CN201908744U - Civil hail suppression and rainfall increment rocket engine - Google Patents
Civil hail suppression and rainfall increment rocket engine Download PDFInfo
- Publication number
- CN201908744U CN201908744U CN2011200311479U CN201120031147U CN201908744U CN 201908744 U CN201908744 U CN 201908744U CN 2011200311479 U CN2011200311479 U CN 2011200311479U CN 201120031147 U CN201120031147 U CN 201120031147U CN 201908744 U CN201908744 U CN 201908744U
- Authority
- CN
- China
- Prior art keywords
- engine
- igniter
- rocket
- motor
- hail suppression
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Abstract
The utility model relates to a civil hail suppression and rainfall increment rocket engine, which belongs to the technical field of projectiles. The civil hail suppression and rainfall increment rocket engine comprises a connecting piece, an engine igniter, a combustion chamber, an engine grain, a spray pipe, a sealing plug and a stabilizing device, wherein the engine igniter is fixed inside the connecting piece; after a mandrel is arranged in the center of the inside of the combustion chamber, the engine grain is directly poured, and the mandrel is extracted after charging; the spray pipe is fixed inside the stabilizing device; the back end of the spray pipe is sealed by the sealing plug; an igniter socket is fixed on the sealing plug; the connecting piece, the combustion chamber and the stabilizing device outside the rocket engine are in threaded connection in turn; and an ignition circuit of the engine igniter is connected with the igniter socket on the sealing plug through a lead so as to form an ignition loop. The space utilization ratio of the combustion chamber is increased, so that the firing range of a hail suppression and rainfall increment rocket projectile, and the using requirement on an effective load conveying carrier during high-altitude hail suppression and rainfall increment operation in a high-altitude region is met.
Description
Technical field
The utility model relates to a kind of civilian hail-proof rain-increasing rocket motor, belongs to play the arrow technical field.
Background technique
China is with a vast territory, the weather complexity, meteorological disasters such as arid, flood, hail frequently take place in China different regions, and hail suppression artificial rainmaking rocket bullet is as the working tool of weather modification, for preventing hail disaster, increase precipitation, alleviating arid threat, played positive effect.
The motor of tradition hail-proof rain-increasing rocket is in being fixed on by the front and back grate after motor grain compacting is finished, and does not contact between motor grain and the motor body, and space availability ratio is low, thereby has limited the hail-proof rain-increasing rocket range.
Summary of the invention
The purpose of this utility model is will solve traditional hail-proof rain-increasing rocket to have problems such as the motor space availability ratio is low, and a kind of hail-proof rain-increasing rocket is provided.
The purpose of this utility model is achieved through the following technical solutions;
A kind of civilian hail-proof rain-increasing rocket motor of the present utility model comprises link, engine ignition tool, firing chamber, motor grain, jet pipe, sealing blanking cover, stabilizer; Link internal fixation engine ignition tool; Motor grain is directly poured into a mould after placing core by the center in inside, firing chamber, takes out core after powder charge is finished; Stabilizer internal fixation jet pipe, the jet pipe rear end is by the sealing of sealing blanking cover, fixed ignition tool socket on the sealing blanking cover; The link of rocket motor outside, firing chamber, stabilizer are threaded successively, and the firing circuit of engine ignition tool passes the central through bore of motor grain and jet pipe by lead and links to each other with igniter socket on the sealing blanking cover, form to get angry the loop.
Wherein, motor grain is a fourth hydroxyl composite propellant.
Working procedure:
After the emission big gun firing circuit that is connected with igniter socket on the rocket motor sealing blanking cover starts, by lead fused signal is passed to the engine ignition tool, engine ignition tool ignition motor grain is for rocket projectile provides flying power.
