CN114043784B - Force-heat integrated light carrier rocket bottom partition plate structure - Google Patents

Force-heat integrated light carrier rocket bottom partition plate structure Download PDF

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CN114043784B
CN114043784B CN202111274763.1A CN202111274763A CN114043784B CN 114043784 B CN114043784 B CN 114043784B CN 202111274763 A CN202111274763 A CN 202111274763A CN 114043784 B CN114043784 B CN 114043784B
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panel
honeycomb core
sandwich
honeycomb
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CN114043784A (en
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蒋亮亮
李东
王珏
田建东
娄路亮
吴会强
骆洪志
章凌
王斌
黄蔚
王桂娇
吴浩
杨帆
李林生
芮兴
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Beijing Institute of Astronautical Systems Engineering
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    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
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    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • 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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
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    • B32—LAYERED PRODUCTS
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    • 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
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
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    • G06—COMPUTING; CALCULATING OR COUNTING
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    • G06F30/00—Computer-aided design [CAD]
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    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
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    • G06F—ELECTRIC DIGITAL DATA PROCESSING
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    • B32B2307/70—Other properties
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Abstract

A force-heat integrated light carrier rocket bottom partition plate structure comprises a three-sandwich two-honeycomb sandwich light structure and a low-density heat-proof layer; the three-sandwich two-honeycomb sandwich light structure sequentially comprises an upper panel, an upper honeycomb core, a middle panel, a lower honeycomb core and a lower panel from top to bottom; the upper layer honeycomb core, the middle layer honeycomb core, the lower layer honeycomb core and the lower panel are sequentially solidified and bonded, the height of the upper layer honeycomb core is the same as that of the lower layer honeycomb core, the thickness of the middle layer honeycomb core is not more than 2mm, and the low-density heat-resistant layer is coated below the lower panel of the force-heat integrated 'three-clamping-two' honeycomb sandwich light structure by adopting a spraying process. The invention does not need riveting or screwing process, has fewer connecting pieces, simple structural process flow and high structural efficiency. The whole structure has high bending rigidity.

