CN118030314A - Engine with silver iodide flame agent as propellant - Google Patents
Engine with silver iodide flame agent as propellant Download PDFInfo
- Publication number
- CN118030314A CN118030314A CN202410150154.2A CN202410150154A CN118030314A CN 118030314 A CN118030314 A CN 118030314A CN 202410150154 A CN202410150154 A CN 202410150154A CN 118030314 A CN118030314 A CN 118030314A
- Authority
- CN
- China
- Prior art keywords
- engine
- igniter
- ignition
- silver iodide
- shell
- 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.)
- Pending
Links
- 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 title claims abstract description 72
- 229910021612 Silver iodide Inorganic materials 0.000 title claims abstract description 72
- 229940045105 silver iodide Drugs 0.000 title claims abstract description 72
- 239000003795 chemical substances by application Substances 0.000 title claims abstract description 62
- 239000003380 propellant Substances 0.000 title claims abstract description 32
- 238000002485 combustion reaction Methods 0.000 claims abstract description 22
- 239000007921 spray Substances 0.000 claims abstract description 22
- 238000007789 sealing Methods 0.000 claims abstract description 20
- 239000000843 powder Substances 0.000 claims description 23
- 238000005266 casting Methods 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000000446 fuel Substances 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 230000001629 suppression Effects 0.000 claims description 3
- 239000002360 explosive Substances 0.000 abstract description 10
- 230000004048 modification Effects 0.000 abstract description 3
- 238000012986 modification Methods 0.000 abstract description 3
- 239000007787 solid Substances 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 11
- 230000001965 increasing effect Effects 0.000 description 9
- 230000000694 effects Effects 0.000 description 5
- 238000009331 sowing Methods 0.000 description 5
- 239000002737 fuel gas Substances 0.000 description 4
- YXFVVABEGXRONW-UHFFFAOYSA-N Toluene Chemical compound CC1=CC=CC=C1 YXFVVABEGXRONW-UHFFFAOYSA-N 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- NLKNQRATVPKPDG-UHFFFAOYSA-M potassium iodide Chemical compound [K+].[I-] NLKNQRATVPKPDG-UHFFFAOYSA-M 0.000 description 3
- 241001083514 Gayophytum Species 0.000 description 2
- 229920002121 Hydroxyl-terminated polybutadiene Polymers 0.000 description 2
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- -1 butyl hydroxy Chemical group 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000000806 elastomer Substances 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 229920000642 polymer Polymers 0.000 description 1
- 150000003384 small molecules Chemical class 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
-
- A—HUMAN NECESSITIES
- A01—AGRICULTURE; FORESTRY; ANIMAL HUSBANDRY; HUNTING; TRAPPING; FISHING
- A01G—HORTICULTURE; CULTIVATION OF VEGETABLES, FLOWERS, RICE, FRUIT, VINES, HOPS OR SEAWEED; FORESTRY; WATERING
- A01G15/00—Devices or methods for influencing weather conditions
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
Landscapes
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Atmospheric Sciences (AREA)
- Environmental Sciences (AREA)
- Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
Abstract
The invention discloses an engine taking silver iodide flame agent as a propellant, belonging to the technical field of weather modification, comprising a front end socket, an igniter, a shell, a grain and a spray pipe; the shell is a circular tube with two open ends; the front seal head and the spray pipe are respectively arranged at two ends of the shell; the igniter is arranged on the front sealing head; the two ends of the igniter are respectively an ignition end and a connecting end, the ignition end penetrates through the front end socket and stretches into the shell, and the connecting end is used for connecting an ignition circuit of the whole engine; the ignition circuit of the engine is connected with the rocket launching controller, and the rocket launching controller is used for generating an ignition signal; a combustion chamber is formed among the front sealing head, the igniter, the spray pipe and the shell; the explosive column is arranged in the combustion chamber, is used as a propellant of the engine, and comprises the silver iodide flame agent. According to the invention, the silver iodide flame agent is used as a power energy source of the solid rocket to replace the original engine propellant, so that the effective load capacity of the rocket can be improved, and the carrying capacity of the silver iodide flame agent of the single-shot rocket is improved.
