CN106762230A - The non-insert nozzle of solid propellant rocket and manufacture method - Google Patents
The non-insert nozzle of solid propellant rocket and manufacture method Download PDFInfo
- Publication number
- CN106762230A CN106762230A CN201611031907.XA CN201611031907A CN106762230A CN 106762230 A CN106762230 A CN 106762230A CN 201611031907 A CN201611031907 A CN 201611031907A CN 106762230 A CN106762230 A CN 106762230A
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- Prior art keywords
- larynx
- revolving body
- lining
- pad
- internal layer
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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
- F02K9/97—Rocket nozzles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/008—Rocket engine parts, e.g. nozzles, combustion chambers
-
- 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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
-
- 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
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Prostheses (AREA)
Abstract
The present invention relates to a kind of non-insert nozzle of solid propellant rocket, the leading portion of its jet pipe revolving body case inside wall is fixedly connected with the lateral wall of converging portion heat insulation layer, the stage casing of jet pipe revolving body case inside wall is fixedly connected with adiabatic ring lateral wall, the back segment of jet pipe revolving body case inside wall is fixedly connected with the lateral wall of diffuser revolving body heat insulation layer, the lateral wall of revolving body larynx lining is fixedly connected with the madial wall of adiabatic ring, the front end that the rear end of converging portion heat insulation layer serves as a contrast with adiabatic ring and revolving body larynx is fixedly connected, the rear end of adiabatic ring and revolving body larynx lining is fixedly connected with the front end of diffuser revolving body heat insulation layer；The outer riser lining of revolving body larynx lining is circumferentially bonded by N block outer risers pad and formed, the internal layer larynx lining of revolving body larynx lining is circumferentially bonded by N block internal layer larynxs pad and formed, the sealant of resistance to ablation is filled between two pieces of adjacent sub- outer riser pads, the sealant of resistance to ablation is also filled between two pieces of adjacent sub- internal layer larynx pads.Homogeneity of product of the invention is preferable.
Description
Technical field
The present invention relates to rocket engine technical field, and in particular to a kind of non-insert nozzle of solid propellant rocket and
Manufacture method.
Background technology
The jet pipe of solid propellant rocket is to turn the combustion gas energy efficient that combustion chamber produces by controlling exhaust expansion
Kinetic energy is changed to, the position of thrust is provided to aircraft.Larynx lining is located at nozzle throat, and its ablation state is most harsh, larynx lining inner mold face
Ablation is washed away by high temperature, high pressure, high speed and hot-fluid containing aggressivity particle and damaged, show as the expansion of larynx footpath, rough surface
Injustice, type face is irregular etc..Especially in engine ignition moment, larynx lining heats up suddenly from normal temperature with more than 2000 DEG C/s speed,
Great thermograde and thermal stress are produced, larynx is foiled existing crackle or fragmentation, the thrust and effect of engine will be directly affected
Rate, or even ability of losing the job.The structure and material of larynx lining are selected to the key of solid propellant rocket work success or failure.At present
Domestic and international Throat Materials for Solid Rocket Motors mainly has：Refractory metal, graphite, carbon carbon composite, reinforced plastics, ceramic base
Composite etc..
Due to developing rapidly for domestic and international Solid Rocket Motor Technology, major diameter, big flow solid propellant rocket should
With more and more, but for larynx lining, due to the limitation of manufacture craft and equipment, when larynx lining reaches certain bottleneck size, meeting
Greatly increase technology difficulty, complexity, the product quality after shaping is poor, it is understood that there may be carburizing is uneven, carbon-rich zone is more,
The defect such as strength of materials dispersion is big, and the uniformity of product is difficult to ensure that, while bringing higher cost price.
The content of the invention
It is an object of the invention to provide a kind of non-insert nozzle of solid propellant rocket and manufacture method, this is non-to slip into
The homogeneity of product of formula jet pipe is preferable, low production cost.