Beneficial effect:
Motor grain is directly poured into a mould after placing core by the center in the inside, firing chamber of rocket motor of the present utility model, increased the space availability ratio of firing chamber, thereby the hail-proof rain-increasing rocket range is provided, has satisfied in the high altitude localities and to carry out carrier is transported in the hail-proof rain-increasing operation to useful load usage requirement in the high-altitude.
Description of drawings
Fig. 1 is the structural representation of rocket motor in the utility model hail-proof rain-increasing rocket;
Among the figure, the 1-link; 2-engine ignition tool; The 3-firing chamber; The 4-motor grain; The 5-jet pipe; 6-seals blanking cover; The 7-stabilizer.
Embodiment
Below in conjunction with drawings and Examples content of the present utility model is described further.
Embodiment
As shown in Figure 1, a kind of civilian hail-proof rain-increasing rocket motor of the present utility model comprises link 1, engine ignition tool 2, firing chamber 3, motor grain 4, jet pipe 5, sealing blanking cover 6, stabilizer 7; Link 1 internal fixation engine ignition tool 2; Motor grain is directly poured into a mould after placing core by the center in 3 inside, firing chamber, takes out core after powder charge is finished; Stabilizer 7 internal fixation jet pipes 5, jet pipe 5 rear ends are by 6 sealings of sealing blanking cover, fixed ignition tool socket on the sealing blanking cover 6; The link 1 of rocket motor 4 outsides, firing chamber 3, stabilizer 7 are threaded successively, the firing circuit of engine ignition tool 2 passes the central through bore of motor grain 4 and jet pipe 5 by lead and links to each other with igniter socket on the sealing blanking cover 6, forms the ignition loop.
Wherein, motor grain 4 is a fourth hydroxyl composite propellant.
Working procedure:
After the emission big gun firing circuit that is connected with igniter socket on the rocket motor 4 sealing blanking covers 6 starts, by lead fused signal is passed to engine ignition tool 2, engine ignition tool 2 ignition motor grains 4 are for rocket projectile provides flying power.
Claims (1)
1. a civilian hail-proof rain-increasing rocket motor is characterized in that comprising: link (1), engine ignition tool (2), firing chamber (3), motor grain (4), jet pipe (5), sealing blanking cover (6), stabilizer (7); Link (1) internal fixation engine ignition tool (2); Firing chamber (3) is inner by directly pouring into a mould motor grain behind the center placement core, takes out core after powder charge is finished; Stabilizer (7) internal fixation jet pipe (5), jet pipe (5) rear end is by sealing blanking cover (6) sealing, and sealing blanking cover (6) is gone up fixed ignition tool socket; Outside link (1), firing chamber (3), the stabilizer (7) of rocket motor (4) is threaded successively, the firing circuit of engine ignition tool (2) passes the central through bore of motor grain (4) and jet pipe (5) by lead and links to each other with igniter socket on the sealing blanking cover (6), forms the ignition loop.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200311479U CN201908744U (en) | 2011-01-28 | 2011-01-28 | Civil hail suppression and rainfall increment rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200311479U CN201908744U (en) | 2011-01-28 | 2011-01-28 | Civil hail suppression and rainfall increment rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201908744U true CN201908744U (en) | 2011-07-27 |
Family
ID=44300947
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011200311479U Expired - Fee Related CN201908744U (en) | 2011-01-28 | 2011-01-28 | Civil hail suppression and rainfall increment rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201908744U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104030866A (en) * | 2014-06-06 | 2014-09-10 | 中国航天科工集团第六研究院四十六所 | Seismic charge prepared by waste hydroxyl-terminated polyb (HTPB) solid propellant slurry and application thereof |
