CN117963183B - Hemispherical bearing structure at bottom of microgravity test cabin and preparation method - Google Patents
Hemispherical bearing structure at bottom of microgravity test cabin and preparation method Download PDFInfo
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- CN117963183B CN117963183B CN202410383489.9A CN202410383489A CN117963183B CN 117963183 B CN117963183 B CN 117963183B CN 202410383489 A CN202410383489 A CN 202410383489A CN 117963183 B CN117963183 B CN 117963183B
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- 230000005486 microgravity Effects 0.000 title claims abstract description 22
- 238000002360 preparation method Methods 0.000 title claims abstract description 10
- 239000002131 composite material Substances 0.000 claims abstract description 31
- 239000010410 layer Substances 0.000 claims description 21
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 14
- 239000004917 carbon fiber Substances 0.000 claims description 14
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical group C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 14
- 239000004744 fabric Substances 0.000 claims description 8
- 238000000034 method Methods 0.000 claims description 8
- 239000003292 glue Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 239000002344 surface layer Substances 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 5
- 238000004088 simulation Methods 0.000 description 5
- 239000000178 monomer Substances 0.000 description 3
- 230000003014 reinforcing effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 210000002435 tendon Anatomy 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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Abstract
The invention relates to a hemispherical bearing structure at the bottom of a microgravity test cabin and a preparation method thereof, wherein the bearing structure comprises a large composite material bearing piece, and the large composite material bearing piece comprises a shell structure and a rib box type combined structure arranged on the bottom surface of the shell structure; the shell structure comprises a support leg structure and a conical surface shell body which is downwards arranged from the middle part of the shell structure, the rib box type combined structure consists of a plurality of modularized rib box type units, and the rib box type units are open box type structures; the rib box units are arranged at the bottom of the shell structure in an outward annular mode around the conical surface shell body and are opened, and the rib box type combined structure is integrally sleeved on the conical surface shell body. The rib box type units are independently formed and then assembled into a rib box type combined structure and a shell structure which are co-cured and integrally formed.
Description
Technical Field
The invention relates to the field of composite materials, in particular to a hemispherical bearing structure at the bottom of a microgravity test cabin and a preparation method thereof.
Background
The microgravity test cabin for aerospace has a capsule-shaped whole structure, a diameter of about 2 meters and a height of about 4.5 meters, and a lower cabin body of the microgravity test cabin is a hemispherical bearing structure, wherein the hemispherical bearing structure comprises a hemispherical shell and a large bearing piece arranged in the hemispherical shell, and particularly referring to fig. 1 and 2, the hemispherical bearing structure is required to bear a load of about 45 tons inside, and the load acts on three supporting feet, and the lower part of the hemispherical bearing structure is supported by a push rod. Because the large bearing piece is large in size and very large in bearing load, if a metal structure is adopted, on one hand, the weight is heavy, on the other hand, the machining and assembling complexity of parts is high, and the forming and assembling are difficult; if the composite material structure is adopted, the advantages of high bearing capacity, convenience in forming and the like can be utilized, and the effect on weight reduction is obvious. The conventional composite material bearing part mainly comprises an outer shell and a plurality of reinforcing ribs arranged on the bottom surface of the shell, wherein the reinforcing ribs and the outer shell are integrally cured and formed, a forming die is complex in integral curing, 8 sets of dies are needed to complete, particularly, the positioning of the web of the ribs is difficult, and risks such as deformation, adhesive shortage and the like are easy to occur at corner parts (see figure 3) of the ribs and the wall plates of the shell in the forming process. Therefore, in the design of large-scale carriers for microgravity test chambers, it has been difficult to use composite designs.
Disclosure of Invention
In view of the above, the invention provides a hemispherical bearing structure at the bottom of a microgravity test cabin and a preparation method thereof, which can solve the technical problems of the existing composite bearing structure.
