CN107201970B - The fixation and sealing structure of solid propellant rocket firing tip - Google Patents
The fixation and sealing structure of solid propellant rocket firing tip Download PDFInfo
- Publication number
- CN107201970B CN107201970B CN201710651581.9A CN201710651581A CN107201970B CN 107201970 B CN107201970 B CN 107201970B CN 201710651581 A CN201710651581 A CN 201710651581A CN 107201970 B CN107201970 B CN 107201970B
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- China
- Prior art keywords
- igniter head
- fixation
- plug
- motor body
- sealing
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Classifications
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- 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
-
- 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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention discloses the fixations and sealing structure of a kind of solid propellant rocket firing tip, it further include sealing film, plug and fixing belt including motor body, the jet pipe being fixed in motor body end, the solid fuel column being arranged in engine shell body and igniter head conducting wire being arranged in solid fuel column.The present invention is sealed the firing tip of solid propellant rocket by sealing film, plug etc., moisture, sundries, insect etc. can be prevented to enter damage fuel column, igniter head etc. in engine, sealing effect is good.And by the fixed plug of fixing belt and igniter head conducting wire, the fixation of igniter head can be made more reliable, being avoided that igniter head loosens influences engine ignition performance.And solid propellant rocket firing tip of the present invention fixation and sealing structure also have structure simple, the low advantage of production cost.
Description
Technical field
The present invention relates to a kind of middle-size and small-size rocket engine, in particular to a kind of igniter head of middle-size and small-size rocket engine
The sealing structure of fixed structure and spout portion.
Background technique
Solid propellant rocket (Solid propellant rocket engine) is the rocket hair to use solid fuel
Motivation, also known as solid engine.Solid propellant burns in a combustion chamber after lighting, and chemical energy is converted into heat
Can, produce the combustion product of high temperature and pressure.Combustion product flows through jet pipe, and expansion accelerates wherein, and thermal energy is kinetic energy, with height
Speed is discharged from jet pipe and generates thrust.
In the prior art, it is embedded with the middle-size and small-size solid propellant rocket of igniter head, igniter head is usually not arranged solid
Structure is determined, so that igniter head is easy loose or dislocation, and then will affect engine ignition success rate in storage and transport process.
In addition, also there is the not pre-buried igniter head of middle-size and small-size solid propellant rocket in the prior art, but igniter head is inserted into before use,
Igniter head is inserted into before use has that cumbersome, time-consuming, risk is big, and not pre-buried igniter head increase it is miscellaneous
Object, toy etc. enter in-engine possibility, and the reliability of solid propellant rocket and safety are lower.
And existing middle-size and small-size solid propellant rocket, especially its firing tip of small-scale solid rocket motor do not have usually
There is setting sealing structure, so that moisture, sundries, insect etc. easily enter in powder column, powder column is caused to fail.
Summary of the invention
In view of this, the object of the present invention is to provide the fixation and sealing structure of a kind of solid propellant rocket firing tip,
With solve powder column igniter head loose or dislocation of existing middle-size and small-size solid propellant rocket influence ignition performance and moisture, sundries,
The technical issues of insect etc. easily enters in powder column, powder column is caused to fail.
The fixation and sealing structure of solid propellant rocket firing tip of the present invention, including motor body, be fixed on and start
Jet pipe, the solid fuel column being arranged in engine shell body in machine shell end and the point being arranged in solid fuel column
Duration and degree of heating conducting wire, it is characterised in that:
It further include the plug being fixed on igniter head conducting wire, the plug is made of front cone section and rear conical section, described
Some or all of front cone section is located in the diffuser of jet pipe, and the end of the rear conical section is located at outside the diffuser of jet pipe；
It further include sealing film, the conical inner ring seal that the sealing film is bonded by the front cone section outer surface with plug
Portion, the end measure sealing cooperated with jet pipe end face and motor body end face and the external cylindrical surface with motor body end
The outer ring seal portion of sealed connection forms；Igniter head conducting wire passes through the conical inner ring seal portion of sealing film；
Further include both ends be fixed on the external cylindrical surface of motor body end, middle part fixing sleeve consolidating on igniter head conducting wire
Determine band, the rear conical section top of the plug is on the fixing belt.
Further, the outer ring seal portion of the sealing film is bonded in the external cylindrical surface of motor body end by double-sided adhesive
On.
Further, the both ends of the fixing belt are fixed on the end external cylindrical surface of motor body by adhesive tape.
