CN104712458B - The solid propellant engine of energy afterbody igniting - Google Patents
The solid propellant engine of energy afterbody igniting Download PDFInfo
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- CN104712458B CN104712458B CN201310682188.8A CN201310682188A CN104712458B CN 104712458 B CN104712458 B CN 104712458B CN 201310682188 A CN201310682188 A CN 201310682188A CN 104712458 B CN104712458 B CN 104712458B
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Abstract
The present invention relates to the solid propellant engine of a kind of energy afterbody igniting, it includes combustor, nozzle component and solid fuel, and nozzle component is arranged on the tail end of combustor, and solid fuel is arranged in combustor；Described solid propellant engine also includes igniting box, igniter and firing lock thereof, and igniting box is arranged on the solid fuel front end in combustor, and igniter is arranged on the tail end of nozzle component；Described solid fuel is cylinder, leaves gap between its lateral wall and combustor medial wall, the central canal of the nozzle combustion room end alignment solid fuel cylinder of described nozzle component.The present invention can realize machinery percussion, and afterbody is lighted a fire, and can the solid fuel of first incendiary rocket head, rocket engine stable work in work.
Description
Technical field
The present invention relates to solid propellant engine.
Background technology
Existing solid propellant engine all adopts head sparking mode, this sparking mode can the solid fuel of first incendiary rocket head, igniting and burning are easier to, rocket engine stable work in work, and current head sparking mode generally adopts electric shock to send out.In some cases, product structure feature requires to adopt mechanical system percussion rocket, and makes rocket motion direction contrary with the mechanical force direction of startup, only takes afterbody sparking mode for this.And afterbody igniting can only the solid fuel of first incendiary rocket afterbody, igniting and ratio of combustion are relatively difficult to, cause rocket engine service behaviour unstable, particularly with the solid propellant rocket bigger equipped with low burning rate propellant and loading density, be less susceptible to igniting at low temperatures.
Summary of the invention
The technical problem to be solved is: propose a kind of can the solid propellant engine of afterbody igniting, it can realize machinery percussion, and afterbody is lighted a fire, and can the solid fuel of first incendiary rocket head, rocket engine stable work in work.
The present invention solves that the adopted solution of problem set forth above is:
The solid propellant engine of energy afterbody igniting, it includes combustor, nozzle component and solid fuel, and nozzle component is arranged on the tail end of combustor, and solid fuel is arranged in combustor；Described solid propellant engine also includes igniting box, igniter and firing lock thereof, and igniting box is arranged on the solid fuel front end in combustor, and igniter is arranged on the tail end of nozzle component；
Described solid fuel is cylinder, leaves gap between its lateral wall and combustor medial wall, the central canal of the nozzle combustion room end alignment solid fuel cylinder of described nozzle component.
In such scheme, described igniting box is box body, is provided with ignition charge in box body, and the box body by solid fuel side has hole.
In such scheme, described igniting box is provided with bearing by the box body of solid fuel side.
In such scheme, between described chamber front end and igniting box, it is provided with cushion pad.
In such scheme, described igniter includes nozzle, ignition charge, the fire in a stove before fuel is added, and the ignition charge in igniter is arranged between the fire in a stove before fuel is added and nozzle, and nozzle is arranged in the jet pipe of nozzle component, and nozzle points to igniting box.
In such scheme, described solid fuel lateral wall is provided with bar shaped boss, and bar shaped boss is parallel with the axis of cylinder.
The present invention arranges igniter at rocket afterbody, one igniting box is set in rocket nose section combustor, during percussion, the high-temperature fuel gas that igniter produces is when nozzle arrives igniting box by the central canal of solid fuel cylinder, ignition charge in igniting box is ignited, producing high-temperature fuel gas will make ballistite start burning from head, make the central canal of high pressure-temperature combustion gas that solid fuel the generates gap between solid fuel lateral wall and combustor medial wall and solid fuel cylinder, spraying from rocket tube assembly, when producing thrust, rocket travels forward.High pressure-temperature combustion gas is at the central canal in the gap between solid fuel lateral wall and combustor medial wall and solid fuel cylinder, can heat and light the solid fuel of surrounding, solve the problem that rocket motor drive end unit low-temperature ignition is difficult so that rocket engine stable work in work.
Compared with prior art, present configuration is simple, and it is convenient to implement, and wide adaptability, cost is low.
Accompanying drawing explanation
Fig. 1 is embodiment of the present invention structural representation.
Fig. 2 is solid-fuelled partial sectional view.
Fig. 3 is solid-fuelled cross-sectional view.
Fig. 4 is the structural representation of igniter.
Fig. 5 is the structural representation of igniting box.
In figure: 1 cushion pad；2 igniting boxes；3 solid fuels；4 combustor；5 nozzle components；6 igniters；7 firing locks；8 bar shaped boss；9 central canals；10 fires in a stove before fuel is added；11 bearings；12 holes；13 ignition charges；14 nozzles.
Detailed description of the invention
The solid propellant engine embodiment of energy afterbody of the present invention igniting as shown in Figure 1, it includes combustor 4, nozzle component 5 and solid fuel 3, and nozzle component 5 is arranged on the tail end of combustor 4, and solid fuel 3 is arranged in combustor 4；It is characterized in that: described solid propellant engine also includes igniting box 2, igniter 6 and firing lock 7 thereof, igniting box 2 is arranged on the solid fuel front end in combustor, and igniter 6 is arranged on the tail end of nozzle component 5.Cushion pad 1 it is provided with, the change that the length to compensate solid fuel 3 produces because of temperature between described chamber front end and igniting box.
