CN115926463B - Dot matrix enhanced heat protection structure - Google Patents
Dot matrix enhanced heat protection structure Download PDFInfo
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- CN115926463B CN115926463B CN202211420816.0A CN202211420816A CN115926463B CN 115926463 B CN115926463 B CN 115926463B CN 202211420816 A CN202211420816 A CN 202211420816A CN 115926463 B CN115926463 B CN 115926463B
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Abstract
The invention discloses a dot matrix reinforced heat protection structure which comprises a reinforcing part and a filling part, wherein the reinforcing part is formed by connecting fibers according to a dot matrix structure, and the filling part is formed by filling pores of the reinforcing part with ablative materials and then solidifying. Because the density and the heat conductivity coefficient of the fiber material are smaller than those of the ablation material, the weight of the heat protection structure and the temperature of the back surface of the heat protection structure are reduced; meanwhile, under the constraint of the reinforcing part, the structural load is mainly borne by the reinforcing part, so that the bearing efficiency and the buffering and energy absorbing characteristics of the heat protection structure are improved; and when the fiber material of the lattice structure bears the shearing load, the fiber material not only acts together with the ablation material, but also protects the lattice structure and the ablation material from debonding due to the interfacial shearing between the lattice structure and the ablation material, so that the shearing resistance of the thermal protection structure is improved.
Description
Technical Field
The invention relates to the field of novel refractory materials, in particular to a dot matrix reinforced heat protection structure.
Background
The related art of the thermal protection structure to which the presently disclosed subject matter relates is disclosed in: the current status of light ablative materials for thermal protection is reported by university of Instructions of Harbin, development.
The density of the light-weight ablative material commonly adopted at present is mostly in the range of 0.2-0.9 g/cm < 3 >. The method comprises the steps of impregnating porous organic silicon resin or phenolic resin in a fibrous matrix of high-melting-point ceramic fibers, long fiber mats of carbon fibers, fine needle penetration or chopped fiber network frameworks and the like, wherein the composite material formed by the method is called a fibrous matrix impregnated light ablative material; the composite material formed by filling silicon rubber, organic silicon resin or phenolic resin in glass fiber/phenolic aldehyde, high silica/phenolic aldehyde or carbon/phenolic aldehyde honeycomb, and adding various functional fillers such as short-cut quartz fiber or short-cut carbon fiber, phenolic hollow microsphere, glass hollow microsphere and radiation agent in the filling phase is called honeycomb reinforced light ablation material.
The heat-proof outsole of the return cabin can face serious ablation problems, and threats such as ablation damage caused by hypersonic airflow shearing when reentry is performed, so that requirements on the multifunctional integration, the light weight and the reliability of the heat-proof outsole are provided.
The existing heat-resistant outsole structure often adopts a honeycomb reinforced ablation material structure form, so that pneumatic ablation is easy to occur, and the preparation process is complex and has high requirements on the ablation material.
Disclosure of Invention
The invention aims to provide a dot matrix reinforced thermal protection structure so as to solve the technical problem that pneumatic ablation is easy to occur when the existing light ablation material is sheared by hypersonic air flow.
In order to solve the technical problems, the invention specifically provides the following technical scheme:
a lattice enhanced thermal protection structure comprising: a reinforcing part formed by connecting fibers in a lattice structure; and the filling part is formed by filling the pores of the reinforcing part with an ablative material and then curing.
Further, the lattice structure comprises a plurality of contiguous cuboctahedra.
Further, the reinforcing part includes a plurality of bars having a length and 2 ends, the ends of the plurality of bars being connected to one node and being periodically arranged in space.
Further, the fiber is any one of ceramic fiber, carbon fiber and glass fiber.
Further, the ablative material is any one of silicone rubber, silicone resin, and phenolic resin.
Further, the ablative material is added with any one or a combination of a plurality of short-cut quartz fibers, short-cut carbon fibers, phenolic hollow microspheres, glass hollow microspheres and a radiation agent.
