WO2023249573A1 - Radiation barrier - Google Patents

Radiation barrier Download PDF

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Publication number
WO2023249573A1
WO2023249573A1 PCT/TR2022/050625 TR2022050625W WO2023249573A1 WO 2023249573 A1 WO2023249573 A1 WO 2023249573A1 TR 2022050625 W TR2022050625 W TR 2022050625W WO 2023249573 A1 WO2023249573 A1 WO 2023249573A1
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WO
WIPO (PCT)
Prior art keywords
radiation
sun
solar
layer
particles
Prior art date
Application number
PCT/TR2022/050625
Other languages
French (fr)
Inventor
Sinan KARTAL
Türkay SİCİM
Ercan Engi̇n
Original Assignee
Kartal Sinan
Sicim Tuerkay
Engin Ercan
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Kartal Sinan, Sicim Tuerkay, Engin Ercan filed Critical Kartal Sinan
Priority to PCT/TR2022/050625 priority Critical patent/WO2023249573A1/en
Publication of WO2023249573A1 publication Critical patent/WO2023249573A1/en

Links

Classifications

    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • B64G1/443—Photovoltaic cell arrays
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/54—Protection against radiation
    • 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
    • G21F3/00—Shielding characterised by its physical form, e.g. granules, or shape of the material
    • 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—Synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/226—Special coatings for spacecraft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F24—HEATING; RANGES; VENTILATING
    • F24S—SOLAR HEAT COLLECTORS; SOLAR HEAT SYSTEMS
    • F24S20/00—Solar heat collectors specially adapted for particular uses or environments
    • F24S20/80—Airborne solar heat collector modules, e.g. inflatable structures

