CN104329186A - Assembling method for secondary combustion chamber of solid stamping engine - Google Patents
Assembling method for secondary combustion chamber of solid stamping engine Download PDFInfo
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- CN104329186A CN104329186A CN201410481939.4A CN201410481939A CN104329186A CN 104329186 A CN104329186 A CN 104329186A CN 201410481939 A CN201410481939 A CN 201410481939A CN 104329186 A CN104329186 A CN 104329186A
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- afterburning chamber
- chamber housing
- insulation layer
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Abstract
The invention discloses an assembling method for a secondary combustion chamber of a solid stamping engine. The assembling method comprises the following steps: (1) ensuring the uniformity of the pore diameter of a secondary combustion chamber shell and rounding; (2) turning a nonmetallic part; (3) ensuring the back end airtightness of a spray pipe assembly and the secondary combustion chamber; (4) assembling and bonding the secondary combustion chamber shell and the nonmetallic part together. Through rounding of the pore diameter of the secondary combustion chamber shell and control on an assembling gap between the secondary combustion chamber shell and a nonmetallic layer, the assembling design requirement is ensured, the operating practicability is enhanced, the assembling quality of the secondary combustion chamber is enhanced, and the assembling efficiency is increased.
Description
Technical field
The present invention relates to afterburning chamber for solid rocket ramjet, specifically refer to a kind of assembly method of solid rocket ramjet afterburning chamber.
Background technique
In solid rocket ramjet field, thrust is the power resources of missile flight, and solid fuel burning produces jet flow and promotes missile flight by afterburning chamber generation thrust.The mechanism of afterburning chamber mainly comprises: afterburning chamber housing, nozzle assembly, front end heat insulation layer, rear end heat insulation layer, nozzle component and O type circle.Nozzle assembly, front end heat insulation layer, rear end heat insulation layer, nozzle component and afterburning chamber housing assemble and fill gap with putty, can sustain jet flow produce high temperature, high pressure thus produce thrust, promote missile flight.
Afterburning chamber qualified, the structural stability of assembling and sealing is well the prerequisite that afterburning chamber normally works, improves the normal work of the assembly quality guarantee afterburning chamber of afterburning chamber.Afterburning chamber housing is long thin wall metal cylinder, forms afterburning chamber with nonmetal by adhesive asserably.Coordinate between housing with non-metal part for Spielpassung, excesssive gap, afterburning chamber cannot seal, and gap is too small or uneven, and assembling difficulty is large.Designing requirement index is: the monolateral gap of mean inside diameter size of rear end heat insulation layer cylindrical, nozzle component cylindrical and afterburning chamber housing rear end position ensures by 0 ~ 0.40mm, the monolateral gap of mean inside diameter size of front end heat insulation layer cylindrical and housing middle-end position ensures by 0 ~ 0.40mm, and the monolateral gap of mean inside diameter size of nozzle assembly cylindrical and housing forward end position ensures by 0 ~ 0.40mm.And during practical set, because afterburning chamber housing entirety is longer, if not metal and housing local gap too small, during assembling, nonmetal be press-fitted assembling difficulty.If excesssive gap, partially sealed poor in assembly process, have impact on the sealing of whole afterburning chamber.
Summary of the invention
The object of the present invention is to provide a kind of assembly method of solid rocket ramjet afterburning chamber, to ensure the assembly quality of afterburning chamber, make afterburning chamber can work to promote rocket normally and run.
For achieving the above object, afterburning chamber assembly method of the present invention comprises the following steps:
1) uniformity in afterburning chamber housing aperture ensures and adjusts circle: afterburning chamber housing is long thin-walled parts, and front and back are all with flanged surface, common machine adds cannot be processed, therefore afterburning chamber housing is divided into three sections from front to back successively: front connector, middle cylinder and rear joint, then three sections of assembly weldings is got up.For increasing intensity and the hardness of part, afterburning chamber housing needs to heat-treat, be out of shape in heat treatment for preventing housing, a plug is welded at front connector flanged surface during heat treatment, by plug of slinging, make housing straight down, distortion can be produced by the effectively part that prevents in heat treatment process like this; After heat treatment completes, then plug is removed.Before assembling, utilize and adjust sired results dress to carry out tune circle to afterburning chamber housing three place: with middle cylinder weld in a, front connector; The middle of b, middle cylinder; With middle cylinder weld on c, rear joint.