Compared with the prior art, the application has the following beneficial effects:
providing a dot matrix reinforced heat protection structure, wherein the heat protection structure is formed by filling ablation materials into reinforced parts formed by connecting fiber materials according to a dot matrix structure and then curing; because the density and the heat conductivity coefficient of the fiber material are smaller than those of the ablation material, the weight of the heat protection structure and the temperature of the back surface of the heat protection structure are reduced; meanwhile, under the constraint of the reinforcing part, the structural load is mainly borne by the reinforcing part, so that the bearing efficiency and the buffering and energy absorbing characteristics of the heat protection structure are improved; and when the fiber material of the lattice structure bears the shearing load, the fiber material not only acts together with the ablation material, but also protects the lattice structure and the ablation material from debonding due to the interfacial shearing between the lattice structure and the ablation material, so that the shearing resistance of the thermal protection structure is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It will be apparent to those of ordinary skill in the art that the drawings in the following description are exemplary only and that other implementations can be obtained from the extensions of the drawings provided without inventive effort.
FIG. 1 is a perspective view of an embodiment of the present invention, showing the filler in a transparent state;
FIG. 2 is an internal block diagram of an embodiment of the present invention;
FIG. 3 is a schematic structural view of a porous substrate according to an embodiment of the present invention;
FIG. 4 is a statistical plot of the deformation contrast of a lattice-enhanced ablative material and an ablative material of equal thickness under the same bending load of an embodiment of this invention;
FIG. 5 is a statistical plot of deformation and energy absorption characteristics of a lattice-enhanced ablative material and an ablative material of equal thickness under the same compressive load of an embodiment of the invention;
FIG. 6 is a statistical plot of the temperature field variation of the back surface of the lattice enhanced ablative material and the ablative material of equal thickness at the same heat flux density according to an embodiment of the present invention;
FIG. 7 is a statistical plot of shear strength changes for a lattice-enhanced ablative material and an ablative material at the same shear load for an embodiment of this invention;
reference numerals in the drawings are respectively as follows:
1-an enhancement section; 11-bar members; 12-node;
2-filling part.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1-3, embodiments of lattice enhanced thermal protection structures are provided to address the above-described technical problems.
The main structure of the reinforced plastic comprises a reinforced part 1 and a filling part 2, wherein the reinforced part 1 is formed by connecting fibers according to a lattice structure, and the filling part 2 is formed by filling pores of the reinforced part 1 with ablative materials and then curing.
The reinforcing part 1 of the lattice structure has the advantages of light weight, high porosity, high specific stiffness and high specific strength, and the replacement of a part of the filling part 2 with the reinforcing part 1 can reduce the weight of the filling part 2 while improving the anti-ablation performance of the filling part 2.
According to different service environments, the spatial lattice structure of the reinforcing part 1 can be designed, and different spatial lattice structure combination forms are utilized to obtain the thermal protection structure suitable for different environments.
The production method of the heat protection structure comprises the following steps:
the reinforcement 1 is formed by additive printing or by drilling rows of holes in 2 plates, stitching the fibers through the holes to form the reinforcement 1, and tensioning and straightening the fibers by increasing the distance between the 2 plates.
The mold is designed according to the shape of the thermal protection structure, the reinforcing part 1 is placed in the mold, then an ablative material is poured into the mold, and the ablative material fills the pores in the mold and the reinforcing part 1 and is solidified to form the filling part 2.
Further:
the lattice structure comprises a plurality of contiguous cuboctahedra.
Further:
the reinforcement 1 comprises a plurality of bars 11, the bars 11 having a length and 2 ends, the ends of a plurality of bars 11 being connected to a node 12 and being arranged periodically in space.
The rods 11 and the nodes 12 are periodically arranged in space, a plurality of rods 11 are connected with each other into a whole, so that the reinforcing part 1 is formed, and gaps among the rods 11 are the pores of the reinforcing part 1.
Optionally:
the bars 11 constitute several contiguous cuboctahedrons.
Optionally:
the fibers are any one of ceramic fibers, carbon fibers, and glass fibers.
In this embodiment, the material of the reinforcing portion 1 is high silica glass fiber.