Description

Force-heat integrated light carrier rocket bottom partition plate structure
Technical Field
The invention relates to a force-heat integrated light carrier rocket bottom partition plate structure, which can be used for a carrier rocket structure bearing force-heat load and belongs to the field of heat structure design.
Background
The carrier rocket bottom partition board is positioned at the bottom of the rocket tail section and is mainly used for protecting products such as an engine, a pipeline, an instrument cable and the like from being impacted by external air flow and thermal environment, and providing a good working environment for each system in the cabin. The rocket is subjected to larger thermal load and force load in the rocket flying process, and has strict requirements on deformation in design, the skin stringer, girder and heat-proof layer are the commonly adopted structural style of the carrier rocket at home and abroad at present. The traditional tail section structure has been applied for decades, and has mature process and reliable structure. Although the design requirements of heat resistance and rigidity can be met, the method has obvious defects that a large number of riveting or screwing processes are needed, and the manufacturing process is complex; secondly, under the condition of adopting a large amount of connecting pieces, the structure efficiency is lower.
The outer, upper and lower outer walls of the conventional honeycomb sandwich structure are made of thin skin materials with high rigidity, and the middle of the honeycomb sandwich structure is made of a low-density honeycomb structure with the thickness far larger than that of the skin. The structural form has the structural characteristic of great bending rigidity, and is widely applied to non-concentrated force rigidity design structures, such as fairings, effective load brackets and the like. The honeycomb in the honeycomb sandwich structure is in a hollow structure form, and has larger heat resistance naturally, so that the structure form has larger heat insulation application prospect. The structural form does not need riveting or screwing technology, and the connecting pieces are fewer.
However, as the diameter of the rocket increases, the span of the heat insulation bottom plate connected with the wall surface only at the edge increases, and the rigidity requirement of the heat insulation bottom plate is higher under the constraint of the deformation displacement requirement of the rated surface loading effect. The traditional single-layer honeycomb structure is limited by process limitation, and the maximum thickness of the honeycomb core is 60mm. This thickness level of honeycomb core stiffness has not met current design requirements.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides a force-heat integrated light carrier rocket bottom partition plate structure which does not need riveting or screwing technology, has fewer connecting pieces, simultaneously meets the current design requirements in terms of heat insulation and rigidity, has simple structural process flow and high structural efficiency, and realizes light weight.
The above object of the present invention is achieved by the following technical solutions:
a force-heat integrated light carrier rocket bottom partition plate structure comprises a three-sandwich two-honeycomb sandwich light structure and a low-density heat-proof layer;
the three-sandwich two-honeycomb sandwich light structure sequentially comprises an upper panel, an upper honeycomb core, a middle panel, a lower honeycomb core and a lower panel from top to bottom; the upper panel, the upper honeycomb core, the middle panel, the lower honeycomb core and the lower panel are sequentially solidified and bonded, the heights of the upper honeycomb core and the lower honeycomb core are the same, the thickness of the middle panel is not more than 2mm, and the total thickness of the three-sandwich two-honeycomb sandwich light structure is not more than 120mm;
The low-density heat-resistant layer is coated below the lower panel of the force-heat integrated 'three-clamping-two' honeycomb sandwich light structure by adopting a spraying process.
The thickness and material modulus of the upper and lower panels satisfy the following formula:
EUtU＝ELtL
Wherein: e U is the modulus of the upper panel, t U is the thickness of the upper panel, E L is the modulus of the lower panel, and t L is the thickness of the lower panel.
The total thickness of the "three-sandwich two" honeycomb sandwich lightweight structure is obtained iteratively by the following formula:
Wherein d is the center distance between the upper panel and the lower panel; r is the radius of the bottom baffle; μ is poisson's ratio of the upper and lower panels; q is the out-of-plane pressure borne by the bottom separator; σ U is the upper panel stress; σ L is the lower panel stress; delta is deflection of the center of the bottom partition plate and is determined by the design requirement of the bottom partition plate; K. v, lambda is a theoretical coefficient; g c is the shear modulus of the honeycomb core, and is obtained through theoretical calculation or test;
v=0 at the first iteration.
λ＝1-μ2。
The upper honeycomb core and the lower honeycomb core are made of the same material and are made of aluminum alloy or other light metals.
The upper honeycomb core and the lower honeycomb core are of porous thin-wall structures, and the cross sections of holes of the porous thin-wall structures are hexagonal.
The upper panel, the middle panel and the lower panel are polished and then are solidified and bonded with the adjacent honeycomb cores.
The upper panel, the middle panel and the lower panel are made of the same material and are one of carbon fiber reinforced composite materials, aramid fiber reinforced composite materials and high silica fiber reinforced composite materials.
Glue is filled in the upper honeycomb core and the lower honeycomb core, and after solidification, an insert is arranged in a glue filling area and used for fixing an instrument bracket.
Compared with the prior art, the invention has the following beneficial effects:
The invention adopts a three-clamping-two honeycomb sandwich light structure and a low-density heat-resistant layer to form a force-heat load integrated light carrier rocket bottom partition plate structure, and a riveting or screwing process is not needed, so that the connecting pieces are fewer, the structural process flow is simple, and the structural efficiency is high. The modulus of the upper panel, the middle panel and the lower panel is more than 70GPa, the light core material between the panels has the strength capable of resisting the design load of shearing, compression and stretching, and meanwhile, the upper panel and the lower panel with enough rigidity support the high modulus to keep a long distance, and the whole structure has high bending rigidity.
Drawings
FIG. 1 is a schematic diagram of a force-heat integrated light carrier rocket bottom partition plate;
FIG. 2 is a schematic diagram of a honeycomb sandwich panel core cell;