The invention relates to a hemispherical bearing structure at the bottom of a microgravity test cabin, which comprises a large composite bearing piece, wherein the large composite bearing piece comprises a shell structure and a rib box type combined structure arranged on the bottom surface of the shell structure; the shell structure comprises a supporting leg structure and a conical surface shell body which is downwards arranged from the middle part of the shell structure, the conical surface shell body comprises a first conical surface shell body and a second conical surface shell body, the diameter of the first conical surface shell body is reduced from top to bottom, the diameter of the second conical surface shell body is increased from top to bottom, and the joint of the first conical surface shell body and the second conical surface shell body is in smooth transition; the rib box type combined structure comprises a plurality of main ribs and a plurality of auxiliary ribs, and the main ribs and the auxiliary ribs are radially arranged at intervals around the conical surface shell; the rib box type combined structure comprises a plurality of modularized rib box type units, and the rib box type units are of an open box type structure; the rib box units are arranged at the bottom of the shell structure in an outward annular mode around the conical surface shell body and are opened, and the rib box type combined structure is integrally sleeved on the conical surface shell body.
Through adopting above-mentioned technical scheme, design large-scale combined material carrier into shell structure and rib box type integrated configuration, again with rib box type integrated configuration design into a plurality of modularization rib box type unit, dispose the forming die of rib box body unit according to the modularization condition, alone shaping out rib box type unit, again adopt the co-curing mould integrated into one piece with shell structure combination, on the one hand avoided the problem such as the lacked that the corner position appears in the rib with shell structure integrated into one piece in the prior art, deformation, satisfy the materialization performance of bearing structure, on the other hand, compare the mould number that uses in the prior art greatly reduced, if need with shell structure integrated into one piece in the prior art, need all set up the mould in the both sides of every rib, if the rib has N, then the mould needs (2-1) N cover mould, and this product structural design, only need dispose the mould cover number according to the rib modularization condition, can accomplish the preparation of rib, very big reduction mould cover number, mould cost has been reduced.
In addition, the design of conical surface casing on the one hand can conveniently take shape, on the other hand is convenient for in the follow-up use, and the upper load concentrates and the diffusion distribution of composite structure mating surface load to lower push rod.
In another embodiment, the housing structure includes 3 radially disposed equal gauge feet; the rib box type combined structure comprises three first rib box type units and three second rib box type units, wherein the first rib box type units and the second rib box type units are arranged in the annular direction which surrounds the conical surface shell at the bottom of the shell structure and is outward in opening; the first rib box type unit and the second rib box type unit are symmetrical and adjacently arranged according to the symmetrical line of the shell structure.
By adopting the technical scheme, the rib box type combined structure is designed into three modularized first rib box type units and three modularized second rib box type units according to the symmetrical condition of the shell structure, and the first rib box type units and the second rib box type units are in mirror symmetry. The first rib box type unit and the second rib box type unit correspond to one set of die respectively, and preparation of the rib box type unit required by the rib box type combined structure can be completed.
The first rib box type unit comprises an upper top surface, a first conical surface, a second conical surface, an upper top surface, ribs I and ribs II; the upper top surface is connected with the bottom surface of the shell structure; the first conical surface and the second conical surface are connected with the conical surface shell of the shell structure in a matched manner; the rib I and the rib II are connected with the upper top surface, the first conical surface and the second conical surface; the second rib box type unit comprises an upper top surface ', a first conical surface ', a second conical surface ', ribs I ' and ribs II '; the upper top surface' is connected with the bottom surface of the shell structure; the first conical surface and the second conical surface are connected with the conical surface shell of the shell structure in a matched manner; the rib I ' and the rib II ' are connected with the upper top surface ', the first conical surface and the second conical surface; the rib I and the rib I' are adjacently arranged and are cured together for the second time to form a complete main rib; the rib II and the rib II' are adjacently arranged and secondarily co-cured to form a complete auxiliary rib.
Through adopting above-mentioned technical scheme, set up the rib into box form, on the one hand, compare prior art integrated into one piece, can the individual shaping, simple process, on the other hand can make things convenient for the rib to solidify with shell structure's connection, guarantees joint strength, has avoided rib position to appear deforming, lack of glue quality problem among the prior art, compares integrated into one piece rib among the prior art, and bulk connection strength is higher.
