CN106704037B - A kind of missile propulsive plant band seam allowance locks underseal header structure - Google Patents
A kind of missile propulsive plant band seam allowance locks underseal header structure Download PDFInfo
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- CN106704037B CN106704037B CN201510781530.9A CN201510781530A CN106704037B CN 106704037 B CN106704037 B CN 106704037B CN 201510781530 A CN201510781530 A CN 201510781530A CN 106704037 B CN106704037 B CN 106704037B
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- seam allowance
- locks
- skirt
- hemisphere
- underseal
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Abstract
The invention discloses a kind of missile propulsive plant band seam allowances to lock underseal header structure, and the band seam allowance lock underseal header structure is welded by hemisphere and with seam allowance lock bottom structure skirt by electron beam.When carrying out electron beam welding, with installation protecting tool set-up is not needed between seam allowance lock bottom skirt and hemisphere, it can be 0 on critical gap theory therebetween, the contour structure size totally provided can be made full use of while construction weight increase is less, engine structure is compacter；In the case of front and rear skirt spacing strictly control, charge space can maximize, and increase explosive payload, always rushed to improving engine, it is with obvious effects to improve engine performance；Electron beam weldering protecting tool set-up need not be customized simultaneously, it is cost-effective, technical process is simplified, improves the efficiency and reliability of welding sequence.
Description
Technical field
The present invention relates to solid propellant rocket, a kind of specific missile propulsive plant band seam allowance locks underseal header structure.
Background technology
End socket is one of important component in missile propulsive plant burning chamber shell, and the hemisphere in end enclosure structure bears to promote
The internal pressure that agent burning generates, skirt are used for connection or the connection with other component between bay section, it is more to bear axis pressure, moment of flexure, shearing etc.
Kind load, stressing conditions are more complicated.Therefore it is required that the hemisphere and skirt in end enclosure structure to have higher bonding strength and just
Degree.
Hemisphere and the weldering of skirt generally use electron beam or argon arc welding are welded, and weld seam is the ground easily destroyed
Side, due to end socket stress complexity, so there is higher requirement to weld strength.Electron beam weldering energy is high, and weld width is small, hot shadow
It is small to ring area, welding joint mechanical property is high, and strength of welded joint can be strong with base material etc..Therefore using the envelope of electron beam weldering welding
Header structure strength and stiffness can meet the requirement of the various internal pressures of missile propulsive plant and outer load.
Fig. 1 is conventional engine end enclosure structure schematic diagram, conventional end enclosure structure when carrying out electron beam weldering, need in skirt and
Protecting tool set-up is added between hemisphere, hemisphere is protected not wounded by electron beam.Therefore it is required that between minimum between skirt and hemisphere
Gap is more than 3mm.In the case of the axial dimensions such as front and rear skirt spacing strictly control, the gap between skirt and hemisphere can reduce powder charge
Amount, influences engine and always rushes, and can not meet the overall requirement to engine axial dimension and explosive payload.In addition, protecting tool set-up is
It is formed by multistage copper sheet sectional, in electron beam welds welding process, welding tooling may generate gap due to displacement, in this way
Protecting tool set-up just cannot play protective effect.It can be seen that protecting tool set-up is not very reliable.
Invention content
To solve the above problems, a kind of missile propulsive plant band seam allowance provided by the invention locks underseal header structure, including hemisphere
Body and with seam allowance lock bottom structure skirt.The band seam allowance lock bottom structure skirt has a circular seam allowance lock bottom structure, band in circumferencial direction
Seam allowance lock bottom structure skirt is welded by electron beam with hemisphere and connected, and seam allowance lock bottom structure replaces protecting tool set-up, so as to protect hemisphere
Body is not wounded in electron beam weldering by electron beam, therefore with can be on the critical gap theory between seam allowance lock bottom structure skirt and hemisphere
It is 0.
Further, the band seam allowance lock bottom structure skirt material is 20CrMnTi, and band seam allowance lock bottom structure skirt is along the circumferential direction
There is one section of circular seam allowance lock bottom structure, the seam allowance lock long 2mm in bottom, wall thickness 1.5mm, seam allowance lock bottom internal diameter is Ф 389.2mm, outside
Diameter is Ф 392.2mm.
Further, the hemisphere structural material is 30Cr3SiNiMoVA (Z), is useful for carrying out electricity with skirt on hemisphere
The step of beamlet weldering has the threaded hole of 32 M10 on hemisphere end face, for being connect with tail pipe.
