CN107702600B - A kind of compound thermal protection struc ture of Large Launch Vehicle cabin - Google Patents
A kind of compound thermal protection struc ture of Large Launch Vehicle cabin Download PDFInfo
- Publication number
- CN107702600B CN107702600B CN201710809825.1A CN201710809825A CN107702600B CN 107702600 B CN107702600 B CN 107702600B CN 201710809825 A CN201710809825 A CN 201710809825A CN 107702600 B CN107702600 B CN 107702600B
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- layer
- thermal protection
- struc ture
- launch vehicle
- cabin
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B21/00—Layered products comprising a layer of wood, e.g. wood board, veneer, wood particle board
- B32B21/04—Layered products comprising a layer of wood, e.g. wood board, veneer, wood particle board comprising wood as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B21/042—Layered products comprising a layer of wood, e.g. wood board, veneer, wood particle board comprising wood as the main or only constituent of a layer, which is next to another layer of the same or of a different material of wood
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B21/00—Layered products comprising a layer of wood, e.g. wood board, veneer, wood particle board
- B32B21/10—Next to a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/105—Ceramic fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/306—Resistant to heat
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/306—Resistant to heat
- B32B2307/3065—Flame resistant or retardant, fire resistant or retardant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
Landscapes
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Wood Science & Technology (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Laminated Bodies (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The present invention provides a kind of compound thermal protection struc ture of Large Launch Vehicle cabin, comprising: soft low density timber layer, with rocket cabin by pasting connection；High density cork layer, with the soft low density timber layer by pasting connection；Refractory ceramic fibre layer is pasted with the high density cork layer and is connected, and is connect by bolt with the rocket cabin on the splicing surface of refractory ceramic fibre layer.The compound thermal protection struc ture of Large Launch Vehicle cabin provided by the invention, it is carried out by the heat insulation material to three kinds of different thermal protective performances and density compound, it solves thousands of degrees Celsius of Large Launch Vehicle cabin of thermal environment protection question, while having reached the requirement of thermal protection struc ture lightweight and low cost.
Description
Technical field
The present invention relates to solar heat protection technical field, in particular to a kind of compound thermal protection struc ture of Large Launch Vehicle cabin.
Background technique
During carrier rocket flight, rocket motor chance generates high-temperature fuel gas, and high-temperature fuel gas passes through the shapes such as convection current, radiation
Formula is diffused into cabin surface, in order to guarantee that section structure is not ablated, and meanwhile control cabinet body internal temperature, rocket cabin outer surface
Thermal protection struc ture must be laid.Carrier rocket scale is bigger, and the high-temperature heat flux that engine generates is also bigger, to the performance of thermal protection struc ture
It is required that also higher.Mainly there are cork, rubber-based thermal protective coating etc. using thermal protection struc ture on country's carrier rocket at present.Single is soft
The small light weight and cost of timber structure density is low, but thermal protective performance is general, it is hard to meet thousands of degrees Celsius of Large Launch Vehicle of hot ring
Border requires.Rubber-based thermal protective coating is able to bear thousands of degrees Celsius of thermal environment requirement, but the big weight weight of density, at high cost, hardly possible
To meet the requirement of Large Launch Vehicle lightweight and low cost.
Summary of the invention
The purpose of the present invention is to provide a kind of compound thermal protection struc tures of Large Launch Vehicle cabin, to solve how to meet
Guarantee section structure not ablated problem when the thermal environment that thousands of degrees Celsius of Large Launch Vehicle requires.
In order to solve the above-mentioned technical problem, the technical scheme is that provide a kind of Large Launch Vehicle cabin compound
Thermal protection struc ture, comprising: soft low density timber layer, with rocket cabin by pasting connection；High density cork layer, with the soft low density
Timber layer is by pasting connection；Refractory ceramic fibre layer is pasted with the high density cork layer and is connected, and in refractory ceramic fibre
The splicing surface of layer is connect by bolt with the rocket cabin.
Further, rocket cabin surface is with projection, to the low-density cork for being located at projection region
Layer carries out aperture processing, and the thickness of the soft low density timber layer is adjusted according to projection height, makes the low-density cork
The outer surface that layer is bonded with the high density cork layer is smooth.
Further, the refractory ceramic fibre layer is the enhanced material of high temperature resistant stainless steel silk.
Further, for the rocket cabin of flat type, stainless steel is used on refractory ceramic fibre layer stitching portion surface
Plate is compressed.
Further, for the rocket cabin of outer stringer form, refractory ceramic fibre layer stitching portion surface using it is U-shaped not
Rust keeper plate of steel is compressed.
The compound thermal protection struc ture of Large Launch Vehicle cabin provided by the invention, by three kinds of different thermal protective performances and density
Heat insulation material carry out it is compound, solve thousands of degrees Celsius of Large Launch Vehicle cabin of thermal environment protection question, reach simultaneously
Thermal protection struc ture lightweight and the requirement of low cost.
