CN105194880A - Foaming plug launching six symmetric tail wing type rotary spray rocket provided with level identification - Google Patents
Foaming plug launching six symmetric tail wing type rotary spray rocket provided with level identification Download PDFInfo
- Publication number
- CN105194880A CN105194880A CN201510701804.9A CN201510701804A CN105194880A CN 105194880 A CN105194880 A CN 105194880A CN 201510701804 A CN201510701804 A CN 201510701804A CN 105194880 A CN105194880 A CN 105194880A
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- rocket
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- air
- water
- spheroid
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- 238000005187 foaming Methods 0.000 title claims abstract description 20
- 239000007921 spray Substances 0.000 title claims abstract description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 41
- 238000007789 sealing Methods 0.000 claims abstract description 11
- 239000000203 mixture Substances 0.000 claims abstract description 4
- 239000012530 fluid Substances 0.000 claims description 12
- 239000004568 cement Substances 0.000 claims description 10
- 235000015842 Hesperis Nutrition 0.000 claims description 6
- 235000012633 Iberis amara Nutrition 0.000 claims description 6
- 102000010637 Aquaporins Human genes 0.000 claims description 3
- 108010063290 Aquaporins Proteins 0.000 claims description 3
- 230000008602 contraction Effects 0.000 claims description 3
- 238000002347 injection Methods 0.000 description 6
- 239000007924 injection Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 239000002351 wastewater Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 108091006146 Channels Proteins 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000005381 potential energy Methods 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008447 perception Effects 0.000 description 1
Abstract
The invention discloses a foaming plug launching six symmetric tail wing type rotary spray rocket provided with a level identification. A launching cover is arranged on a launching cylinder in a thread fit manner, a tapered foaming plug is arranged in the launching cover, and sealing can be realized by screwing the launching cover; a level identification is arranged on a launching frame; a plastic ellipsoid is arranged at the upper part of a rocket body, the lower part of the plastic ellipsoid is firmly connected with an outer pipe in a sealing manner, a center air pipe is arranged inside the outer pipe, inserted into the plastic ellipsoid and co-axially embedded into the outer pipe in a non-full contact manner, a Rafael conical surface expansion chamber which compressed air and pressure water enter is formed, a rotational flow body is arranged at the water inlet position, and a water and air mixture body is jetted from a nozzle in the lower part of the rocket at a high speed; six symmetric tail wings are arranged on the outer wall of the lower part of the outer pipe. According to the foaming plug launching six symmetric tail wing type rotary spray rocket provided with the level identification, pressure launching and primary compressed air ejection flying are ingenuously realized; secondary ejection flying ingenuously simulates secondary ignition flight of the rocket, the rocket has good operability and scientific exploration educational characteristic, and the rocket is a teaching tool and toy with high practicability.
Description
Technical field
The present invention relates to a kind of teaching aid or toy, specifically refer to that the foaming bung of band Horizontal identification launches six symmetrical empennage-type churning water rockets.
Background technology
Rocket is development in science and technology product to a certain extent, and it occurs existing century-old history, and the transmitting of rocket contains very complicated dynamic process, is also giving full play to and applying of physical principle.
Therefore, in order to learn the operation principle of rocket launching, be necessary the rocket making a kind of teaching aid or toy-type, making under its condition of launching in low cost just can the operation principle of abundant rocket launching analog, allow student and child at the physical principle of the process learning rocket launching played, arouse the interest in study, also can strengthen recreational.
Summary of the invention
The technical problem to be solved in the present invention overcomes the deficiencies in the prior art exactly, a kind of ingenious application Rafael nozzle operation principle is provided to carry out teaching aid or the toy-type rocket of air water injection, this rocket has the advantages that structure is simple, implementation cost is low, is particularly suitable for doing teaching aid or toy use.
