CN201993048U - Hail-suppression and rain-enhancement rocket projectile - Google Patents
Hail-suppression and rain-enhancement rocket projectile Download PDFInfo
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- CN201993048U CN201993048U CN2011200311765U CN201120031176U CN201993048U CN 201993048 U CN201993048 U CN 201993048U CN 2011200311765 U CN2011200311765 U CN 2011200311765U CN 201120031176 U CN201120031176 U CN 201120031176U CN 201993048 U CN201993048 U CN 201993048U
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- 238000010899 nucleation Methods 0.000 claims abstract description 138
- 238000010304 firing Methods 0.000 claims abstract description 59
- 239000003054 catalyst Substances 0.000 claims abstract description 31
- 238000002485 combustion reaction Methods 0.000 claims abstract description 19
- 239000000843 powder Substances 0.000 claims description 70
- 230000003111 delayed effect Effects 0.000 claims description 24
- 238000007789 sealing Methods 0.000 claims description 23
- 239000000567 combustion gas Substances 0.000 claims description 20
- 238000009331 sowing Methods 0.000 claims description 14
- ZBMRKNMTMPPMMK-UHFFFAOYSA-N 2-amino-4-[hydroxy(methyl)phosphoryl]butanoic acid;azane Chemical compound [NH4+].CP(O)(=O)CCC(N)C([O-])=O ZBMRKNMTMPPMMK-UHFFFAOYSA-N 0.000 claims description 10
- 229920000742 Cotton Polymers 0.000 claims description 9
- 230000003019 stabilising effect Effects 0.000 claims description 9
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 238000009413 insulation Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 7
- 238000010008 shearing Methods 0.000 abstract description 2
- 238000011084 recovery Methods 0.000 abstract 5
- 239000002775 capsule Substances 0.000 abstract 3
- 235000015842 Hesperis Nutrition 0.000 abstract 1
- 235000012633 Iberis amara Nutrition 0.000 abstract 1
- 239000002737 fuel gas Substances 0.000 abstract 1
- 229910021612 Silver iodide Inorganic materials 0.000 description 6
- 239000003795 chemical substances by application Substances 0.000 description 6
- 239000003814 drug Substances 0.000 description 3
- JKFYKCYQEWQPTM-UHFFFAOYSA-N 2-azaniumyl-2-(4-fluorophenyl)acetate Chemical compound OC(=O)C(N)C1=CC=C(F)C=C1 JKFYKCYQEWQPTM-UHFFFAOYSA-N 0.000 description 2
- 238000005422 blasting Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 125000002887 hydroxy group Chemical group [H]O* 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 229940045105 silver iodide Drugs 0.000 description 2
- 230000001629 suppression Effects 0.000 description 2
- 229920001187 thermosetting polymer Polymers 0.000 description 2
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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Abstract
The utility model relates to a hail-suppression and rain-enhancement rocket projectile, and belongs to the technical field of projectiles and rockets. The rocket projectile comprises a projectile head, a catalyst seeding device, a delay fuze, a recovery capsule and a rocket engine, wherein the projectile head, the catalyst seeding device, the delay fuze, the recovery device and the rocket engine are connected in sequence through screw threads; the catalyst seeding device adopts a shrapnel filling manner; one end of an umbrella capsule cover of the recovery device is fixed through a shearing screw, and the other end of the umbrella capsule cover of the recovery device is connected in a position clamping manner through a positioning platform structure; after a core mold is placed at the center of the inner part of a combustion chamber of the rocket engine, an engine grain is directly poured; two sets of firing circuits of the delay fuze are connected with an igniter of the seeding device and a fuel gas actuating cylinder respectively, thereby forming firing loops respectively; and a start-up circuit of the delay fuze is connected with a circuit closing/opening interface of the igniter of the seeding device, thereby forming a start-up closing/opening loop. The rocket projectile has the advantages of good seeding effect, controllable seeding opportunity, high reliability of the delay fuze and the recovery device, and high safety; and the maximal range of the rocket projectile can reach 12km.
Description
Technical field
The utility model relates to a kind of hail-proof rain-increasing rocket, belongs to play the arrow technical field.
Background technology
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 power tool of weather modification, for preventing hail disaster, increase precipitation, alleviating arid threat, played positive effect.
