EP1120795A1 - Laminated lightweight radiation shielding materials - Google Patents
Laminated lightweight radiation shielding materials Download PDFInfo
- Publication number
- EP1120795A1 EP1120795A1 EP01300625A EP01300625A EP1120795A1 EP 1120795 A1 EP1120795 A1 EP 1120795A1 EP 01300625 A EP01300625 A EP 01300625A EP 01300625 A EP01300625 A EP 01300625A EP 1120795 A1 EP1120795 A1 EP 1120795A1
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- European Patent Office
- Prior art keywords
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- structure recited
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- radiation
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- 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
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- G—PHYSICS
- G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
- G21F—PROTECTION AGAINST X-RADIATION, GAMMA RADIATION, CORPUSCULAR RADIATION OR PARTICLE BOMBARDMENT; TREATING RADIOACTIVELY CONTAMINATED MATERIAL; DECONTAMINATION ARRANGEMENTS THEREFOR
- G21F1/00—Shielding characterised by the composition of the materials
- G21F1/12—Laminated shielding materials
- G21F1/125—Laminated shielding materials comprising metals
-
- G—PHYSICS
- G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
- G21F—PROTECTION AGAINST X-RADIATION, GAMMA RADIATION, CORPUSCULAR RADIATION OR PARTICLE BOMBARDMENT; TREATING RADIOACTIVELY CONTAMINATED MATERIAL; DECONTAMINATION ARRANGEMENTS THEREFOR
- G21F1/00—Shielding characterised by the composition of the materials
- G21F1/02—Selection of uniform shielding materials
- G21F1/10—Organic substances; Dispersions in organic carriers
- G21F1/103—Dispersions in organic carriers
- G21F1/106—Dispersions in organic carriers metallic dispersions
Definitions
- the present invention relates generally to radiation shielding materials, and more particularly, to improved laminated lightweight radiation shielding materials.
- laminated lightweight radiation shielding materials such as may be used in a spacecraft environment, that overcome limitations of conventional materials, and provide the opportunity for significant mass savings and/or increased reliability.
- a lightweight radiation shielding structure (10) comprising: a first layer (11) comprised of one or more materials having low atomic number/atomic weight ratio that preferentially attenuates electron and proton radiation, while possibly generating Bremsstrahlung radiation in the process; a second layer (12) comprised of one or more materials with high atomic number squared/atomic weight ratio that preferentially attenuates Bremsstrahlung radiation, while possibly generating photo-electrons in the process; and a third layer (13) comprised of one or more materials having low atomic number/atomic weight ratio that attenuates photo-electrons emitted from the second layer, as well as electrons and protons that get through the first and second layers.
- the present invention provides for a laminated material or structure that provides radiation shielding for spacecraft components in orbit against electron and proton radiation.
- the laminated material provides equivalent radiation shielding for spacecraft components in orbit against electron and proton radiation at a greatly reduced mass.
- the laminated material may be configured to provide greatly increased radiation shielding at equivalent mass.
- the laminated material or structure comprises three laminated layers.
- the first layer is made of one or more materials having a low Z/A (atomic number/atomic weight) ratio that preferentially attenuate electron and proton radiation, although they may generate Bremsstrahlung radiation in the process.
- the second layer is made of one or more materials with a high Z 2 /A (atomic number squared/atomic weight) ratio that preferentially attenuate Bremsstrahlung radiation, although they may generate photo-electrons in the process.
- the third layer is made of one or more materials having a low Z/A (atomic number/atomic weight) ratio that attenuate photo-electrons emitted from the second layer, as well as electrons and protons that pass through the first and second layers.
- the unique layered structure of the present invention sequentially attenuates electrons, protons, and secondarily generated radiation.
- the present invention minimizes mass while maximizing shielding and providing an optimum ratio range of shielding effectiveness per unit mass.
- the design of the laminated material takes into account the effects of thermal expansion mismatch between the layers, thus minimizing the risks of delamination and warpage.
- the present invention uses commonly available materials.
- the present invention is lower in mass than aluminum, for example.
- the present invention does not require special formulations of materials, such as the Physical Sciences design mentioned in the Background section.
- the present invention uses high atomic number material in the center for maximum efficacy.
