CN100419245C - Delay igniter for composite enhanced distance bullet rocket engine - Google Patents
Delay igniter for composite enhanced distance bullet rocket engine Download PDFInfo
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- CN100419245C CN100419245C CNB2004100968396A CN200410096839A CN100419245C CN 100419245 C CN100419245 C CN 100419245C CN B2004100968396 A CNB2004100968396 A CN B2004100968396A CN 200410096839 A CN200410096839 A CN 200410096839A CN 100419245 C CN100419245 C CN 100419245C
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- starting mix
- gunpowder
- transmitting
- box
- igniter
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Abstract
The present invention discloses a delay igniter for composite enhanced distance bullet rocket engines of bottom row rockets, and a delay mechanism in the present invention is designed as a fully sealed structure. A flame cap and a fixed air chamber are arranged in the delay mechanism so as to assure the stable burning of lighting and transmitting gunpowder, a gunpowder transmitting box is in a front and back separation type, one gunpowder transmitting box is arranged at the back end of a propellant stick of the rocket engine, and the other gunpowder transmitting box is arranged at the front end of the propellant stick. The center of the propellant stick between the two gunpowder transmitting boxes is provided with a flame energy transmission path of which the diameter is from 15 to 180mm, and the present invention effectively solves the problems of fire lighting and transmitting reliability and delay time stability of the igniter.
Description
Technical field
The present invention relates to the rocket motor Dark Ignition tool of end row's rocket composite distance increasing shell.
Background technique
The ignition mechanism of common rocket motor is positioned at the front end of rocket motor propellant agent, and igniter and medicine box in the ignition mechanism design for one, realizes that easily point passes fiery function reliably.Adopt the composite distance increasing bullet of elder generation's end row back rocket cascaded structure, for increasing the charge space of rocket motor propellant agent coyote hole, can only be with rocket Dark Ignition tool postposition in the rocket tube rear end, its problem of bringing is, rocket tube rear end gun pressure height, overload is high, rotational speed is high, and igniter is lighted a fire from the propellant agent ear end face, because propellant charge is longer, igniter starting mix box flame energy has lost a lot when arriving the propellant charge front end by certain passage, can not guarantee that igniter point passes the reliability and the defer time stability of fire.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of rocket motor Dark Ignition tool of composite distance increasing shell, the Dark Ignition that is positioned at the rocket tube rear end is had imitate the fiery function of realization point biography reliably.
Rocket motor Dark Ignition tool for the composite distance increasing shell of forming by base, firing lock, delay device, starting mix box, the delay device that the present invention adopts is hermetically sealed, igniter cap and fixing air chamber are arranged in the delay device, the starting mix box is the front and back separately placed type, a starting mix box is arranged on the rear end of rocket motor propellant charge, and another starting mix box is arranged on the front end of propellant charge.There is the flame energy transfer passage of 15 to 180 millimeters of diameters at propellant charge center between above-mentioned former and later two starting mix boxes.
After adopting said structure, because delay device is hermetically sealed and leaves fixedly air chamber, can the guarantee point starting mix smooth combustion in fixing air chamber, delay device and igniter cap are integrated, make delay device in a fiery process of biography, not destroy sealing configuration, be not subjected to the influence of outside high speed rotating environment.The starting mix box is the front and back separately placed type, increases a starting mix box at the propellant agent front end, and obviously enhanced system point flame transfer dependability has fundamentally solved igniter point and passed the reliability of fire and the problem of defer time stability.
Embodiment
During the cannon emission, the gas that gunpowder produces makes the interior firing lock effect of igniter and lights delay device, through lighting back starting mix box after certain defer time, back starting mix box is lighted the passage of back by the propellant agent center hole, give preceding starting mix box with the flame energy transfer, preceding starting mix box amplifies the flame energy, and finally lights the rocket motor propellant agent.
Description of drawings
1. delay devices among the figure, 2. back starting mix box, 3. preceding starting mix box, 4. propellant charge, 5. base, 6. firing lock.
Claims (2)
1. the rocket motor Dark Ignition tool of a composite distance increasing shell, it comprises base, firing lock, delay device, starting mix box, it is characterized in that: described delay device (1) is for hermetically sealed, in igniter cap and fixing air chamber are arranged, described starting mix box is the front and back separately placed type, back starting mix box (2) is arranged on the rear end of propellant charge (4), and preceding starting mix box (3) is arranged on the front end of propellant charge (4), and the propellant charge between two starting mix boxes has flame energy transfer passage.
2. the rocket motor Dark Ignition tool of composite distance increasing shell according to claim 1, it is characterized in that: the diameter of the flame energy transfer passage in the propellant charge (4) between former and later two starting mix boxes is 15 to 180 millimeters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100968396A CN100419245C (en) | 2004-12-08 | 2004-12-08 | Delay igniter for composite enhanced distance bullet rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100968396A CN100419245C (en) | 2004-12-08 | 2004-12-08 | Delay igniter for composite enhanced distance bullet rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1786451A CN1786451A (en) | 2006-06-14 |
| CN100419245C true CN100419245C (en) | 2008-09-17 |
Family
ID=36784042
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2004100968396A Active CN100419245C (en) | 2004-12-08 | 2004-12-08 | Delay igniter for composite enhanced distance bullet rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100419245C (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102967181B (en) * | 2012-11-29 | 2015-03-04 | 中国人民解放军济南军区72465部队 | Accurate fuse transferring powder box structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1468814A (en) * | 1974-12-03 | 1977-03-30 | Secr Defence | Rocket propulsion motors |
| FR2651834A1 (en) * | 1989-09-08 | 1991-03-15 | Thomson Brandt Armements | SAFETY IGNITER FOR PROPELLER. |
| US6244185B1 (en) * | 2000-02-03 | 2001-06-12 | Po Sing Fireworks Ltd. | Skyrocket |
| US20040068979A1 (en) * | 2002-10-11 | 2004-04-15 | Hy Pat Corporation | Ignition systems for hybrid and solid rocket motors |
-
2004
- 2004-12-08 CN CNB2004100968396A patent/CN100419245C/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1468814A (en) * | 1974-12-03 | 1977-03-30 | Secr Defence | Rocket propulsion motors |
| FR2651834A1 (en) * | 1989-09-08 | 1991-03-15 | Thomson Brandt Armements | SAFETY IGNITER FOR PROPELLER. |
| US6244185B1 (en) * | 2000-02-03 | 2001-06-12 | Po Sing Fireworks Ltd. | Skyrocket |
| US20040068979A1 (en) * | 2002-10-11 | 2004-04-15 | Hy Pat Corporation | Ignition systems for hybrid and solid rocket motors |
Non-Patent Citations (6)
| Title |
|---|
| 复式点火技术研究. 胡大宁，屠小昌.航空兵器，第2004年第3期. 2004 |
| 复式点火技术研究. 胡大宁，屠小昌.航空兵器，第2004年第3期. 2004 * |
| 大长细比小型固体发动机后点火试验研究. 屠小，张春英，万东，张建伟.固体火箭技术，第24卷第1期. 2001 |
| 大长细比小型固体发动机后点火试验研究. 屠小，张春英，万东，张建伟.固体火箭技术，第24卷第1期. 2001 * |
| 药盒式可燃点火器的设计和应用. 屠小昌.推进技术，第18卷第6期. 1991 |
| 药盒式可燃点火器的设计和应用. 屠小昌.推进技术，第18卷第6期. 1991 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1786451A (en) | 2006-06-14 |
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