2) join Chefei's metalwork: afterburning chamber housing need assemble one by one with non-metal part nozzle component, rear end heat insulation layer, front end heat insulation layer, nozzle assembly, being exerted pressure to the back-end from front end to non-metal part by press machine is put in place non-metal part assembling.For ensureing that non-metal part can slide smoothly in the process be press-fitted, when joining Chefei's metalwork, by measuring afterburning chamber housing inner diameter value, non-metal part external diameter value is calculated again according to the clearance meter of afterburning chamber housing and non-metal part, by calculated value Vehicle Processing non-metal part external diameter, enough gaps are had between afterburning chamber housing and non-metal part when can ensure to assemble, avoid occurring making nonmetal cannot normally sliding backward because front inner diameter is too small in assembly process and affecting assembling, ensure normally carrying out of assembling, concrete control is as follows: a, the monolateral gap of mean inside diameter size of joint after nozzle component and afterburning chamber housing, the monolateral gap of mean inside diameter size at rear end heat insulation layer cylindrical and afterburning chamber housing middle cylinder place allows to ensure by 0.30 ~ 0.40mm, the monolateral gap of mean inside diameter size at b, front end heat insulation layer cylindrical and afterburning chamber housing middle cylinder place allows to ensure by 0.20 ~ 0.30mm, the monolateral gap of mean inside diameter size of c, nozzle assembly cylindrical and front connector place of afterburning chamber housing allows to ensure by 0.05 ~ 0.20mm.
Especially, when the mean inside diameter of afterburning chamber housing front connector place be of a size of front connector, middle cylinder, rear joint three place mean inside diameter size minimum average B configuration internal diameter size time, the monolateral gap of mean inside diameter size of nozzle component, rear end heat insulation layer cylindrical, front end heat insulation layer cylindrical, nozzle heat insulation layer cylindrical and front connector place allows to ensure by 0.05 ~ 0.10mm.
3) guarantee of nozzle component and afterburning chamber back-end sealing: for ensureing the sealing of afterburning chamber entirety, adopts D03 single-component room-temperature vulcanized silicone rubber putty, is fixed on by O type circle in jet pipe heat insulation layer seal groove, to ensure the sealing that whole afterburning chamber assembles.
4) afterburning chamber housing is bonding with the assembling of non-metal part: be Spielpassung between afterburning chamber housing and non-metal part, the fitting surface of afterburning chamber housing and non-metal part is filled with a sealing by D03 single-component room-temperature vulcanized silicone rubber putty, and the interface between each non-metal part is filled with a sealing by D03 single-component room-temperature vulcanized silicone rubber putty equally.Because afterburning chamber overall dimensions is partially long, during assembling, the interface on the fitting surface of each non-metal part and afterburning chamber housing and between each non-metal part scribbles D03 single-component room-temperature vulcanized silicone rubber putty.By assemble sequence successively by nozzle component, rear end heat insulation layer, front end heat insulation layer, nozzle assembly the past tip side loading afterburning chamber housing one by one, press machine is used to exert pressure to the back-end from front end, nonmetal slow slide downward is made until be finally press-fitted and put in place by the lubrication of D03 single-component room-temperature vulcanized silicone rubber putty, the bonding of whole afterburning chamber also just completes to the solidification of D03 single-component room-temperature vulcanized silicone rubber putty to be press-fitted pressurize a period of time after putting in place.