Yet also there is following shortcoming in present hail suppression artificial rainmaking rocket bullet on structural design:
1) sowing of traditional hail-proof rain-increasing medicament is to sow hole time-delay ejection by what sowing apparatus side in the rocket projectile had, the time-delay of the hail-proof rain-increasing medicament time of sowing is determined when body assembles, this structural design, it is less to cause the hail-proof rain-increasing medicament to sow area, and can not begin to sow according to the cloud layer actual height, cause the significant wastage of silver iodide;
2) retracting device of traditional hail-proof rain-increasing rocket is arranged on the body head, this structure makes body when the descending branch parachute-opening, because the rocket projectile flying speed is fast, easily break umbrella, poor stability, reliability is low, therefore can only set body parachute-opening when the ascent stage, has reduced the time of sowing and has sowed height; The separating mechanism of retracting device is by being threaded, relying on pneumatic means to shear screw thread during parachute-opening and promote the canopy unlatching, therefore the shearing force of separating mechanism threaded connection place being had relatively high expectations; And because the influence of air drag when rising, the parachute-opening poor reliability easily causes rocket projectile to injure accidents such as personnel, facility by a crashing object and takes place;
3) engine of traditional 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 exist sowing apparatus to sow problems such as efficient is low, the retracting device security reliability is poor, the engine 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 hail-proof rain-increasing rocket of the present utility model comprises bullet, catalyst seeding device, time-delay fuze, retracting device, rocket engine;
Wherein, the catalyst seeding device comprises seeding device body, center powder column, buster, sows bullet, seeding device housing, seeding device powder column, bag carry out layer, igniting powder column, closure plate, nozzle and seeding device igniter; The seeding device body is a solid cylinder, and seeding device body inside has cylindrical bore, filling center powder column in the cylindrical bore, and shothole is sowed in the processing of seeding device body sidewall; Sowing bullet is the bullet housing of an end opening, the inner bullet powder column of filling; Sow inside insertion of bullet opening one end and sow shothole, sow the bullet powder column and the powder column junction, center of bullet and place buster, and make three's cementation; The seeding device housing is the hollow cylinder of both ends open, fill seeding device powder column and igniting powder column in the seeding device housing successively, and it is heat insulation to carry out layer by bag between seeding device housing and the seeding device powder column; The nozzle blind end is the seeding device igniter fixedly, and nozzle wall has spray-hole in the other direction along the rocket projectile operation; Seeding device body, seeding device housing and nozzle are successively by being threaded, form the sealing component, the interior seeding device powder column gap of center powder column in the seeding device body cylindrical bore and seeding device housing is connected, igniting powder column in the seeding device housing is relative with the nozzle opening end, place closure plate between igniting powder column and the nozzle, the closure plate center has the combustion face, and control is to the combustion front of igniting powder column;
Constant time lag fuse in the fuse housing, time-delay fuze comprises delayed startup circuit, seeding device time-delay firing circuit and retracting device time-delay firing circuit, the delayed startup circuit is connected with retracting device time-delay firing circuit with seeding device time-delay firing circuit respectively, the delayed startup of delayed startup circuit control seeding device time-delay firing circuit and retracting device time-delay firing circuit;
Retracting device comprises that cabin body, location-plate, combustion gas do tube, umbrella hatchcover and recorery parachute and cross the cabin lead; Body two ends, cabin are the stationary positioned plate respectively, on the location-plate of cabin body one end fixedly combustion gas do the tube, the cabin body sidewall has the umbrella hatchcover, and the back-up block that umbrella hatchcover one end is done on the tube by shear screw and combustion gas is fixed, and the umbrella hatchcover other end is connected with cabin body screens by the positioning table structure; Recorery parachute comprises main chute, secondary umbrella and traction casing, and umbrella hatchcover lower end is by the umbrella cover of cotton rope auxiliary connection umbrella, and the cotton rope of secondary umbrella connects traction casing, and the traction casing that secondary umbrella connects entangles the umbrella cover of main chute, and the cotton rope of main chute and body two ends, cabin location-plate are fixed;
Rocket engine comprises connector, engine ignition tool, combustion chamber, motor grain, jet pipe, sealing blanking cover, stabilising arrangement; Connector internal fixation engine ignition tool, processing on/off road, engine ignition tool rear end interface, on/off road interface is an off-state before the igniting of engine ignition tool, on/off road interface is an on-state in engine ignition tool igniting back; Motor grain is directly poured into a mould after placing core by the center in inside, combustion chamber, takes out core after powder charge is finished; Stabilising arrangement internal fixation jet pipe, jet pipe rear end seal fixed ignition tool socket and time-delay bookbinding interface on the blanking cover by the sealing of sealing blanking cover; The connector of rocket engine outside, combustion chamber, stabilising arrangement are threaded successively, and the firing circuit of engine ignition tool passes the central through hole 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.