Further, the rib box type unit comprises an intermediate layer and an outer surface layer coated on the intermediate layer, wherein the intermediate layer is carbon fiber unidirectional tape prepreg, and the layering angles of the carbon fiber unidirectional tape prepreg sheets are 0 degree (+/-45 degrees) and 90 degrees; the outer surface layer is made of carbon fiber fabric prepreg, and the layering angle of the carbon fiber fabric prepreg is layering at 45 degrees.
The invention relates to a preparation method of a composite material microgravity test cabin bottom bearing structure, which comprises the steps of preparing a large composite material bearing piece, wherein the specific steps of preparing the large composite material bearing piece comprise:
S1, designing a large composite material bearing piece into a shell structure and a rib box type combined structure, wherein the rib box type combined structure is designed into a plurality of modularized rib box type units;
s2, independently forming a plurality of modularized rib box-shaped units;
S3, in the co-curing mold, finishing the layering of the material sheets of the shell structure according to the layering design, then arranging a plurality of modularized rib box type units radially around the conical surface of the shell, and then carrying out autoclave curing molding after carrying out bagging and vacuumizing on the whole co-curing mold.
By adopting the technical scheme, the forming die of the large composite bearing piece in the prior art is simplified, and importantly, the quality problems of glue shortage, deformation and the like occurring during integral forming of the reinforcing ribs and the shell structure in the existing production process are also avoided. In addition, in the process, the preformed rib box type unit can be equivalent to a part of a co-curing mold, and curing pressure is applied to the shell structure, so that the molding quality of the shell structure is ensured.
In another embodiment, when the rib box unit is prepared in the step S2, the material sheet layer of the middle layer is sequentially laid for a plurality of cycles according to angles of 0 °, 45 °, 90 °, and-45 °, then sequentially laid for a plurality of cycles according to angles of-45 °, and-45 °, then laid for a plurality of central layers according to 0 °, and then the central layers are used as symmetry axes to complete the rest of the laid layers; the outer surface carbon fiber fabric prepreg is paved in the 45-degree direction.
By adopting the technical scheme, the mechanical property of the rib box type unit can be ensured to be enough to meet the mechanical property requirement of a large-scale bearing piece.
In another embodiment, in step S3, the method further includes filling structural glue in corners of the rib-box-shaped monomer and the shell structure.
Through adopting above-mentioned technical scheme, guarantee integrated into one piece back, corner position does not have bridging and space, further ensures the joint strength of connecting rib box-type monomer and shell structure.
Compared with the prior art, the technical scheme of the invention has the following advantages:
1. The large composite material bearing piece is designed into the shell structure and the rib structure, the rib structure in the prior art is designed into the rib box type combined structure, the rib box type combined structure is further designed into a modularized rib box type unit and preformed, and the modularized rib box type unit and the rib box type combined structure are co-cured with the shell structure of the large composite material bearing piece, so that the quality problems of deformation, glue shortage and the like of rib parts in the prior art are avoided, and the molding of the rib structure of the large composite material bearing piece is realized;
2. Compared with the rib integrally formed in the prior art, the rib box type combined structure has obvious effect of improving the overall mechanical property of the bearing piece;
3. compared with the prior art that dies are required to be arranged on two sides of each rib, the rib box type structural design can be used for configuring the die number of corresponding sets according to the rib modularization condition, so that the die number is greatly reduced, and the die cost is reduced.