Definitions

  • the invention is related to the radiation-proof radiation barrier, which aims to reduce the radiation that may emanate from the Sun by being inserted between the Sun and the Mars, as well as aiming to achieve a healthier life with the modules to be inserted.
  • Radiological protection Radiation protection, sometimes also referred to as radiological protection, is defined by the International Atomic Energy Agency (IAEA) as "The protection of people from harmful effects of exposure to ionizing radiation, and the means for achieving this".
  • IAEA International Atomic Energy Agency
  • the IAEA also has also stated that “Radiation protection applies only to individuals. Whether this protection applies to non-human species and the environment is debatable”.
  • Ionizing radiation is used in industry and manufacturing of pharmaceuticals and poses a major health risk. It causes microscopic damage to living tissue, causing skin burns or radiation sickness (tissue or determinant effect) at high exposure levels. Cancer risk increases statistically in low exposures.
  • the basis of radiation protection is to reduce the exposure dose to which individuals are exposed.
  • IRPC International Committee on Radiation Protection
  • ICRU International Commission on Radiation Units and Measurements
  • Shielding comes from covering a reactor or other radioactive source with absorbing materials and reducing the radiation to a safe level for humans.
  • the usefulness of the biological shield used depends on the scattering and absorption cross-sectional area of the material.
  • Particle radiation consists of a stream of charged or neutral particles, including charged ions and subatomic elementary particles. These include solar wind, cosmic radiation, neutron flux within nuclear reactors .
  • Alpha particles are the least penetrating. Even the most energetic alpha particles can be stopped with a single sheet of paper.
  • Beta particles are more penetrating, but can still be absorbed by a few millimeters of aluminum . However, in a situation where high-energy beta particles are emitted, low atomic weight materials such as plastic, wood, water or acrylic glass should be used as shielding.
  • the solar wind is a plasma wave emanating from the Sun's upper atmosphere.
  • the vast majority are made up of electrons, protons and alpha particles with energies usually between 1.5 and 10 keV.
  • the density, temperature, and velocity of this particle stream vary with time and the longitude of the Sun. These particles can escape the Sun's gravity thanks to their high energies from the high temperature of the solar corona and the magnetic, electrical and electromagnetic phenomena they are exposed to.
  • the solar wind supersonically radiates outward, towards long distances filling the heliosphere, a bubble-like space of a huge volume surrounded by the interstellar matter.
  • auroras Northern and Southern lights
  • comets' plasma tails that are always outward from the Sun
  • geomagnetic storms that can deflect magnetic field lines and create strong currents in Earth's power grids.
  • the Sun's corona is a region where plasma is heated to over one million degrees Celsius.
  • the velocities of particles in the inner corona with respect to range and dispersion are described by the Maxwellian distribution .
  • the average velocity of these particles is approximately 145 km/sec and this speed is lower than the solar escape velocity which is 618 km/sec. But few particles reach the energy levels that enable them to go up to the escape velocity of 400 km/sec, which allows them to feed the solar winds.
  • electrons due to their much smaller mass, reach the escape velocity and create an electric field that accelerates the ions and charged atoms that are far from the Sun.
  • the radiation environment of the deep space is very different from that of the Earth's surface or the low Earth orbit , due to the very large fluxes of galactic cosmic rays, solar proton events (SPEs), and radiation belts.
  • SPEs solar proton events
  • Galactic cosmic rays generate a sustained dose of radiation within the Solar system (solar activity), which decreases as solar activity increases and increases as solar activity decreases.
  • the inner and outer radiation belts are two particle fields confined within the solar winds, which are subsequently accelerated by the earth's magnetic field through dynamic interactions. Although the radiation dose is always high, it can rise much more during the geomagnetic storms and secondary storms .
  • Solar proton events are the Sun's ejection of high-energy protons. They happen rarely and generate extremely high levels of radiation. Without thick shielding, SPEs are strong enough to result in severe radiation poisoning and death.
  • the gyro radius within the Earth's magnetic field is small enough to allow the rays to be able to be deflected from the Earth. Since missions beyond low Earth orbit are outside of geomagnetic field shielding, they are exposed to Van Allen radiation belts . Therefore, on missions, they must be shielded from exposure to cosmic rays, Van Allen radiation, or solar eruptions.
  • the region between the distances of two and four radii from the Sun lies between the two radiation belts and is sometimes called the "safe zone".
  • the interplanetary magnetic field also deflects cosmic rays.
  • the cosmic ray flux and solar cycle in the heliosphere are inversely proportional.
  • NASA scientists said in a statement that there may be a large amount of radiation hazard during the possible manned mission to Mars , and that this radiation stems from the energetic particle radiation detected by the radiation assessment detector (RAD) located at the Mars Science Laboratory .
  • RAD radiation assessment detector
  • the deployed electromagnetic radiation deflector shield may include a power source and an electromagnet configured to generate a magnetic field to deflect the radiation.
  • the deployed electromagnetic radiation deflector shield is emplaced away from either the spacecraft or the base station to minimize the effect of the magnetic field on one of the two, i.e. either the spacecraft or the base station”.
  • the present invention relates to the radiation-proof radiation barrier, which aims to reduce the radiation that may emanate from the Sun by being inserted between the Sun and the Mars as well as aiming to achieve a healthier life with the modules to be included.
  • the wings disclosed in the invention will be positioned between the Sun and Mars.
  • the wings disclosed in the invention will prevent the radiation emanating from the Sun and ensure that it does not reach the Earth.
  • the subject of the invention will prevent the passage of radiation by being mounted on the satellites and by covering the wing parts with the special fabrics as well as the solar panels located thereon that will be referred to in the detailed description.
  • the radiation barrier of the invention can be produced as larger and smaller, in different shapes, and different sizes and dimensions.
  • the invention is radiation-proof satellite wings, characterized in that they comprise thereon carbon fabric, magnesium oxide, lead, and on their top surface, a solar panel.
  • the fins are connected to the satellites by means of nuts, bolts or any other fasteners.
  • the energy needed by the satellite is provided by these solar panels.
  • the solar panel has a thickness of preferably 1 .5 mm, carbon fabric a thickness of preferably 0.1-5 mm, lead a thickness of preferably 0.1-5 mm, and magnesium oxide a thickness of preferably 0.1-5 mm.
  • carbon fabric is the carbon fabric used in document with the application no. PCT/TR2021/050875. Applicants will use the carbon fabric of their application as a layer herein.

Abstract

The invention is related to the radiation-proof radiation barrier, which aims to reduce the radiation that may emanate from the Sun by being inserted between the Sun and the Mars, as well as aiming to achieve a healthier life with the modules to be inserted.