In order to solve the above technical problems, the non-insert nozzle of a kind of solid propellant rocket disclosed by the invention, its feature
It is：It includes jet pipe revolving body housing, diffuser revolving body heat insulation layer, adiabatic ring, revolving body larynx lining and converging portion heat insulation layer,
Wherein, the leading portion of jet pipe revolving body case inside wall is fixedly connected with the lateral wall of converging portion heat insulation layer, jet pipe revolving body housing
The stage casing of madial wall is fixedly connected with adiabatic ring lateral wall, and the back segment of jet pipe revolving body case inside wall is exhausted with diffuser revolving body
The lateral wall of thermosphere is fixedly connected, and the lateral wall of revolving body larynx lining is fixedly connected with the madial wall of adiabatic ring, converging portion heat insulation layer
The front end that is served as a contrast with adiabatic ring and revolving body larynx of rear end be fixedly connected, rear end and the diffuser of adiabatic ring and revolving body larynx lining are turned round
The front end of body heat insulation layer is fixedly connected；
The outer riser lining of the revolving body larynx lining is circumferentially bonded by N block outer risers pad and formed, and it is interior that revolving body larynx is served as a contrast
Layer larynx lining is circumferentially bonded by N block internal layer larynxs pad and formed, and resistance to ablation sealing is filled between two pieces of adjacent sub- outer riser pads
Putty, the sealant of resistance to ablation is also filled between two pieces of adjacent sub- internal layer larynx pads.
Further, adhesive is filled between every piece of sub- outer riser pad and corresponding sub- internal layer larynx pad.
Further, the rear end of the converging portion heat insulation layer wraps the front end of revolving body larynx lining.
Further, the junction between two pieces of adjacent sub- outer riser pads serves as a contrast with adjacent two pieces sub- internal layer larynxs
Junction between block is into being in staggered distribution.
Further, adhesive is filled between the lateral wall of the revolving body larynx lining and the madial wall of adiabatic ring.
Further, the N is 3~7.
A kind of manufacture method of the non-insert nozzle of solid propellant rocket, it is characterised in that it includes as follows
Step：
Step 1：By regular cuboid larynx pad, Milling Machining is into desired N block outer riser pads and N on CNC milling machine
Block internal layer larynx pad；
Step 2：N block outer riser pads and N block internal layer larynx pads are assembled into revolving body larynx using splicing machine to serve as a contrast；
Step 3：According to conventional turning processing method, by jet pipe revolving body housing, diffuser revolving body heat insulation layer, adiabatic ring and
Converging portion heat insulation layer is machining；
Step 4：To fill adhesive between the lateral wall of revolving body larynx lining and the madial wall of adiabatic ring, and by revolving body larynx
Lining is be bonded into throat lining body with adiabatic ring；
Step 5：The leading portion of jet pipe revolving body case inside wall is glued with the lateral wall of converging portion heat insulation layer by adhesive
Connect, the stage casing of jet pipe revolving body case inside wall is Nian Jie with adiabatic ring lateral wall, after jet pipe revolving body case inside wall
Section is Nian Jie with the lateral wall of diffuser revolving body heat insulation layer, and the rear end of converging portion heat insulation layer is Nian Jie with the front end of throat lining body, will
The rear end of throat lining body is Nian Jie with the front end of diffuser revolving body heat insulation layer, so as to form the non-submersible spray of solid propellant rocket
Pipe；
Step 6：The non-insert nozzle of solid propellant rocket is connected with ammunition-loading engine, igniter, ground is carried out
Fire trial, analyzes the ablating rate of sub- outer riser pad and sub- internal layer larynx pad, and carried out with conventional integrated throat ablating rate it is right
Than the ablation property to sub- outer riser pad and sub- internal layer larynx pad is analyzed, and carries out the detection of structure anti-thermal shock reliability.
Further, the step 1 neutron outer riser pad and sub- internal layer larynx pad vertical machining centre or it is horizontal plus
Processed using CNC milling machine on work center.