Description
Technical Field
The invention belongs to the technical field of weather modification, and particularly relates to an engine taking silver iodide flame agent as a propellant.
Background
Cloud catalysts based on silver iodide are widely used in weather-friendly operations to produce artificial ice nuclei. At present, a rocket, a carrier or a ground smoke furnace is mainly adopted in China to broadcast a silver iodide flame agent, and the silver iodide flame agent is mainly prepared by mixing ammonium perchlorate, silver iodide, potassium iodide, organic combustibles and some additives. The rocket operation is that the silver iodide flame agent is sent into the high altitude through the rocket engine, and the silver iodide artificial ice core is formed by burning the flame agent in the air, thereby realizing the functions of increasing rain and suppressing hail.
Typically, the silver iodide flame agent is all part of the load, so the total carrying amount of the silver iodide flame agent that can be carried by the rocket is completely dependent on the load capacity of the rocket. The load of the silver iodide flame agent in the existing rocket, carrier or ground smoke furnace sowing mode cannot fully exert the rain-increasing hail-suppressing effect of the silver iodide flame agent, so that the load of the silver iodide flame agent of the rocket needs to be improved in a mode, and the rain-increasing hail-suppressing effect is improved.
Disclosure of Invention
In view of the above, the invention provides an engine using silver iodide flame agent as propellant, which uses silver iodide flame agent as power energy of solid rocket instead of original engine propellant, so as to remarkably improve the effective load capacity of rocket and greatly improve the carrying capacity of silver iodide flame agent of single rocket.
The invention is realized by the following technical scheme:
An engine using silver iodide flame agent as propellant, comprising: the front end socket, the igniter, the shell, the explosive column and the spray pipe;
the shell is a circular tube with two open ends;
the front seal head is arranged at one end of the shell, and the spray pipe is arranged at the other end of the shell;
The igniter is arranged on the front sealing head; one end of the igniter is an ignition end, and the other end of the igniter is a connecting end; the ignition end of the igniter penetrates through the front end socket and stretches into the shell, and the connection end of the igniter is used for being connected with an ignition circuit of the whole engine; the ignition circuit of the engine is connected with the rocket launching controller, and the rocket launching controller is used for generating an ignition signal;
A combustion chamber is formed among the front sealing head, the igniter, the spray pipe and the shell;
The grain is arranged in the combustion chamber, is used as a propellant of an engine and comprises a silver iodide flame agent;
After the engine is ignited, the igniter ignites the explosive column, the silver iodide flame agent burns to form silver iodide artificial ice cores, and the silver iodide artificial ice cores are sprayed out by the spray pipe to realize rain enhancement and hail suppression.
Further, the igniter includes: the ignition device comprises a plug, an igniter shell, ignition powder, a sealing cover, two binding posts, two ignition heads and two wires;
The plug is of a cylindrical structure and is fixedly connected with the front end socket;
the igniter shell is of a cylindrical structure with two open ends, and one end of the igniter shell is fixedly connected with the plug; a plurality of gas holes are processed on the igniter shell, and the gas holes are uniformly distributed; the outer surface of the igniter shell is adhered with an aluminized film, and the aluminized film covers all the fuel holes of the igniter shell;
the sealing cover is arranged on the other end of the igniter shell;
the plug, the igniter shell bonded with the aluminized film and the sealing cover form a closed space together;
The two binding posts are respectively arranged in the plug, and both the two binding posts penetrate through the two ends of the plug;
The two ignition heads are both positioned in the closed space; two ends of each ignition head are respectively connected with one end of each binding post in the closed space in a one-to-one correspondence manner;
One end of each of the two wires is connected to the other end of each of the two binding posts, which extends out of the plug, in a one-to-one correspondence manner;
the ignition powder is filled in the closed space;
The two wires, the two binding posts and the two ignition heads are connected to form an ignition circuit of the engine, wherein the two binding posts, the two ignition heads, the ignition powder, the igniter shell and the sealing cover jointly form an ignition end of the igniter, and the two binding posts and the two wires jointly form a connection end of the igniter.
