Multifunctional radiation-hardened laminate

An enclosed cylindrical symmetric composite structure from inboard to outboard comprising:

• a first layer of high modulus metal;
• a first fiber layer including a plurality of high modulus balanced and symmetric plys, each ply comprising carbon fiber or boron fiber, in a cyanate ester resin or epoxy resin matrix, the first of fiber layer adhesively attached to the first layer of metal;
• a second layer of high modulus metal adhesively attached to the first fiber layer and a second layer fiber layer;
• a second fiber layer including a plurality of high modulus balanced and symmetric plys, each ply comprising carbon fiber or boron fiber, in a cyanate ester resin or epoxy resin matrix;
• and
• a third layer of high modulus metal adhesively attached to the second fiber layer.

A rhomboid balanced and symmetric composite structure from inboard to outboard comprising:

• a first layer of high modulus metal;
• a first fiber layer including a plurality of high modulus balanced and symmetric plys, each ply comprising carbon fiber or boron fiber, in a cyanate ester resin or epoxy resin matrix, the first of fiber layer adhesively attached to the first layer of metal;
• a second layer of high modulus metal adhesively attached to the first fiber layer and a second layer fiber layer;
• a second fiber layer including a plurality of high modulus balanced and symmetric plys, each ply comprising carbon fiber or boron fiber, in a cyanate ester resin or epoxy resin matrix;
• and
• a third layer of high modulus metal adhesively attached to the second fiber layer.

A thin layered flat balanced and symmetric composite structure from inboard to outboard comprising:

• a first layer of high modulus metal;
• a first fiber layer including a plurality of high modulus balanced and symmetric plys, each ply comprising one ply of carbon fiber in a cyanate ester resin or epoxy resin matrix, the first fiber layer plurality of plys attached to the first metal layer and a second metal layer;
• a second layer of high modulus metal adhesively attached to the first fiber layer and a second fiber layer;
• a second fiber layer including a plurality of high modulus balanced and symmetric plys, each ply comprising one ply of boron fiber or commingled boron fiber and carbon fiber, each ply in cyanate ester resin or epoxy resin matrix adhesively attached to the second and a third metal layer of high modulus metal;
• a third layer of high modulus metal adhesively attached to the second fiber layer plurality of plys and a third fiber layer;
• a third fiber layer including a plurality of plys of high modulus balanced and symmetric plys, each ply comprising one of carbon fiber in a cyanate ester resin or epoxy resin matrix, adhesively attached to the third and a forth metal layer;
• and
• a fourth layer of high modulus metal.

A conformal balanced and symmetric composite structure from inboard to outboard comprising:

• a first layer of high modulus metal;
• a first fiber layer including a plurality of balanced and symmetric plys, each ply comprising carbon fiber in a cyanate ester resin having nano-particles therein or epoxy resin matrix having nano-particles therein, the first fiber layer attached to the first layer of metal;
• a second layer of high modulus metal adhesively attached to the first fiber layer and a second fiber layer;
• a second fiber layer including a plurality of high modulus balanced and symmetric plys, each ply comprising carbon fiber in a cyanate ester resin having nano-particles therein or epoxy resin matrix having nano-particles therein;
• and
• a third layer of metal attached to the second fiber layer.

A method for utilizing rule-of-mixtures analysis results for designing a dimensionally stable laminate composite structure comprising:

• determining materials for layers of the laminate composite structure based on radiation shielding requirements for a payload for radiation shielding compared to requirements for thermal expansion/distortion performance affected by thickness, stiffness, and coefficient of thermal expansion of the layers;
• determining thicknesses of the materials for the laminate composite structure based on radiation shielding requirements for a payload for radiation shielding compared to the requirements for thermal expansion/distortion performance affected by thickness, stiffness, and coefficient of thermal expansion of the layers;
• determining combinations of materials used in each layer of the layers of the laminate composite structure based on radiation shielding requirements for a payload for radiation shielding compared to the requirements for thermal expansion/distortion performance affected by thickness, stiffness, and coefficient of thermal expansion of the layers;
• and
• determining the symmetry, orientation, and balancing the thermal expansion and contraction of the five main high modulii adhesively joined alternating metal and graphite layers comprising the laminate composite structure for minimizing thermal growth and distortion of the layers.

A method from the radiation transmission analysis of results for a radiation shielding laminate composite structure, in conjunction with 69, comprising:

• determining Z combinations of materials for the layers of the laminate composite structure based on the material for each layer having a resistance to wide spectrum ionizing and non-ionizing radiation, backside impact spalling, electromagnetic ionization, electrostatic surface discharge, surface charging, thermal pulse, EMI, EMP, and environmental protection, where the interaction of certain metal foil high Z plus low Z combinations tune the shielding for both primary and secondary transmissions;
• determining number of layers of the laminate composite structure based on a material for each layer having a resistance to wide spectrum ionizing and non-ionizing radiation, backside impact spalling, electromagnetic ionization, electrostatic surface discharge, surface charging, thermal pulse, EMI, EMP, and environmental protection;
• determining types of materials for the layers of the laminate composite structure based on the material for each layer having a resistance to wide spectrum ionizing and non-ionizing radiation, backside impact spalling, electromagnetic ionization, electrostatic surface discharge, surface charging, thermal pulse, EMI, EMP, and environmental protection;
• determining thicknesses of the materials for the layers of the laminate composite structure, the materials for the layers of the laminate composite structure based on the material for each layer having a resistance to wide spectrum ionizing and non-ionizing radiation, backside impact spalling, electromagnetic ionization, electrostatic surface discharge, surface charging, thermal pulse, EMI, EMP, and environmental protection;
• determining an order of the material Zs used for each layer of the layers of the laminate composite structure, the materials for the layers of the laminate composite structure based on the material Zs for each layer having a resistance to wide spectrum ionizing and non-ionizing radiation, backside impact spalling, electromagnetic ionization, electrostatic surface discharge, surface charging, thermal pulse, EMI, EMP, and environmental protection;
• and
• with possible variants for different target types, forming a total multifunctional laminate composite structure.