Detailed description of the invention
Invention is described further with reference to the accompanying drawing:
Fig. 1 is the schematic diagram of the section structure of the compound thermal protection struc ture of Large Launch Vehicle cabin provided in an embodiment of the present invention；
Fig. 2 is the cross-section structure signal of the compound thermal protection struc ture of rocket cabin of flat type provided in an embodiment of the present invention
Figure；
Fig. 3 is that the outer surface structure of the compound thermal protection struc ture of rocket cabin of outer stringer form provided in an embodiment of the present invention shows
It is intended to；
Fig. 4 is the U-shaped stainless steel pressure of the compound thermal protection struc ture of rocket cabin of outer stringer form provided in an embodiment of the present invention
Hardened structure.
Specific embodiment
The compound thermal protection struc ture of Large Launch Vehicle cabin proposed by the present invention is made below in conjunction with the drawings and specific embodiments
It is further described.According to following explanation and claims, advantages and features of the invention will be become apparent from.It should be noted
It is that attached drawing is all made of very simplified form and using non-accurate ratio, only to facilitate, lucidly aid in illustrating this hair
The purpose of bright embodiment.
Core of the invention thought is, the compound thermal protection struc ture of Large Launch Vehicle cabin provided by the invention, by right
The heat insulation material progress of three kinds of different thermal protective performances and density is compound, solves thousands of degrees Celsius of Large Launch Vehicle cabin of heat
Environmental protection problem, while having reached the requirement of thermal protection struc ture lightweight and low cost.
Fig. 1 is the schematic diagram of the section structure of the compound thermal protection struc ture of Large Launch Vehicle cabin provided in an embodiment of the present invention.
Referring to Fig.1, the compound thermal protection struc ture of Large Launch Vehicle cabin, comprising: soft low density timber layer 11 passes through stickup with rocket cabin 10
Connection；High density cork layer 12, with the soft low density timber layer 11 by pasting connection；Refractory ceramic fibre layer 13, and it is described
High density cork layer 12 pastes connection, and passes through bolt and the rocket cabin on the splicing surface of refractory ceramic fibre layer 13
10 connections.
In embodiments of the present invention, soft low density timber layer 11 and rocket cabin 10 are by pasting connection, for rocket cabin
The projections such as 10 surface bolts, rivet carry out aperture processing, while soft low density to the soft low density timber layer 11 of protrusion object area
The thickness of timber layer 11 is adjusted according to projection height, guarantees the smooth no projection in 11 outer surface of soft low density timber layer, finally
Realize that thermal protection struc ture outer surface is flat and smooth.
Soft low density timber layer 11 and 12 main function of high density cork layer be it is heat-insulated, it is soft by low-density cork and high density
The chemical reactions such as the wooden pyrolyzing absorb amount of heat, and take away heat by volatilization, while low-density cork and high density are soft
The carburization zone formed after wood pyrolysis has effectively blocked external heat inwardly to transmit；13 main function of refractory ceramic fibre layer is heat-insulated
And anti-ablation, a part of heat, the carbonization of another aspect ceramic fiber cloth are on the one hand taken away by itself carbonization of ceramic fiber cloth
The inside delivery rate of external heat can be effectively reduced in structure afterwards, reduce the change of soft low density timber layer 11 and high density cork layer 12
Reaction rate is learned, while protecting the carburization zone structural intergrity after low-density cork and the pyrolysis of high density cork.
In embodiments of the present invention, refractory ceramic fibre layer 13 selects the enhanced product of high temperature resistant stainless steel silk, high temperature resistant
Stainless steel wire can effectively improve thermal protection struc ture and wash away and intensity under the conditions of thermal environment in high-speed flow.
Fig. 2 is the cross-section structure signal of the compound thermal protection struc ture of rocket cabin of flat type provided in an embodiment of the present invention
Figure.Referring to Fig. 2, for the rocket cabin of flat type, stainless steel flat plate is used on 13 stitching portion surface of refractory ceramic fibre layer
21 are compressed, to improve thermal protection struc ture connection reliability.
Fig. 3 is that the outer surface structure of the compound thermal protection struc ture of rocket cabin of outer stringer form provided in an embodiment of the present invention shows
It is intended to；Fig. 4 is the U-shaped stainless steel platen knot of the compound thermal protection struc ture of rocket cabin of outer stringer form provided in an embodiment of the present invention
Structure.Referring to Fig. 3 and Fig. 4, for the rocket cabin of outer stringer form, U is used on 13 stitching portion surface of refractory ceramic fibre layer
Type stainless steel platen 31 is compressed, to improve thermal protection struc ture connection reliability, U-shaped stainless steel platen 31 be located at outer stringer 32 it
Between.
Obviously, those skilled in the art can carry out various changes and deformation without departing from essence of the invention to the present invention
Mind and range.In this way, if these modifications and changes of the present invention belongs to the range of the claims in the present invention and its equivalent technologies
Within, then the present invention is also intended to include these modifications and variations.