The seeding device body of catalyst seeding device is threaded with bullet, the nozzle of catalyst seeding device is connected with the threaded one end of fuse housing, the other end of fuse housing is done the tube threaded one end with the combustion gas of retracting device cabin body and is connected, and the other end of retracting device cabin body is threaded with the connector of rocket engine;
The firing circuit of seeding device igniter is connected by lead in the seeding device of time-delay fuze time-delay firing circuit and the catalyst seeding device, form the ignition loop, the firing circuit that combustion gas is done tin in the retracting device of time-delay fuze time-delay firing circuit and the retracting device is connected by lead, form the ignition loop, the delayed startup circuit of time-delay fuze passes retracting device by lead and links to each other with the on/off road interface of engine ignition tool, forms delayed startup on/off loop; The seeding device of time-delay fuze time-delay firing circuit and retracting device time-delay firing circuit pass the central through hole of retracting device, motor grain and jet pipe by lead respectively and link to each other with time-delay bookbinding interface on the sealing blanking cover.
Wherein, seeding device body, seeding device housing, nozzle all adopt the thermosetting nonmetallic materials; Motor grain is a fourth hydroxyl composite propellant, and seeding device powder column, center powder column, buster are and contain the agent of AgI flame, and the bullet powder column is for containing the agent of AgI flame or nanometer Ag I sows agent.
The course of work:
At first set rocket projectile in the time of sowing of catalyst seeding device and the deployment time of retracting device according to ceiling of clouds, by the time-delay bookbinding interface on the rocket engine sealing blanking cover, respectively to the bookbinding of delaying time of the seeding device of time-delay fuze time-delay firing circuit and retracting device time-delay firing circuit, at this moment, the on/off road interface of engine ignition tool rear end is an off-state, and the delayed startup circuit of time-delay fuze is an off-state; After emission big gun firing circuit startup that igniter socket on the rocket engine sealing blanking cover is connected, by engine ignition tool igniting blasting motor grain, for rocket projectile provides flying power; In the time of the igniting of engine ignition tool, make the on/off road interface of engine ignition tool rear end become on-state, the delayed startup circuit control seeding device time-delay firing circuit of time-delay fuze and retracting device time-delay firing circuit delayed startup; After the time-delay of seeding device time-delay firing circuit in the time-delay fuze reaches the scheduled time, seeding device time-delay firing circuit starts the igniting of seeding device igniter, the seeding device igniter is by ignite igniting powder column in the seeding device housing of nozzle, and then the center powder column in interior seeding device powder column of the seeding device housing that ignites and the seeding device body, the hail-proof rain-increasing catalyst that produces after the seeding device powder column ignites is from the spray-hole ejection of nozzle wall, after center powder column in the seeding device body ignites, to sow bullet by buster and dish out, sow hail-proof rain-increasing catalyst that bullet powder column that bullet ignites the bullet enclosure interior produces in flight course from sowing the boat tail ejection; After the time-delay of retracting device time-delay firing circuit reaches the scheduled time, retracting device time-delay firing circuit starts combustion gas and makees tube, combustion gas is made tube and is cut off and the fixing shear screw of umbrella hatchcover one end, the umbrella hatchcover is opened under aerodynamic effect, the fixing secondary umbrella in umbrella hatchcover lower end involves the back by traction casing with main chute and breaks away from body, main chute is opened fully, and the rocket projectile remains slow down gradually to drift about under the effect of parachute and descend, until finally landing.
