CN107702600A - A kind of compound thermal protection struc ture of Large Launch Vehicle nacelle - Google Patents
A kind of compound thermal protection struc ture of Large Launch Vehicle nacelle Download PDFInfo
- Publication number
- CN107702600A CN107702600A CN201710809825.1A CN201710809825A CN107702600A CN 107702600 A CN107702600 A CN 107702600A CN 201710809825 A CN201710809825 A CN 201710809825A CN 107702600 A CN107702600 A CN 107702600A
- Authority
- CN
- China
- Prior art keywords
- nacelle
- layer
- thermal protection
- struc ture
- launch vehicle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
Abstract
The present invention provides a kind of compound thermal protection struc ture of Large Launch Vehicle nacelle, including：Soft low density timber layer, connected with rocket nacelle by pasting；High density cork layer, connected with the soft low density timber layer by pasting；Refractory ceramic fibre layer, paste and connect with the high density cork layer, and be connected on the splicing surface of refractory ceramic fibre layer by bolt with the rocket nacelle.The compound thermal protection struc ture of Large Launch Vehicle nacelle provided by the invention, it is compound by being carried out to the heat insulation material of three kinds of different thermal protective performances and density, solve the thermal environment protection question of thousands of degrees Celsius of Large Launch Vehicle nacelle, while reached thermal protection struc ture lightweight and the requirement of low cost.
Description
Technical field
The present invention relates to solar heat protection technical field, more particularly to a kind of compound thermal protection struc ture of Large Launch Vehicle nacelle.
Background technology
During carrier rocket flight, rocket motor chance produces high-temperature fuel gas, and high-temperature fuel gas passes through the shapes such as convection current, radiation
Formula is diffused into nacelle surface, in order to ensure that section structure is not ablated, and meanwhile control cabinet body internal temperature, rocket nacelle outer surface
Thermal protection struc ture must be laid.Carrier rocket scale is bigger, and high-temperature heat flux is also bigger caused by engine, to the performance of thermal protection struc ture
It is it is required that also higher.Mainly there are cork, rubber-based thermal protective coating etc. using thermal protection struc ture on current domestic carrier rocket.Single is soft
Timber structure density it is small it is in light weight, cost is low, but thermal protective performance is general, it is hard to meet the hot ring of thousands of degrees Celsius of Large Launch Vehicle
Border requires.Rubber-based thermal protective coating can bear thousands of degrees Celsius of thermal environment requirement, but the big weight weight of density, cost are high, difficult
To meet Large Launch Vehicle lightweight and the requirement of low cost.
The content of the invention
It is an object of the invention to provide a kind of compound thermal protection struc ture of Large Launch Vehicle nacelle, to solve how to meet
Ensure the problem of section structure is not ablated during the thermal environment requirement that thousands of degrees Celsius of Large Launch Vehicle.
In order to solve the above-mentioned technical problem, the technical scheme is that：It is compound to provide a kind of Large Launch Vehicle nacelle
Thermal protection struc ture, including：Soft low density timber layer, connected with rocket nacelle by pasting；High density cork layer, with the soft low density
Timber layer is connected by pasting；Refractory ceramic fibre layer, paste and connect with the high density cork layer, and in refractory ceramic fibre
The splicing surface of layer is connected by bolt with the rocket nacelle.
Further, the rocket nacelle surface has ridge, is pointed to protrude the low-density cork of object area
Layer carries out perforate processing, and the thickness of the soft low density timber layer is highly adjusted according to ridge, 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 nacelle of flat type, stainless steel is used on refractory ceramic fibre layer stitching portion surface
Flat board is compressed.
Further, for the rocket nacelle 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 nacelle provided by the invention, by three kinds of different thermal protective performances and density
Heat insulation material carry out it is compound, solve the thermal environment protection question of thousands of degrees Celsius of Large Launch Vehicle nacelle, reach simultaneously
Thermal protection struc ture lightweight and the requirement of low cost.