Description

RADIATION BARRIER
TECHNICAL FIELD
The invention is related to the radiation-proof radiation barrier, which aims to reduce the radiation that may emanate from the Sun by being inserted between the Sun and the Mars, as well as aiming to achieve a healthier life with the modules to be inserted.
BACKGROUND ART
Radiation protection, sometimes also referred to as radiological protection, is defined by the International Atomic Energy Agency (IAEA) as "The protection of people from harmful effects of exposure to ionizing radiation, and the means for achieving this". The IAEA also has also stated that "Radiation protection applies only to individuals. Whether this protection applies to non-human species and the environment is debatable".
Ionizing radiation is used in industry and manufacturing of pharmaceuticals and poses a major health risk. It causes microscopic damage to living tissue, causing skin burns or radiation sickness (tissue or determinant effect) at high exposure levels. Cancer risk increases statistically in low exposures.
The basis of radiation protection is to reduce the exposure dose to which individuals are exposed. For radiation protection and dose measurement evaluations, the International Committee on Radiation Protection (IRPC) and the International Commission on Radiation Units and Measurements (ICRU) published their data and recommendations on the effects of radiation on the human body, and set regulatory and guiding limits.
There are three factors that determine the amount or dose of radiation received from a source. Radiation exposure is measured by a combination of these three factors: 1. Time: Reducing the radiation exposure time proportionally reduces the effective dose exposed to. One way of reducing radiation exposure by reducing the time is to improve worker training and shorten the time it takes to do a given job.
2. Distance: According to the inverse square law, increasing the distance decreases the dose of exposure. For example, using forceps instead of handling the source.
3. Shielding: The term "biological shield" comes from covering a reactor or other radioactive source with absorbing materials and reducing the radiation to a safe level for humans. The usefulness of the biological shield used depends on the scattering and absorption cross-sectional area of the material.
In radiation interaction with shielding, different types of ionizing radiation interact with different shielding material. The efficiency of the shielding depends on the material used and the power to stop the radiation particles which are dependent on the energy of the radiation.
Particle radiation consists of a stream of charged or neutral particles, including charged ions and subatomic elementary particles. These include solar wind, cosmic radiation, neutron flux within nuclear reactors .
• Alpha particles (helium nuclei) are the least penetrating. Even the most energetic alpha particles can be stopped with a single sheet of paper.
• Beta particles (electrons) are more penetrating, but can still be absorbed by a few millimeters of aluminum . However, in a situation where high-energy beta particles are emitted, low atomic weight materials such as plastic, wood, water or acrylic glass should be used as shielding.
• Neutron radiation cannot be absorbed as easily as charged particle radiations, which makes it very penetrating. Neutrons are absorbed by atomic nuclei in nuclear reactions. This poses a secondary radiation hazard, because the absorbing core is unstable as it transforms into the heavier isotope. • Cosmic radiation is not a general concern as the Earth's atmosphere absorbs it and the magnetosphere acts as a shield against it, but it poses a problem for satellites and astronauts anyway. Those who frequently escape from the atmosphere also pose a minor risk. Cosmic radiation has very high energy and is very penetrating.
The solar wind is a plasma wave emanating from the Sun's upper atmosphere. The vast majority are made up of electrons, protons and alpha particles with energies usually between 1.5 and 10 keV. The density, temperature, and velocity of this particle stream vary with time and the longitude of the Sun. These particles can escape the Sun's gravity thanks to their high energies from the high temperature of the solar corona and the magnetic, electrical and electromagnetic phenomena they are exposed to.
The solar wind supersonically radiates outward, towards long distances filling the heliosphere, a bubble-like space of a huge volume surrounded by the interstellar matter. Among other phenomena related to this subject are the auroras (Northern and Southern lights), comets' plasma tails that are always outward from the Sun, and geomagnetic storms that can deflect magnetic field lines and create strong currents in Earth's power grids.
While older models conceived for solar winds mainly used heat energy to accelerate materials, by the 1960s it was clear that thermal acceleration was not the only cause of the solar winds' high velocity. An additional unknown acceleration mechanism was required, and this acceleration was related to the magnetic fields in the Sun's atmosphere.
The Sun's corona, or its expanded outer layer, is a region where plasma is heated to over one million degrees Celsius. As a result of thermal collisions, the velocities of particles in the inner corona with respect to range and dispersion are described by the Maxwellian distribution . The average velocity of these particles is approximately 145 km/sec and this speed is lower than the solar escape velocity which is 618 km/sec. But few particles reach the energy levels that enable them to go up to the escape velocity of 400 km/sec, which allows them to feed the solar winds. At the same temperature, electrons, due to their much smaller mass, reach the escape velocity and create an electric field that accelerates the ions and charged atoms that are far from the Sun.
The sum of the particles carried from the Sun by the solar wind is approximately 1.3xl036per second. Therefore, the total mass loss per year is approximately (2-3) x10 ’14 solar masses [19] or one billion kilograms per second. This equates to a loss of mass equal to the mass of the Earth every 150 million years. [20] However, there has been a loss of only 0.01 % due to the solar winds. [21] Other stars have much stronger stellar winds, and these winds cause much more considerable loss of mass.
Over the Sun's lifetime, interactions of the Sun's surface layers with escaping solar winds markedly reduced its surface rotation rate. Along with the Sun's radiation, the wind has been blamed for comet tails. The solar winds caused fluctuations in the enormous radio waves observed on Earth by the effect of the interplanetary scintillation.
The radiation environment of the deep space is very different from that of the Earth's surface or the low Earth orbit , due to the very large fluxes of galactic cosmic rays, solar proton events (SPEs), and radiation belts.