- the present invention preferably uses a symmetrical design to minimize warpage, unlike the Composite Optics design mentioned in the Background section.
- Fig. 1 illustrates an exemplary laminated lightweight radiation shielding material 10 or structure 10 in accordance with the principles of the present invention.
- the laminated lightweight radiation shielding material 10 or structure 10 comprises three layers 11, 12, 13.
- the first layer 11 comprises one or more materials having a low Z/A (atomic number/atomic weight) ratio, such as boron, graphite, aramid, or other polymer-based fiber-reinforced non-metallic matrix composite materials.
- the materials forming the first layer 11 may be fabricated from commercially available composite materials, with no modification.
- the first layer may be comprised of sub-layers of differing low Z/A materials.
- the first layer 11 preferentially attenuates electron and proton radiation, but may generate Bremsstrahlung (secondary) radiation in the process.
- the second layer 12 comprises one or more materials with a high Z 2 /A (atomic number squared/atomic weight) ratio, such as gold, lead, silver, titanium, tantalum, or tungsten.
- the materials forming the second layer 12 may be fabricated from commercially available metal foils, for example.
- the second layer may be comprised of fiber-reinforced metallic or non-metallic matrix composite where the fibers have been coated with high Z 2 /A material, such as tantalum or tungsten.
- the second layer may be comprised of sub-layers of differing high Z 2 /A materials, although other materials may be between the sub-layers of high Z 2 /A materials to bond them together.
- the second layer 12 preferentially attenuates Bremsstrahlung radiation, but may generate photo-electrons in the process. It is preferred that the material forming the second layer 12 have low tensile modulus and low tensile strength, or a thermal expansion that approximates that of the first and third layers 11, 13 to minimize interlaminar stresses.
- the third layer 13 comprises one or more materials having a low Z/A (atomic number/atomic weight) ratio.
- the third layer 13 may be made of the same material as the first layer.
- the third layer may be comprised of sub-layers of differing low Z/A materials.
- the third layer 13 attenuates photo-electrons emitted from the second layer 12, as well as electrons and protons that get through the first and second layers.
- the thickness and materials properties of the third layer 13 are preferably, but not necessarily, the same as the thickness and materials properties of the first layer 11 to minimize warpage of the laminated lightweight radiation shielding material 10 or structure 10. Thermal expansion of the first and third layers 11, 13 may also be tailored to approximate that of the second layer to minimize warpage of the laminated material.
- the laminated radiation shielding material 10 or structure 10 may be fabricated using a hot press, an oven, or an autoclave. Layers and sub-layers of the laminated radiation shielding material 10 may be co-cured together or secondarily bonded together. Fiber fabrics preimpregnated with uncured non-metallic matrix may be used in the first and third layers 11, 13. The uncured non-metallic matrix may be used as and adhesive to bond to the second layer 12 during a co-cure process. If metal foils are to be used in the second layer 12, the surface of the metal foils must be prepared for enhanced adhesion to the adjacent layers of the laminated material. This preparation may be through abrasion, chemical etching, and/or application of primer. Fiber fabrics preimpregnated with uncured non-metallic matrix may be used in the second layer 12. In which case, it would be advantageous to co-cure the three layers 11, 12, 13 together at the same time.
- End covers for existing enclosures may easily be made from the laminated radiation shielding material 10 or structure 10 that is fabricated in planar form.
- the shielding material 10 may be molded into complex shapes using appropriate tooling. In such cases, all three layers 11, 12, 13 of the shielding material 10 conform to the contours of the complex shape, as is illustrated in Fig. 2.
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- Chemical & Material Sciences (AREA)
- Dispersion Chemistry (AREA)
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- High Energy & Nuclear Physics (AREA)
- Laminated Bodies (AREA)
Abstract
Laminated materials or structures that provide radiation shielding for
spacecraft components in an orbiting spacecraft against electron and proton radiation.