For overcoming the deficiencies in the prior art, the present invention takes following technical scheme:
Foaming bung with Horizontal identification launches six symmetrical empennage-type churning water rockets, comprises launching tube and rocket body, it is characterized in that: launching tube is by triangle launcher fixed support, and launcher is provided with Horizontal identification; Launching tube top is provided with the transmitting lid of threaded engagement, launches in lid and has taper foaming bung, and screw transmitting lid and can realize sealing, when launching cylinder pressure and being enough large, taper foaming bung can quick-fried spray out, and repeatedly can assemble use; Launching tube bottom is provided with valve input compressed-air, is provided with centre of location stake and carries out nested type centralized positioning to the bottom spout of inserting rocket bottom launching tube; Plastic cement spheroid is arranged at rocket body top, microgap Air-tight piston formula can be carried out slide in smooth launching tube, plastic cement spheroid upper middle position has through hole and check valve sheet, through hole can realize air inlet and pour water, check valve sheet can be carried out unidirectional control and be realized closing sealing, similar basketball valve under positive pressure; The firm airtight connection outer tube in spheroid bottom, outer tube has center tracheae, and center tracheae inserts in spheroid, and center tracheae Minimal Tension is closed and realized sealing and be connected by the contraction elasticity of spheroid through hole plastic cement, can conducting when having an interior pressure; Outer tube bottom is that inwall first expands the air water jet pipe reduced again, air water jet pipe water nozzle is provided with rotary fluid, the inwall of rotary fluid is carved with helicla flute, tracheae lower end, center is conical, and to be provided with aperture be compressed air spout, the coaxial embedding outer tube of center tracheae non-fully contact, formed in outer tube and between central tube and bore tubular throttling aquaporin and daraf(reciprocal of farad) that conical surface expansion chambers, your conical surface expansion chambers of daraf(reciprocal of farad) is the mixing chamber that compressed air and pressure (hydraulic) water enter simultaneously, and gas-water mixture is by the bottom spout high velocity jet of rocket; The outer wall of outer tube bottom is provided with six symmetrical empennages.
Altitude scale is provided with in described spheroid.
The present invention mainly carries out the optimal design of air water rocket by flexible Application Rafael nozzle operation principle, can fly get Geng Gao to realize air water rocket.
The operation principle of Rafael nozzle is such: the jet pipe of band trunnion, classical hydrodynamics is followed when Compressed Gas first progressively enters the narrowest and small throat's process by the pipe position that cross section is larger, cross section diminish flow velocity increase, resistance also significantly increases sharply, form the flowing of a kind of gas throttling, but the convergent divergent channel part that Compressed Gas progressively expands by entering cross section after throat's smallest cross-sectional, due to the decompressional expansion of Compressed Gas, gas no longer follows Classical Fluid Mechanics, but can be sprayed by convergent divergent channel with very high speed, if compression pressure is enough high and nozzle structure is reasonable, gas can spray from spout with supersonic speed.Rafael nozzle operation principle is applied to jet airplane and rocket, significantly improves efficiency and the power of jet engine, achieves space flight, the leaping of science and technology of aviation.
The present invention is that the operation principle of application Rafael nozzle carries out mixing wastewater with air high velocity jet, and can realize the most rational Conversion of Energy, make the very high of rocket flight, its course of work is such:
1, the spheroid of rocket body is poured into suitable quantity of water, water level is the highest, and to be no more than center tracheae suitable for reading, assembles and adjust perpendicularity just can connect valve and carry out compressed-air actuated input, now progressively can be full of compressed air in launching tube and rocket body;
2, when pressure increase is to when making that taper foaming bung is quick-fried to be sprayed out, the air pressure of rocket spheroid front end reduces to atmospheric pressure instantaneously, and spheroid bottom compressed air is then rapid as shell is launched, by rocket body outburst injection, valve block can be closed rapidly under interior pressure effect, realizes one-level and launches;
3, six symmetrical empennages can control rocket stabilization flight, spheroid compressed air is by the ejection of tracheae lower end, center spout simultaneously, retaining in compressed air-driven spheroid enters outer tube by elasticity open gaps between spheroid and center tracheae and carries downwards, mixing chamber is entered from lower end cone tubular throttling passage eddy flow by rotary fluid, due to daraf(reciprocal of farad) that effect, compressed air expansion driven mixing wastewater with air is also spouting from spout at a high speed, obtain powerful recoil power, the second motive force realizing water rocket sprays, and makes it to fly get Geng Gao.
In order to rocket body compressed air potential energy is converted into injection power most effectively, it is optimal state that air water has sprayed simultaneously; Pipe throttle can make air water optimal proportion mixing jetting, can realize peak efficiency and strong impetus is flown, and supports to fly get Geng Gao, farther.