The present invention compared with conventional engine end enclosure structure, advantage and has due to locking underseal header structure using band seam allowance
Beneficial effect is：
1) band seam allowance lock bottom structure skirt and hemisphere axial gap can be theoretically 0 in band seam allowance lock underseal header structure, this
Sample can make full use of overall contour structure size, make engine structure compacter；In the feelings that front and rear skirt spacing strictly controls
Under condition, charge space can maximize, and increase explosive payload, improve engine and always rush；Improve engine performance；
2) protecting tool set-up need not be customized, it is cost-effective；Under the premise of free loading propellant charge constitution form is determined, simplify
Technical process improves efficiency of assembling；
3) band seam allowance lock bottom (head) structural reliability is higher than protecting tool set-up, can ensure that hemisphere is not hit in electron beam weldering
Wound.
Description of the drawings
Technical scheme of the present invention is illustrated below by way of specific embodiment.
Fig. 1 is the schematic diagram of conventional missile engine end enclosure structure；
Fig. 2 is the schematic diagram that the missile propulsive plant that present invention implementation provides locks underseal header structure with seam allowance.
Specific embodiment
Hereinafter, the present invention is further elaborated in conjunction with the accompanying drawings and embodiments.
As shown in Fig. 2, it is schematic diagram of the missile propulsive plant provided by the invention with seam allowance lock bottom rear head structure.Engine
Burning chamber shell rear head employs band seam allowance and locks bottom (head) structure type, including：Later half sphere 1, with after seam allowance lock bottom structure
Skirt 2.The band seam allowance lock underseal header structure is using electron beam weldering connection, to ensure that end enclosure structure has enough strength and stiffness.
Band seam allowance lock bottom structure rear skirt 2 has a circular seam allowance lock bottom, and the seam allowance lock bottom is used to protect hemisphere in electron beam weldering
It is not wounded by electron beam, so as to complete the welding of end socket, to ensure that end socket has enough strength and stiffness.
The later half sphere 1 is processed in the form of solid forging, and later half sphere solid forging is rushed compared to segmentation
Molded, rigidity and intensity higher, craftsmanship is more preferable, and the later half sphere of solid forging is being heat-treated and the deformation in hydraulic test
Smaller.There is the threaded hole of 32 M10 on rear quarter body end face simultaneously, for being connect with tail pipe.
The band seam allowance lock bottom structure rear skirt 2 is there are one circular ring shape seam allowance lock bottom, it can substitute protecting tool set-up, after protection
Hemisphere is not wounded in electron beam weldering, while rear skirt end face has the threaded hole of 8 φ 8.5 and the pin hole of a φ 8 to be used for
It is docked with steering gear flat.
This tyre seam allowance lock bottom structure rear skirt is identical with the external diameter of rear quarter, band seam allowance lock bottom structure rear skirt and later half sphere
It is useful for carrying out the step of electron beam weldering, the straightway that welding is used on step is 5.6mm, and electron beam postwelding weld penetration should
More than or equal to 5.5mm, and seam allowance lock bottom inner surface must not penetrate.There is transition in 2 seam allowance lock bottom root of band seam allowance lock bottom structure rear skirt
Circular arc R 0.3 so that have certain interval therebetween, this gap is conducive to the metallic vapour and impurity generated in the welding process
Gas overflowing avoids generating intensive stomata.
Coordinated according to the mechanical interface totally assigned and size requires, determine the structure size of burning chamber shell Butt Section.
If using conventional missile propulsive plant end enclosure structure as shown in Figure 1, being needed between skirt and hemisphere when carrying out electron beam weldering
Protecting tool set-up is installed, hemisphere to be protected not wounded by electron beam, therefore it requires to have not less than between 3mm between skirt and hemisphere
Gap, to install protecting tool set-up.Overall simultaneously to have strict demand to burning chamber shell axial dimension, general front and rear skirt spacing is solid
Definite value since gap is in the presence of that can cause the axial distance of powder charge section to shorten, reduces explosive payload, reduces engine performance.The present invention
The circular ring shape seam allowance lock bottom structure with seam allowance lock bottom structure rear skirt can serve as protecting tool set-up, because without additionally mounted protection
Tooling can be 0 on the critical gap theory between skirt and hemisphere.If front and rear end socket all can make dress using band seam allowance lock underseal header structure
The axial length increase about 6mm of medicine section increases explosive payload, improves engine performance, simplifies technique, cost-effective, meets overall
Requirement to axial dimension.
By taking diameter 400mm engines as an example, requirement is coordinated according to general machine, housing outer diameter and front and rear connector ruler is determined
It is very little, and in the case where axial dimension strictly controls, rear head employs band seam allowance and locks underseal header structure.Band seam allowance lock bottom structure
Rear skirt material is 20CrMnTi, seam allowance the lock long 2mm in bottom, wall thickness 1.5mm, for later half sphere to be protected not wounded by electron beam.