The high silica glass fiber following the lattice structure is used as the reinforcing part 1, the porosity is high, the ablation material is easy to fill, the anti-ablation performance of the ablation material can be improved, the bearing performances of bending resistance, compression resistance and the like of the ablation material are improved, the energy absorption characteristic of the ablation material is improved, and the back surface temperature of the ablation material can be reduced.
Optionally:
the ablative material is any one of silicone rubber, silicone resin, and phenolic resin.
Further:
any one or a combination of a plurality of short-cut quartz fibers, short-cut carbon fibers, phenolic hollow microspheres, glass hollow microspheres and a radiation agent is added into the ablative material.
In this embodiment, the ablative material is carbon fiber reinforced phenyl silicone rubber.
Further:
as shown in fig. 4-7, the lattice-enhanced thermal protection structure is compared with an equal thickness of ablated material in this embodiment to conclude that the lattice-enhanced ablated material composite is superior to the ablated material.
Wherein:
fig. 4 and 5 show a comparison of deformation of lattice-enhanced ablated material and ablated material of equal thickness under the same bending load and compressive load conditions.
It can be seen that the load carrying capacity of the lattice-enhanced ablative material composite is much greater than that of a structure with only ablative material.
With the increase of the loading time, the deformation of the structure only containing the ablation material is larger and larger, and the deformation amplitude of the lattice reinforced ablation material composite structure is far smaller than that of the structure only containing the ablation material.
This is due to the skeletal support of the lattice structure.
Under the constraint of the lattice sandwich, the structural load is mainly borne by the lattice structure.
The mass of the lattice-enhanced ablative material composite is now slightly lower than the mass of the structure with only ablative material.
This is because the material density of the glass fibers is less than that of the silicone rubber-based ablative material, and as the relative density of the lattice structure increases, the load carrying capacity of the lattice-reinforced ablative material composite increases, but the quality will further decrease.
Therefore, the glass fiber lattice is used as a reinforcing structure of the ablation material, so that the structural quality can be reduced, and the structural bearing efficiency and the buffering and energy absorbing characteristics are obviously improved.
Fig. 6 shows the variation of the back surface temperature field for both the lattice enhanced ablated material and the ablated material of equal thickness at the same heat flux density.
It can be seen that the thermal insulation capability of the lattice enhanced ablative material composite is superior to that of the ablative material alone structure.
With increasing loading time, the temperature of the back surface of the structure and the lattice-reinforced ablative material composite of only ablative material is higher and higher, but the temperature rise of the lattice-reinforced ablative material composite is lower than that of the structure of only ablative material.
This is due to the insulating effect of the glass fiber lattice structure.
Because the heat conductivity of the high silica glass fiber is lower than that of the silicon rubber-based ablative material, the structure can not generate a thermal short-circuit effect under the action of the glass fiber lattice sandwich, and the temperature of the back surface is reduced.
It can be seen that the ablative insulating ability of the glass fiber lattice reinforced ablative material composite is superior to that of the ablative material alone under the same heat flux conditions.
Fig. 7 shows the change in shear strength of the lattice enhanced ablated material and ablated material at the same shear load.
It can be seen that the shear resistance of the lattice-enhanced ablative material composite is superior to that of the ablative material alone structure.
The specific calculation process is as follows: the bearing capacity of the ablative material under shear load is that of the lattice reinforced ablative material composite, and the shear strength is that of the lattice reinforced ablative material composite.
The shear strength of the composite consists of three parts: the shear strength of the ablated material, the shear strength of the lattice, and the shear strength caused by the interaction between the lattice and the ablated material.
Then the shear strength of the lattice enhanced ablative material composite can be expressed as:
τ c ＝τ am +τ l +τ i (1)
the interaction between the lattice and the ablated material is mainly caused by the interfacial bond strength between the lattice and the ablated material.
Then, according to the principle of composite interfacial failure, the shear strength caused by the interaction between the lattice and the ablated material can be expressed as:
the change of the carrying capacity of the composite of only the ablation material and the lattice reinforced ablation material under the same shear load condition is given by the formula (1) and the formula (2), and the ratio of the shear strength of the composite to the shear strength of the structure of only the ablation material is larger and larger along with the increase of the relative density of the lattice structure.