The laminated materials or structures have three laminated layers. The first layer (11)
is made of one or more materials having a low Z/A (atomic number/atomic weight)
ratio that preferentially attenuates electron and proton radiation, although they may
generate Bremsstrahlung radiation in the process. The second layer (12) is made of
one or more materials with a high Z2/A (atomic number squared/atomic weight) ratio
that preferentially attenuate Bremsstrahlung radiation, although the materials may
generate photo-electrons in the process. The third layer (13) is made of one or more
materials having a low Z/A (atomic number/atomic weight) ratio that attenuate photo-electrons
emitted from the second layer, as well as electrons and protons that pass
through the first and second layers.
Description
The present invention relates generally to radiation shielding materials, and
more particularly, to improved laminated lightweight radiation shielding materials.
The prevailing conventional solution for shielding electronic enclosures is to
increase wall thickness, typically aluminum, as necessary to achieve the required
shielding capability. Physical Sciences Inc. and Composite Optics, Inc. have
produced prototypes of laminated lightweight shielding material. Also, shielding
materials are disclosed in US Patent No. 5,324,952 and US Patent No. 4,833,334. US
Patent No. 5,324,952 discloses shielding that shields against neutrons, while US
Patent No. 4,833,334 discloses shielding that shields against x-rays. Neither patent is
particularly relevant to the present invention.
A technical paper written by B. D. Spieth et al., entitled "Shielding Electronics
Behind Composite Structures", Dec. 1998, mentions the use of a three-layer
composite structure, with tantalum as the center layer, for radiation shielding in
various orbits. The Spieth et al. paper discloses the use of a metal center layer and
shielding in geosynchronous orbit. This paper also indicates that the advantage of the
three layer structure is to minimize warpage. This paper does not disclose or suggest
anything about material selection (such as polymer outer layers or a high atomic
number/low modulus center layer) to optimize the shielding effectiveness. This paper
also does not disclose or suggest anything regarding minimizing the risk of
delamination due to thermal expansion mismatch between the outer layers and the
metal center layer.
Accordingly, it would be advantageous to have laminated lightweight radiation
shielding materials, such as may be used in a spacecraft environment, that overcome
limitations of conventional materials, and provide the opportunity for significant mass
savings and/or increased reliability.
According to the invention there is provided a lightweight radiation shielding
structure (10), comprising: a first layer (11) comprised of one or more materials
having low atomic number/atomic weight ratio that preferentially attenuates electron
and proton radiation, while possibly generating Bremsstrahlung radiation in the
process; a second layer (12) comprised of one or more materials with high atomic
number squared/atomic weight ratio that preferentially attenuates Bremsstrahlung
radiation, while possibly generating photo-electrons in the process; and a third layer
(13) comprised of one or more materials having low atomic number/atomic weight
ratio that attenuates photo-electrons emitted from the second layer, as well as
electrons and protons that get through the first and second layers.
The present invention provides for a laminated material or structure that
provides radiation shielding for spacecraft components in orbit against electron and
proton radiation. Relative to a material that is currently used by the assignee of the
present invention, the laminated material provides equivalent radiation shielding for
spacecraft components in orbit against electron and proton radiation at a greatly
reduced mass. Alternatively, the laminated material may be configured to provide
greatly increased radiation shielding at equivalent mass.
The laminated material or structure comprises three laminated layers. The
first layer is made of one or more materials having a low Z/A (atomic number/atomic
weight) ratio that preferentially attenuate electron and proton radiation, although they
may generate Bremsstrahlung radiation in the process. The second layer is made of
one or more materials with a high Z2/A (atomic number squared/atomic weight) ratio
that preferentially attenuate Bremsstrahlung radiation, although they may generate
photo-electrons in the process. The third layer is made of one or more materials
having a low Z/A (atomic number/atomic weight) ratio that attenuate photo-electrons
emitted from the second layer, as well as electrons and protons that pass through the
first and second layers.
The unique layered structure of the present invention sequentially attenuates
electrons, protons, and secondarily generated radiation. The present invention
minimizes mass while maximizing shielding and providing an optimum ratio range of
shielding effectiveness per unit mass. The design of the laminated material takes into
account the effects of thermal expansion mismatch between the layers, thus
minimizing the risks of delamination and warpage. The present invention uses
commonly available materials.
The present invention is lower in mass than aluminum, for example. The
present invention does not require special formulations of materials, such as the
Physical Sciences design mentioned in the Background section. The present
invention uses high atomic number material in the center for maximum efficacy. The
present invention preferably uses a symmetrical design to minimize warpage, unlike
the Composite Optics design mentioned in the Background section.
