CN102168937A - Hail-suppression and rainfall-increment rocket bomb - Google Patents
Hail-suppression and rainfall-increment rocket bomb Download PDFInfo
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- CN102168937A CN102168937A CN2011100317658A CN201110031765A CN102168937A CN 102168937 A CN102168937 A CN 102168937A CN 2011100317658 A CN2011100317658 A CN 2011100317658A CN 201110031765 A CN201110031765 A CN 201110031765A CN 102168937 A CN102168937 A CN 102168937A
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Abstract
The invention discloses a hail-suppression and rainfall-increment rocket bomb, belonging to the technical field of projectiles. The rocket bomb comprises a bullet, a catalyst distributor, a delay fuse, a recovery capsule and a rocket engine which are in threaded connection in sequence; the catalyst spreader is filled in a cluster bomb way; one end of a parachute cabin cover of a recovery device is fixed through a shear screw, and the other end of the parachute cabin cover is connected by clamping through a positioning platform structure; a core die is arranged in the center of the inside of a combustion chamber of the rocket engine, and then an engine grain is directly poured; two sets of ignition circuits of the delay fuse are connected with a spreader ignition tool and a fuel gas actuating barrel respectively and constitute an ignition loop respectively; and a starting circuit of the delay fuse is connected with a switch-on/off interface of an engine ignition tool to constitute a delay starting switch-on/off loop. The hail-suppression and rainfall-increment rocket bomb has a good spreading effect and controllable spreading time; the delay fuse and the recovery device has high reliability and high safety; and the extreme range of the hail-suppression and rainfall-increment rocket bomb can be up to 12 kilometers.
Description
Technical field
The present invention relates to a kind of hail-proof rain-increasing rocket, belong to bullet 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 objective of the invention is to solve traditional hail-proof rain-increasing rocket and 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 objective of the invention is to be achieved through the following technical solutions;
A kind of hail-proof rain-increasing rocket of the present invention 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 in the time-delay fuze 2 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.
Beneficial effect of the present invention:
(1) catalyst seeding device of the present invention 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 present invention 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 present invention 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 invention, 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 invention 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 a hail-proof rain-increasing rocket general structure schematic diagram of the present invention;
Fig. 2 is the structural representation of catalyst seeding device in the hail-proof rain-increasing rocket of the present invention;
Fig. 3 is the structural representation of retracting device in the hail-proof rain-increasing rocket of the present invention;
Fig. 4 is the structural representation of rocket engine in the hail-proof rain-increasing rocket of the present invention;
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 invention is described further.
Embodiment
As shown in Figure 1, a kind of hail-proof rain-increasing rocket of the present invention 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 reaches the scheduled time, tube 22 is made in retracting device time-delay firing circuit startup combustion gas in the time-delay fuze 2, 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 (5)
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 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.
2. a kind of hail-proof rain-increasing rocket according to claim 1 is characterized in that comprising: seeding device body (7), seeding device housing (12), nozzle (17) all adopt the thermosetting nonmetallic materials.
3. a kind of hail-proof rain-increasing rocket according to claim 1 is characterized in that comprising: motor grain (29) is a fourth hydroxyl composite propellant.
4. a kind of hail-proof rain-increasing rocket according to claim 1 is characterized in that comprising: seeding device powder column (13), center powder column (8), buster (9) are and contain the agent of AgI flame.