The beneficial effects of the utility model:
(1) catalyst seeding device of the present utility model adopts shrapnel filling form, when improving loaded catalyst effectively, realized also that line is sowed and sowed the body that combines with space multistory and sow function, scope is sowed in the space of adopting this kind technical scheme to enlarge markedly the silver iodide catalyst, has strengthened the actual effect of hail-proof rain-increasing operation significantly;
(2) the utility model adopts time-delay fuze to controlling the opportunity of implementing catalyst and sowing, can in time set and sow time parameter according to the Practical Meteorological Requirements condition (as ceiling of clouds, thickness and drift velocity thereof, ground wind speed, wind direction etc.) of operation field, thereby realization is received the best in good time suitablely and is sowed the purpose of effect, and the on/off road interface that the control time-delay fuze starts is set in engine ignition tool rear end, has improved the reliability of time-delay fuze;
(3) the utility model is arranged on the middle part of hail-proof rain-increasing rocket with retracting device, has realized body in the descending branch parachute-opening, promptly sows at catalyst and finishes the back parachute-opening, has improved the time of sowing and has sowed height; The topology layout of middle part parachute-opening makes air force become parachute-opening power, and the parachute-opening reliability that makes retracting device of secondary umbrella that increases and traction casing is higher; And after parachute is aloft opened, the rocket projectile remains will keep a kind of and ground to be the attitude landing of a low-angle angle aloft and finally land, thereby reduced remains effectively because of harm, improved the security of hail-proof rain-increasing operation may cause when landing perpendicular to the attitude on ground;
(4) motor grain is directly poured into a mould after placing core by the center in the inside, combustion chamber of rocket engine of the present utility model, increased the space availability ratio of combustion chamber, thereby provide the hail-proof rain-increasing rocket range, hail-proof rain-increasing rocket maximum of the present utility model is penetrated and can be reached 12km, has satisfied in the high altitude localities and to have carried out carrier is transported in the hail-proof rain-increasing operation to payload instructions for use in the high-altitude.
Description of drawings
Fig. 1 is the utility model hail-proof rain-increasing rocket general structure schematic diagram;
Fig. 2 is the structural representation of catalyst seeding device in the utility model hail-proof rain-increasing rocket;
Fig. 3 is the structural representation of retracting device in the utility model hail-proof rain-increasing rocket;
Fig. 4 is the structural representation of rocket engine in the utility model hail-proof rain-increasing rocket;
Wherein, 1-catalyst seeding device; The 2-time-delay fuze; The 3-retracting device; The 4-rocket engine; The 6-bullet; The 7-body; 8-center powder column; 9 busters; 10 bullet housings; 11-bullet powder column; 12-seeding device housing; 13-seeding device powder column; The 14-bag is carried out layer; The 15-powder column of lighting a fire; The 16-closure plate; The 17-nozzle; 19-seeding device igniter; 20-cabin body; Tube is made in the 22-combustion gas; 23-umbrella hatchcover; The 24-recorery parachute; The 26-connector; 27-engine ignition tool; The 28-combustion chamber; The 29-motor grain; The 30-jet pipe; 31-seals blanking cover; The 32-stabilising arrangement.
The specific 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 hail-proof rain-increasing rocket of the present utility model comprises bullet 6, catalyst seeding device 1, time-delay fuze 2, retracting device 3, rocket engine 4;
Wherein, catalyst seeding device 1 comprises seeding device body 7, center powder column 8, buster 9, sows bullet, seeding device housing 12, seeding device powder column 13, bag carry out layer 14, igniting powder column 15, closure plate 16, nozzle 17 and seeding device igniter 19; Seeding device body 7 is a solid cylinder, and seeding device body 7 inside have cylindrical bore, filling center powder column 8 in the cylindrical bore, and shothole is sowed in the processing of seeding device body 7 sidewalls; Sowing bullet is the bullet housing 10 of an end opening, the inner bullet powder column 11 of filling; Sow inside insertion of bullet opening one end and sow shothole, sow the bullet powder column 11 of bullet and place buster 9, and make three's cementation with center powder column 8 junctions; Seeding device housing 12 is the hollow cylinder of both ends open, fill seeding device powder column 13 and igniting powder column 15 in the seeding device housing 12 successively, and it is heat insulation to carry out layer 14 by bag between seeding device housing 12 and the seeding device powder column 13; The nozzle blind end is seeding device igniter 19 fixedly, and nozzle wall has spray-hole in the other direction along the rocket projectile operation; Seeding device body 7, seeding device housing 12 and nozzle 17 are successively by being threaded, form the sealing component, center powder column 8 in seeding device body 7 cylindrical bore and seeding device housing 12 interior seeding device powder column 13 gaps are connected, igniting powder column 15 in the seeding device housing 12 is relative with the nozzle opening end, place closure plate 16 between igniting powder column 15 and the nozzle, closure plate 16 centers have the combustion face, and control is to the combustion front of igniting powder column 15;