Beneficial effects of the present invention:
The fixation and sealing structure of solid propellant rocket firing tip of the present invention start solid-rocket by sealing film
The firing tip of machine is sealed, and auxiliary section of the moisture between jet pipe and shell, jet pipe inner hole can be prevented slowly to be immersed in and start
Damage fuel column, igniter head etc. in machine, while can also prevent sundries, insect etc. from entering from jet pipe inner hole and damage fuel in engine
Column, igniter head etc., while the barrier effect of plug is added, it can further enhance and sundries, insect etc. is prevented to enter engine, sealing
Effect is good.And by the conducting wire of fixing belt fixed plug and igniter head, the fixation of igniter head can be made more reliable, be avoided that igniter head
Loosening influences engine ignition performance.And solid propellant rocket firing tip of the present invention fixation and sealing structure also there is knot
Structure is simple, the low advantage of production cost.
Detailed description of the invention
Fig. 1 is the fixation of solid propellant rocket firing tip of the present invention and the structural schematic diagram of sealing structure；
Fig. 2 is the structural schematic diagram for sealing film；
Fig. 3 is the enlarged structure schematic diagram in the portion P in Fig. 1.
Specific embodiment
The invention will be further described with reference to the accompanying drawings and examples.
As shown, the fixation and sealing structure of the present embodiment solid propellant rocket firing tip, including motor body
1, the jet pipe 2 that is fixed in motor body end, the solid fuel column 3 being arranged in engine shell body and setting are solid
Igniter head conducting wire 4 in fluid fuel column；
It further include the plug 7 being fixed on igniter head conducting wire, the plug is made of front cone section and rear conical section, described
The part of front cone section is located in the diffuser of jet pipe, certainly can also be the jet pipe that is entirely located in of plug in different embodiments
In diffuser；The end of conical section is located at outside the diffuser of jet pipe after described；
It further include sealing film 5, the conical inner ring seal that the sealing film is bonded by the front cone section outer surface with plug
Portion 51, the end measure sealing 52 cooperated with jet pipe end face and motor body end face and the outer circle with motor body end
The outer ring seal portion 53 that cylinder is tightly connected forms；Igniter head conducting wire passes through the conical inner ring seal portion of sealing film；
Further include both ends be fixed on the external cylindrical surface of motor body end, middle part fixing sleeve consolidating on igniter head conducting wire
Determine band 8, the rear conical section top of the plug is on the fixing belt.
The fixation of the present embodiment solid propellant rocket firing tip and the assembling process of sealing structure are as follows: first fix plug
On igniter head conducting wire, igniter head conducting wire is then passed through into sealing film and makes to seal Membrane cover in the front cone section of plug, then
Sealing film by plug and thereon is put into the diffuser of jet pipe, is started followed by the edge fold for sealing film to be adhesively fixed on
On the end external cylindrical surface of casing body, followed by fixing belt is fixed on igniter head conducting wire and makes to be pressed in the middle part of fixing belt
In the rear conical section of plug, finally the both ends of fixing belt are adhesively fixed on the end external cylindrical surface of motor body.
The fixation and sealing structure of the present embodiment solid propellant rocket firing tip, assembling is simple and convenient, and production cost is low.
It is sealed the firing tip of solid propellant rocket by sealing film, can prevent cooperation of the moisture between jet pipe and shell
Portion, jet pipe inner hole are slowly immersed in damage fuel column, igniter head etc. in engine, while also sundries, insect etc. can be prevented from spray
Pipe orifice enters damage fuel column, igniter head etc. in engine, while adding the barrier effect of plug, can further enhance prevention
Sundries, insect etc. enter engine, and sealing effect is good.And by the fixed plug of fixing belt, the fixation of igniter head can be made more reliable,
Being avoided that igniter head loosens influences engine ignition performance.
In the present embodiment, the joint portion in the conical inner ring seal portion of igniter head conducting wire and sealing film passes through bonding agent
6 adhering and sealings further improve the sealing reliability of firing tip.
In the present embodiment, the outer ring seal portion of the sealing film is bonded in the outer of motor body end by double-sided adhesive 9
On cylindrical surface, the fixation for sealing film is simple and convenient.
In the present embodiment, in the present embodiment, fixing belt 8 is adhesive tape, and fixing belt middle part is fixedly connected with igniter head conducting wire
It is simple and convenient, while the both ends of fixing belt 8 are fixed on the end external cylindrical surface of motor body by adhesive tape 10, fixing belt 8
End fixation it is also simple and convenient.
It is additionally provided with a circle in the present embodiment, on motor body and is bonded in the edge in outer ring seal portion 53, double-sided adhesive 9
The sealant 11 of the edge of edge, the end of fixing belt 8 and adhesive tape 10 can also improve outer while improving sealing performance
The fixation reliability of ring sealing 53, double-sided adhesive 9, fixing belt 8 and adhesive tape 10 avoids edge from falling off problem.
Finally, it is stated that the above examples are only used to illustrate the technical scheme of the present invention and are not limiting, although referring to compared with
Good embodiment describes the invention in detail, those skilled in the art should understand that, it can be to skill of the invention
Art scheme is modified or replaced equivalently, and without departing from the objective and range of technical solution of the present invention, should all be covered at this
In the scope of the claims of invention.