Further, it is to borrow outer riser first revolving body larynx to be served as a contrast with the adiabatic be bonded specific method into throat lining body of ring
Lining bag holds the outer riser lining of ring bonding revolving body larynx lining, then that outer riser lining outer mold surface is Nian Jie with adiabatic ring integral, then leads to
Cross internal layer larynx lining bag and hold the internal layer larynx lining that N block internal layer larynxs pad bonding is assembled into ring revolving body larynx lining, then by internal layer larynx
Lining outer mold surface and outer riser lining, thermal insulation ring carry out bonding being assembled into throat lining body.
In the step 4, it is with the adiabatic be bonded specific method into throat lining body of ring by revolving body larynx lining, borrows contain first
The outer riser lining of ring bonding revolving body larynx lining, it is then that outer riser lining outer mold surface is Nian Jie with adiabatic ring integral, then by containing
N block internal layer larynxs pad bonding is assembled into ring the internal layer larynx lining of revolving body larynx lining, and internal layer larynx then is served as a contrast into outer mold surface and outer layer
Larynx lining, adiabatic ring carry out bonding and are assembled into throat lining body.
The present invention is served as a contrast by original monoblock type larynx lining structure by by larynx, is divided into some sub- outer riser pads and sub- internal layer
Larynx pad, between any two again by assembly technology connect into monoblock type larynx serve as a contrast, then with non-insert nozzle other structures parts group
Dress up jet pipe.Single larynx pad volume diminishes, and will be effectively reduced production and the difficulty of processing of larynx lining；Because of the size to embryo material
It is required that also diminishing, can effectively save material, prepared by technique and processing cost is also minimized；Simultaneously because single larynx
Pad size reduces, and thickness is thinning so that carburizing is more uniform, the quality conformance of the non-insert nozzle of solid propellant rocket
It is easier to ensure that.
Brief description of the drawings
Fig. 1 is non-insert nozzle Anatomical Structure schematic diagram in the present invention；
Fig. 2 is larynx lining partitioned organization schematic diagram in the present invention；
Fig. 3 is the sectional view of Fig. 2；
Fig. 4 is outer riser lining and its frock schematic diagram in the present invention；
Fig. 5 is outer riser lining in the present invention and adiabatic ring assembling schematic diagram；
Fig. 6 is internal layer larynx lining and its frock schematic diagram in the present invention；
Fig. 7 is throat lining body structural representation in the present invention.
Wherein, 1-jet pipe revolving body housing, 2-diffuser revolving body heat insulation layer, 3-adiabatic ring, 4-revolving body larynx lining,
5-converging portion heat insulation layer, 6-outer riser lining bag hold ring, 7-internal layer larynx lining bag and hold ring, 8-sub- outer riser pad, 9-sub- internal layer
Larynx pad, 10-throat lining body, 11-larynx lining and adiabatic czermak space, 12-outer riser pad clearance, 13-internal layer larynx pad clearance,
14-larynx lining interlayer spacings, 15-internal layer larynx lining inner mold face, 16-larynx lining end face, 17-outer riser lining outer mold surface, 18-outer layer
Larynx lining inner mold face, 19-internal layer larynx lining outer mold surface.
Specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail：
The non-insert nozzle of a kind of solid propellant rocket designed by the present invention, as shown in Fig. 1~7, it includes jet pipe
Revolving body housing 1, diffuser revolving body heat insulation layer 2, adiabatic ring 3, revolving body larynx serve as a contrast 4 and converging portion heat insulation layer 5, wherein, jet pipe
The leading portion of the madial wall of revolving body housing 1 is fixedly connected with the lateral wall of converging portion heat insulation layer 5, the madial wall of jet pipe revolving body housing 1
Stage casing be fixedly connected with the adiabatic lateral wall of ring 3, back segment and the diffuser revolving body heat insulation layer of the madial wall of jet pipe revolving body housing 1
2 lateral wall is fixedly connected, and the lateral wall of revolving body larynx lining 4 is fixedly connected with the madial wall of adiabatic ring 3, converging portion heat insulation layer 5
Rear end be fixedly connected with the front end of adiabatic ring 3 and revolving body larynx lining 4, the rear end and diffuser of adiabatic ring 3 and revolving body larynx lining 4
The front end of revolving body heat insulation layer 2 is fixedly connected；
The outer riser lining of the revolving body larynx lining 4 is formed by circumferential bonding of N block outer risers pad 8, revolving body larynx lining 4
Internal layer larynx lining is formed by circumferential bonding of N block internal layer larynxs pad 9, and the resistance to burnings of D03 are filled between two pieces of adjacent sub- outer riser pads 8
Erosion sealant, also fills the D03 sealants of resistance to ablation, every piece of sub- outer riser lining between two pieces of adjacent sub- internal layer larynx pads 9
(larynx serves as a contrast interlayer spacings 14) the filling adhesive of anchor 101 between block 8 and corresponding sub- internal layer larynx pad 9.Assembling is in place with putty
Extruded from gap and be defined.
In above-mentioned technical proposal, the rear end of the converging portion heat insulation layer 5 wraps the front end of revolving body larynx lining 4.Prevent outer
Layer larynx pad clearance 12 and internal layer larynx pad clearance 13 are directly exposed at gas shock, cause engine operational failure.
In above-mentioned technical proposal, junction and two pieces of adjacent sons between two pieces of adjacent sub- outer riser pads 8
Junction between internal layer larynx pad 9 is into being in staggered distribution.The above-mentioned form being in staggered distribution, forms " blind area " structure, prevents string fire
And direct ablation jet pipe revolving body housing 1, cause engine operational failure.
In above-mentioned technical proposal, anchor is filled between the lateral wall of the revolving body larynx lining 4 and the madial wall of adiabatic ring 3
101 adhesive.
In above-mentioned technical proposal, the N is 3~7.
A kind of manufacture method of the non-insert nozzle of above-mentioned solid propellant rocket, it comprises the following steps：
Step 1：By regular cuboid larynx pad, Milling Machining is into the desired He of N block outer risers pad 8 on CNC milling machine
N block internal layer larynxs pad 9；
Step 2：N block outer risers pad 8 and N block internal layer larynxs pad 9 are assembled into revolving body larynx lining 4 using splicing machine
(it is by technique for sticking and special bonding machining tool, larynx pad assembly is integral, and the machine that larynx is served as a contrast is added into required size)；
Step 3：According to conventional turning processing method, by jet pipe revolving body housing 1, diffuser revolving body heat insulation layer 2, adiabatic ring
3 and converging portion heat insulation layer 5 it is machining；
Step 4：The adhesive of anchor 101 will be filled between the madial wall of the lateral wall of revolving body larynx lining 4 and adiabatic ring 3, and
Revolving body larynx lining 4 is be bonded into throat lining body 10 with adiabatic ring 3；
Step 5：By adhesive by the lateral wall of the leading portion of the madial wall of jet pipe revolving body housing 1 and converging portion heat insulation layer 5
Bonding, the stage casing of the madial wall of jet pipe revolving body housing 1 is Nian Jie with the adiabatic lateral wall of ring 3, by the madial wall of jet pipe revolving body housing 1
Back segment it is Nian Jie with the lateral wall of diffuser revolving body heat insulation layer 2, by the front end of the rear end of converging portion heat insulation layer 5 and throat lining body 10
Bonding, the rear end of throat lining body 10 is Nian Jie with the front end of diffuser revolving body heat insulation layer 2, so that it is non-to form solid propellant rocket
Insert nozzle；
Step 6：The non-insert nozzle of solid propellant rocket is connected with ammunition-loading engine, igniter, ground is carried out
Fire trial, analyzes the ablating rate of sub- outer riser pad 8 and sub- internal layer larynx pad 9, and is carried out with conventional integrated throat ablating rate
Contrast, the ablation property to sub- outer riser pad 8 and sub- internal layer larynx pad 9 is analyzed, and carries out structure anti-thermal shock reliability
Detection.