Constant time lag fuse 2 in the fuse housing, time-delay fuze 2 comprises delayed startup circuit, seeding device time-delay firing circuit and retracting device time-delay firing circuit, the delayed startup circuit is connected with retracting device time-delay firing circuit with seeding device time-delay firing circuit respectively, the delayed startup of delayed startup circuit control seeding device time-delay firing circuit and retracting device time-delay firing circuit;
Retracting device 3 comprises that cabin body 20, location-plate, combustion gas do tube 22, umbrella hatchcover 23 and recorery parachute 24; Cabin body 20 two ends are the stationary positioned plate respectively, on the location-plate of cabin body 20 1 ends fixedly combustion gas do the tube 22, body 20 sidewalls in cabin have umbrella hatchcover 23, the back-up block that umbrella hatchcover 23 1 ends are done on the tube 22 by shear screw and combustion gas is fixed, and umbrella hatchcover 23 other ends are connected with 20 screens of cabin body by the positioning table structure; Recorery parachute 24 comprises main chute, secondary umbrella and traction casing, and umbrella hatchcover 23 lower ends are by the umbrella cover of cotton rope auxiliary connection umbrella, and the cotton rope of secondary umbrella connects traction casing, and the traction casing that secondary umbrella connects entangles the umbrella cover of main chute, and the cotton rope of main chute and cabin body 20 two ends location-plates are fixed;
Rocket engine 4 comprises connector 26, engine ignition tool 27, combustion chamber 28, motor grain 29, jet pipe 30, sealing blanking cover 31, stabilising arrangement 32; Connector 26 internal fixation engine ignition tools 27, processing on/off road, engine ignition tool 27 rear ends interface, on/off road interface is an off-state before 27 igniting of engine ignition tool, on/off road interface is an on-state in engine ignition tool 27 igniting backs; Motor grain is directly poured into a mould after placing core by the center in 28 inside, combustion chamber, takes out core after powder charge is finished; Stabilising arrangement 32 internal fixation jet pipes 30, jet pipe 30 rear ends seal fixed ignition tool socket and time-delay bookbinding interface on the blanking cover 31 by 31 sealings of sealing blanking cover; The connector 26 of rocket engine 4 outsides, combustion chamber 28, stabilising arrangement 32 are threaded successively, the firing circuit of engine ignition tool 27 passes the central through hole of motor grain 29 and jet pipe by lead and links to each other with igniter socket on the sealing blanking cover 31, forms to get angry the loop.
The seeding device body 7 of catalyst seeding device 1 is threaded with bullet 6, the nozzle 17 of catalyst seeding device 1 is connected with the threaded one end of fuse housing, the other end of fuse housing is done tube 22 threaded one ends with the combustion gas of retracting device 3 cabin bodies 20 and is connected, and the other end of retracting device 3 cabin bodies 20 is threaded with the connector 26 of rocket engine 4;
The firing circuit of seeding device igniter 19 is connected by lead in the seeding device of time-delay fuze 2 time-delay firing circuit and the catalyst seeding device 1, form the ignition loop, combustion gas is made tins 22 firing circuit and is connected by lead in the retracting device of time-delay fuze 2 time-delay firing circuit and the retracting device 3, form the ignition loop, the delayed startup circuit of time-delay fuze 2 passes retracting device 3 by lead and links to each other with the on/off road interface of engine ignition tool 27, forms delayed startup on/off loop; The seeding device of time-delay fuze 2 time-delay firing circuit and retracting device time-delay firing circuit pass the central through hole of retracting device 3, motor grain and jet pipe 30 by lead respectively and link to each other with time-delay bookbinding interface on the sealing blanking cover 31.
Wherein, seeding device body 7, seeding device housing 12, nozzle 17 all adopt the thermosetting nonmetallic materials; Motor grain 29 is a fourth hydroxyl composite propellant, and seeding device powder column 13, center powder column 8, buster 9 are and contain the agent of AgI flame, and bullet powder column 11 is for containing the agent of AgI flame or nanometer Ag I sows agent.