Drawings
In order to more clearly illustrate the detailed description or the prior art, the drawings required in the detailed description or the prior art will be briefly described, which are apparent to those skilled in the art that the present invention is embodied in some form and other drawings may be obtained from these drawings without inventive effort,
FIG. 1 is a schematic view of a hemispherical load-bearing structure at the bottom of a microgravity test chamber;
FIG. 2 is a schematic view of a prior art large carrier structure;
FIG. 3 is an enlarged view of the A-plane cross-section of FIG. 2;
FIG. 4 is a schematic view of a large composite load bearing member structure according to the present invention;
FIG. 5 is a schematic view of the structure of the housing;
FIG. 6 is a schematic view of a rib box type assembly structure;
FIG. 7 is a schematic view of a first rib box unit structure;
FIG. 8 is a schematic diagram of a second rib box unit structure;
FIG. 9 is a simulation schematic diagram of the vertical deformation of the lower cabin under the influence of overload under the suspension loop braking condition;
FIG. 10 is a schematic diagram of simulation of vertical deformation of the lower cabin under the influence of overload under the condition of the ejector rod braking condition;
FIG. 11 is a schematic diagram of simulation of vertical deformation of the lower cabin under the influence of overload under the condition of the brake bias load of the ejector rod;
FIG. 12 is a schematic diagram of simulation of vertical deformation of the lower cabin under the influence of overload under normal working conditions;
Wherein: 1. a housing structure, 11-leg; 12-cone shell; 121-a first cone housing; 122-a second conical shell; 2-rib box type combined structure; 21-main tendons; 22-auxiliary ribs; 23-a first rib box unit; 231-a first conical surface; 232-a second conical surface; 233-upper top surface; 234-rib I; 235-rib II; 24-a second rib box unit; 241-first conical surface ', 242-second conical surface ', 243-upper top surface ', 244-rib I ', 265-rib II '.
Detailed Description
The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making clear and defining the scope of the present invention.
In the description of the present invention, it should be noted that the positional or positional relationship indicated by the terms such as "center", "upper", "lower", "inner", "outer", etc. are based on the positional or positional relationship shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element in question must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The bottom bearing structure of the microgravity test cabin comprises a large composite bearing piece, referring to fig. 4-5, wherein the composite bearing piece comprises a shell structure 1 and a rib box type combined structure 2 arranged on the bottom surface of the shell structure 1; the shell structure 1 comprises three equal-specification supporting legs 11 which are arranged in a radial direction and a conical surface shell 12 which is downwards arranged from the middle part of the shell structure 1; the cone housing 12 includes a first cone housing 121 and a second cone housing 122; the diameter of the first conical surface shell 121 gradually decreases from top to bottom; the diameter of the second conical surface shell 122 gradually increases from top to bottom; the first conical surface shell 121 and the second conical surface shell 122 are in smooth transition at the joint; the rib box type combined structure 2 comprises three main ribs 21 and three auxiliary ribs 22, and the three main ribs 21 and the three auxiliary ribs 22 are arranged at radial intervals around the conical surface shell.
Referring to fig. 6-8, a conical surface matched with the conical surface shell 12 is arranged in the middle of the rib box type combined structure 2; the rib box type combined structure 2 comprises three modularized first rib box type units 23 and three second rib box type units 24, and the first rib box type units 23 and the second rib box type units 24 are of open box type structures; the first rib box-shaped unit 23 and the second rib box-shaped unit 24 are arranged at the bottom of the shell structure 1 around the outwards annular opening of the conical surface shell 12, and the first rib box-shaped unit 23 and the second rib box-shaped unit 24 are symmetrically and adjacently arranged according to the symmetry line of the shell structure 1; the first rib box unit 23 includes a first conical surface 231, a second conical surface 232, an upper top surface 233, ribs i 234, and ribs ii 235; the first conical surface 231 and the second conical surface 232 are connected with the conical surface shell 12 of the shell structure 1 in a matching way; the upper top surface 233 is connected with the bottom surface of the shell structure 1; the rib I234 and the rib II 235 are connected with the upper top surface 233, the first conical surface 231 and the second conical surface 232; the second rib box unit 24 includes a first conical surface 241, a second conical surface 242, an upper top surface 243, a rib I '244, and a rib II' 245; the rib I234 is arranged adjacent to the rib I' 244 and is cured twice together to form a complete main rib 21; the rib II 235 is disposed adjacent to the rib II' 245 and is secondarily co-cured to form a complete rib auxiliary rib 22.
Further, the first rib box type unit and the second rib box type unit comprise an intermediate layer and an outer surface layer coated on the intermediate layer, the intermediate layer is carbon fiber unidirectional tape prepreg, and the layering angles of the carbon fiber unidirectional tape prepreg are 0 degree, +/-45 degrees and 90 degrees; the outer surface layer is made of carbon fiber fabric prepreg, and the layering angle of the carbon fiber fabric prepreg is 45 degrees.