Further, the powder strength of the ignition powder was 35.9X104 N.multidot.m/kg.
Further, when the rocket engine does not work, the other ends of the two wires are connected with each other, and the ignition circuit forms a short circuit state;
Before using the engine, disconnecting the two wires connected with each other, and after disconnecting, obtaining the two wires which are respectively connected with the ignition circuit of the rocket body.
Further, the silver iodide flame agent is formed by casting, solidifying and forming or by a steel film pressing mode.
Further, the nozzle has a Laval nozzle pneumatic inner profile.
Further, the combustion speed formula using silver iodide flame agent as propellant is as follows: r=2.68P 0.409;
wherein r is the burning speed, the unit is mm/s, P is the working pressure, and the unit is MPa;
the combustion speed formula is used to calculate an internal ballistic performance parameter of the engine.
Further, the surface of the grain is roughened.
Further, the engine may be a first stage engine or a second stage engine.
The beneficial effects are that:
(1) According to the engine using the silver iodide flame agent as the propellant, the combustion chamber is formed among the front end enclosure, the spray pipe and the shell, so that a high-temperature and high-pressure gas space can be provided for the combustion of the explosive column, and the high-temperature and high-pressure gas formed by the combustion of the explosive column can be ensured to be sprayed out from the rear end of the engine to form forward thrust; the components of the propellant grains are silver iodide flame agents, and the silver iodide flame agents serve as the propellant and can directly provide power for the rocket; silver iodide artificial ice nuclei generated by the silver iodide flame agent during combustion are sprayed out by a spray pipe along with high-temperature and high-pressure gas formed during the combustion of the explosive column, so that the effects of rain enhancement and hail suppression are realized; the silver iodide flame agent is used as the propellant, so that the effective load capacity of the rocket to the silver iodide flame agent can be remarkably improved, and the carrying capacity of the silver iodide flame agent of the single-shot rocket can be improved, thereby improving the rain-increasing hail-suppressing effect of the rocket.
(2) According to the engine taking the silver iodide flame agent as the propellant, the igniter comprises the two ignition heads, when one ignition head is damaged, the ignition can be realized through the other ignition head, and the ignition reliability of the engine can be improved.
(3) The engine with silver iodide flame agent as propellant has the igniting powder of 35.9 x 104 N.m/kg and high igniting powder, and can raise the igniting speed of the powder.
(4) According to the engine using the silver iodide flame agent as the propellant, when the engine does not work, the other ends of the two wires are connected with each other, so that the ignition circuit forms a short circuit state, and the engine ignition caused by accidental ignition of the dead point flame can be prevented.
(5) The engine using silver iodide flame agent as propellant, the spray pipe is provided with a Laval spray pipe pneumatic inner molded surface, high-temperature and high-pressure fuel gas can be sprayed to the right rear or the inclined rear of the engine, and the reaction force generated during the gas spraying is used as the thrust of the engine.
(6) According to the engine using the silver iodide flame agent as the propellant, the surface of the grain is roughened, so that the grain is easier to ignite, and the ignition delay time of the grain is reduced.
(7) The engine using the silver iodide flame agent as the propellant can be used as a first-stage engine or a second-stage engine, and the range of a rocket can be increased when the engine is used as the second-stage engine, so that the sowing height or the sowing radius of the silver iodide flame agent can be increased.