Galactic cosmic rays generate a sustained dose of radiation within the Solar system (solar activity), which decreases as solar activity increases and increases as solar activity decreases. The inner and outer radiation belts are two particle fields confined within the solar winds, which are subsequently accelerated by the earth's magnetic field through dynamic interactions. Although the radiation dose is always high, it can rise much more during the geomagnetic storms and secondary storms . Solar proton events are the Sun's ejection of high-energy protons. They happen rarely and generate extremely high levels of radiation. Without thick shielding, SPEs are strong enough to result in severe radiation poisoning and death.
Life on Earth is protected from Galactic cosmic rays by a number of factors: 1 . Since the Earth's atmosphere (GeV) does not transmit primary cosmic rays with energies below 1 gigaelectron volt, only secondary radiation can reach the surface. Secondary radiation, in addition to being attenuated by the absorption of its atmosphere, is also weakened by the in-flight decay of particles such as muons. Particularly, particles entering from directions close to the horizon are attenuated. The fact that the world population is exposed to cosmic radiation by, on average, only 0.4% Millisievert (mSv) is due to atmospheric shielding (excluding other radiation exposures such as inhaled radon). At an altitude of 12 km, above most of the atmospheric shielding, the annual amount of radiation varies according to solar maximum and minimum conditions, with 20 mSv at the equator and 50-120 mSv at the poles.
2. Except for very high energy galactic cosmic rays, the gyro radius within the Earth's magnetic field is small enough to allow the rays to be able to be deflected from the Earth. Since missions beyond low Earth orbit are outside of geomagnetic field shielding, they are exposed to Van Allen radiation belts . Therefore, on missions, they must be shielded from exposure to cosmic rays, Van Allen radiation, or solar eruptions. The region between the distances of two and four radii from the Sun lies between the two radiation belts and is sometimes called the "safe zone".
3. Embedded in the solar, the interplanetary magnetic field also deflects cosmic rays. As a result, the cosmic ray flux and solar cycle in the heliosphere are inversely proportional.
Consequently, the energy input of GCRs into the atmosphere is negligible - i°-9th of S0|ar radiation, which is roughly equivalent to the sunlight.
From among the foregoing factors, all but the first are included in low orbital structures, such as the Space Shuttle and the International Space Station .The average annual radiation exposure on the ISS is 150 mSv, but the risk is minimized by frequent crew rotations. The average radiation exposure of astronauts working on Apollo and Skylab missions was in the range of1.2 mSv/day and 1.4 mSv/day. Since unlike near-earth asteroids or Mars missions, the mission times of Apollo and Skylab are shorter, their radiation exposure times are also less to the same extent. On May 31 , 2013, NASA scientists said in a statement that there may be a large amount of radiation hazard during the possible manned mission to Mars , and that this radiation stems from the energetic particle radiation detected by the radiation assessment detector (RAD) located at the Mars Science Laboratory .
In the prior art, there are numerous articles about the negative effects of these radiations on humans and other living beings. It has been observed that, as will be described below, the invention is not included on the satellite fins.
In the invention with the publication number US10583939B2, titled "Deployed electromagnetic radiation deflector shield (DERDS) which creates a zone of minimum radiation and magnetic/plasma effects for spacecraft and extra- planetary base station protection" of the prior art, "example aspects of a deployed electromagnetic radiation deflector shield assembly and a method for using a deployed electromagnetic radiation deflector shield" are disclosed. The deployed electromagnetic radiation deflector shield may include a power source and an electromagnet configured to generate a magnetic field to deflect the radiation. Here, it can be summarized as follows, the deployed electromagnetic radiation deflector shield is emplaced away from either the spacecraft or the base station to minimize the effect of the magnetic field on one of the two, i.e. either the spacecraft or the base station”.
In conclusion, the abovementioned shortcomings and the inadequacy of the current practice entail an improvement in the respective technical field. Thus, there is a need for an invention to overcome the described problems.
DESCRIPTION OF THE INVENTION
For the purpose of eliminating the shortcomings mentioned above and introducing new advantages to the technical field, the present invention relates to the radiation-proof radiation barrier, which aims to reduce the radiation that may emanate from the Sun by being inserted between the Sun and the Mars as well as aiming to achieve a healthier life with the modules to be included. The wings disclosed in the invention will be positioned between the Sun and Mars.
The wings disclosed in the invention will prevent the radiation emanating from the Sun and ensure that it does not reach the Earth.
The subject of the invention will prevent the passage of radiation by being mounted on the satellites and by covering the wing parts with the special fabrics as well as the solar panels located thereon that will be referred to in the detailed description.
The radiation barrier of the invention can be produced as larger and smaller, in different shapes, and different sizes and dimensions.
DETAILED DESCRIPTION OF THE INVENTION
The preferred embodiment alternatives of the radiation barrier of the invention, which are mentioned in this detailed description, are only intended for providing a better understanding of the subject-matter, and should not be construed in any restrictive sense.
The invention is radiation-proof satellite wings, characterized in that they comprise thereon carbon fabric, magnesium oxide, lead, and on their top surface, a solar panel.
On radiation-proof satellite wings, there is a solar panel at the top, then a carbon fabric as the second layer, lead as the third layer, and lastly magnesium oxide as the fourth layer, and all of these layers are laminated to each other with epoxy, thus obtaining a 4-layer structure.
The fins are connected to the satellites by means of nuts, bolts or any other fasteners. The energy needed by the satellite is provided by these solar panels. The solar panel has a thickness of preferably 1 .5 mm, carbon fabric a thickness of preferably 0.1-5 mm, lead a thickness of preferably 0.1-5 mm, and magnesium oxide a thickness of preferably 0.1-5 mm.
With this application, the radiation problem will be solved.
What is meant by the carbon fabric is the carbon fabric used in document with the application no. PCT/TR2021/050875. Applicants will use the carbon fabric of their application as a layer herein.