| CN105557409A (en) * | 2015-12-18 | 2016-05-11 | 重庆长安工业(集团)有限责任公司 | Artificial rainfall rocket projectile catalyst scattering device based on molten metal |
| CN104612856B (en) * | 2014-11-28 | 2016-07-06 | 西安近代化学研究所 | A kind of band medicine reel stress release device |
| CN107100761A (en) * | 2017-06-29 | 2017-08-29 | 湖北三江航天江河化工科技有限公司 | A kind of test engine |
| CN110886669A (en) * | 2019-11-25 | 2020-03-17 | 湖北三江航天江河化工科技有限公司 | Test engine for testing solid rocket propellant |
-
2011
- 2011-01-28 CN CN2011200311479U patent/CN201908744U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104030866A (en) * | 2014-06-06 | 2014-09-10 | 中国航天科工集团第六研究院四十六所 | Seismic charge prepared by waste hydroxyl-terminated polyb (HTPB) solid propellant slurry and application thereof |
| CN104030866B (en) * | 2014-06-06 | 2017-04-19 | 中国航天科工集团第六研究院四十六所 | Seismic charge prepared by waste hydroxyl-terminated polyb (HTPB) solid propellant slurry and application thereof |
| CN104612856B (en) * | 2014-11-28 | 2016-07-06 | 西安近代化学研究所 | A kind of band medicine reel stress release device |
| CN105557409A (en) * | 2015-12-18 | 2016-05-11 | 重庆长安工业(集团)有限责任公司 | Artificial rainfall rocket projectile catalyst scattering device based on molten metal |
| CN107100761A (en) * | 2017-06-29 | 2017-08-29 | 湖北三江航天江河化工科技有限公司 | A kind of test engine |
| CN107100761B (en) * | 2017-06-29 | 2019-07-02 | 湖北三江航天江河化工科技有限公司 | A kind of test engine |
| CN110886669A (en) * | 2019-11-25 | 2020-03-17 | 湖北三江航天江河化工科技有限公司 | Test engine for testing solid rocket propellant |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201908744U (en) | Civil hail suppression and rainfall increment rocket engine | |
| CN102168937B (en) | Hail-suppression and rainfall-increment rocket bomb | |
| CN111207006B (en) | Solid rocket engine large-debonding full-filling explosive filling structure | |
| CN201503024U (en) | Strength air cannon | |
| CN109373811A (en) | A kind of multistage actuation catapult-launching gear using travelling charge | |
| CN201317466Y (en) | Continuous separation device for transversely separating expansion pipe | |
| CN103960096B (en) | A kind of method utilizing aerosol catalytic agent manually to eliminate sleet | |
| CN202384544U (en) | Civilian solid rocket motor nozzle sealing device | |
| CN201993048U (en) | Hail-suppression and rain-enhancement rocket projectile | |
| CN102524004B (en) | Hail suppressing and rain increasing catalyst body seeder | |
| CN201843700U (en) | Igniter motor shell with integral structure | |
| CN104234867A (en) | Scramjet engine | |
| CN202005180U (en) | Body-spread catalyst spreading device for hail suppression and rain enhancement | |
| CN208872535U (en) | A kind of pack boronitriding experimental rig of simulated altitude environment | |
| CN202822560U (en) | Mini thrust misalignment composite nozzle for fire extinguishing shrapnel | |
| CN213354875U (en) | Unmanned aerial vehicle rocket booster of adjustable thrust | |
| CN204798884U (en) | Liquid oxygen and fuel mixing arrangement | |
| CN201426031Y (en) | Aerial power transmission and distribution wire ice removing device | |
| CN204327265U (en) | A kind of supercharging type four-stroke internal combustion engine | |
| CN206876062U (en) | multi-point initiation device | |
| CN204438928U (en) | A kind of civil rocket bullet monoblock type projectile tail | |
| CN113606057A (en) | Axial sliding type partition plate suitable for multi-pulse solid rocket engine | |
| CN205102704U (en) | Dummy round suitable for pop -up of formula air defence missile is shouldered to shoulder | |
| CN109339948A (en) | Bullet gas-turbine unit inlet duct | |
| CN204515153U (en) | The power valve of high-power program control focus |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110727 Termination date: 20150128 |
|
| EXPY | Termination of patent right or utility model |