Claims (3)
1. a kind of fixation and sealing structure of solid propellant rocket firing tip, including motor body, it is fixed on engine shell
Jet pipe, the solid fuel column being arranged in engine shell body in body end portion and the igniter head being arranged in solid fuel column
Conducting wire, it is characterised in that:
It further include the plug being fixed on igniter head conducting wire, the plug is made of front cone section and rear conical section, round before described
It bores some or all of section to be located in the diffuser of jet pipe, the end of the rear conical section is located at outside the diffuser of jet pipe；
Further include sealing film, it is described sealing film be bonded by the front cone section outer surface with plug conical inner ring seal portion, and
The end measure sealing and seal company with the external cylindrical surface of motor body end that jet pipe end face and motor body end face cooperate
The outer ring seal portion composition connect；Igniter head conducting wire pass through sealing film conical inner ring seal, and igniter head conducting wire with it is close
The joint portion in the conical inner ring seal portion of sealer passes through bonding agent adhering and sealing；
Further include both ends be fixed on the external cylindrical surface of motor body end, fixation of the middle part fixing sleeve on igniter head conducting wire
Band, the rear conical section top of the plug is on the fixing belt.
2. the fixation and sealing structure of solid propellant rocket firing tip according to claim 1, it is characterised in that: described
The outer ring seal portion of sealing film is bonded on the external cylindrical surface of motor body end by double-sided adhesive.
3. the fixation and sealing structure of solid propellant rocket firing tip according to claim 1, it is characterised in that: described
The both ends of fixing belt are fixed on the end external cylindrical surface of motor body by adhesive tape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710651581.9A CN107201970B (en) | 2017-08-02 | 2017-08-02 | The fixation and sealing structure of solid propellant rocket firing tip |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710651581.9A CN107201970B (en) | 2017-08-02 | 2017-08-02 | The fixation and sealing structure of solid propellant rocket firing tip |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107201970A CN107201970A (en) | 2017-09-26 |
| CN107201970B true CN107201970B (en) | 2019-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710651581.9A Active CN107201970B (en) | 2017-08-02 | 2017-08-02 | The fixation and sealing structure of solid propellant rocket firing tip |
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| Country | Link |
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| CN (1) | CN107201970B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108306246B (en) * | 2018-03-28 | 2020-12-11 | 科耐特输变电科技股份有限公司 | Novel cable joint protection box |
| CN110985240A (en) * | 2019-11-25 | 2020-04-10 | 上海新力动力设备研究所 | Ignition device suitable for end fuel column and assembling method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3010020A1 (en) * | 1980-03-15 | 1981-10-01 | Heinz Till | Cover for rocket engine test bed - has membrane supported on wire mesh for quick release of pressure after ignition under vacuum |
| JPH09178398A (en) * | 1995-12-28 | 1997-07-11 | Tech Res & Dev Inst Of Japan Def Agency | Detonating fuse type crusher |
| CN2258282Y (en) * | 1996-05-07 | 1997-07-23 | 南京理工大学 | Geologic structure detecting rocket |
| CN2646402Y (en) * | 2003-05-26 | 2004-10-06 | 黄振芬 | Highly overloaded solid-propellant rocket engine for shells |
| CN102168631A (en) * | 2011-04-14 | 2011-08-31 | 北京航空航天大学 | Aluminum film baffle device and pulse solid engine applying same |
-
2017
- 2017-08-02 CN CN201710651581.9A patent/CN107201970B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3010020A1 (en) * | 1980-03-15 | 1981-10-01 | Heinz Till | Cover for rocket engine test bed - has membrane supported on wire mesh for quick release of pressure after ignition under vacuum |
| JPH09178398A (en) * | 1995-12-28 | 1997-07-11 | Tech Res & Dev Inst Of Japan Def Agency | Detonating fuse type crusher |
| CN2258282Y (en) * | 1996-05-07 | 1997-07-23 | 南京理工大学 | Geologic structure detecting rocket |
| CN2646402Y (en) * | 2003-05-26 | 2004-10-06 | 黄振芬 | Highly overloaded solid-propellant rocket engine for shells |
| CN102168631A (en) * | 2011-04-14 | 2011-08-31 | 北京航空航天大学 | Aluminum film baffle device and pulse solid engine applying same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107201970A (en) | 2017-09-26 |
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Address after: Jiulongpo Culture Village 401331 Chongqing City No. 7 unit 2 4-4 Applicant after: Cao Yuan Address before: 401331 Career Academy, Chongqing, Shapingba District University City East Road 76 Chongqing Electronic Engineering, Career Academy (Cao Yuan) Applicant before: Cao Yuan |
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