Claims

CLAIMS - The invention relates to the radiation-proof radiation barrier, which aims to reduce the radiation that may emanate from the Sun by being inserted between the Sun and the Mars, as well as aiming to achieve a healthier life with the modules to be inserted, characterized in that it comprises as 1st layer, which is also its top layer, a solar panel, and as its 2nd layer the carbon fabric, as its 3rd layer the lead, and as its 4th layer, which is also its bottom layer, the magnesium oxide.
PCT/TR2022/050625 2022-06-21 2022-06-21 Radiation barrier WO2023249573A1 (en)

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120090658A1 (en) * 2010-10-19 2012-04-19 The Boeing Company Technological field
US20150048209A1 (en) * 2013-08-16 2015-02-19 Robert Hoyt Structures with Internal Microstructures to Provide Multifunctional Capabilities
EP3278971A1 (en) * 2016-08-02 2018-02-07 The Boeing Company Multi-functional composite structure for extreme environments
WO2022115614A1 (en) * 2020-11-25 2022-06-02 Cosmic Shielding Corporation Composite multifunctional structural material for high energetic charged particle radiation shielding

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120090658A1 (en) * 2010-10-19 2012-04-19 The Boeing Company Technological field
US20150048209A1 (en) * 2013-08-16 2015-02-19 Robert Hoyt Structures with Internal Microstructures to Provide Multifunctional Capabilities
EP3278971A1 (en) * 2016-08-02 2018-02-07 The Boeing Company Multi-functional composite structure for extreme environments
WO2022115614A1 (en) * 2020-11-25 2022-06-02 Cosmic Shielding Corporation Composite multifunctional structural material for high energetic charged particle radiation shielding

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
"Aerospace Materials and Applications", 1 January 2018, AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS, INC., Reston ,VA, ISBN: 978-1-62410-489-3, article FINCKENOR MIRIA M.: "Materials for Spacecraft", pages: 403 - 434, XP093126010, DOI: 10.2514/5.9781624104893.0403.0434 *
HANFI M.Y., SAYYED M.I., LACOMME E., AKKURT I., MAHMOUD K.A.: "The influence of MgO on the radiation protection and mechanical properties of tellurite glasses", NUCLEAR ENGINEERING AND TECHNOLOGY, KOREAN NUCLEAR SOCIETY, KP, vol. 53, no. 6, 1 June 2021 (2021-06-01), KP , pages 2000 - 2010, XP093126005, ISSN: 1738-5733, DOI: 10.1016/j.net.2020.12.012 *
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