The present invention is by being arranged on the igniter 6 of rocket afterbody and being arranged on the two-stage ignition mode that the igniting box of rocket nose section forms.Its firing lock 7 adopts mechanical system firing lock, and rocket motion direction is contrary with the mechanical force direction of startup.
Described solid fuel 3 is cylinder, leaving gap between its lateral wall and combustor 4 medial wall, as shown in Figure 2,3, described solid fuel 3 lateral wall is provided with bar shaped boss 8, bar shaped boss 8 is parallel with the axis of cylinder so that produce gap between lateral wall and combustor 4 medial wall.The central canal 9 of the nozzle combustion room end alignment solid fuel cylinder of described nozzle component 5.
As shown in Figure 5, described igniting box 2 is box body, is provided with ignition charge 13, the box body by solid fuel side has hole 12 in box body, the high-temperature fuel gas that igniter produces arrives igniting box through nozzle 14 by the central canal of solid fuel cylinder, enters firing point gunpowder in igniting box by hole 12.
Described igniting box 2 is provided with bearing 11 by the box body of solid fuel side, is used for being supported between solid fuel and igniting box 2, forms gap, passes through for high-temperature fuel gas.
As shown in Figure 4, described igniter 6 includes nozzle 14, ignition charge 13, the fire in a stove before fuel is added 10, and the ignition charge 13 in igniter is arranged between the fire in a stove before fuel is added 10 and nozzle 14, and nozzle 14 is arranged in the jet pipe of nozzle component 5, and nozzle 14 points to igniting box.When starting mechanical type firing lock, striker will fire the fire in a stove before fuel is added, and the flame that the fire in a stove before fuel is added produces, by point of ignition gunpowder, then produces a large amount of high-temperature fuel gas, sprays through nozzle 14.
Claims (6)
1. the solid propellant engine of energy afterbody igniting, it includes combustor (4), nozzle component (5) and solid fuel (3), nozzle component (5) is arranged on the tail end of combustor (4), and solid fuel (3) is arranged in combustor (4)；It is characterized in that: described solid propellant engine also includes the firing lock (7) of igniting box (2), igniter (6) and igniter, igniting box (2) is arranged on the solid fuel front end in combustor, and igniter (6) is arranged on the tail end of nozzle component (5)；
Described solid fuel (3) is cylinder, leaving gap between its lateral wall and combustor (4) medial wall, the jet pipe of described nozzle component (5) is directed at the central canal (9) of solid fuel cylinder near one end of combustor.
2. solid propellant engine as claimed in claim 1, it is characterised in that: described igniting box (2) is box body, is provided with ignition charge (13) in box body, and the box body by solid fuel side has hole (12).
3. solid propellant engine as claimed in claim 2, it is characterised in that: described igniting box (2) is provided with bearing (11) by the box body of solid fuel side.
4. solid propellant engine as claimed in claim 1, it is characterised in that: it is provided with cushion pad (1) between described chamber front end and igniting box.
5. solid propellant engine as claimed in claim 1, it is characterized in that: described igniter (6) includes nozzle (14), ignition charge (13), the fire in a stove before fuel is added (10), ignition charge (13) in igniter is arranged between the fire in a stove before fuel is added (10) and nozzle (14), nozzle (14) is arranged in the jet pipe of nozzle component (5), and nozzle (14) points to igniting box.
6. solid propellant engine as claimed in claim 1, it is characterised in that: described solid fuel (3) lateral wall is provided with bar shaped boss (8), and bar shaped boss (8) is parallel with the axis of cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310682188.8A CN104712458B (en) | 2013-12-13 | 2013-12-13 | The solid propellant engine of energy afterbody igniting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310682188.8A CN104712458B (en) | 2013-12-13 | 2013-12-13 | The solid propellant engine of energy afterbody igniting |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104712458A CN104712458A (en) | 2015-06-17 |
| CN104712458B true CN104712458B (en) | 2016-07-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310682188.8A Active CN104712458B (en) | 2013-12-13 | 2013-12-13 | The solid propellant engine of energy afterbody igniting |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108060990A (en) * | 2016-11-07 | 2018-05-22 | 贾海亮 | A kind of series connection unit solid engines |
| CN107269424B (en) * | 2017-07-25 | 2023-04-18 | 南京理工大学 | Secondary ignition structure of solid rocket engine |
| CN107939549B (en) * | 2017-11-08 | 2019-10-15 | 航宇救生装备有限公司 | A kind of miniature multistage pulses thrust solid propellant rocket |
| CN111707150A (en) * | 2020-05-13 | 2020-09-25 | 陕西中天火箭技术股份有限公司 | Accurate rocket two-stage electronic time delay ignition device |
| CN113494386B (en) * | 2021-07-26 | 2022-11-11 | 江西新明机械有限公司 | Miniaturized multifunctional rocket engine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA1217944A (en) * | 1983-03-16 | 1987-02-17 | Christian J.L. Carrier | Integrated weatherseal/igniter for solid rocket motor |
| FR2594891B1 (en) * | 1986-02-21 | 1989-10-13 | Poudres & Explosifs Ste Nale | IGNITER FIXABLE IN THE NOZZLE OF A PROPELLER |
| DE3637967A1 (en) * | 1986-11-07 | 1988-05-19 | Huels Troisdorf | Multi-chamber rocket motor |
| CN102168631B (en) * | 2011-04-14 | 2013-07-24 | 北京航空航天大学 | Aluminum film baffle device and pulse solid engine applying same |
| CN203769964U (en) * | 2013-12-13 | 2014-08-13 | 航宇救生装备有限公司 | Solid-propellant rocket engine allowing tail portion ignition |
-
2013
- 2013-12-13 CN CN201310682188.8A patent/CN104712458B/en active Active
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| CN104712458A (en) | 2015-06-17 |
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