Drawings
FIG. 1 is a schematic diagram of an engine configuration of the present invention;
FIG. 2 is a schematic view of an igniter according to the present invention;
Wherein, 1-front end socket, 2-igniter, 3-shell, 4-grain, 5-spray tube, 6-wire, 7-terminal, 8-plug, 9-igniter shell, 10-igniter, 11-ignition powder, 12-closing cap.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
Example 1:
the embodiment provides an engine using silver iodide flame agent as a propellant, as shown in fig. 1, including: the front end socket 1, the igniter 2, the shell 3, the grain 4 and the spray pipe 5;
the shell 3 is a circular tube with two open ends, the left side in fig. 1 is the front end of the shell 3, and the right side is the rear end of the shell 3;
the front end enclosure 1 is arranged at the front end of the shell 3, the front end enclosure 1 is of a cylindrical structure with one end open and one end closed, a boss is machined at the open end of the front end enclosure 1 along the circumferential direction of the front end enclosure 1, the closed end of the front end enclosure 1 is inserted from the front end of the shell 3, and the boss is abutted against the open end of the front end enclosure 1;
The spray pipe 5 is arranged at the rear end of the shell 3; in this embodiment, the nozzle 5 has a laval nozzle pneumatic inner surface, so that the high-temperature and high-pressure fuel gas is sprayed to the right rear or the inclined rear, and the reaction force generated when the fuel gas is sprayed is used as the thrust of the engine;
after the front end socket 1 and the spray pipe 5 are arranged, a combustion chamber is formed among the front end socket 1, the spray pipe 5 and the shell 3;
The grain 4 is arranged in the combustion chamber; the grain 4 is used as a propellant of a rocket engine, and a high-temperature and high-pressure gas space is formed in a combustion chamber when the grain 4 is combusted; the grain 4 is formed by casting, solidifying and forming of silver iodide flame agent; in this embodiment, the silver iodide flame agent is formed by mixing and curing a butyl hydroxy adhesive (HTPB) polymer adhesive and a curing agent Toluene Dicyanoate (TDI) small molecule; the HTPB adhesive and TDI react with each other at a proper temperature to form a three-dimensional reticular structure elastomer, and the three-dimensional reticular structure fixes silver iodide particles, so that the integral solidification of the silver iodide flame agent is realized; the casting, curing and forming process is mature and the cost is controllable; the silver iodide flame agent can also be formed by a steel film pressing mode; in the embodiment, the surface of the grain 4 is roughened, and the ignition performance of the grain is improved by increasing the roughness of the surface of the grain 4, so that the grain 4 is easier to ignite, and the ignition delay time of the grain 4 is reduced;
The igniter 2 is coaxially arranged on the closed end of the front end socket 1 and is positioned in the inner space of the front end socket 1 and the shell 3; as shown in fig. 2, the igniter 2 includes: the ignition device comprises a plug 8, an igniter shell 9, ignition powder 11, a sealing cover 12, two binding posts 7, two ignition heads 10 and two leads 6;
the plug 8 is of a cylindrical structure, and the plug 8 is fixedly connected with the closed end of the front sealing head 1;
the igniter shell 9 is of a cylindrical structure with two open ends, one end of the igniter shell 9 is fixedly connected with one end of the plug 8, and the other end of the igniter shell 9 is positioned in a circular truncated cone-shaped through hole in the explosive column 4; a plurality of gas holes are processed on the igniter shell 9 and are uniformly distributed; the outer surface of the igniter shell 9 is adhered with an aluminized film, and all the fuel holes of the igniter shell 9 are covered by the aluminized film;
The sealing cover 12 is arranged on the other end of the igniter shell 9;
the plug 8, the igniter shell 9 bonded with the aluminized film and the sealing cover 12 form a closed space together;
The two binding posts 7 are respectively arranged in the plug 8, and the two binding posts 7 penetrate through two ends of the plug 8;
Both the electric fire heads 10 are positioned in the closed space; two ends of each ignition head 10 are respectively connected to one end of two binding posts in the closed space in a one-to-one correspondence manner; the ignition head 10 is connected with one end of the binding post 7 in the closed space, and one ends of the two wires 6 are respectively connected with the other end of the binding post 7 in a one-to-one correspondence manner (namely, the end of the binding post 7 extending out of the plug 8) is connected; when one ignition head 10 is damaged, the igniter 2 can realize ignition through the other ignition head 10, so that the ignition reliability of the engine can be improved;
The ignition powder 11 is filled in the closed space; in this embodiment, the ignition powder 11 is a mixed high-energy ignition powder, so that the ignition speed of the powder column 4 can be increased; the powder strength of the mixed high-energy ignition powder is 35.9X104 N.m/kg (29X 104 N.m/kg higher than that of the black powder);