The preparation method of the composite material microgravity test cabin bottom bearing structure comprises the steps of preparing a large composite material bearing piece, wherein the specific steps of preparing the large composite material bearing piece comprise:
s1, designing a large composite material bearing piece into a shell structure 1 and a rib box type combined structure 2, wherein the rib box type combined structure 2 is designed into three modularized first rib box type units 23 and three modularized second rib box type units 24 along the symmetry line of the shell structure 1 according to the symmetry condition and the stress condition of the shell structure 1;
s2, independently forming three first rib box-shaped units 23 and three second rib box-shaped units 24;
S3, in a co-curing mold, finishing the layering of the material sheets of the shell structure 1 according to the layering design, arranging the first rib box type units 23 and the second rib box type units 24 around the conical surface shell 12 at intervals in a circumferential direction, and performing autoclave curing molding after bagging and vacuumizing.
Further, when the rib box unit is prepared in the step S2, the web laying angle of the middle layer is firstly sequentially laid for a plurality of cycles according to angles of 0 °, 45 °, 90 °, and-45 °, then sequentially laid for a plurality of cycles according to angles of-45 °, and-45 °, then laid for a plurality of central layers according to directions of 0 °, and then laid for the rest webs with the central layers as symmetry axes.
Further, in the step S3, the method further includes filling structural glue at a corner of the rib-box-shaped monomer and the shell structure.
Simulation tests of different working conditions are carried out on the bearing structure at the bottom of the microgravity test cabin. Referring to fig. 9, under the condition of the suspension loop braking, the maximum vertical deformation of the lower cabin body is 4.81mm under the influence of overload; referring to fig. 10, under the condition of the ejector rod braking, the maximum vertical deformation of the lower cabin body is 6.76mm under the influence of overload; referring to FIG. 11, the maximum vertical deformation of the lower cabin body is 11.07mm under the influence of overload under the condition of the brake unbalanced load condition of the ejector rod; referring to fig. 12, under the influence of overload, the maximum vertical deformation of the lower cabin body is 1.12mm under the normal working condition. The deformation meets the related stress requirements.
Claims (7)
1. The hemispherical bearing structure at the bottom of the microgravity test cabin comprises a large composite bearing piece and is characterized in that the large composite bearing piece comprises a shell structure and a rib box type combined structure arranged on the bottom surface of the shell structure; the shell structure comprises a supporting leg structure and a conical surface shell body which is downwards arranged from the middle part of the shell structure, the conical surface shell body comprises a first conical surface shell body and a second conical surface shell body, the diameter of the first conical surface shell body is reduced from top to bottom, the diameter of the second conical surface shell body is increased from top to bottom, and the joint of the first conical surface shell body and the second conical surface shell body is in smooth transition; the rib box type combined structure comprises a plurality of main ribs and a plurality of auxiliary ribs, and the main ribs and the auxiliary ribs are radially arranged at intervals around the conical surface shell; the rib box type combined structure consists of a plurality of modularized rib box type units, and the rib box type units are open box type structures; the rib box units are arranged at the bottom of the shell structure in an outward annular mode around the conical surface shell body and are opened, and the rib box type combined structure is integrally sleeved on the conical surface shell body.
2. A microgravity test bilge hemispherical load carrying structure according to claim 1 wherein the housing structure comprises 3 equally sized legs arranged radially and uniformly; the rib box type combined structure comprises three first rib box type units and three second rib box type units, wherein the first rib box type units and the second rib box type units are arranged in the annular direction which surrounds the conical surface shell at the bottom of the shell structure and is outward in opening; the first rib box type unit and the second rib box type unit are symmetrical and adjacently arranged according to the symmetry line of the shell structure.
