head nest combines, and loads frock;
Wherein, test platform is arranged on ground, and test platform arranges P
1~ P
8loading equipemtn, provides axial load up, P
1~ P
8loading equipemtn upper end connected unit stepwise power transmission frock, for for testpieces transmitted load;
At test platform surrounding quadrant place, load base is set, on load base, successively up wedge shaped support is set, P
9~ P
12loading equipemtn, 400 tons of pressure type dynamometers, power transmission depression bar, high-mechanic ball head nest combines, and loads frock; Power transmission depression bar top is ball head structure, and the socket arrangement combining downside with high-mechanic ball head nest coordinates, and in high-mechanic ball head nest combination upper end, arranges loading frock, loads frock joint test part, provide oblique load upwards to testpieces.
One as above bundlees a top load inclined push type charger more, wherein: along test platform radially outward, in the outside of high-mechanic ball head nest combination, connects the P providing horizontal load
13~ P
16loading equipemtn, P
13~ P
16loading equipemtn is by oblique upright supports.
One as above bundlees a top load inclined push type charger more, wherein: described oblique load is upwards in vertical direction with 7 degree of angles, and angle is produced by wedge shaped support.
Beneficial effect
Adopt and of the present inventionly bundle some top load inclined push type chargers more and complete binding low temperature associating slow test before core level smoothly, for the slow test of subsequent models low temperature enforcement and carry out and established firmly experimental technique deposit.In whole process of the test, test each system run all right, meet testing requirements, and reach test examination object, satisfactorily complete problem task.The success of this test is significant to the smooth development of whole model, and this problem is the low temperature associating slow test that the large-scale tank multi-section section associating assembly that history is carried out for the first time developed by my institute's rocket, multiple binding concentrated force loads simultaneously simultaneously.Examine structure more really, based under the connected load effect bundling concentrated force and real structure be power transmission border, at low temperature environment temperature, oxygen case meets requirement of strength design near the axial compression unstability intensity of the regional area of front binding and structural stress, and provides foundation and reference for the similar pilot project in other Project R&D processes.
Accompanying drawing explanation
Before Fig. 1 core level, binding low temperature static(al) Combined Trials loads and requires schematic diagram;
Fig. 2 is of the present invention bundlees some top load inclined push type charger schematic diagram more;
Fig. 3 bundlees a concentrated force load vector exploded relationship.
In Fig. 1, transition rings border before 1-, brevicone before 2-one-level oxygen case, 3-one-level oxygen case, brevicone after 4-one-level oxygen case, 5-bundlees bearing, 6-one-level inter-tank section, brevicone before 7-one-level hydrogen case, and 8-tests built-in boundary;
In Fig. 2, brevicone before 19-one-level hydrogen case, 20-step power transmission frock, 21-P
9~ P
12loading equipemtn, 22-P
13~ P
16loading equipemtn, the oblique column of 23-, 24-P
1~ P
8loading equipemtn, 25-test platform, 26-ground hard point, 28-load track, 29-ground, 30-load base, 31-wedge shaped support, 32-400 ton pressure type dynamometer, 33-power transmission depression bar, 34-loads frock, and 35-high-mechanic ball head nest combines.
Embodiment
Below, by reference to the accompanying drawings and embodiment, the present invention is described further.
Below, with specific embodiment, the present invention is further detailed by reference to the accompanying drawings.
According to the applying requirement about load in test mission, as can be seen from Figure 1, test load comprises the centre-point load N on rear end face sectional axis compressive load F and 4 binding bearing 5 of brevicone 7 before one-level oxygen case 3 pneumatic die cushion pressure load P, one-level hydrogen case altogether
4and N
6.Test axis compressive load F and binding point concentrated force load adopt 16 passage automatic synchronization loading systems to realize, force cell is used to measure load, and according to Q/Y316-2009 " guided missile and carrier rocket finite element analysis specification ", load in charter is scaled the load that each load(ing) point applies, chooses actuator and the force cell of suitable size according to magnitude of load.
According to above-mentioned requirements, realize 16 points of load of testpieces load, be designated as P respectively
1~ P
16; Below with regard to P
1~ P
16load(ing) point provides the corresponding relation between the load of each load(ing) point and test load respectively.
(1) P
1~ P
8the relation of the point of load and axial compression load F:
P
1＝P
2＝…＝P
8＝F/8
(2) P
9~ P
16the point of load and binding concentrated force load N
4and N
6relation:
The vector correlation of single binding point concentrated force load as shown in Figure 3, with P
13, P
9for example illustrates, thus obtain:
Table 1 pair test load implementation method has been described in detail.