In above-mentioned technical proposal, the step 1 neutron outer riser pad 8 and sub- internal layer larynx pad 9 are in vertical machining centre
Or processed using CNC milling machine on horizontal Machining centers.
In the step of above-mentioned technical proposal 4, by revolving body larynx lining 4 and the be bonded specific method into throat lining body 10 of adiabatic ring 3
For, the outer riser lining that outer riser lining bag holds the bonding revolving body larynx of ring 6 lining 4 is borrowed first, then by outer riser lining outer mold surface 17 with
Adiabatic ring 3 is bonded integrally (to be carried out be bonded) in larynx lining and adiabatic czermak space 11, then holds ring 7 by N blocks by internal layer larynx lining bag
The internal layer larynx lining that the bonding of internal layer larynx pad 9 is assembled into revolving body larynx lining 4 (with outer riser lining with in-car layer larynx lining outer mold surface 19, is protected
Demonstrate,prove unilateral gap 0.1mm), then internal layer larynx lining outer mold surface 19 and outer riser lining, thermal insulation ring 3 are carried out bonding to be assembled into throat lining body
Internal layer larynx lining outer mold surface 19 (is applied the adhesive of anchor 101, internal layer larynx pad clearance 13 applies D03 ablation putty, is separately assembled to by 10
In outer riser lining.After cured, machine adds internal layer larynx to serve as a contrast inner mold face 15).
The content that this specification is not described in detail belongs to prior art known to professional and technical personnel in the field.
Claims (10)
1. the non-insert nozzle of a kind of solid propellant rocket, it is characterised in that：It includes jet pipe revolving body housing (1), diffusion
Section revolving body heat insulation layer (2), adiabatic ring (3), revolving body larynx lining (4) and converging portion heat insulation layer (5), wherein, jet pipe revolution body shell
The leading portion of body (1) madial wall is fixedly connected with the lateral wall of converging portion heat insulation layer (5), jet pipe revolving body housing (1) madial wall
Stage casing is fixedly connected with adiabatic ring (3) lateral wall, and the back segment of jet pipe revolving body housing (1) madial wall is adiabatic with diffuser revolving body
The lateral wall of layer (2) is fixedly connected, and the lateral wall of revolving body larynx lining (4) is fixedly connected with the madial wall of adiabatic ring (3), converging portion
The rear end of heat insulation layer (5) is fixedly connected with the front end of adiabatic ring (3) and revolving body larynx lining (4), and adiabatic ring (3) and revolving body larynx are served as a contrast
(4) rear end is fixedly connected with the front end of diffuser revolving body heat insulation layer (2)；
The outer riser lining of revolving body larynx lining (4) is circumferentially bonded by N block outer risers pad (8) and formed, revolving body larynx lining (4)
Internal layer larynx lining by N blocks internal layer larynx pad (9) circumferentially bond form, between two pieces of adjacent sub- outer riser pads (8) fill
The sealant of resistance to ablation, the sealant of resistance to ablation is also filled between two pieces of adjacent sub- internal layer larynx pads (9).
2. the non-insert nozzle of solid propellant rocket according to claim 1, it is characterised in that：Every piece of sub- outer riser lining
Adhesive is filled between block (8) and corresponding sub- internal layer larynx pad (9).
3. the non-insert nozzle of solid propellant rocket according to claim 1, it is characterised in that：The converging portion is adiabatic
The rear end of layer (5) wraps the front end of revolving body larynx lining (4).
4. the non-insert nozzle of solid propellant rocket according to claim 1, it is characterised in that：Described adjacent two pieces
The junction between junction and adjacent two pieces sub- internal layer larynx pads (9) between sub- outer riser pad (8) is into being in staggered distribution.
5. the non-insert nozzle of solid propellant rocket according to claim 1, it is characterised in that：The revolving body larynx lining
(4) adhesive is filled between the madial wall of lateral wall and adiabatic ring (3).