Claims (5)
1. a kind of compound thermal protection struc ture of Large Launch Vehicle cabin characterized by comprising
Soft low density timber layer, with rocket cabin by pasting connection；
High density cork layer, with the soft low density timber layer by pasting connection；
Refractory ceramic fibre layer is pasted with the high density cork layer and is connected, and on the splicing surface of refractory ceramic fibre layer
It is connect by bolt with the rocket cabin；
Soft low density timber layer and high density cork layer main function be it is heat-insulated, pass through low-density cork and high density cork itself heat
Solution chemical reaction absorbs amount of heat, and takes away heat, while shape after low-density cork and the pyrolysis of high density cork by volatilization
At carburization zone effectively blocked external heat inwardly to transmit；
Refractory ceramic fibre layer main function is heat-insulated and anti-ablation, on the one hand takes away one by itself carbonization of ceramic fiber cloth
Partial heat, the structure after the carbonization of another aspect ceramic fiber cloth can be effectively reduced the inside delivery rate of external heat, reduce low
The chemical reaction rate of density cork layer and high density cork layer, while after protecting low-density cork and high density cork to be pyrolyzed
Carburization zone structural intergrity.
2. the compound thermal protection struc ture of Large Launch Vehicle cabin as described in claim 1, which is characterized in that the rocket cabin table
Face is with projection, carries out aperture processing, the soft low density timber layer to the soft low density timber layer for being located at projection region
Thickness according to projection height be adjusted, the outer surface for being bonded the soft low density timber layer with the high density cork layer
It is smooth.
3. the compound thermal protection struc ture of Large Launch Vehicle cabin as described in claim 1, which is characterized in that the refractory is fine
Dimension layer is the enhanced material of high temperature resistant stainless steel silk.
4. the compound thermal protection struc ture of Large Launch Vehicle cabin as described in claim 1, which is characterized in that for flat type
Rocket cabin is compressed on refractory ceramic fibre layer stitching portion surface using stainless steel flat plate.
5. the compound thermal protection struc ture of Large Launch Vehicle cabin as described in claim 1, which is characterized in that be directed to outer stringer form
Rocket cabin, compressed on refractory ceramic fibre layer stitching portion surface using U-shaped stainless steel platen.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710809825.1A CN107702600B (en) | 2017-09-11 | 2017-09-11 | A kind of compound thermal protection struc ture of Large Launch Vehicle cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710809825.1A CN107702600B (en) | 2017-09-11 | 2017-09-11 | A kind of compound thermal protection struc ture of Large Launch Vehicle cabin |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107702600A CN107702600A (en) | 2018-02-16 |
| CN107702600B true CN107702600B (en) | 2019-05-28 |
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| CN201710809825.1A Active CN107702600B (en) | 2017-09-11 | 2017-09-11 | A kind of compound thermal protection struc ture of Large Launch Vehicle cabin |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109855480B (en) * | 2019-04-02 | 2023-10-03 | 北京星际荣耀空间科技有限公司 | Solid carrier rocket sub-level recovery structure and ballistic trajectory-lifting type reentry spacecraft |
| CN110723275B (en) * | 2019-10-24 | 2021-08-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN112177697B (en) * | 2020-09-09 | 2022-02-22 | 西安交通大学 | Thermal protection coupling open Brayton power generation system based on thermal decomposition reaction |
| CN112829955B (en) * | 2021-03-03 | 2022-07-26 | 上海机电工程研究所 | Aircraft air inlet duct and cabin axial installation area heat seal structure |
| CN115234555A (en) * | 2022-06-23 | 2022-10-25 | 上海宇航系统工程研究所 | Preparation method for bonding cork on surface of large-diameter riveting cabin |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US4431697A (en) * | 1982-08-02 | 1984-02-14 | The United States Of America As Represented By The Secretary Of The Air Force | Laser hardened missile casing structure |
| FR2612280B1 (en) * | 1987-03-13 | 1989-06-30 | France Etat Armement | COATING FOR THERMAL PROTECTION OF A STRUCTURE SUBJECT TO CONDITIONS OF INTENSE THERMAL AGGRESSION |
| GB8821396D0 (en) * | 1988-09-13 | 1989-03-30 | Royal Ordnance Plc | Thermal insulators for rocket motors |
| FR2672961B1 (en) * | 1991-02-15 | 1993-09-03 | Delaporte Denisselle Ets | PLATE MATERIAL CAPABLE OF FORMING A THERMAL INSULATING BARRIER, FIRE PROTECTION WALL COMPRISING SUCH MATERIAL AND HOUSING COMPRISING SUCH A WALL. |
| JP3052644B2 (en) * | 1993-03-10 | 2000-06-19 | 日産自動車株式会社 | Thermal protection treatment method for aerodynamic heating |
| CN102704615A (en) * | 2012-06-07 | 2012-10-03 | 西安理工大学 | Square cabin composite plate |
| CN103287568B (en) * | 2013-05-27 | 2015-08-05 | 北京玻钢院复合材料有限公司 | A kind of high-speed aircraft anti-heat insulation structural of large area interlayer and forming method thereof |
| CN205997432U (en) * | 2016-06-17 | 2017-03-08 | 浙江鑫宙竹基复合材料科技有限公司 | Rocket composite material casing |
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