The two wires 6, the two binding posts 7 and the two ignition heads 10 together form an ignition circuit of the engine, wherein the two binding posts 7, the two ignition heads 10, the ignition powder 11, the igniter shell 9 and the sealing cover 12 together form an ignition end of the igniter 2, and the two binding posts 7 and the two wires 6 together form a connection end of the igniter 2;
the connecting end of the igniter 2 is used for connecting an ignition circuit of the rocket assembly; when the rocket engine does not work, the other ends of the two wires 6 (namely, the ends which are not connected with the two binding posts 7) are connected with each other, and the ignition circuit forms a short circuit state and is used for preventing the ignition of the engine caused by accidental ignition of the dead-point flame 10; before the engine is used, the two parallel wires 6 are disconnected, the two wires 6 are respectively connected with the ignition circuit of the rocket body to form a new ignition circuit, and the new ignition circuit is required to be short-circuited until the ignition operation is implemented;
When the silver iodide flame agent is used as the propellant, the combustion speed formula of the propellant is r=2.68P 0.409, wherein r is the combustion speed, the unit is mm/s, and P is the working pressure, the unit is MPa; the combustion speed formula is used for calculating the internal ballistic performance parameter of the engine when the silver iodide flame agent is used as a propellant;
The engine in this example was subjected to the ground test as follows: firstly, the engine can normally ignite, the ignition delay time is about 0.03s, and the engine meets the requirements in view of the fact that the ignition delay time of the common engine is not more than 0.08 s; secondly, the thrust and the pressure do not obviously fluctuate, the engine works normally, the critical pressure of the engine is 2MPa, the specific impulse of the engine is 150s, and the specific impulse is smaller than 200s of the specific impulse of a common double-click propellant, but the silver iodide flame agent serving as the propellant of the engine is a payload, so that the load capacity of the rocket can be obviously improved;
The engine in this embodiment can be used not only as a first-stage engine but also as a second-stage engine, and the range of the rocket can be increased by using the engine in this embodiment as the second-stage engine, so that the sowing height or sowing radius of the silver iodide flame agent can be increased.
Working principle:
Before operation, a new ignition circuit is connected with a rocket launching controller, and when in operation, the launching controller generates an ignition signal to cause the ignition head 10 to ignite so as to ignite the ignition powder 11; the ignition gas generated when the ignition powder 11 burns passes through the aluminized film and is sprayed out from the sealing hole on the igniter shell 9; the sprayed ignition gas contacts the surface of the explosive column 4 and ignites the explosive column 4; the high-temperature and high-pressure fuel gas generated during the combustion of the explosive column 4 is sprayed out of the spray pipe 5, and at the moment, a reaction force is generated and provides power for the rocket; the grain 4 solidified and formed by the silver iodide flame agent forms silver iodide artificial ice nuclei when burned in the air, and is sprayed out of the spray pipe 5 along with high-temperature high-pressure gas, so that rain and hail are increased; as the carrying amount of the silver iodide flame agent of the engine is increased, the effect of enhancing rain and hail of the silver iodide can be improved.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. An engine using silver iodide flame agent as propellant, comprising: the device comprises a front seal head (1), an igniter (2), a shell (3), a grain (4) and a spray pipe (5);
The shell (3) is a round pipe with two open ends;
the front seal head (1) is arranged at one end of the shell (3), and the spray pipe (5) is arranged at the other end of the shell (3);
The igniter (2) is arranged on the front sealing head (1); one end of the igniter (2) is an ignition end, and the other end is a connecting end; the ignition end of the igniter (2) penetrates through the front end socket (1) and stretches into the shell (3), and the connection end of the igniter (2) is used for being connected with an ignition circuit of the whole engine; the ignition circuit of the engine is connected with the rocket launching controller, and the rocket launching controller is used for generating an ignition signal;
a combustion chamber is formed among the front sealing head (1), the igniter (2), the spray pipe (5) and the shell (3);
the grain (4) is arranged in the combustion chamber, the grain (4) is used as a propellant of an engine, and the grain is composed of a silver iodide flame agent;
after the engine is ignited, an igniter (2) ignites a grain (4), a silver iodide flame agent burns to form silver iodide artificial ice nuclei, and the silver iodide artificial ice nuclei are sprayed out by a spray pipe (5) to realize rain enhancement and hail suppression.