Table 1 test load implementation method
Test loading procedure is such, treat that tank liquid nitrogen is filled into the liquid level required by test, each loading system connects ready, then combines assembling test part according to the requirement about slow test loading procedure in Q/Y316-2009 " guided missile and carrier rocket finite element analysis specification " to multi-section section and carry out multistage loadings and measure step by step.
As shown in Figure 2, of the present inventionly bundle some top load inclined push type chargers more and comprise: step power transmission frock 20, oblique column 23, P
1~ P
8loading equipemtn 24, test platform 25, ground 29,
P
13~ P
16loading equipemtn 22, P
9~ P
12loading equipemtn 21, load base 30, wedge shaped support 31,400 tons of pressure type dynamometers 32, power transmission depression bar 33, high-mechanic ball head nest combination 35, loads frock 34;
Wherein, test platform 25 is arranged on ground 29, and test platform 25 arranges P
1~ P
8loading equipemtn 24, provides axial load up, P
1~ P
8loading equipemtn 24 upper end connected unit stepwise power transmission frock 20, for for testpieces transmitted load;
At test platform 25 surrounding quadrant place, load base 30 is set, on load base 30, wedge shaped support 31, P is up set successively
9~ P
12loading equipemtn 21,400 tons of pressure type dynamometers 32, power transmission depression bar 33, high-mechanic ball head nest combination 35, loads frock 34; Power transmission depression bar 33 top is ball head structure, the socket arrangement combined on the downside of in the of 35 with high-mechanic ball head nest coordinates, 35 upper ends are combined at high-mechanic ball head nest, arrange and load frock 34, load frock 34 joint test part, there is provided oblique load upwards to testpieces, this load is in vertical direction with 7 degree of angles herein, and angle is produced by wedge shaped support 31;
Along test platform 25 radially outward, in the outside of high-mechanic ball head nest combination 35, the P that horizontal load is provided is connected
13~ P
16loading equipemtn 22, P
13~ P
16loading equipemtn 22 is supported by oblique column 23.
Adopt and of the present inventionly bundle some top load inclined push type chargers more and complete binding low temperature associating slow test before core level smoothly, for the slow test of subsequent models low temperature enforcement and carry out and established firmly experimental technique deposit.
Although bundle some top load inclined push type chargers more by above-described embodiment be described in detail of the present invention, but above-mentioned explanation is not limitation of the invention, without departing from the spirit and scope of the invention, various distortion and change can be carried out, such as, optimized method can be selected in the various methods of prior art.
Claims (3)
1. the point of binding more than a top load inclined push type charger, is characterized in that: comprising: step power transmission frock (20), oblique column (23), P
1~ P
8loading equipemtn (24), test platform (25), ground (29), P
13~ P
16loading equipemtn (22), P
9~ P
12loading equipemtn (21), load base (30), wedge shaped support (31), 400 tons of pressure type dynamometers (32), power transmission depression bar (33), high-mechanic ball head nest combination (35), loads frock (34);
Wherein, test platform (25) is arranged on ground (29), and test platform (25) arranges P
1~ P
8loading equipemtn (24), provides axial load up, P
1~ P
8loading equipemtn (24) upper end connected unit stepwise power transmission frock (20), for for testpieces transmitted load;
At test platform (25) surrounding quadrant place, load base (30) is set, on load base (30), wedge shaped support (31) is up set successively, P
9~ P
12loading equipemtn (21), 400 tons of pressure type dynamometers (32), power transmission depression bar (33), high-mechanic ball head nest combination (35), loads frock (34); Power transmission depression bar (33) top is ball head structure, the socket arrangement combining (35) downside with high-mechanic ball head nest coordinates, in high-mechanic ball head nest combination (35) upper end, arrange and load frock (34), load frock (34) joint test part, provide oblique load upwards to testpieces.
2. one as claimed in claim 1 bundlees some top load inclined push type chargers more, it is characterized in that: along test platform (25) radially outward, in the outside of high-mechanic ball head nest combination (35), connects the P providing horizontal load
13~ P
16loading equipemtn (22), P
13~ P
16loading equipemtn (22) is supported by oblique column (23).
