CN103644047B - A kind of ignition initiation devices of solid propellant rocket - Google Patents
A kind of ignition initiation devices of solid propellant rocket Download PDFInfo
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- CN103644047B CN103644047B CN201310586552.0A CN201310586552A CN103644047B CN 103644047 B CN103644047 B CN 103644047B CN 201310586552 A CN201310586552 A CN 201310586552A CN 103644047 B CN103644047 B CN 103644047B
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- annular igniter
- cushion pad
- solid propellant
- initiation devices
- powder charge
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Abstract
The present invention relates to a kind of ignition initiation devices of solid propellant rocket, belong to Solid Rocket Motor Technology field.The present invention is mated with the spacing of powder charge by the selection of cushion pad that arranges in annular igniter and thickness matching, cushion pad end face, reduce the distortion of annular igniter housing under electric initiator impacts, effectively avoid this process mid-point firearm shell construction on the impact of powder charge Grain structure.Meanwhile, annular igniter housing can also be made to keep complete in the course of the work, ensure the service behaviour of annular igniter.
Description
Technical field
The present invention relates to Solid Rocket Motor Technology field, be specifically related to a kind of ignition initiation devices of solid propellant rocket.
Background technique
Solid propellant rocket is the power plant that weaponry is widely applied, and mounting point is flexible, physical dimension can be widely applied thereon with the annular igniter of installation position structure adaptability change.
For in the annular igniter working procedure of the ignition initiation devices of guarantee solid propellant rocket, its structure does not impact powder charge Grain structure, most annular igniter adopts plastic medicine box.But because the structural strength of plastic medicine box is low, when annular igniter radius is larger, the impact of electric initiator work is easy to destroy medicine box, is unfavorable for the propagation of electric initiator flame in igniter inside, the service behaviour of Influential cases firearm, makes the ignition trigger increased periods of motor.Mini-test proves, at electric initiator corresponding position, under electric initiator gets angry percussion, medicine box distortion is comparatively serious, there is the possibility impacted corresponding position powder charge Grain structure.
Summary of the invention
(1) technical problem that will solve
The technical problem to be solved in the present invention is: how to reduce the ignition initiation devices of solid propellant rocket in ignition trigger process, the impact of its inner annular igniter case on powder charge Grain structure under electric initiator impacts.
(2) technological scheme
In order to solve the problems of the technologies described above, the invention provides a kind of ignition initiation devices of solid propellant rocket, described ignition initiation devices comprises annular igniter, cushion pad, and powder charge powder column, described powder charge powder column is positioned at the side of described annular igniter, and be spaced a distance between described powder charge powder column and annular igniter, described cushion pad is two pieces, be installed on the side near described powder charge powder column in described annular igniter, and lay respectively at the two ends (corresponding electric initiator mounting point) of same diameter in described annular igniter, distance D between the end face of described cushion pad and described powder charge powder column is 5mm ~ 8mm, the thickness H of described cushion pad is 15mm ~ 20mm, the material of described cushion pad is RPUF.
Preferably, described cushion pad is installed in described annular igniter in the mode of pasting.
Preferably, between described powder charge powder column and annular igniter, the distance at interval is greater than 20mm.
Preferably, the housing of described annular igniter adopts aluminum material to make.
Preferably, the ignition initiation devices of described solid propellant rocket also comprises the electric initiator of the opposite side being positioned at described annular igniter.
(3) beneficial effect
The present invention is mated with the spacing of powder charge by the selection of cushion pad that arranges in annular igniter and thickness matching, cushion pad end face, reduce the distortion of annular igniter housing under electric initiator impacts, effectively avoid this process mid-point firearm shell construction on the impact of powder charge Grain structure.Meanwhile, annular igniter housing can also be made to keep complete in the course of the work, ensure the operating time of annular igniter.
Accompanying drawing explanation
Fig. 1 be in device of the present invention annular igniter and on the structural representation of cushion pad;
Fig. 2 is apparatus structure schematic diagram of the present invention, and wherein the structure of annular igniter and cushion pad is the A-A direction view of Fig. 1.
Wherein, annular igniter-1; Cushion pad-2; Powder charge powder column-3.
Embodiment
For making object of the present invention, content and advantage clearly, below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.
As shown in Figure 2, embodiments provide a kind of ignition initiation devices of solid propellant rocket, described ignition initiation devices comprises annular igniter 1, cushion pad 2, and powder charge powder column 3, described powder charge powder column 3 is positioned at the side of described annular igniter 1, and be spaced a distance between described powder charge powder column 3 and annular igniter 1, described cushion pad 2 is two pieces, be installed on the side near described powder charge powder column 3 in described annular igniter 1, and lay respectively at the two ends (corresponding electric initiator mounting point) of same diameter in described annular igniter 1, distance D between the end face of described cushion pad 2 and described powder charge powder column 3 is 5mm ~ 8mm, the thickness H of described cushion pad 2 is 15mm ~ 20mm, the material of described cushion pad 2 is RPUF.
In the present embodiment, described cushion pad 2 is installed in described annular igniter 1 in the mode of pasting.
In the present embodiment, between described powder charge powder column 3 and annular igniter 1, the distance at interval is greater than 20mm.