5. a kind of hail-proof rain-increasing rocket according to claim 1 is characterized in that comprising: bullet powder column (11) contains the agent of AgI flame or nanometer Ag I sows agent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110031765 CN102168937B (en) | 2011-01-28 | 2011-01-28 | Hail-suppression and rainfall-increment rocket bomb |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110031765 CN102168937B (en) | 2011-01-28 | 2011-01-28 | Hail-suppression and rainfall-increment rocket bomb |
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| Publication Number | Publication Date |
|---|---|
| CN102168937A true CN102168937A (en) | 2011-08-31 |
| CN102168937B CN102168937B (en) | 2013-03-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110031765 Expired - Fee Related CN102168937B (en) | 2011-01-28 | 2011-01-28 | Hail-suppression and rainfall-increment rocket bomb |
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| CN102878870A (en) * | 2012-10-24 | 2013-01-16 | 晋西工业集团有限责任公司 | Extinguishment shrapnel type rocket bomb |
| CN103234400A (en) * | 2012-12-06 | 2013-08-07 | 北方华安工业集团有限公司 | Lateral cabin opening parachute structure used for anti-hail precipitation-enhancement rocket bomb |
| 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 |
| CN106839900A (en) * | 2017-03-28 | 2017-06-13 | 北京厚力德仪器设备有限公司 | A kind of hail-proof rain-increasing rocket based on warm cloud catalyst |
| CN107201971A (en) * | 2017-08-02 | 2017-09-26 | 曹袁 | Solid rocket motor case component with jet pipe |
| CN107956599A (en) * | 2017-12-15 | 2018-04-24 | 江西洪都航空工业集团有限责任公司 | A kind of tube grain fires face structure |
| CN109253666A (en) * | 2018-09-07 | 2019-01-22 | 陕西中天火箭技术股份有限公司 | A kind of low cost simulated training rocket |
| CN110966898A (en) * | 2019-12-06 | 2020-04-07 | 上海机电工程研究所 | Missile projectile recovery system after examination flight test |
| CN112444166A (en) * | 2020-12-07 | 2021-03-05 | 云南锐达民爆有限责任公司 | Timing accurate safe and reliable passive digital rain-increasing hail-suppression rocket |
| CN113314017A (en) * | 2021-07-04 | 2021-08-27 | 西北工业大学 | Model rocket kit for aerospace science popularization education |
| CN114524065A (en) * | 2022-02-25 | 2022-05-24 | 中国人民解放军海军潜艇学院 | Interactive actual combat underwater training equipment recovery method |
| CN115388716A (en) * | 2022-09-05 | 2022-11-25 | 关屹瀛 | Wireless spraying type recovery type lightning-extinguishing rocket projectile capable of being launched movably and operation method thereof |
| WO2023108567A1 (en) * | 2021-12-16 | 2023-06-22 | 陕西中天火箭技术股份有限公司 | Catalyst sowing device and high-temperature-resistant precipitation-increasing rocket having same |
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| CN103234400A (en) * | 2012-12-06 | 2013-08-07 | 北方华安工业集团有限公司 | Lateral cabin opening parachute structure used for anti-hail precipitation-enhancement rocket bomb |
| 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 |
| CN106839900A (en) * | 2017-03-28 | 2017-06-13 | 北京厚力德仪器设备有限公司 | A kind of hail-proof rain-increasing rocket based on warm cloud catalyst |
| CN107201971B (en) * | 2017-08-02 | 2019-02-01 | 曹袁 | Solid rocket motor case component with jet pipe |
| CN107201971A (en) * | 2017-08-02 | 2017-09-26 | 曹袁 | Solid rocket motor case component with jet pipe |
| CN107956599A (en) * | 2017-12-15 | 2018-04-24 | 江西洪都航空工业集团有限责任公司 | A kind of tube grain fires face structure |
| CN109253666A (en) * | 2018-09-07 | 2019-01-22 | 陕西中天火箭技术股份有限公司 | A kind of low cost simulated training rocket |
| CN109253666B (en) * | 2018-09-07 | 2020-10-09 | 陕西中天火箭技术股份有限公司 | Low-cost simulation training rocket |
| CN110966898A (en) * | 2019-12-06 | 2020-04-07 | 上海机电工程研究所 | Missile projectile recovery system after examination flight test |
| CN110966898B (en) * | 2019-12-06 | 2022-07-01 | 上海机电工程研究所 | Missile projectile recovery system after completion of assessment flight test |
| CN112444166A (en) * | 2020-12-07 | 2021-03-05 | 云南锐达民爆有限责任公司 | Timing accurate safe and reliable passive digital rain-increasing hail-suppression rocket |
| CN113314017A (en) * | 2021-07-04 | 2021-08-27 | 西北工业大学 | Model rocket kit for aerospace science popularization education |
| WO2023108567A1 (en) * | 2021-12-16 | 2023-06-22 | 陕西中天火箭技术股份有限公司 | Catalyst sowing device and high-temperature-resistant precipitation-increasing rocket having same |
| CN114524065A (en) * | 2022-02-25 | 2022-05-24 | 中国人民解放军海军潜艇学院 | Interactive actual combat underwater training equipment recovery method |
| CN115388716A (en) * | 2022-09-05 | 2022-11-25 | 关屹瀛 | Wireless spraying type recovery type lightning-extinguishing rocket projectile capable of being launched movably and operation method thereof |
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