Brief description of the drawings
Invention is described further below in conjunction with the accompanying drawings：
Fig. 1 is the cross-sectional view of the compound thermal protection struc ture of Large Launch Vehicle nacelle provided in an embodiment of the present invention；
Fig. 2 is the cross-sectional view of the compound thermal protection struc ture of rocket nacelle of flat type provided in an embodiment of the present invention；
Fig. 3 is the outer surface structure signal of the compound thermal protection struc ture of rocket nacelle of outer stringer form provided in an embodiment of the present invention
Figure；
Fig. 4 is the U-shaped stainless steel platen knot of the compound thermal protection struc ture of rocket nacelle of outer stringer form provided in an embodiment of the present invention
Structure.
Embodiment
The compound thermal protection struc ture of Large Launch Vehicle nacelle 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 become apparent from.It should be noted
It is that accompanying drawing uses using very simplified form and non-accurately ratio, only to convenience, lucidly aids in illustrating this hair
The purpose of bright embodiment.
The present invention core concept be, the compound thermal protection struc ture of Large Launch Vehicle nacelle provided by the invention, by right
Three kinds of different thermal protective performances and the progress of the heat insulation material of density are compound, solve the heat of thousands of degrees Celsius of Large Launch Vehicle nacelle
Environmental protection problem, while reached thermal protection struc ture lightweight and the requirement of low cost.
Fig. 1 is the cross-sectional view of the compound thermal protection struc ture of Large Launch Vehicle nacelle provided in an embodiment of the present invention.
Reference picture 1, the compound thermal protection struc ture of Large Launch Vehicle nacelle, including：Soft low density timber layer 11, pass through stickup with rocket nacelle 10
Connection；High density cork layer 12, connected with the soft low density timber layer 11 by pasting；Refractory ceramic fibre layer 13, it is and described
High density cork layer 12 pastes connection, and passes through bolt and the rocket nacelle on the splicing surface of refractory ceramic fibre layer 13
10 connections.
In embodiments of the present invention, soft low density timber layer 11 is connected with rocket nacelle 10 by pasting, for rocket nacelle
The ridges such as 10 surface bolts, rivet, perforate processing, while soft low density are carried out to the soft low density timber layer 11 for protruding object area
The thickness of timber layer 11 is highly adjusted according to ridge, ensures the smooth no ridge in outer surface of soft low density timber layer 11, finally
Realize thermal protection struc ture outer surface flat smooth.
Soft low density timber layer 11 and the main function of high density cork layer 12 be it is heat-insulated, it is soft by low-density cork and high density
The chemical reactions such as 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；The main function of refractory ceramic fibre layer 13 is heat-insulated
And anti-yaw damper, 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
Structure afterwards can effectively reduce the inside transfer rate of external heat, reduce the change of soft low density timber layer 11 and high density cork layer 12
Reaction rate is learned, while protects 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 be washed away and the intensity under the conditions of thermal environment in high velocity air.
Fig. 2 is the cross-section structure signal of the compound thermal protection struc ture of rocket nacelle of flat type provided in an embodiment of the present invention
Figure.Reference picture 2, for the rocket nacelle of flat type, stainless steel flat plate is used on the stitching portion surface of refractory ceramic fibre layer 13
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 nacelle 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 nacelle of outer stringer form provided in an embodiment of the present invention
Structure.Reference picture 3 and Fig. 4, for the rocket nacelle of outer stringer form, U is used on the stitching portion surface of refractory ceramic fibre layer 13
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 the essence of various changes and deformation without departing from the present invention to the present invention
God and scope.So, if these modifications and variations of the present invention belong to the scope of the claims in the present invention and its equivalent technologies
Within, then the present invention is also intended to comprising including these changes and modification.