2. An engine with silver iodide flame agent as claimed in claim 1, characterized in that the igniter (2) comprises: the igniter comprises a plug (8), an igniter shell (9), ignition powder (11), a sealing cover (12), two binding posts (7), two ignition heads (10) and two leads (6);
the plug (8) is of a cylindrical structure, and the plug (8) is fixedly connected with the front end socket (1);
The igniter shell (9) is of a cylindrical structure with two open ends, and one end of the igniter shell (9) is fixedly connected with the plug (8); a plurality of gas holes are processed on the igniter shell (9), and the gas holes are uniformly distributed; the outer surface of the igniter shell (9) is adhered with an aluminized film, and all the fuel holes of the igniter shell (9) are covered by the aluminized film;
The sealing cover (12) is arranged on the other end of the igniter shell (9);
the plug (8), the igniter shell (9) adhered with the aluminized film and the sealing cover (12) form a closed space together;
the two binding posts (7) are respectively arranged in the plug (8), and the two binding posts (7) penetrate through the two ends of the plug (8);
Both ignition heads (10) are positioned in the closed space; two ends of each ignition head (10) are respectively connected with one end of each binding post (7) in the closed space in a one-to-one correspondence manner;
One end of each of the two wires (6) is correspondingly connected with the other end of each of the two binding posts (7) extending out of the plug (8);
the ignition powder (11) is filled in the closed space;
The two wires (6), the two binding posts (7) and the two ignition heads (10) are connected to form an ignition circuit of the engine, wherein the two binding posts (7), the two ignition heads (10), the ignition powder (11), the igniter shell (9) and the sealing cover (12) jointly form an ignition end of the igniter (2), and the two binding posts (7) and the two wires (6) jointly form a connection end of the igniter (2).
3. An engine with silver iodide flame as claimed in claim 2, characterized in that the ignition charge (11) has a charge strength of 35.9 x 104N-m/kg.
4. An engine with silver iodide flame agent as claimed in claim 2, characterized in that the other ends of the two wires (6) are connected to each other when the rocket engine is not in operation, the ignition circuit forming a short-circuit state;
Before using the engine, disconnecting the two wires (6) connected with each other, and after disconnecting, obtaining the two wires (6) to be respectively connected with an ignition circuit of the rocket body.
5. An engine using silver iodide flame agent as propellant as set forth in claim 1, wherein the silver iodide flame agent is formed by casting, solidifying or by steel film pressing.
6. An engine with silver iodide flame agent as claimed in claim 1, characterized in that the nozzle (5) has a laval nozzle aerodynamic inner profile.
7. An engine with silver iodide flame agent as set forth in any one of claims 1 to 6, wherein the combustion speed formula with silver iodide flame agent as propellant is: r=2.68P 0.409;
wherein r is the burning speed, the unit is mm/s, P is the working pressure, and the unit is MPa;
the combustion speed formula is used to calculate an internal ballistic performance parameter of the engine.
8. An engine with silver iodide flame agent as claimed in claim 1, characterized in that the surface of the grain (4) is roughened.
9. An engine using silver iodide flame agent as set forth in claim 1, wherein the engine can be used as a first stage engine or a second stage engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410150154.2A CN118030314A (en) | 2024-02-02 | 2024-02-02 | Engine with silver iodide flame agent as propellant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410150154.2A CN118030314A (en) | 2024-02-02 | 2024-02-02 | Engine with silver iodide flame agent as propellant |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118030314A true CN118030314A (en) | 2024-05-14 |
Family
ID=90992661
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410150154.2A Pending CN118030314A (en) | 2024-02-02 | 2024-02-02 | Engine with silver iodide flame agent as propellant |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118030314A (en) |
-
2024
- 2024-02-02 CN CN202410150154.2A patent/CN118030314A/en active Pending
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