CN202994436U - Rocket diaphragm sheet storage box roll-over test apparatus - Google Patents
Rocket diaphragm sheet storage box roll-over test apparatus Download PDFInfo
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- CN202994436U CN202994436U CN 201220564077 CN201220564077U CN202994436U CN 202994436 U CN202994436 U CN 202994436U CN 201220564077 CN201220564077 CN 201220564077 CN 201220564077 U CN201220564077 U CN 201220564077U CN 202994436 U CN202994436 U CN 202994436U
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Abstract
The utility model discloses a rocket diaphragm sheet storage box roll-over test apparatus which comprises an upper ring, long screw bolts, connecting screw bolts, rotating shafts, a support seat, a lower ring, a seat rack, a directional foot wheel, a universal foot wheel, stop pins, an upper half ball, a lower half ball, and positioning screw bolts, wherein the upper half ball and the lower half ball are used for simulating a rocket storage box housing, and a storage box diaphragm sheet is clamped between the upper half ball and the lower half ball through screw bolts; the upper half ball and the lower half ball are connected with rotating shafts on the seat rack through the upper ring, the long screw bolts and the lower ring; the stop pins are mounted on the rotating shafts; and the directional foot wheel and the universal foot wheel are mounted at a bottom part of the seat rack. The rocket diaphragm sheet storage box roll-over test apparatus successfully realizes a roll-over and discharge test of the rocket diaphragm sheet storage box when the rocket diaphragm sheet storage box is in horizontal 0 degree and +/- 90 degree states.
Description
Technical field
The utility model relates to a kind of rocket diaphragm tank roll-over test device.
Background technology
By pressure gas, diaphragm is overturn in the carrier rocket emission process, thereby the fuel agent in tank is pressed in engine; In the upset performance of diaphragm and switching process, the feed flow of fuel agent size directly affects the stability of the overall emission process of rocket, even whether has influence on successful launch.Be the rationality of the design of checking diaphragm structure and theoretical analysis, grasp diaphragm upset performance and emission behavior, be necessary the diaphragm tank is carried out roll-over test with correctness, the rationality of checking diaphragm structure design proposal and process program.
Carrier rocket diaphragm tank is not of uniform size, for guaranteeing the stability of serviceability in emission process, need to carry out on ground the multiple authentication test.Diaphragm is hemispherical dome structure, and during practical work process, diaphragm is placed in the middle of spherical tank, and compressed gas effect diaphragm will be recessed state by the epirelief state turnover, simultaneously the liquid fuel agent in spherical tank be pushed away.Be the analog fuel state during ground experiment, generally adopt water as the analog fuel medium, for reducing the fuel gravity effect, pressure gas is blown into from the top simultaneously, acts on diaphragm, and the diaphragm upset extrudes the fuel of below.Existing technical scheme relates to following problem, for carrying out test of many times, adopt the bolt riveted structure between the upper and lower hemispheres of simulation tank and diaphragm, reach dozens of along circumference one circle bolt quantity, need after installation to overturn 180 ° and fill with water and overturn and get back to original state, fill with the water test installation weight and reach kilograms up to a hundred; Operation implements comparatively loaded down with trivial details, takes time and effort, and needs to improve to realize test method quickly and easily.There is no at present discovery with explanation or the report of the utility model similar techniques, not yet collect both at home and abroad similarly data yet.
The utility model content
In order to solve prior art scheme operation inconvenience, the problem such as take time and effort, it is a kind of easy to operate that the utility model provides, the rocket diaphragm tank roll-over test device of light practicality, the framed structure of taking to match with the tank external diameter supports whole test unit, realizes freely overturning of whole test unit by the flip-flop movement of framed structure, and framed structure adopts Plate Welding to form, the centre is the engraved structure form, avoids the interference effect between riveted joint bolt.
Rocket diaphragm tank roll-over test device provided by the invention comprises: pressed on ring, thru-bolt, coupling bolt, rotating shaft, bearing, lower ring, mounting, direction-caster, universal caster wheel, episphere, stop pin, bolt, lower semisphere; Described episphere is identical with the diameter of lower semisphere; Described thru-bolt is separately fixed at described upper ring and lower ring on episphere and lower semisphere, and episphere and lower semisphere are waled; Two coupling bolts pass respectively the two ends of pressed on ring and lower ring diameter, and pressed on ring is connected with rotating shaft with lower ring; The bearing center hole is passed in rotating shaft, and stop pin, bolt are used for the horizontal and vertical position of fixed rotating shaft; Bearing is positioned at the two ends of the diameter of episphere and lower semisphere binding face, and bearing is fixed on mounting, and described episphere and lower semisphere are supported.