FIG. 3 is a schematic diagram of relevant dimensions of a force-heat integrated light carrier rocket bottom partition structure;
FIG. 4 is a three-dimensional schematic view of a force-heat integrated light carrier rocket bottom baffle structure;
wherein: 1-upper panel, 2-upper layer honeycomb core, 3-middle panel, 4-lower layer honeycomb core, 5-lower panel, 6-low density heat-proof layer.
Detailed Description
The invention is described in detail below with reference to the drawings and specific embodiments.
Based on the light-weight design target, the invention discloses a force-heat integrated three-clamp-two honeycomb sandwich light-weight structure, the outer surface of the structure is covered with a layer of low-density ablation material, the force-heat integrated design of the bottom partition plate structure of the tail section of the carrier rocket is realized, and finally the light-weight design target of the structure is realized. The tail section structure is first used in China.
Specifically, as shown in fig. 1, the force-heat integrated light carrier rocket bottom partition plate structure comprises a three-sandwich two-honeycomb sandwich light structure and a low-density heat-proof layer. As shown in fig. 1-4, the three-sandwich two-honeycomb sandwich light structure sequentially comprises an upper panel 1, an upper honeycomb core 2, a middle panel 3, a lower honeycomb core 4 and a lower panel 5 from top to bottom; the upper panel 1, the upper honeycomb core 2, the middle panel 3, the lower honeycomb core 4 and the lower panel 5 are sequentially solidified and bonded, the upper honeycomb core and the lower honeycomb core are the same in height, the thickness of the middle panel is not more than 2mm, the total thickness of the three-sandwich two-honeycomb sandwich light structure is not more than 120mm, and the low-density heat-resistant layer 6 is coated below the lower panel of the force-heat integrated three-sandwich two-honeycomb sandwich light structure by adopting a spraying process.
The upper and lower panel thicknesses and material moduli satisfy the following formulas:
EUtU＝ELtL
wherein:
E U -modulus of the upper panel;
t U —thickness of upper panel;
E L -modulus of the lower panel;
t L —thickness of lower panel;
the total thickness of the honeycomb sandwich panel, the thickness of the upper panel and the lower panel meet the following conditions:
wherein:
d-in fig. 3 d, panel center distance;
r-radius of bottom separator in FIG. 3 r;
μ -poisson ratio of the upper and lower panels;
Out-of-plane pressure experienced by the q-bottom separator;
sigma U -upper panel stress, taking a value slightly smaller than allowable stress;
Sigma L -lower panel stress, taking a value slightly smaller than allowable stress;
The deflection of the delta-bottom baffle at the center is determined by the design requirement of the bottom baffle;
k, V-theoretical coefficient;
Lambda-theoretical coefficient of 1-mu 2;
The shear modulus of the G c -honeycomb core can be obtained through theoretical calculation or test;
the thickness of the sandwich structure is iteratively designed by the above formula, assuming as a first approximation v=0.
The upper honeycomb core and the lower honeycomb core are made of the same material and are made of aluminum alloy or other light metals.
The upper honeycomb core and the lower honeycomb core are of porous thin-wall structures, and the cross sections of holes of the porous thin-wall structures are hexagonal.
The upper panel, the middle panel and the lower panel are polished and then are solidified and bonded with the adjacent honeycomb cores. The shearing strength of the connecting interface of the adhesive is more than 12MPa under the working temperature environment.
The upper panel, the middle panel and the lower panel are made of the same material and are one of carbon fiber reinforced composite materials, aramid fiber reinforced composite materials and high silica fiber reinforced composite materials. The modulus of the upper, middle and lower panels is greater than 70GPa.
Glue is filled in the upper honeycomb core and the lower honeycomb core, and after solidification, an insert is arranged in a glue filling area and used for fixing an instrument bracket.
The thickness of the low-density heat-proof layer is determined through thermal simulation analysis iteration, and the inner side temperature of the heat-proof layer is lower than 150 ℃.
Example 1
A power and heat integrated light carrier rocket bottom baffle structure, comprising:
(1) The three-sandwich-two honeycomb sandwich panel has the dimensions of 1.5mm of upper panel thickness, 50mm of upper honeycomb core thickness, 0.6mm of middle panel thickness, 50mm of lower honeycomb core thickness, 1.5mm of lower panel thickness and 4mm of low-density heat-resistant layer thickness, and is coated below the lower panel.
(2) The thickness of the upper panel and the lower panel is selected according to a design formula. The upper panel and the lower panel are made of carbon fiber reinforced composite materials, the laminated plate technology is adopted, the total thickness of the upper panel and the lower panel is 1.5mm, the thickness of the single-layer unidirectional plate for the upper panel or the lower panel is 0.15mm, 10 layers are added, and the layering angle is 90 degrees+/-45 degrees/0 degrees/45 degrees/90 degrees/45 degrees/0 degrees.
(3) The middle panel is made of carbon fiber reinforced composite material, the total thickness is 0.6mm, the thickness of the single-layer unidirectional plate is 0.15mm, the total number of the layers is 4, and the layering angle is 90 degrees/+/-45 degrees/0 degrees.
(4) The upper layer and the lower layer honeycomb core are made of aluminum alloy, the structure is a porous thin-wall structure, the cross section of each hole is hexagonal, as shown in figure 2, the side length of the cross section of each hole is 5mm, and the single-layer wall thickness t is 0.05mm.
(5) The low-density heat-proof layer is made of a low-density heat-insulating material TR42, and is coated below the lower panel by adopting a spraying process, and the thickness of the low-density heat-proof layer is selected according to a design formula.
The invention realizes the structural design under the heat prevention and strict displacement constraint of the structure, has higher bending rigidity of unit mass and simple process.
The design of the embodiment meets the rigidity requirement that the maximum deformation is not more than 60mm under the conditions of internal and external differential pressure of +/-15 kPa through a ground static test.
Through a heat-proof test, the embodiment meets the structural heat-proof requirement of the high heat flow of 550kW and 485s long-time 380kW of the instantaneous peak value of the bottom of the rocket, and realizes the lightweight design of the structure.
The embodiment adopts the tail section of the multilayer honeycomb sandwich structure, and the weight is reduced by more than 500kg compared with the traditional tail section structure, and the weight reduction effect is more than 30%.
What is not described in detail in the present specification belongs to the known technology of those skilled in the art.