This is because the lattice acts as a reinforcement for the ablated material, acting not only with the ablated material when the structure is subjected to shear loads, but also the interfacial shear between the lattice and ablated material protects the lattice from debonding from the ablated material.
The above embodiments are only exemplary embodiments of the present invention and are not intended to limit the present invention, the scope of which is defined by the claims. Various modifications and equivalent arrangements of this invention will occur to those skilled in the art, and it is intended to be within the spirit and scope of the invention as defined by the appended claims.
Claims (5)
1. A lattice enhanced thermal protection structure, comprising:
a reinforcing part (1) formed by connecting fibers in a lattice structure;
a filling part (2) formed by filling the pores of the reinforcing part (1) with an ablative material and then curing;
the lattice structure comprises a plurality of contiguous cuboctahedra.
2. A dot matrix enhanced thermal protection structure according to claim 1,
the reinforcement (1) comprises a number of bars (11), the bars (11) having a length and 2 ends;
the ends of a plurality of rods (11) are connected to a node (12) and are arranged periodically in space.
3. A dot matrix enhanced thermal protection structure according to claim 1,
the fibers are any one of ceramic fibers, carbon fibers, and glass fibers.
4. A dot matrix enhanced thermal protection structure according to claim 1 or 3,
the ablative material is any one of silicone rubber, silicone resin, and phenolic resin.
5. The lattice enhanced thermal protection structure according to claim 4,
any one or a combination of a plurality of short-cut quartz fibers, short-cut carbon fibers, phenolic hollow microspheres, glass hollow microspheres and a radiation agent is added into the ablative material.
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| GB2103349A (en) * | 1981-05-26 | 1983-02-16 | Messerschmitt Boelkow Blohm | Combustion chamber |
| CN103087464A (en) * | 2013-02-01 | 2013-05-08 | 哈尔滨工业大学 | Preparation method of thermal-protection ablative material |
| CN109968757A (en) * | 2019-04-22 | 2019-07-05 | 中国人民解放军国防科技大学 | Ablation-resistant light heat-proof heat-insulation integrated composite material and preparation method thereof |
| CN111775511A (en) * | 2020-06-15 | 2020-10-16 | 中国科学院力学研究所 | Integrated bullet structure formed by composite filling dot matrix interlayer |
| CN113601922A (en) * | 2021-06-30 | 2021-11-05 | 上海宇航系统工程研究所 | Metal lattice reinforced ablation material sandwich plate structure |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11103296B2 (en) * | 2011-07-14 | 2021-08-31 | Afreeze Gmbh | Ablation applicator with a matrix filled with particles |
| AU2012282473B2 (en) * | 2011-07-14 | 2017-02-16 | Afreeze Gmbh | Ablation applicator with a matrix filled with particles |
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- 2022-11-11 CN CN202211420816.0A patent/CN115926463B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2103349A (en) * | 1981-05-26 | 1983-02-16 | Messerschmitt Boelkow Blohm | Combustion chamber |
| CN103087464A (en) * | 2013-02-01 | 2013-05-08 | 哈尔滨工业大学 | Preparation method of thermal-protection ablative material |
| CN109968757A (en) * | 2019-04-22 | 2019-07-05 | 中国人民解放军国防科技大学 | Ablation-resistant light heat-proof heat-insulation integrated composite material and preparation method thereof |
| CN111775511A (en) * | 2020-06-15 | 2020-10-16 | 中国科学院力学研究所 | Integrated bullet structure formed by composite filling dot matrix interlayer |
| CN113601922A (en) * | 2021-06-30 | 2021-11-05 | 上海宇航系统工程研究所 | Metal lattice reinforced ablation material sandwich plate structure |
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| 刚性短切碳纤维预制体和酚醛浸渍碳烧蚀体的制备及性能;杨威;贾献峰;乔文明;凌立成;龙东辉;;宇航材料工艺(第02期);第17-22页 * |
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