Preferably, the above-mentioned episphere of the utility model and lower semisphere are transparent configuration, and inflatable interface, compressive stress measurement interface, freeing port are arranged.
Preferably, the above-mentioned upper ring and lower ring of the utility model is symmetrical structure, is comprised of two different big or small donuts of diameter respectively, is welded to connect by reinforcement between large small circle ring, reinforcement and episphere, lower semisphere contact site is arc structure, and surface of contact is enclosed with wool felt; The bolt that has 12 through holes to be used between upper ring and lower ring, rotating shaft on the large circle circumference connects.
Preferably, above-mentioned rotating shaft, the bearing quantity for connecting upper ring and lower ring of the utility model is 2, described rotating shaft is welded to form by U-shaped structure and cylindrical structure two parts, and U-shaped structure division is connected with upper ring and lower ring by coupling bolt and is processed with 4 through holes and is used for being fixedly connected with of bolt and bearing; Cylindrical structure partly passes the circular port on bearing, on cylindrical radial and bearing, pilot hole is arranged, and realizes that by stop pin rotating shaft position fixes.
Preferably, the above-mentioned bearing of the utility model and mounting are bolted, and are welded with the triangle reinforcement between mounting crossbeam and vertical beam, and two of fronts, mounting bottom pin is equipped with 2 direction-casters, and two of back pin is equipped with 2 universal caster wheels.
When test, at first adopt bolt to be connected with bearing, base on lower ring, and the bolt in rotating shaft and stop pin are plugged; Diaphragm is loaded between episphere and lower semisphere, and diaphragm and lower semisphere form a Spherical chamber, and be with bolts between episphere, diaphragm and lower semisphere.After with bolts between ring and rotating shaft, bearing and base under test unit, mounted upper and lower hemispheres is positioned on lower ring, lower semisphere and lower loop contacts are placed in pressed on ring on episphere.Adopt coupling bolt that pressed on ring and lower ring are connected and fixed and with bolt, pressed on ring and bearing are fixed, stop pin in the taking-up rotating shaft and the bolt on bearing, upper and lower ring and upper and lower hemisphere assembly are rotated 180 °, plug stop pin and bolt, realize that the position fixes, fill with and take out stop pin and bolt after water, upper and lower ring and upper and lower hemisphere assembly are rotated 180 ° be back to original position and carry out emission testing.
A kind of rocket diaphragm tank roll-over test device that the utility model provides, owing to taking above-mentioned technical scheme, utilize outside turning gear to realize freely overturning of rocket diaphragm tank testpieces, guarantee by stop pin and bolt device the stable of rear level and upright position that overturn; Apparatus structure is simple, and conveniently moving effectively reduces labour intensity and the security of test operation, guarantees the stability of test technology.
Description of drawings
Fig. 1 is the forward structure schematic diagram of rocket diaphragm tank roll-over test device provided by the utility model;
Fig. 2 is the side direction structural representation of rocket diaphragm tank roll-over test device provided by the utility model.
In figure, 1 is that pressed on ring, 2 is that thru-bolt, 3 is that coupling bolt, 4 is that rotating shaft, 5 is that bearing, 6 is that lower ring, 7 is that mounting, 8 is that direction-caster, 9 is that universal caster wheel, 10 is that episphere, 11 is that stop pin, 12 is that bolt, 13 is lower semisphere.
Embodiment
Below in conjunction with the drawings and specific embodiments, further set forth the utility model.These embodiment are interpreted as only being used for explanation the utility model and are not used in restriction protection domain of the present utility model.After the content of having read the utility model record, those skilled in the art can make various changes or modifications the utility model, and these equivalences change and modification falls into the utility model claim limited range equally.