Beneficial effect of the present invention:
Assembly method of the present invention is by round to the tune of afterburning chamber housing inner diameter and control afterburning chamber housing and non-metallic layer fit up gap, and the designing requirement of the assembling of guarantee, adds the feasibility of operation, and improves assembly quality and the efficiency of afterburning chamber.
The afterburning chamber of assembly method assembling provided by the invention is through repeatedly ground experiment examination, and quality of product meets design requirement completely.Assembly method of the present invention not only may be used for afterburning chamber, can also be used for the assembling of other similar products.
Accompanying drawing explanation
Fig. 1 is the structural representation of afterburning chamber.
Fig. 2 is the assembly structure schematic diagram of nozzle component and afterburning chamber housing.
Fig. 3 is the assembly structure schematic diagram of nozzle assembly and afterburning chamber housing.
Embodiment
Be described in further detail the present invention below in conjunction with accompanying drawing and instantiation, what deserves to be explained is, following examples are explanation of the invention instead of limitation of the present invention.
As can be seen from Figure 1, afterburning chamber comprises afterburning chamber housing 1, nozzle assembly 2, front end heat insulation layer 3, rear end heat insulation layer 4, nozzle component 5 and O type circle 6.As can be seen from Figure 2, O type circle 6 is fixed in the seal groove of jet pipe heat insulation layer 501 of nozzle component 5 by D03 single-component room-temperature vulcanized silicone rubber putty.As can be seen from Figure 3, nozzle assembly 2 is provided with nozzle heat insulation layer 201.
1) uniformity of afterburning chamber housing 1 diameter ensures and adjusts circle: afterburning chamber housing 1 is long thin-walled parts, and front and back are all with flanged surface, common machine adds cannot be processed, therefore afterburning chamber housing 1 is divided into three sections from front to back successively: front connector 101, middle cylinder 103 and rear joint 102, then three sections of assembly weldings is got up.The division of front connector 101, rear joint 102 and each segment length of middle cylinder 103 does not have strict requirement, but for convenience of meter, the length of the length of general front connector 101 and the nozzle heat insulation layer 201 of nozzle assembly 2 adapts, the length of the length of rear joint 102 and the jet pipe heat insulation layer 501 of nozzle component 5 adapts, and the length of middle cylinder 103 and the total length of front end heat insulation layer 3 and rear end heat insulation layer 4 adapt.For increasing intensity and the hardness of part, afterburning chamber housing 1 needs to heat-treat, be out of shape in heat treatment for preventing afterburning chamber housing 1, a plug is welded at the flanged surface of front connector 101 during heat treatment, by plug of slinging, make afterburning chamber housing 1 straight down, distortion can be produced by the effectively part that prevents in heat treatment process like this; After heat treatment completes, then plug is removed.Before assembling, utilize and adjust sired results dress to carry out adjusting circle to three places of afterburning chamber housing 1: with the weld of middle cylinder 103 in a, front connector 101; The middle of b, middle cylinder 103; With the weld of middle cylinder 103 on c, rear joint 102.
2) Chefei's metalwork is joined: afterburning chamber housing 1 need assemble one by one with non-metal part nozzle component 5, rear end heat insulation layer 4, front end heat insulation layer 3, nozzle assembly 2.
The non-metal part assembled before processing, diameter first by measuring afterburning chamber housing 1 joins Chefei's metalwork, and specific requirement is: the monolateral gap of mean inside diameter size, the rear end heat insulation layer cylindrical 4 at rear joint 102 place of a, nozzle component 5 and afterburning chamber housing 1 allow by 0.30 ~ 0.40mm with the monolateral gap of mean inside diameter size at afterburning chamber housing middle cylinder 103 place; The monolateral gap of mean inside diameter size at the cylindrical of b, front end heat insulation layer 3 and middle cylinder 103 place of afterburning chamber housing 1 allows to ensure by 0.20 ~ 0.30mm; The cylindrical of c, nozzle assembly 2 and the monolateral gap of mean inside diameter size at front connector 101 place allow to ensure by 0.05 ~ 0.20mm.