Later half sphere and outer diameter with seam allowance lock bottom structure rear skirt are 400mm, and the two is for the straightway of electron beam welding
5.6mm, electron beam postwelding weld penetration is more than or equal to 5.5mm, and seam allowance lock bottom inner surface must not penetrate.Later half sphere and band stop
There is the gap of 0.3mm between mouth lock bottom structure rear skirt, this gap is conducive to the metallic vapour generated in the welding process and impurity gas
Body overflows, and avoids generating intensive stomata.
The structure is applied in certain model, and Product Process has been verified with productibility, and passed through stress-should
Body slow test outside change experiment, hydraulic test, explosion bulge test and internal pressure under load combined effect, structure is reliable, meets overall
It is required that.
Claims (5)
1. a kind of missile propulsive plant band seam allowance locks underseal header structure, it is characterised in that：Including band seam allowance lock bottom structure skirt and hemisphere
Body；The band seam allowance lock bottom structure skirt and hemisphere are welded using electron-bombardment welding；Have on the band seam allowance lock bottom structure skirt
Circular seam allowance locks bottom, which can protect hemisphere not wounded during electron-bombardment welding.
2. missile propulsive plant band seam allowance as described in claim 1 locks underseal header structure, it is characterised in that：The band seam allowance locks bottom
Structure skirt material is 20CrMnTi, and seam allowance lock bottom structure is one section of annulus, and seam allowance locks the long 2mm in bottom, wall thickness 1.5mm.
3. missile propulsive plant band seam allowance as claimed in claim 2 locks underseal header structure, it is characterised in that：The band seam allowance locks bottom
There are the threaded hole of 8 φ 8.5 and the pin hole of a φ 8 in structure skirt end face for being docked with other bay sections.
4. missile propulsive plant band seam allowance as described in claim 1 locks underseal header structure, it is characterised in that：The hemisphere of material
For 30Cr3SiNiMoVA (Z), there is the threaded hole of 32 M10 on hemisphere end face, for being connect with tail pipe.
5. missile propulsive plant band seam allowance as described in claim 1 locks underseal header structure, it is characterised in that：The band seam allowance locks bottom
Structure skirt is identical with hemisphere outer diameter, and the boss of welding is useful for seam allowance lock bottom structure skirt and hemisphere, and straightway is
5.6mm, weld penetration >=5.5mm after welding, and seam allowance lock bottom inner surface must not penetrate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510781530.9A CN106704037B (en) | 2015-11-16 | 2015-11-16 | A kind of missile propulsive plant band seam allowance locks underseal header structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510781530.9A CN106704037B (en) | 2015-11-16 | 2015-11-16 | A kind of missile propulsive plant band seam allowance locks underseal header structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106704037A CN106704037A (en) | 2017-05-24 |
| CN106704037B true CN106704037B (en) | 2018-06-26 |
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| Application Number | Title | Priority Date | Filing Date |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201997863U (en) * | 2010-12-09 | 2011-10-05 | 西安优耐特容器制造有限公司 | Welding protection tool of circumferential weld |
| CN103492112A (en) * | 2012-04-16 | 2014-01-01 | 株式会社谷黑组 | Soldering device and method, and manufactured substrate and electronic component |
| CN103506751A (en) * | 2012-06-20 | 2014-01-15 | 上海新力动力设备研究所 | Method for welding vacuum electron beam of stainless steel cylinder body |
| CN104696104A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Connection structure of blocking ring of solid rocket engine |
| CN104696106A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Connection structure of opening clamping key of solid rocket engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050074215A1 (en) * | 2003-08-01 | 2005-04-07 | United States Of America As Represented By The Secretary Of The Navy | Fabrication of high air fraction photonic band gap fibers |
-
2015
- 2015-11-16 CN CN201510781530.9A patent/CN106704037B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201997863U (en) * | 2010-12-09 | 2011-10-05 | 西安优耐特容器制造有限公司 | Welding protection tool of circumferential weld |
| CN103492112A (en) * | 2012-04-16 | 2014-01-01 | 株式会社谷黑组 | Soldering device and method, and manufactured substrate and electronic component |
| CN103506751A (en) * | 2012-06-20 | 2014-01-15 | 上海新力动力设备研究所 | Method for welding vacuum electron beam of stainless steel cylinder body |
| CN104696104A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Connection structure of blocking ring of solid rocket engine |
| CN104696106A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Connection structure of opening clamping key of solid rocket engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106704037A (en) | 2017-05-24 |
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