6. the non-insert nozzle of solid propellant rocket according to claim 1, it is characterised in that：The N is 3~7.
7. the manufacture method of the non-insert nozzle of solid propellant rocket described in a kind of claim 1, it is characterised in that it includes
Following steps：
Step 1：By regular cuboid larynx pad, Milling Machining is into desired N block outer risers pad (8) and N on CNC milling machine
Block internal layer larynx pad (9)；
Step 2：N block outer risers pad (8) and N blocks internal layer larynx pad (9) are assembled into revolving body larynx using splicing machine to serve as a contrast
(4)；
Step 3：According to conventional turning processing method, by jet pipe revolving body housing (1), diffuser revolving body heat insulation layer (2), adiabatic ring
And converging portion heat insulation layer (5) is machining (3)；
Step 4：Adhesive will be filled between the lateral wall of revolving body larynx lining (4) and the madial wall of thermal insulation ring (3), and by revolving body
It is be bonded into throat lining body (10) with adiabatic ring (3) that larynx serves as a contrast (4)；
Step 5：By adhesive by the lateral wall of the leading portion of jet pipe revolving body housing (1) madial wall and converging portion heat insulation layer (5)
Bonding, the stage casing of jet pipe revolving body housing (1) madial wall is Nian Jie with adiabatic ring (3) lateral wall, by jet pipe revolving body housing (1)
The back segment of madial wall is Nian Jie with the lateral wall of diffuser revolving body heat insulation layer (2), and the rear end of converging portion heat insulation layer (5) and larynx are served as a contrast
The front end bonding of body (10), the rear end of throat lining body (10) is Nian Jie with the front end of diffuser revolving body heat insulation layer (2), so as to be formed
The non-insert nozzle of solid propellant rocket.
8. manufacture method according to claim 7, it is characterised in that：Also include step 6 after the step 5：By solid fire
The non-insert nozzle of arrow engine is connected with ammunition-loading engine, igniter, carries out ground firing, analyzes sub- outer riser lining
Block (8) and the ablating rate of sub- internal layer larynx pad (9), and contrasted with conventional integrated throat ablating rate, to sub- outer riser pad
(8) it is analyzed with the ablation property of sub- internal layer larynx pad (9), and carries out the detection of structure anti-thermal shock reliability.
9. manufacture method according to claim 7, it is characterised in that：In the step 1 neutron outer riser pad (8) and son
Layer larynx pad (9) is processed in vertical machining centre or horizontal Machining centers using CNC milling machine.
10. manufacture method according to claim 7, it is characterised in that：In the step 4, by revolving body larynx lining (4) with it is exhausted
The specific method that hot ring (3) is bonded into throat lining body (10) is to borrow outer riser lining bag first to hold ring (6) bonding revolving body larynx lining
(4) outer riser lining, then serves as a contrast outer mold surface (17) Nian Jie with adiabatic ring (3) integrally by outer riser, then by internal layer larynx lining bag
N blocks internal layer larynx pad (9) bondings are assembled into Rong Huan (7) the internal layer larynx lining of revolving body larynx lining (4), then that internal layer larynx lining is outer
Type face (19) and outer riser are served as a contrast, adiabatic ring (3) carries out bonding being assembled into throat lining body (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611031907.XA CN106762230B (en) | 2016-11-22 | 2016-11-22 | The non-insert nozzle of solid propellant rocket and manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611031907.XA CN106762230B (en) | 2016-11-22 | 2016-11-22 | The non-insert nozzle of solid propellant rocket and manufacturing method |