Compared with prior art, beneficial effect of the present invention is also:
Ingenious achieve pressure launch with one stage of compression air launch flight; The ingenious two-stage ignition flight simulating rocket of two-stage injection flight; Also ingeniously merge classical Rafael nozzle principle to promote experimental level and to promote student to the perception of science, make rocket fly get Geng Gao, farther; Foaming bung moderate pressure, is applicable to toy and teaching aid uses, and does not have potential safety hazard.
Apparatus of the present invention structure is simple, reliable, ingenious, cost is low, has good operability and Science Explorations intelligence development characteristic, is the teaching aid and toy that practicality is very strong.
Accompanying drawing explanation
Fig. 1 is planar structure schematic diagram of the present invention.
Fig. 2 is the structural representation of empennage.
Fig. 3 is the partial enlarged drawing of jet pipe.
Fig. 4 is the profile of rotary fluid.
Fig. 5 is the bottom view of rotary fluid.
In figure, each label represents:
1, foaming bung; 2, lid is launched; 3, threaded engagement; 4, through hole; 5, check valve sheet; 6, center tracheae; 7, launching tube; 8, plastic cement spheroid; 9, outer tube; 10, empennage; 11, launcher; 12, air water jet pipe; 13, centre of location stake; 14, valve; 15, daraf(reciprocal of farad) that conical surface expansion chambers; 16, mixing wastewater with air spout; 17, compressed air spout; 18, rotary fluid; 21, altitude scale; 22, Horizontal identification.
Detailed description of the invention
Now by reference to the accompanying drawings, the present invention is illustrated further.
As shown in Figure 1, Figure 2, the foaming bung of the Horizontal identification of band shown in Fig. 3, Fig. 4 and Fig. 5 launches six symmetrical empennage-type churning water rockets, and comprise launching tube 7 and rocket body, launching tube 7 is by triangle launcher 11 fixed support, and launcher 11 is provided with Horizontal identification 22; Launching tube 7 top is provided with the transmitting lid 2 of threaded engagement 3, launches in lid 2 and has taper foaming bung 1, and screw transmitting lid 2 and can realize sealing, when in launching tube 7, pressure is enough large, taper foaming bung 1 can quick-fried spray out, and repeatedly can assemble use; Launching tube 7 bottom is provided with valve 14 input compressed-air, is provided with centre of location stake 13 and carries out nested type centralized positioning to the bottom spout 17 of inserting rocket bottom launching tube 7; Plastic cement spheroid 8 is arranged at rocket body top, microgap Air-tight piston formula can be carried out slide in smooth launching tube 7, plastic cement spheroid 8 upper middle position has through hole 4 and check valve sheet 5, through hole 4 can realize air inlet and pour water, check valve sheet 5 can be carried out unidirectional control and be realized closing sealing, similar basketball valve under positive pressure; The firm airtight connection outer tube 9 in spheroid bottom, there is center tracheae 6 outer tube 9 inside, and center tracheae 6 inserts in spheroid 8, and center tracheae 6 Minimal Tension is closed and realized sealing and be connected by the contraction elasticity of spheroid through hole plastic cement, can conducting when having an interior pressure; Outer tube 9 bottom is that inwall first expands the air water jet pipe 12 reduced again, air water jet pipe 12 water nozzle is provided with rotary fluid 18, the inwall of rotary fluid 18 is carved with helicla flute, center tracheae 6 lower end is conical, and to be provided with aperture be compressed air spout 17, the coaxial embedding outer tube 9 of the non-full-contact of center tracheae 6, formed in outer tube 9 and between central tube 6 and bore tubular throttling aquaporin and daraf(reciprocal of farad) that conical surface expansion chambers 15, your conical surface expansion chambers 15 of daraf(reciprocal of farad) is the mixing chamber that compressed air and pressure (hydraulic) water enter simultaneously, and gas-water mixture is by bottom spout 16 high velocity jet of rocket; The outer wall of outer tube 9 bottom is provided with six symmetrical empennages 10.
Altitude scale 21 is provided with in described spheroid 8.