Claims (6)

1. A power and heat integrated light carrier rocket bottom partition plate structure is characterized in that: comprises a three-sandwich two-honeycomb sandwich light structure and a low-density heat-proof layer;
the three-sandwich two-honeycomb sandwich light structure sequentially comprises an upper panel, an upper honeycomb core, a middle panel, a lower honeycomb core and a lower panel from top to bottom; the upper panel, the upper honeycomb core, the middle panel, the lower honeycomb core and the lower panel are sequentially solidified and bonded, the heights of the upper honeycomb core and the lower honeycomb core are the same, the thickness of the middle panel is not more than 2mm, and the total thickness of the three-sandwich two-honeycomb sandwich light structure is not more than 120mm;
The low-density heat-resistant layer is coated below the lower panel of the force-heat integrated 'three-clamp-two' honeycomb sandwich light structure by adopting a spraying process;
the thickness and material modulus of the upper and lower panels satisfy the following formula:
EUtU＝ELtL
wherein: e U is the modulus of the upper panel, t U is the thickness of the upper panel, E L is the modulus of the lower panel, and t L is the thickness of the lower panel;
the total thickness of the "three-sandwich two" honeycomb sandwich lightweight structure is obtained iteratively by the following formula:
Wherein d is the center distance between the upper panel and the lower panel; r is the radius of the bottom baffle; μ is poisson's ratio of the upper and lower panels; q is the out-of-plane pressure borne by the bottom separator; σ U is the upper panel stress; σ L is the lower panel stress; delta is deflection of the center of the bottom partition plate and is determined by the design requirement of the bottom partition plate; K. v, lambda is a theoretical coefficient; g c is the shear modulus of the honeycomb core, and is obtained through theoretical calculation or test;
V=0 at the first iterative calculation;
The upper panel, the middle panel and the lower panel are made of the same material and are one of carbon fiber reinforced composite materials, aramid fiber reinforced composite materials and high silica fiber reinforced composite materials, 10 layers are formed on the upper panel or the lower panel, and the layering angle is 90 degrees+/+/-45 degrees/0 degrees+/-45 degrees/90 degrees+/-45 degrees/0 degrees; the middle panel has 4 layers and the layering angle is 90 degrees/45 degrees/0 degrees.
2. A mechanothermal integrated light carrier rocket base bulkhead structure according to claim 1, wherein λ=1- μ 2.
3. A power and heat integrated light carrier rocket bottom partition structure according to claim 1, wherein: the upper honeycomb core and the lower honeycomb core are made of the same material and are made of aluminum alloy or other light metals.
4. A power and heat integrated light carrier rocket bottom partition structure according to claim 1, wherein: the upper honeycomb core and the lower honeycomb core are of porous thin-wall structures, and the cross sections of holes of the porous thin-wall structures are hexagonal.
5. A power and heat integrated light carrier rocket bottom partition structure according to claim 4, wherein: the upper panel, the middle panel and the lower panel are polished and then are solidified and bonded with the adjacent honeycomb cores.
6. A power and heat integrated light carrier rocket bottom partition structure according to claim 1, wherein: glue is filled in the upper honeycomb core and the lower honeycomb core, and after solidification, an insert is arranged in a glue filling area and used for fixing an instrument bracket.
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CN111696502A (en) * 2020-06-01 2020-09-22 西安交通大学 Underwater sound absorption metamaterial structure with damping lining and double-layer honeycomb perforated plate

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CN204076944U (en) * 2014-09-12 2015-01-07 雅港（嘉兴）复合材料有限公司 The special cellular board of a kind of many sandwich shelter
CN107953656A (en) * 2016-10-14 2018-04-24 深圳光启高等理工研究院 A kind of manufacture method of the honeycomb sandwich construction composite material with clamp area
CN106584993A (en) * 2016-12-08 2017-04-26 株洲时代新材料科技股份有限公司 Honeycomb sandwich plate, and high sound insulation method, making method and application thereof
CN111696502A (en) * 2020-06-01 2020-09-22 西安交通大学 Underwater sound absorption metamaterial structure with damping lining and double-layer honeycomb perforated plate

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