As shown in Figure 1 and Figure 2, the test unit that provides in the utility model preferred embodiment comprises pressed on ring 1, thru-bolt 2, coupling bolt 3, rotating shaft 4, bearing 5, lower ring 6, mounting 7, direction-caster 8, universal caster wheel 9, episphere 10, stop pin 11, bolt 12, lower semisphere 13.Its configuration annexation is as follows:
Described pressed on ring 1, lower ring 6 are symmetrical structure, are comprised of two different big or small donuts of diameter respectively, are welded to connect by reinforcement between large small circle ring, and reinforcement and episphere 10, lower semisphere 13 contacts site are arc structure, and surface of contact is enclosed with wool felt; Pressed on ring 1, lower ring 6 adopt thru-bolt 2 that episphere 10, lower semisphere 13 are fixed from the periphery by the through hole on large circle separately, the connection that coupling bolt 3 is used between pressed on ring 1, lower ring 6 and rotating shaft 4.
Described rotating shaft 4 is welded to form by U-shaped structure and cylindrical structure two parts, and U-shaped structure division is connected with pressed on ring 1, lower ring 6 by coupling bolt 3 and is processed with 4 through holes and is used for being fixedly connected with of bolt 12 and bearing 5; Cylindrical structure partly passes the circular port on bearing 5, on cylindrical radial and bearing 5, pilot hole is arranged, and realizes that by stop pin 11 position of rotating shaft 4 is fixed.
Described bearing 5 is bolted with mounting 7, is welded with the triangle reinforcement between mounting 7 crossbeams and vertical beam, and mounting two of 7 fronts, bottom pin respectively is installed by a direction-caster 8 and two of back pin is respectively installed a universal caster wheel 9.
Described episphere 10 is transparent configuration with lower semisphere 13, and inflatable interface, compressive stress measurement interface, freeing port are arranged.
Illustrate course of action of the present utility model below in conjunction with accompanying drawing.
During test, diaphragm is loaded between episphere 10 and lower semisphere 13, diaphragm and lower semisphere 13 form a Spherical chamber, and be with bolts between episphere 10 and lower semisphere 13.After with bolts between the lower ring 6 of device and rotating shaft 4, bearing 5 and mounting 7, stop pin 11 is inserted in the pilot hole of rotating shaft 4 and bearing 5 and the bolt 12 of screwing on; Mounted episphere 10, diaphragm, lower semisphere 13 assemblys are positioned on lower ring 6, and lower semisphere 13 contacts with lower ring 6, and pressed on ring 1 is placed on episphere 10.Utilize thru-bolt 2 that pressed on ring 1, lower ring 6 are connected and fixed; Adopt coupling bolt 3 that pressed on ring 1 and rotating shaft 4 are connected and fixed, stop pin 11 in taking-up rotating shaft 4 and the bolt 12 on bearing 5, the assembly of pressed on ring 1, lower ring 6 and episphere 10 and lower semisphere 13 is rotated 180 ° take rotating shaft as fulcrum, plug stop pin 11 and bolt 12, realize that the position fixes.Connect discharge pipe line to water filling port and valve-off from lower semisphere 13 tops after filling with water in the diaphragm spherical cavity, take out stop pin 11 and bolt 13, pressed on ring 1, lower ring 6 and episphere 10 are rotated 180 ° with lower semisphere 13 assemblys take rotating shaft as fulcrum, be back to original position, connect inflation loading pipeline and stress test sensor and carry out emission testing.
It will be appreciated by those skilled in the art that, instructions just schematically illustrates and sets forth spirit of the present utility model and essence, and any modification of the present utility model and replacement are all belonged to protection scope of the present invention.
Claims (5)
1. rocket diaphragm tank roll-over test device, it is characterized in that, comprising: pressed on ring (1), thru-bolt (2), coupling bolt (3), rotating shaft (4), bearing (5), lower ring (6), mounting (7), direction-caster (8), universal caster wheel (9), episphere (10), stop pin (11), bolt (12), lower semisphere (13);
Described episphere (10) is identical with the diameter of lower semisphere (13); Described thru-bolt (2) is separately fixed at described pressed on ring (1), lower ring (6) on episphere (10) and lower semisphere (13), and episphere (10) and lower semisphere (13) are waled; Two coupling bolts (3) pass respectively the two ends of pressed on ring (1) and lower ring (6) diameter, and pressed on ring (1) is connected with rotating shaft (4) with lower ring (6); Bearing (5) center hole is passed in rotating shaft (4), and stop pin (11), bolt (12) are used for the horizontal and vertical position of fixed rotating shaft (4); Bearing (5) is positioned at the two ends of the diameter of episphere (10) and lower semisphere (13) binding face, and bearing (5) is fixed on mounting (7), and described episphere (10) and lower semisphere (13) are supported.