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| Publication Number | Publication Date |
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| CN106762230A true CN106762230A (en) | 2017-05-31 |
| CN106762230B CN106762230B (en) | 2018-10-02 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107718576A (en) * | 2017-09-14 | 2018-02-23 | 湖北三江航天江北机械工程有限公司 | The ring piecemeal assembly method of insert nozzle larynx lining |
| CN107956597A (en) * | 2017-12-06 | 2018-04-24 | 内蒙动力机械研究所 | A kind of small-sized jet pipe to work long hours |
| CN109026445A (en) * | 2018-07-12 | 2018-12-18 | 上海新力动力设备研究所 | Multi nozzle solid attitude control engine blocking cover structure |
| CN109184959A (en) * | 2018-07-26 | 2019-01-11 | 西安航天动力技术研究所 | A kind of laminated cloth needle thorn larynx lining jet pipe |
| CN110080909A (en) * | 2018-12-28 | 2019-08-02 | 湖北航天技术研究院总体设计所 | A kind of jet pipe of solid propellant rocket |
| CN110805505A (en) * | 2019-11-15 | 2020-02-18 | 西安近代化学研究所 | Heat insulation layer assembly suitable for aluminum alloy long-tail nozzle solid rocket engine |
| CN112523902A (en) * | 2020-11-30 | 2021-03-19 | 内蒙动力机械研究所 | 3D printing-based composite material fixing shell for spray pipe |
| CN113323770A (en) * | 2021-05-18 | 2021-08-31 | 湖北三江航天江北机械工程有限公司 | Special device for precisely bonding throat linings of large solid rocket engine in blocks |
| CN113915029A (en) * | 2021-12-14 | 2022-01-11 | 星河动力(北京)空间科技有限公司 | Test device for nozzle throat lining of rocket engine |
| CN114876673A (en) * | 2022-04-12 | 2022-08-09 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and machining method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107718576A (en) * | 2017-09-14 | 2018-02-23 | 湖北三江航天江北机械工程有限公司 | The ring piecemeal assembly method of insert nozzle larynx lining |
| CN107956597A (en) * | 2017-12-06 | 2018-04-24 | 内蒙动力机械研究所 | A kind of small-sized jet pipe to work long hours |
| CN109026445A (en) * | 2018-07-12 | 2018-12-18 | 上海新力动力设备研究所 | Multi nozzle solid attitude control engine blocking cover structure |
| CN109184959A (en) * | 2018-07-26 | 2019-01-11 | 西安航天动力技术研究所 | A kind of laminated cloth needle thorn larynx lining jet pipe |
| CN109184959B (en) * | 2018-07-26 | 2021-04-20 | 西安航天动力技术研究所 | Weftless fabric needle-punched throat insert spray pipe |
| CN110080909B (en) * | 2018-12-28 | 2020-04-28 | 湖北航天技术研究院总体设计所 | Jet pipe of solid rocket engine |
| CN110080909A (en) * | 2018-12-28 | 2019-08-02 | 湖北航天技术研究院总体设计所 | A kind of jet pipe of solid propellant rocket |
| CN110805505A (en) * | 2019-11-15 | 2020-02-18 | 西安近代化学研究所 | Heat insulation layer assembly suitable for aluminum alloy long-tail nozzle solid rocket engine |
| CN112523902A (en) * | 2020-11-30 | 2021-03-19 | 内蒙动力机械研究所 | 3D printing-based composite material fixing shell for spray pipe |
| CN113323770A (en) * | 2021-05-18 | 2021-08-31 | 湖北三江航天江北机械工程有限公司 | Special device for precisely bonding throat linings of large solid rocket engine in blocks |
| CN113323770B (en) * | 2021-05-18 | 2022-08-09 | 湖北三江航天江北机械工程有限公司 | Special device for precisely bonding throat linings of large solid rocket engine in blocks |
| CN113915029A (en) * | 2021-12-14 | 2022-01-11 | 星河动力(北京)空间科技有限公司 | Test device for nozzle throat lining of rocket engine |
| CN114876673A (en) * | 2022-04-12 | 2022-08-09 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and machining method thereof |
| CN114876673B (en) * | 2022-04-12 | 2024-03-29 | 西安零壹空间科技有限公司 | Low-cost ablation-resistant embedded spray pipe and processing method thereof |
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|---|---|
| CN106762230B (en) | 2018-10-02 |
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