Claims (5)
- A kind of 1. compound thermal protection struc ture of Large Launch Vehicle nacelle, it is characterised in that including：Soft low density timber layer, connected with rocket nacelle by pasting；High density cork layer, connected with the soft low density timber layer by pasting；Refractory ceramic fibre layer, paste and connect with the high density cork layer, and on the splicing surface of refractory ceramic fibre layer It is connected by bolt with the rocket nacelle.
- 2. the compound thermal protection struc ture of Large Launch Vehicle nacelle as claimed in claim 1, it is characterised in that the rocket nacelle table Face has ridge, and the soft low density timber layer for being pointed to protrude object area carries out perforate processing, the soft low density timber layer Thickness be highly adjusted according to ridge, the outer surface for making the soft low density timber layer be bonded with the high density cork layer It is smooth.
- 3. the compound thermal protection struc ture of Large Launch Vehicle nacelle as claimed in claim 1, it is characterised 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 nacelle as claimed in claim 1, it is characterised in that for flat type Rocket nacelle, 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 nacelle as claimed in claim 1, it is characterised in that for outer stringer form Rocket nacelle, 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 true CN107702600A (en) | 2018-02-16 |
| CN107702600B CN107702600B (en) | 2019-05-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109855480A (en) * | 2019-04-02 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Solid Launch Vehicle grade recovery structure and ballistic, trajectory-lift formula Reentry vehicle |
| CN110723275A (en) * | 2019-10-24 | 2020-01-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN112177697A (en) * | 2020-09-09 | 2021-01-05 | 西安交通大学 | Thermal protection coupling open Brayton power generation system based on thermal decomposition reaction |
| CN112829955A (en) * | 2021-03-03 | 2021-05-25 | 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 |
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| US5038561A (en) * | 1988-09-13 | 1991-08-13 | Royal Ordnance Plc | Thermal insulators for rocket motors |
| FR2672961A1 (en) * | 1991-02-15 | 1992-08-21 | Delaporte Denisselle Ets | Material in the form of a plate capable of forming a heat-insulating barrier, fire-protection wall including this material, and casing including such a wall |
| JPH06255599A (en) * | 1993-03-10 | 1994-09-13 | Nissan Motor Co Ltd | Thermal protective treatment method to aerodynamic heating |
| CN102704615A (en) * | 2012-06-07 | 2012-10-03 | 西安理工大学 | Square cabin composite plate |
| CN103287568A (en) * | 2013-05-27 | 2013-09-11 | 北京玻钢院复合材料有限公司 | High-speed aircraft large-area interlayer heat protection and insulation structure 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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|---|---|---|---|---|
| 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 |
| EP0283385A1 (en) * | 1987-03-13 | 1988-09-21 | ETAT-FRANCAIS représenté par le DELEGUE GENERAL POUR L'ARMEMENT (DPAG) | Covering for the thermal protection of a structure subject to intense thermal stresses |
| US5038561A (en) * | 1988-09-13 | 1991-08-13 | Royal Ordnance Plc | Thermal insulators for rocket motors |
| FR2672961A1 (en) * | 1991-02-15 | 1992-08-21 | Delaporte Denisselle Ets | Material in the form of a plate capable of forming a heat-insulating barrier, fire-protection wall including this material, and casing including such a wall |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109855480A (en) * | 2019-04-02 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Solid Launch Vehicle grade recovery structure and ballistic, trajectory-lift formula Reentry vehicle |
| 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 |
| CN110723275A (en) * | 2019-10-24 | 2020-01-24 | 湖北航天技术研究院总体设计所 | High-temperature heat-proof opening cover structure |
| CN112177697A (en) * | 2020-09-09 | 2021-01-05 | 西安交通大学 | Thermal protection coupling open Brayton power generation system based on thermal decomposition reaction |
| CN112829955A (en) * | 2021-03-03 | 2021-05-25 | 上海机电工程研究所 | Aircraft air inlet duct and cabin axial installation area heat seal structure |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN107702600B (en) | 2019-05-28 |
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