The course of work:
At first set rocket projectile in the time of sowing of catalyst seeding device 1 and the deployment time of retracting device 3 according to ceiling of clouds, by the time-delay bookbinding interface on the rocket engine 4 sealing blanking covers 31, respectively to the bookbinding of delaying time of the seeding device of time-delay fuze 2 time-delay firing circuit and retracting device time-delay firing circuit, at this moment, the on/off road interface of engine ignition tool 27 rear ends is an off-state, and the delayed startup circuit of time-delay fuze 2 is an off-state; After emission big gun firing circuit startup that igniter socket on the rocket engine 4 sealing blanking covers 31 is connected, by engine ignition tool 27 igniting blasting motor grains 29, for rocket projectile provides flying power; In the time of 27 igniting of engine ignition tool, make the on/off road interface of engine ignition tool 27 rear ends become on-state, the delayed startup circuit control seeding device time-delay firing circuit of time-delay fuze 2 and retracting device time-delay firing circuit delayed startup; After the time-delay of seeding device time-delay firing circuit in the time-delay fuze 2 reaches the scheduled time, seeding device time-delay firing circuit starts 19 igniting of seeding device igniter, seeding device igniter 19 is by ignite igniting powder column 15 in the seeding device housing 12 of nozzle 17, and then the center powder column 8 in ignite seeding device housing 12 interior seeding device powder columns 13 and the seeding device body 7, the hail-proof rain-increasing catalyst that produces after seeding device powder column 13 ignites is from the spray-hole ejection of nozzle wall, after center powder column 8 in the seeding device body 7 ignites, to sow bullet by buster 9 and dish out, sow hail-proof rain-increasing catalyst that bullet powder column 11 that bullet ignites bullet housing 10 inside produces in flight course from sowing the boat tail ejection; After the time-delay of retracting device time-delay firing circuit in the time-delay fuze 2 reaches the scheduled time, retracting device time-delay firing circuit starts combustion gas and makees tube 22, combustion gas is made tube 22 and is cut off and umbrella hatchcover 23 1 end fixed shear screws, umbrella hatchcover 23 is opened under aerodynamic effect, the fixing secondary umbrella in umbrella hatchcover 23 lower ends involves the back by traction casing with main chute and breaks away from body, main chute is opened fully, and the rocket projectile remains slow down gradually to drift about under the effect of parachute and descend, until finally landing.
Claims (1)
1. a hail-proof rain-increasing rocket is characterized in that comprising: bullet (6), catalyst seeding device (1), time-delay fuze (2), retracting device (3), rocket engine (4);
Wherein, catalyst seeding device (1) comprises seeding device body (7), center powder column (8), buster (9), sows bullet, seeding device housing (12), seeding device powder column (13), bag carry out layer (14), igniting powder column (15), closure plate (16), nozzle (17) and seeding device igniter (19); Seeding device body (7) is a solid cylinder, and seeding device body (7) inside has cylindrical bore, filling center powder column (8) in the cylindrical bore, and shothole is sowed in the processing of seeding device body (7) sidewall; Sowing bullet is the bullet housing (10) of an end opening, the inner bullet powder column (11) of filling; Sow inside insertion of bullet opening one end and sow shothole, sow the bullet powder column (11) of bullet and place buster (9), and make three's cementation with center powder column (8) junction; Seeding device housing (12) is the hollow cylinder of both ends open, fill seeding device powder column (13) and igniting powder column (15) in the seeding device housing (12) successively, and it is heat insulation to carry out layer (14) by bag between seeding device housing (12) and the seeding device powder column (13); The nozzle blind end is seeding device igniter (19) fixedly, and nozzle wall has spray-hole in the other direction along the rocket projectile operation; Seeding device body (7), seeding device housing (12) and nozzle (17) are successively by being threaded, form the sealing component, interior seeding device powder column (13) gap of center powder column (8) in seeding device body (7) cylindrical bore and seeding device housing (12) is connected, igniting powder column (15) in the seeding device housing (12) is relative with the nozzle opening end, place closure plate (16) between igniting powder column (15) and the nozzle, closure plate (16) center has the combustion face, and control is to the combustion front of igniting powder column (15);
Constant time lag fuse (2) in the fuse housing, time-delay fuze (2) comprises delayed startup circuit, seeding device time-delay firing circuit and retracting device time-delay firing circuit, the delayed startup circuit is connected with retracting device time-delay firing circuit with seeding device time-delay firing circuit respectively, the delayed startup of delayed startup circuit control seeding device time-delay firing circuit and retracting device time-delay firing circuit;