In the present embodiment, the housing of described annular igniter 1 adopts aluminum material to make.
In the present embodiment, the ignition initiation devices of described solid propellant rocket also comprises the electric initiator (not shown) of the opposite side being positioned at described annular igniter.
In the ignition trigger process of the ignition initiation devices of solid propellant rocket, the electric initiator combustion gas (be called for short and get angry) generated fast of detonating can cause certain impact force to the housing of annular igniter, and in this process, owing to being provided with above-mentioned special cushion pad in the present invention, because the selection of this cushion pad and thickness matching, cushion pad end face mate with the spacing of powder charge, the distortion of annular igniter housing under electric initiator gets angry impact can be reduced, effectively avoid this process mid-point firearm shell construction on the impact of powder charge Grain structure.Meanwhile, annular igniter shell construction can also be made to keep complete in the course of the work, be beneficial to the propagation of electric initiator flame in annular igniter inside, ensure the service behaviour of annular igniter.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and distortion, these improve and distortion also should be considered as protection scope of the present invention.
Claims (5)
1. the ignition initiation devices of a solid propellant rocket, it is characterized in that, described ignition initiation devices comprises annular igniter (1), cushion pad (2) and powder charge powder column (3), described powder charge powder column (3) is positioned at the side of described annular igniter (1), and be spaced a distance between described powder charge powder column (3) and annular igniter (1), described cushion pad (2) is two pieces, be installed on the upper side near described powder charge powder column (3) of described annular igniter (1), and lay respectively at the two ends of the upper same diameter of described annular igniter (1), distance D between the end face of described cushion pad (2) and described powder charge powder column (3) is 5mm ~ 8mm, the thickness H of described cushion pad (2) is 15mm ~ 20mm, the material of described cushion pad (2) is RPUF.
2. the ignition initiation devices of solid propellant rocket as claimed in claim 1, it is characterized in that, described cushion pad (2) is installed in described annular igniter (1) in the mode of pasting.
3. the ignition initiation devices of solid propellant rocket as claimed in claim 1, it is characterized in that, between described powder charge powder column (3) and annular igniter (1), the distance at interval is greater than 20mm.
4. the ignition initiation devices of solid propellant rocket as claimed in claim 1, is characterized in that, the housing of described annular igniter (1) adopts aluminum material to make.
5. the ignition initiation devices of the solid propellant rocket according to any one of Claims 1 to 4, is characterized in that, the ignition initiation devices of described solid propellant rocket also comprises the electric initiator of the opposite side being positioned at described annular igniter (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310586552.0A CN103644047B (en) | 2013-11-21 | 2013-11-21 | A kind of ignition initiation devices of solid propellant rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310586552.0A CN103644047B (en) | 2013-11-21 | 2013-11-21 | A kind of ignition initiation devices of solid propellant rocket |
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| Publication Number | Publication Date |
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| CN103644047A CN103644047A (en) | 2014-03-19 |
| CN103644047B true CN103644047B (en) | 2015-09-23 |
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| CN201310586552.0A Active CN103644047B (en) | 2013-11-21 | 2013-11-21 | A kind of ignition initiation devices of solid propellant rocket |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104806381B (en) * | 2015-04-03 | 2017-01-04 | 北京航空航天大学 | Solid-liquid rocket lighter and head outlet method thereof |
| CN105003357B (en) * | 2015-07-17 | 2017-02-01 | 南京理工大学 | Pasty propellant fuel gas generator ignition device based on solid rocket engine |
| CN109357256B (en) * | 2018-10-31 | 2019-10-18 | 北京动力机械研究所 | A kind of igniter for ram rocket type heater |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4503773A (en) * | 1982-12-27 | 1985-03-12 | Thiokol Corporation | Aft end igniter for full, head-end web solid propellant rocket motors |
| US4539910A (en) * | 1983-09-19 | 1985-09-10 | Morton Thiokol, Inc. | Igniter pellet cup |
| CN101545416A (en) * | 2008-03-24 | 2009-09-30 | 沈阳理工大学 | Solid rocket engine |
| CN102650245A (en) * | 2011-02-24 | 2012-08-29 | 西北工业大学 | Miniature solid rocket engine |
| CN102996284A (en) * | 2012-11-27 | 2013-03-27 | 北京航空航天大学 | Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide |
-
2013
- 2013-11-21 CN CN201310586552.0A patent/CN103644047B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4503773A (en) * | 1982-12-27 | 1985-03-12 | Thiokol Corporation | Aft end igniter for full, head-end web solid propellant rocket motors |
| US4539910A (en) * | 1983-09-19 | 1985-09-10 | Morton Thiokol, Inc. | Igniter pellet cup |
| CN101545416A (en) * | 2008-03-24 | 2009-09-30 | 沈阳理工大学 | Solid rocket engine |
| CN102650245A (en) * | 2011-02-24 | 2012-08-29 | 西北工业大学 | Miniature solid rocket engine |
| CN102996284A (en) * | 2012-11-27 | 2013-03-27 | 北京航空航天大学 | Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide |
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| CN103644047A (en) | 2014-03-19 |
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