The various features and advantages of the present invention may be more
readily understood with reference to the following detailed description taken in
conjunction with the accompanying drawing figures, wherein like reference numerals
designate like structural elements, and in which:
Referring to the drawing figures, Fig. 1 illustrates an exemplary laminated
lightweight radiation shielding material 10 or structure 10 in accordance with the
principles of the present invention. The laminated lightweight radiation shielding
material 10 or structure 10 comprises three layers 11, 12, 13. The first layer 11
comprises one or more materials having a low Z/A (atomic number/atomic weight)
ratio, such as boron, graphite, aramid, or other polymer-based fiber-reinforced non-metallic
matrix composite materials. The materials forming the first layer 11 may be
fabricated from commercially available composite materials, with no modification.
The first layer may be comprised of sub-layers of differing low Z/A materials. The
first layer 11 preferentially attenuates electron and proton radiation, but may generate
Bremsstrahlung (secondary) radiation in the process.
The second layer 12 comprises one or more materials with a high Z2/A
(atomic number squared/atomic weight) ratio, such as gold, lead, silver, titanium,
tantalum, or tungsten. Thus, the materials forming the second layer 12 may be
fabricated from commercially available metal foils, for example. The second layer
may be comprised of fiber-reinforced metallic or non-metallic matrix composite
where the fibers have been coated with high Z2/A material, such as tantalum or
tungsten. The second layer may be comprised of sub-layers of differing high Z2/A
materials, although other materials may be between the sub-layers of high Z2/A
materials to bond them together. The second layer 12 preferentially attenuates
Bremsstrahlung radiation, but may generate photo-electrons in the process. It is
preferred that the material forming the second layer 12 have low tensile modulus and
low tensile strength, or a thermal expansion that approximates that of the first and
third layers 11, 13 to minimize interlaminar stresses.
The third layer 13 comprises one or more materials having a low Z/A (atomic
number/atomic weight) ratio. The third layer 13 may be made of the same material as
the first layer. The third layer may be comprised of sub-layers of differing low Z/A
materials. The third layer 13 attenuates photo-electrons emitted from the second layer
12, as well as electrons and protons that get through the first and second layers. The
thickness and materials properties of the third layer 13 are preferably, but not
necessarily, the same as the thickness and materials properties of the first layer 11 to
minimize warpage of the laminated lightweight radiation shielding material 10 or
structure 10. Thermal expansion of the first and third layers 11, 13 may also be
tailored to approximate that of the second layer to minimize warpage of the laminated
material.
The laminated radiation shielding material 10 or structure 10 may be
fabricated using a hot press, an oven, or an autoclave. Layers and sub-layers of the
laminated radiation shielding material 10 may be co-cured together or secondarily
bonded together. Fiber fabrics preimpregnated with uncured non-metallic matrix may
be used in the first and third layers 11, 13. The uncured non-metallic matrix may be
used as and adhesive to bond to the second layer 12 during a co-cure process. If
metal foils are to be used in the second layer 12, the surface of the metal foils must be
prepared for enhanced adhesion to the adjacent layers of the laminated material. This
preparation may be through abrasion, chemical etching, and/or application of primer.
Fiber fabrics preimpregnated with uncured non-metallic matrix may be used in the
second layer 12. In which case, it would be advantageous to co-cure the three layers
11, 12, 13 together at the same time.
End covers for existing enclosures may easily be made from the laminated
radiation shielding material 10 or structure 10 that is fabricated in planar form. In
addition, the shielding material 10 may be molded into complex shapes using
appropriate tooling. In such cases, all three layers 11, 12, 13 of the shielding material
10 conform to the contours of the complex shape, as is illustrated in Fig. 2.
Thus, laminated lightweight radiation shielding materials or structures have
been disclosed. It is to be understood that the described embodiments are merely
illustrative of some of the many specific embodiments that represent applications of
the principles of the present invention. Clearly, numerous and other arrangements
can be readily devised by those skilled in the art without departing from the scope of
the invention. Materials may be selected to accomplish the satisfaction of structural
requirements, and/or thermal requirements, and/or radiation shielding requirements,
or any combination of requirements.