Retracting device (3) comprises that cabin body (20), location-plate, combustion gas do tube (22), umbrella hatchcover (23) and recorery parachute (24); Cabin body (20) two ends are the stationary positioned plate respectively, on the location-plate of cabin body (20) one ends fixedly combustion gas do the tube (22), cabin body (20) sidewall has umbrella hatchcover (23), the back-up block that umbrella hatchcover (23) one ends are done on the tube (22) by shear screw and combustion gas is fixed, and umbrella hatchcover (23) other end is connected with cabin body (20) screens by the positioning table structure; Recorery parachute (24) comprises main chute, secondary umbrella and traction casing, umbrella hatchcover (23) lower end is by the umbrella cover of cotton rope auxiliary connection umbrella, the cotton rope of secondary umbrella connects traction casing, and the traction casing that secondary umbrella connects entangles the umbrella cover of main chute, and the cotton rope of main chute and cabin body (20) two ends location-plate are fixed;
Rocket engine (4) comprises connector (26), engine ignition tool (27), combustion chamber (28), motor grain (29), jet pipe (30), sealing blanking cover (31), stabilising arrangement (32); Connector (26) internal fixation engine ignition tool (27), processing on/off road, engine ignition tool (27) rear end interface, on/off road interface is an off-state before engine ignition tool (27) igniting, and on/off road interface is an on-state in engine ignition tool (27) igniting back; Combustion chamber (28) is inner by directly pouring into a mould motor grain behind the center placement core, takes out core after powder charge is finished; Stabilising arrangement (32) internal fixation jet pipe (30), jet pipe (30) rear end are by sealing blanking cover (31) sealing, and sealing blanking cover (31) is gone up fixed ignition tool socket and time-delay bookbinding interface; Outside connector (26), combustion chamber (28), the stabilising arrangement (32) of rocket engine (4) is threaded successively, the firing circuit of engine ignition tool (27) passes the central through hole of motor grain (29) and jet pipe by lead and links to each other with igniter socket on the sealing blanking cover (31), forms to get angry the loop;
The seeding device body (7) of catalyst seeding device (1) is threaded with bullet (6), the nozzle (17) of catalyst seeding device (1) is connected with the threaded one end of fuse housing, the other end of fuse housing is done tube (22) threaded one end with the combustion gas of retracting device (3) cabin body (20) and is connected, and the other end of retracting device (3) cabin body (20) is threaded with the connector (26) of rocket engine (4);
The seeding device time-delay firing circuit of time-delay fuze (2) is connected by lead with the firing circuit of the middle seeding device igniter (19) of catalyst seeding device (1), form the ignition loop, the retracting device time-delay firing circuit of time-delay fuze (2) is connected by lead with the firing circuit that tube (22) is made in the middle combustion gas of retracting device (3), form the ignition loop, the delayed startup circuit of time-delay fuze (2) passes retracting device (3) by lead and links to each other with the on/off road interface of engine ignition tool (27), forms delayed startup on/off loop; The seeding device of time-delay fuze (2) time-delay firing circuit and retracting device time-delay firing circuit pass the central through hole of retracting device (3), motor grain and jet pipe (30) by lead respectively and bind interface with the time-delay on the sealing blanking cover (31) and link to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200311765U CN201993048U (en) | 2011-01-28 | 2011-01-28 | Hail-suppression and rain-enhancement rocket projectile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011200311765U CN201993048U (en) | 2011-01-28 | 2011-01-28 | Hail-suppression and rain-enhancement rocket projectile |
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| CN201993048U true CN201993048U (en) | 2011-09-28 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102168937A (en) * | 2011-01-28 | 2011-08-31 | 晋西工业集团有限责任公司 | Hail-suppression and rainfall-increment rocket bomb |
| CN105890469A (en) * | 2014-10-20 | 2016-08-24 | 重庆长安工业(集团)有限责任公司 | Artificial precipitation enhancement anti-hail rocket projectile capable of repeatedly spreading catalysts |
| CN108801079A (en) * | 2018-07-27 | 2018-11-13 | 西安迈瑞智联信息技术有限公司 | A kind of hail-proof rain-increasing rocket sequential control system |
-
2011
- 2011-01-28 CN CN2011200311765U patent/CN201993048U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102168937A (en) * | 2011-01-28 | 2011-08-31 | 晋西工业集团有限责任公司 | Hail-suppression and rainfall-increment rocket bomb |
| CN105890469A (en) * | 2014-10-20 | 2016-08-24 | 重庆长安工业(集团)有限责任公司 | Artificial precipitation enhancement anti-hail rocket projectile capable of repeatedly spreading catalysts |
| CN108801079A (en) * | 2018-07-27 | 2018-11-13 | 西安迈瑞智联信息技术有限公司 | A kind of hail-proof rain-increasing rocket sequential control system |
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