3. The hemispherical load-carrying structure at the bottom of a microgravity test chamber according to claim 2, wherein the first rib box unit comprises an upper top surface, a first conical surface, a second conical surface, ribs i and ribs ii; the upper top surface is connected with the bottom surface of the shell structure; the first conical surface and the second conical surface are connected with the conical surface shell of the shell structure in a matched manner; the rib I and the rib II are connected with the upper top surface, the first conical surface and the second conical surface; the second rib box type unit comprises an upper top surface ', a first conical surface ', a second conical surface ', ribs I ' and ribs II '; the upper top surface' is connected with the bottom surface of the shell structure; the first conical surface and the second conical surface are connected with the conical surface shell of the shell structure in a matched manner; the rib I ' and the rib II ' are connected with the upper top surface ', the first conical surface and the second conical surface; the rib I and the rib I' are adjacently arranged and are cured together for the second time to form a complete main rib; the rib II and the rib II' are adjacently arranged and secondarily co-cured to form a complete auxiliary rib.
4. The hemispherical load-carrying structure at the bottom of a microgravity test cabin according to claim 1, wherein the rib box-shaped unit comprises an intermediate layer and an outer surface layer coated on the intermediate layer, the intermediate layer is carbon fiber unidirectional tape prepreg, and the layering angles of the carbon fiber unidirectional tape prepreg are 0 °, ±45°, 90 °; the outer surface layer is made of carbon fiber fabric prepreg, and the layering angle of the carbon fiber fabric prepreg is 45 degrees.
5. A method for preparing a microgravity test cabin bottom bearing structure based on the microgravity test cabin bottom hemispherical bearing structure of any one of claims 1-4, comprising the specific steps of preparing a large composite bearing, wherein the preparation of the large composite bearing comprises the following specific steps:
s1, designing a large composite material bearing piece into a shell structure and a rib box type combined structure, wherein the rib box type combined structure comprises a plurality of modularized rib box type units;
s2, independently forming a plurality of modularized rib box-shaped units;
s3, in a large composite material bearing piece co-curing mold, finishing material sheet layering of the shell structure according to layering design, arranging a plurality of modularized rib box units around the conical surface of the shell in a circumferential manner, and then bagging, vacuumizing and curing and molding in an autoclave.
6. The method for preparing the bottom bearing structure of the microgravity test cabin according to claim 5, wherein when the rib box type unit is prepared in the step S2, the material sheet of the middle layer is sequentially paved for a plurality of cycles according to angles of 0 °, 45 °,90 °, and-45 °, then sequentially paved for a plurality of cycles according to angles of-45 °, and-45 °, then paved for a plurality of layers according to 0 ° as a central layer, and then the central layer is used as a symmetry axis, so that the rest paving is completed; the outer surface carbon fiber fabric prepreg is paved in the 45-degree direction.
7. The method for manufacturing a bottom load bearing structure of a microgravity test chamber according to claim 5, wherein in step S3, structural glue is filled at the corners of the rib box unit and the shell structure.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106291513A (en) * | 2016-08-31 | 2017-01-04 | 武汉大学 | Laser satellite reflector array thermal vacuum test system and method |
| CN108725852A (en) * | 2018-05-30 | 2018-11-02 | 中国科学院空间应用工程与技术中心 | A kind of electromagnetism upthrow microgravity device, control method and system |
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| KR101421949B1 (en) * | 2014-05-12 | 2014-08-13 | 한국항공우주연구원 | System and operation method for Spherical magnetic levitation |
| WO2020096477A1 (en) * | 2018-11-09 | 2020-05-14 | Дмитрий Вячеславович ФЕДОТОВ | Thermodynamic test bench for simulating aerodynamic heating |
| CN209581942U (en) * | 2019-03-04 | 2019-11-05 | 南京晓庄学院 | A kind of three dimensional microgravity environment test device |
| CN112014081B (en) * | 2020-07-30 | 2021-06-25 | 北京航空航天大学 | Low-impact separation simulation experiment device and using method |
| CN114261540A (en) * | 2022-01-17 | 2022-04-01 | 江苏工程职业技术学院 | Kilometer-level space station |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106291513A (en) * | 2016-08-31 | 2017-01-04 | 武汉大学 | Laser satellite reflector array thermal vacuum test system and method |
| CN108725852A (en) * | 2018-05-30 | 2018-11-02 | 中国科学院空间应用工程与技术中心 | A kind of electromagnetism upthrow microgravity device, control method and system |
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