Especially: when the mean inside diameter at front connector 101 place of afterburning chamber housing 1 is of a size of front connector 101, middle cylinder 103, rear joint 102 3 place minimum average B configuration internal diameter size, car-distribution method: the cylindrical of nozzle component 5, rear end heat insulation layer 4, front end heat insulation layer 3, nozzle heat insulation layer 2 and the monolateral gap of mean inside diameter size at front connector 101 place allow to ensure by 0.05 ~ 0.10mm.
This gap control can not only ensure designing requirement, and can ensure to there will not be in the process that non-metal part assembles in entirety and to make because local gap is too small non-metal part cannot the situation of movement to the back-end.
3) guarantee of nozzle component 5 and afterburning chamber housing 1 back-end sealing: for ensureing the sealing of afterburning chamber entirety, adopt D03 single-component room-temperature vulcanized silicone rubber putty, O type circle 6 is fixed in jet pipe heat insulation layer 501 seal groove, to ensure the sealing that whole afterburning chamber assembles.
4) afterburning chamber housing 1 is bonding with the assembling of non-metal part: the gap between afterburning chamber housing 1 and non-metal part is filled by D03 single-component room-temperature vulcanized silicone rubber putty, this putty mainly seals, carry out in the process be press-fitted at non-metal part and afterburning chamber housing 1 in addition, putty also can play certain lubrication.The assembling of non-metal part is vertically exerted pressure by press machine and is assembled bonding putting in place.During assembling, fixing afterburning chamber housing 1, front connector 101 end upward, overall in vertical state, by assemble sequence successively by nozzle component 5, rear end heat insulation layer 4, front end heat insulation layer 3, nozzle assembly 2 loads from front connector 101 end one by one and vertically exerts pressure to non-metal part towards afterbody with press machine, to reach the object be finally seated, specific operation are: first by nozzle component 5 and afterburning chamber housing 1 just to after assembling, with press machine, nozzle component 5 is pressed into the inside of afterburning chamber housing 1, afterwards by rear end heat insulation layer 4 with afterburning chamber housing 1 just to assembling, and dock with nozzle component 5, press machine is exerted pressure to rear end heat insulation layer 4, promote rear end heat insulation layer 4 to slide inwards, and drive nozzle component 5 to slide inwards together, and then by front end heat insulation layer 3, with afterburning chamber housing 1 just to assembling, and dock with rear end heat insulation layer 4, press machine is exerted pressure to front end heat insulation layer 3, in the same way, load nozzle assembly 2, finally each non-metal part is press-fitted and puts in place.The bonding of whole afterburning chamber also just completes to the solidification of D03 single-component room-temperature vulcanized silicone rubber putty to be press-fitted pressurize a period of time after putting in place.Before assembling, the interface on the fitting surface of each non-metal part and afterburning chamber housing 1 and between each non-metal part need coat D03 single-component room-temperature vulcanized silicone rubber putty.
After assembling afterburning chamber with said method, indices meets design requirement completely: whole afterburning chamber assembling is bonding to put in place and good airproof performance.