Claims (22)
- A lightweight radiation shielding structure (10), comprising:a first layer (11) comprised of one or more materials having low atomic number/atomic weight ratio that preferentially attenuates electron and proton radiation, while possibly generating Bremsstrahlung radiation in the process;a second layer (12) comprised of one or more materials with high atomic number squared/atomic weight ratio that preferentially attenuates Bremsstrahlung radiation, while possibly generating photo-electrons in the process; anda third layer (13) comprised of one or more materials having low atomic number/atomic weight ratio that attenuates photo-electrons emitted from the second layer, as well as electrons and protons that get through the first and second layers.
- The structure recited in claim 1 wherein the first (11) and/or third (13) layer comprise boron fiber-reinforced non-metallic matrix composite material.
- The structure recited in claim 1 or 2 wherein the first (11) and/or third (13) layer comprise graphite fiber-reinforced non-metallic matrix composite material.
- The structure recited in any preceding claim wherein the first (11) and/or third (13) layer comprise high strength, high modulus, and/or high thermal conductivity graphite fiber-reinforced non-metallic matrix composite material.
- The structure recited in any preceding claim wherein the first (11) and/or third (13) layer comprise aramid fiber-reinforced non-metallic matrix composite material.
- The structure recited in any preceding claim wherein the first (11) and/or third (13) layer comprise a polymer-based fiber-reinforced non-metallic matrix composite material.
- The structure recited in claim 1 wherein the first layer (11) comprises sub-layers of differing low Z/A ratio materials.
- The structure recited in any preceding claim wherein the second layer (12) comprises gold.
- The structure recited in any of claims 1 to 7 wherein the second layer (12) comprises lead.
- The structure recited in any of claims 1 to 7 wherein the second layer (12) comprises silver.
- The structure recited in any of claims 1 to 7 wherein the second layer (12) comprises titanium.
- The structure recited in any of claims 1 to 7 wherein the second layer (12) comprises tantalum.
- The structure recited in any of claims 1 to 7 wherein the second layer (12) comprises tungsten.
- The structure recited in any of claims 1 to 7 wherein the second layer (12) comprises metal foil.
- The structure recited in any of claims 1 to 7 wherein the second layer (12) has low tensile modulus and low tensile strength to minimize interlaminar stresses.
- The structure recited in any claim preceding wherein the second layer (12) comprises sub-layers of differing high Z2/A ratio materials.
- The structure recited in any of claims 1 to 7 wherein the second layer (12) comprises fiber-reinforced metallic or non-metallic matrix composite whose fibers are coated with high Z2/A material.
- The structure recited in claim 17 wherein the high Z2/A material comprises tantalum or tungsten.
- The structure recited in any preceding claim wherein the second layer (12) has a thermal expansion that approximates that of the first and third layers (11,13) to minimize interlaminar stresses.
- The structure recited in any preceding claim wherein thermal expansion characteristics of the first and third layers (11,13) is tailored to approximate that of the second layer (12) to minimize interlaminar stresses.
- The structure recited in any preceding claim wherein the thickness and material properties of the third layer (13) are substantially the same as the thickness and material properties of the first layer (11) to minimize warpage.