The present invention is that the operation principle of application Rafael nozzle carries out mixing wastewater with air high velocity jet, and can realize the most rational Conversion of Energy, make the very high of rocket flight, its course of work is such:
1, rocket body spheroid 8 is poured into suitable quantity of water, water level is the highest, and to be no more than center tracheae 6 suitable for reading, assembles and adjust perpendicularity just can connect valve 14 and carry out compressed-air actuated input, now progressively can be full of compressed air in launching tube 7 and rocket body;
2, when pressure increase is to when making that taper foaming bung 1 is quick-fried to be sprayed out, the air pressure of rocket spheroid 8 front end reduces to atmospheric pressure instantaneously, and spheroid bottom compressed air is then rapid as shell is launched, by rocket body outburst injection, valve block 5 can be closed rapidly under interior pressure effect, realizes one-level and launches;
3, six symmetrical empennages 10 can control rocket stabilization flight, spheroid compressed air is sprayed by tracheae lower end, center spout 17 simultaneously, retaining in compressed air-driven spheroid enters outer tube by elasticity open gaps between spheroid and center tracheae and carries downwards, mixing chamber is entered from lower end cone tubular throttling passage eddy flow by rotary fluid, due to daraf(reciprocal of farad) that effect, compressed air expansion driven mixing wastewater with air is also spouting from spout 16 at a high speed, obtain powerful recoil power, the second motive force realizing water rocket sprays, and makes it to fly get Geng Gao.
In order to rocket body compressed air potential energy is converted into injection power most effectively, it is optimal state that air water has sprayed simultaneously; Pipe throttle can make air water optimal proportion mixing jetting, can realize peak efficiency and strong impetus is flown, and supports to fly get Geng Gao, farther.
Above-mentioned just preferred embodiment of the present invention, not does any pro forma restriction to the present invention.Any those of ordinary skill in the art, when not departing from technical solution of the present invention scope, can utilize the technology contents of above-mentioned announcement to make many possible variations and modification to technical solution of the present invention, or being revised as the Equivalent embodiments of equivalent variations.Therefore, every content not departing from technical solution of the present invention, according to the technology of the present invention essence to any simple modification made for any of the above embodiments, equivalent variations and modification, all should drop in the scope of technical solution of the present invention protection.
Claims (2)
1. the foaming bung with Horizontal identification launches six symmetrical empennage-type churning water rockets, comprises launching tube and rocket body, it is characterized in that: launching tube is by triangle launcher fixed support, and launcher is provided with Horizontal identification; Launching tube top is provided with the transmitting lid of threaded engagement, launches in lid and has taper foaming bung, and screw transmitting lid and can realize sealing, when launching cylinder pressure and being enough large, taper foaming bung can quick-fried spray out, and repeatedly can assemble use; Launching tube bottom is provided with valve input compressed-air, is provided with centre of location stake and carries out nested type centralized positioning to the bottom spout of inserting rocket bottom launching tube; Plastic cement spheroid is arranged at rocket body top, microgap Air-tight piston formula can be carried out slide in smooth launching tube, plastic cement spheroid upper middle position has through hole and check valve sheet, through hole can realize air inlet and pour water, check valve sheet can be carried out unidirectional control and be realized closing sealing, similar basketball valve under positive pressure; The firm airtight connection outer tube in spheroid bottom, outer tube has center tracheae, and center tracheae inserts in spheroid, and center tracheae Minimal Tension is closed and realized sealing and be connected by the contraction elasticity of spheroid through hole plastic cement, can conducting when having an interior pressure; Outer tube bottom is that inwall first expands the air water jet pipe reduced again, air water jet pipe water nozzle is provided with rotary fluid, the inwall of rotary fluid is carved with helicla flute, tracheae lower end, center is conical, and to be provided with aperture be compressed air spout, the coaxial embedding outer tube of center tracheae non-fully contact, formed in outer tube and between central tube and bore tubular throttling aquaporin and daraf(reciprocal of farad) that conical surface expansion chambers, your conical surface expansion chambers of daraf(reciprocal of farad) is the mixing chamber that compressed air and pressure (hydraulic) water enter simultaneously, and gas-water mixture is by the bottom spout high velocity jet of rocket; The outer wall of outer tube bottom is provided with six symmetrical empennages.