2. rocket diaphragm tank roll-over test device as claimed in claim 1 is characterized in that: described episphere (10) is transparent configuration with lower semisphere (13), and inflatable interface, compressive stress measurement interface, freeing port are arranged.
3. rocket diaphragm tank roll-over test device as claimed in claim 1, it is characterized in that: described pressed on ring (1), lower ring (6) are symmetrical structure, formed by two different big or small donuts of diameter respectively, be welded to connect by reinforcement between large small circle ring, reinforcement and episphere (10), lower semisphere (13) contact site is arc structure, and surface of contact is enclosed with wool felt; The bolt that has 12 through holes to be used between pressed on ring (1), lower ring (6), rotating shaft (4) on the large circle circumference connects.
4. rocket diaphragm tank roll-over test device as claimed in claim 1, it is characterized in that: be respectively 2 for connection pressed on ring (1), the rotating shaft (4) of lower ring (6), bearing (5) quantity, described rotating shaft (4) and bearing (5) are used for supporting episphere (10) and lower semisphere (13), described rotating shaft (4) is welded to form by U-shaped structure and cylindrical structure two parts, U-shaped structure division is connected with pressed on ring (1), lower ring (6) by coupling bolt (3), and is processed with 4 through holes being fixedly connected with for bolt (12) and bearing (5); Cylindrical structure partly passes the circular port on bearing (5), and cylindrical radial and bearing have pilot hole on (5), realizes that by stop pin (11) rotating shaft position fixes.
5. rocket diaphragm tank roll-over test device as claimed in claim 1, it is characterized in that: described bearing (5) is bolted with mounting (7), be welded with the triangle reinforcement between mounting (7) crossbeam and vertical beam, two of fronts, mounting (7) bottom pin is installed by two direction-casters (8) and two of back pin is installed two universal caster wheels (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220564077 CN202994436U (en) | 2012-10-31 | 2012-10-31 | Rocket diaphragm sheet storage box roll-over test apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220564077 CN202994436U (en) | 2012-10-31 | 2012-10-31 | Rocket diaphragm sheet storage box roll-over test apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202994436U true CN202994436U (en) | 2013-06-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220564077 Expired - Lifetime CN202994436U (en) | 2012-10-31 | 2012-10-31 | Rocket diaphragm sheet storage box roll-over test apparatus |
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| CN (1) | CN202994436U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105737693A (en) * | 2016-04-18 | 2016-07-06 | 南京理工大学 | Movable test bed for rocket projectile |
| CN107167292A (en) * | 2017-07-03 | 2017-09-15 | 贵州航天朝阳科技有限责任公司 | A kind of vibration testing device of spacecraft propulsion agent tank metallic membrane |
| CN107628174A (en) * | 2017-09-30 | 2018-01-26 | 桂林电子科技大学 | Omnidirectional's ball wheel drive is without handlebar self-balancing bicycle |
| CN109352244A (en) * | 2018-11-30 | 2019-02-19 | 上海航天精密机械研究所 | Circumferential weld welding equipment device for bearing type spherical shape tank |
-
2012
- 2012-10-31 CN CN 201220564077 patent/CN202994436U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105737693A (en) * | 2016-04-18 | 2016-07-06 | 南京理工大学 | Movable test bed for rocket projectile |
| CN105737693B (en) * | 2016-04-18 | 2017-06-27 | 南京理工大学 | Rocket projectile may move testing stand |
| CN107167292A (en) * | 2017-07-03 | 2017-09-15 | 贵州航天朝阳科技有限责任公司 | A kind of vibration testing device of spacecraft propulsion agent tank metallic membrane |
| CN107628174A (en) * | 2017-09-30 | 2018-01-26 | 桂林电子科技大学 | Omnidirectional's ball wheel drive is without handlebar self-balancing bicycle |
| CN109352244A (en) * | 2018-11-30 | 2019-02-19 | 上海航天精密机械研究所 | Circumferential weld welding equipment device for bearing type spherical shape tank |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130612 |