3. one as claimed in claim 1 bundlees some top load inclined push type chargers more, it is characterized in that: described oblique load is upwards in vertical direction with 7 degree of angles, and angle is produced by wedge shaped support (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410264700.1A CN105223003A (en) | 2014-06-13 | 2014-06-13 | Bundle some top load inclined push type chargers more |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410264700.1A CN105223003A (en) | 2014-06-13 | 2014-06-13 | Bundle some top load inclined push type chargers more |
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|---|---|
| CN105223003A true CN105223003A (en) | 2016-01-06 |
Family
ID=54992080
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|---|---|---|---|
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106706284A (en) * | 2016-11-23 | 2017-05-24 | 上海宇航***工程研究所 | Simplified verification method for bearing capacity of support type multi-sphere storage box |
| CN107702903A (en) * | 2017-09-18 | 2018-02-16 | 上海航天精密机械研究所 | A kind of bending resistance expandable type testing platform system with aiding support |
| CN109752155A (en) * | 2019-01-08 | 2019-05-14 | 上海航天精密机械研究所 | Structural member slow test fixed boundary freedom degree discharges system |
| CN110793799A (en) * | 2019-11-22 | 2020-02-14 | 西安航天动力技术研究所 | Cable cover and cable support combined loading test device and method for simulating internal pressure load |
| CN110940574A (en) * | 2019-12-01 | 2020-03-31 | 西安航天动力测控技术研究所 | Multipoint loading stress application cap for static test |
| CN112213088A (en) * | 2020-09-22 | 2021-01-12 | 上海航天精密机械研究所 | Cabin structure compression-shear coupling load test device |
| CN113702152A (en) * | 2021-07-30 | 2021-11-26 | 中国航空工业集团公司济南特种结构研究所 | Static test direction adjusting structure for 16 channels |
| WO2023123731A1 (en) * | 2021-12-31 | 2023-07-06 | 北京空间机电研究所 | Truss-type structure loading device and method for static test of spacecraft hull propulsion module |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106706284A (en) * | 2016-11-23 | 2017-05-24 | 上海宇航***工程研究所 | Simplified verification method for bearing capacity of support type multi-sphere storage box |
| CN107702903A (en) * | 2017-09-18 | 2018-02-16 | 上海航天精密机械研究所 | A kind of bending resistance expandable type testing platform system with aiding support |
| CN107702903B (en) * | 2017-09-18 | 2020-05-15 | 上海航天精密机械研究所 | Bending resistance extensible type test platform system with auxiliary support |
| CN109752155A (en) * | 2019-01-08 | 2019-05-14 | 上海航天精密机械研究所 | Structural member slow test fixed boundary freedom degree discharges system |
| CN109752155B (en) * | 2019-01-08 | 2021-02-02 | 上海航天精密机械研究所 | Fixed boundary freedom degree release system for static test of structural part |
| CN110793799A (en) * | 2019-11-22 | 2020-02-14 | 西安航天动力技术研究所 | Cable cover and cable support combined loading test device and method for simulating internal pressure load |
| CN110940574A (en) * | 2019-12-01 | 2020-03-31 | 西安航天动力测控技术研究所 | Multipoint loading stress application cap for static test |
| CN112213088A (en) * | 2020-09-22 | 2021-01-12 | 上海航天精密机械研究所 | Cabin structure compression-shear coupling load test device |
| CN113702152A (en) * | 2021-07-30 | 2021-11-26 | 中国航空工业集团公司济南特种结构研究所 | Static test direction adjusting structure for 16 channels |
| WO2023123731A1 (en) * | 2021-12-31 | 2023-07-06 | 北京空间机电研究所 | Truss-type structure loading device and method for static test of spacecraft hull propulsion module |
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Inventor after: Yang Rong Inventor after: Liu Yanmao Inventor after: Guo Bing Inventor after: Gu Haibei Inventor after: Yin Wei Inventor after: Wang Feiran Inventor after: Zheng Bin Inventor after: Zhang Kai Inventor after: Xu Guoliang Inventor after: Zhang Hui Inventor after: Zhu Yuqiang Inventor after: Wu Bing Inventor after: Gong Shuying Inventor after: Jiang Yating Inventor after: Ding Wenqi Inventor after: Wang Limin Inventor after: Wang Jue Inventor after: Li Dong Inventor after: Zhang Zhengping Inventor after: Zhu Xiquan Inventor after: Bai Lu Inventor after: Du Jun Inventor after: Ni Jingda Inventor after: Wang Hongbo Inventor after: Liu Yantao Inventor after: Chen Hao Inventor after: Mao Lina Inventor before: Yang Rong Inventor before: Liu Yanmao Inventor before: Guo Bing Inventor before: Gu Haibei Inventor before: Yin Wei Inventor before: Wang Feiran Inventor before: Zheng Bin Inventor before: Zhang Kai Inventor before: Xu Guoliang Inventor before: Zhang Hui Inventor before: Zhu Yuqiang Inventor before: Wu Bing Inventor before: Gong Shuying Inventor before: Jiang Yating Inventor before: Ding Wenqi Inventor before: Wang Limin Inventor before: Bai Lu Inventor before: Du Jun Inventor before: Ni Jingda Inventor before: Wang Hongbo Inventor before: Liu Yantao Inventor before: Chen Hao Inventor before: Mao Lina |
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Application publication date: 20160106 |
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| RJ01 | Rejection of invention patent application after publication |