Claims (2)
1. an assembly method for solid rocket ramjet afterburning chamber, is characterized in that: comprise the following steps:
1) uniformity in afterburning chamber housing aperture ensures and adjusts circle: described afterburning chamber housing is got up by front connector, middle cylinder and rear joint three sections of assembly weldings from front to back; Weld a plug at front connector flanged surface during described afterburning chamber housing heat treatment, by plug of slinging, make housing straight down; Before assembling, utilize and adjust sired results dress to carry out tune circle respectively to three places below afterburning chamber housing: with middle cylinder weld in a, front connector; The middle of b, middle cylinder; With middle cylinder weld on c, rear joint;
2) Chefei's metalwork is joined: described non-metal part is respectively nozzle component, rear end heat insulation layer, front end heat insulation layer, nozzle assembly; When joining Chefei's metalwork, first measure afterburning chamber housing inner diameter value, each non-metal part external diameter value is calculated again according to the clearance meter of afterburning chamber housing and non-metal part, by each non-metal part external diameter of calculated value Vehicle Processing, ensure normally carrying out of assembling, concrete control as follows: the monolateral gap of mean inside diameter size at the monolateral gap of mean inside diameter size of joint after a, nozzle component and afterburning chamber housing, rear end heat insulation layer cylindrical and afterburning chamber housing middle cylinder place allows to press 0.30 ~ 0.40mm and ensures; The monolateral gap of mean inside diameter size at b, front end heat insulation layer cylindrical and afterburning chamber housing middle cylinder place allows to ensure by 0.20 ~ 0.30mm; The monolateral gap of mean inside diameter size of c, nozzle heat insulation layer cylindrical and front connector place of afterburning chamber housing allows to ensure by 0.05 ~ 0.20mm;
3) guarantee of nozzle component and afterburning chamber back-end sealing: before assembling, adopts D03 single-component room-temperature vulcanized silicone rubber, is fixed on by O type circle in jet pipe heat insulation layer seal groove;
4) afterburning chamber housing is bonding with the assembling of non-metal part: during assembling, fixing afterburning chamber housing, front connector 101 end end upward, vertical placement, and the interface on the fitting surface of each non-metal part and afterburning chamber housing and between each non-metal part is coated D03 single-component room-temperature vulcanized silicone rubber putty, then assemble sequence is pressed successively by nozzle component, rear end heat insulation layer, front end heat insulation layer, nozzle assembly one by one the past tip side loads afterburning chamber housing, press machine is used successively to be press-fitted by each non-metal part to the back-end from front end, and pressurize is solidified to D03 single-component room-temperature vulcanized silicone rubber putty, ensure that final assembling is bonding to put in place.
2. the assembly method of solid rocket ramjet afterburning chamber according to claim 1, it is characterized in that: described step 2) in the mean inside diameter of afterburning chamber housing front connector place be of a size of the minimum value of front connector, middle cylinder, rear joint three place mean inside diameter size, nozzle component, rear end heat insulation layer cylindrical, front end heat insulation layer cylindrical, nozzle heat insulation layer cylindrical and the monolateral gap of mean inside diameter size of front connector place allow to press 0.05 ~ 0.10mm and ensure.
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| CN201410481939.4A CN104329186B (en) | 2014-09-19 | 2014-09-19 | The assembly method of solid rocket ramjet afterburning chamber |
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| CN201410481939.4A CN104329186B (en) | 2014-09-19 | 2014-09-19 | The assembly method of solid rocket ramjet afterburning chamber |
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| CN104329186B CN104329186B (en) | 2016-06-22 |
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| CN106735829A (en) * | 2016-11-30 | 2017-05-31 | 湖北三江航天江北机械工程有限公司 | The welding method of many designs of part of liquid rocket engine thrust chamber head injector |
| CN107322246A (en) * | 2017-08-23 | 2017-11-07 | 湖北三江航天江北机械工程有限公司 | The big jet pipe bonding press-fitting technique of solid propellant rocket |
| CN108007280A (en) * | 2017-12-28 | 2018-05-08 | 北京威标至远科技发展有限公司 | A kind of steering engine thermal protection struc ture |
| CN114603900A (en) * | 2022-03-02 | 2022-06-10 | 北京玻钢院复合材料有限公司 | Composite external pressure shell reinforcement structure and forming method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108007280B (en) * | 2017-12-28 | 2023-08-15 | 北京威标至远科技发展有限公司 | Steering engine heat-proof structure |
| CN114603900A (en) * | 2022-03-02 | 2022-06-10 | 北京玻钢院复合材料有限公司 | Composite external pressure shell reinforcement structure and forming method thereof |
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| CN104329186B (en) | 2016-06-22 |
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