- The structure recited in any preceding claim wherein the third layer comprises sub-layers of low Z/A materials.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US48963500A | 2000-01-24 | 2000-01-24 | |
US489635 | 2000-01-24 |
Publications (1)
Publication Number | Publication Date |
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EP1120795A1 true EP1120795A1 (en) | 2001-08-01 |
Family
ID=23944649
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01300625A Withdrawn EP1120795A1 (en) | 2000-01-24 | 2001-01-24 | Laminated lightweight radiation shielding materials |
Country Status (2)
Country | Link |
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EP (1) | EP1120795A1 (en) |
JP (1) | JP2001208891A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102479562A (en) * | 2010-11-25 | 2012-05-30 | 上海交通大学医学院附属第三人民医院 | Anti-radiation material |
CN103971776A (en) * | 2014-04-30 | 2014-08-06 | 大连理工高邮研究院有限公司 | Soft-carbon fiber-based heat insulation material for nuclear radiation protection and manufacturing method thereof |
WO2015113160A1 (en) * | 2014-01-30 | 2015-08-06 | Magellan Aerospace, Winnipeg A Division Of Magellan Aerospace Limited | Composite shielding structure for space applications |
US9640288B1 (en) | 2015-11-30 | 2017-05-02 | Space Systems/Loral, Llc | Flexible radiation shield |
CZ307676B6 (en) * | 2014-05-15 | 2019-02-13 | 5M S.R.O. | Composite structural panel for miniature quadratic cosmic satellite |
GB2593530A (en) * | 2020-03-27 | 2021-09-29 | Bae Systems Plc | Impact shield structures |
US11358375B1 (en) | 2020-11-04 | 2022-06-14 | Space Systems/Loral, Llc | Flexible micrometeoroid shield |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2509480A (en) * | 2012-07-06 | 2014-07-09 | Qioptiq Ltd | Radiation stable shield |
CN106601319B (en) * | 2016-12-09 | 2019-05-14 | 北京师范大学 | Graphene oxide-lead composite material, preparation method and the usage |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0242295A1 (en) * | 1986-04-16 | 1987-10-21 | AEROSPATIALE Société Nationale Industrielle | X-ray shielded electronic circuit box |
US4923741A (en) * | 1988-06-30 | 1990-05-08 | The United States Of America As Represented By The Administrator, National Aeronautics And Space Administration | Hazards protection for space suits and spacecraft |
US5324952A (en) * | 1992-07-10 | 1994-06-28 | Ball Corporation | Radiation shielding for spacecraft components |
-
2000
- 2000-11-30 JP JP2000363979A patent/JP2001208891A/en active Pending
-
2001
- 2001-01-24 EP EP01300625A patent/EP1120795A1/en not_active Withdrawn
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0242295A1 (en) * | 1986-04-16 | 1987-10-21 | AEROSPATIALE Société Nationale Industrielle | X-ray shielded electronic circuit box |
US4923741A (en) * | 1988-06-30 | 1990-05-08 | The United States Of America As Represented By The Administrator, National Aeronautics And Space Administration | Hazards protection for space suits and spacecraft |
US5324952A (en) * | 1992-07-10 | 1994-06-28 | Ball Corporation | Radiation shielding for spacecraft components |
Non-Patent Citations (1)
Title |
---|
SPIETH B D ET AL: "Shielding electronics behind composite structures", 1998 IEEE NUCLEAR AND SPACE RADIATION EFFECTS CONFERENCE (NSREC'98), NEWPORT BEACH, CA, USA, 20-24 JULY 1998, vol. 45, no. 6, pt.1, IEEE Transactions on Nuclear Science, Dec. 1998, IEEE, USA, pages 2752 - 2757, XP002163551, ISSN: 0018-9499 * |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102479562A (en) * | 2010-11-25 | 2012-05-30 | 上海交通大学医学院附属第三人民医院 | Anti-radiation material |
CN102479562B (en) * | 2010-11-25 | 2016-05-11 | 上海交通大学医学院附属第三人民医院 | A kind of radiation proof material |
WO2015113160A1 (en) * | 2014-01-30 | 2015-08-06 | Magellan Aerospace, Winnipeg A Division Of Magellan Aerospace Limited | Composite shielding structure for space applications |
CN103971776A (en) * | 2014-04-30 | 2014-08-06 | 大连理工高邮研究院有限公司 | Soft-carbon fiber-based heat insulation material for nuclear radiation protection and manufacturing method thereof |
CZ307676B6 (en) * | 2014-05-15 | 2019-02-13 | 5M S.R.O. | Composite structural panel for miniature quadratic cosmic satellite |
US9640288B1 (en) | 2015-11-30 | 2017-05-02 | Space Systems/Loral, Llc | Flexible radiation shield |
GB2593530A (en) * | 2020-03-27 | 2021-09-29 | Bae Systems Plc | Impact shield structures |
US11358375B1 (en) | 2020-11-04 | 2022-06-14 | Space Systems/Loral, Llc | Flexible micrometeoroid shield |
Also Published As
Publication number | Publication date |
---|---|
JP2001208891A (en) | 2001-08-03 |
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