2. the foaming bung according to claim 1 with Horizontal identification launches six symmetrical empennage-type churning water rockets, it is characterized in that: be provided with altitude scale in described spheroid.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510701804.9A CN105194880B (en) | 2015-10-27 | 2015-10-27 | Foaming bung with Horizontal identification launches six symmetrical empennage-type churning water rockets |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510701804.9A CN105194880B (en) | 2015-10-27 | 2015-10-27 | Foaming bung with Horizontal identification launches six symmetrical empennage-type churning water rockets |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105194880A true CN105194880A (en) | 2015-12-30 |
| CN105194880B CN105194880B (en) | 2017-12-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510701804.9A Expired - Fee Related CN105194880B (en) | 2015-10-27 | 2015-10-27 | Foaming bung with Horizontal identification launches six symmetrical empennage-type churning water rockets |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105194880B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107387929A (en) * | 2017-07-31 | 2017-11-24 | 江苏中超环保股份有限公司 | A kind of device of simple increase flow velocity |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3943656A (en) * | 1972-02-04 | 1976-03-16 | Damon Corporation | Two stage rocket with pressure responsive means for frictionally engaging second stage |
| CN2064256U (en) * | 1989-11-26 | 1990-10-24 | 上海市闵行区侨海新技术开发事务所 | Liquid rocket |
| US5415153A (en) * | 1992-06-22 | 1995-05-16 | Johnson; Lonnie G. | Pressurized air/water rocket and launcher |
| CN2247553Y (en) * | 1996-07-03 | 1997-02-19 | 张义芬 | Automatic pressurizing launching toy rocket |
| CN2449773Y (en) * | 2000-11-06 | 2001-09-26 | 谢祯恭 | Bottle launching device |
-
2015
- 2015-10-27 CN CN201510701804.9A patent/CN105194880B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3943656A (en) * | 1972-02-04 | 1976-03-16 | Damon Corporation | Two stage rocket with pressure responsive means for frictionally engaging second stage |
| CN2064256U (en) * | 1989-11-26 | 1990-10-24 | 上海市闵行区侨海新技术开发事务所 | Liquid rocket |
| US5415153A (en) * | 1992-06-22 | 1995-05-16 | Johnson; Lonnie G. | Pressurized air/water rocket and launcher |
| CN2247553Y (en) * | 1996-07-03 | 1997-02-19 | 张义芬 | Automatic pressurizing launching toy rocket |
| CN2449773Y (en) * | 2000-11-06 | 2001-09-26 | 谢祯恭 | Bottle launching device |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107387929A (en) * | 2017-07-31 | 2017-11-24 | 江苏中超环保股份有限公司 | A kind of device of simple increase flow velocity |
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| Publication number | Publication date |
|---|---|
| CN105194880B (en) | 2017-12-01 |
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| TA01 | Transfer of patent application right | ||
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Effective date of registration: 20170731 Address after: 510640 Guangdong City, Tianhe District Province, No. five, road, public education building, unit 371-1, unit 2401 Applicant after: Guangdong Gaohang Intellectual Property Operation Co., Ltd. Address before: 416000 Hunan, Xiangxi Tujia and Miao Autonomous Prefecture, Jishou City People's road, No. 120 Applicant before: Jishou University |
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| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Chen Fengshan Inventor before: Zhang Xu Inventor before: Zhang Siyan Inventor before: Yin Yongzhong |
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Effective date of registration: 20171016 Address after: 362400 Fujian province Quanzhou city Anxi County miracle Town Village Zhen Ren hall No. 31 Applicant after: Chen Fengshan Address before: 510640 Guangdong City, Tianhe District Province, No. five, road, public education building, unit 371-1, unit 2401 Applicant before: Guangdong Gaohang Intellectual Property Operation Co., Ltd. |
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Effective date of registration: 20191011 Address after: Room 604, 2 stairs, building 41, Zhongxin garden, No.147, Third Ring Road, Luocheng garden, Hui'an County, Fujian Province, 362100 Patentee after: Lin Shao Zhong Address before: 362400 Fujian province Quanzhou city Anxi County miracle Town Village Zhen Ren hall No. 31 Patentee before: Chen Feng Shan |
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Effective date of registration: 20191120 Address after: 221000 room 607, block B, University Pioneer Park, No. 99, University Road, Tongshan District, Xuzhou high tech Industrial Development Zone, Jiangsu Province Patentee after: Jiangsu Luzi Mali Food Co., Ltd Address before: Room 604, 2 stairs, building 41, Zhongxin garden, No.147, Third Ring Road, Luocheng garden, Hui'an County, Fujian Province, 362100 Patentee before: Lin Shaozhong |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
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Granted publication date: 20171201 Termination date: 20201027 |