Patent Publication Number: US-2023158566-A1

Title: Tuned multilayered material systems and methods for manufacturing

Description:
PRIORITY 
     This application is a divisional of U.S. Ser. No. 16/733,498 filed on Jan. 3, 2020. 
    
    
     FIELD 
     The present application relates to the field of multilayered materials and methods for manufacturing tuned multilayered material systems (TMMS), particularly tuned multilayered material systems for extreme environment hypersonic airframe structures, including the fuselage, wings, tails, control surfaces, leading edges, internal structure, air induction system, and thermal protection systems in general. 
     BACKGROUND 
     Traditional materials with the ability to provide a path to manufacturable, durable, and rapidly deployable extreme environment hypersonic airframe structure, including the fuselage, wings, tails, control surfaces, leading edges, internal structure, and air induction system are expensive and require long fabrication cycles. To deliver affordable and robust airframe structures and thermal protection systems for future extreme environment applications, new technologies are required that can offer multilayered material systems tuned to locally meet stringent thermomechanical loading requirements on an airframe. 
     Accordingly, those skilled in the art continue with research and development in the field of tuned multilayered material systems. 
     SUMMARY 
     In one example, a graded multilayered composite comprises a metal matrix material having a first side and a second side opposite the first side. The graded multilayered composite also comprises a first layer of microspheres dispersed on the first side of the metal matrix material, and a second layer of microspheres dispersed on the second side of the metal matrix material. 
     In another example, a graded multilayered material system comprises a non-graded multilayered composite. The graded multilayered material system also comprises at least one graded layer joined to the non-graded multilayered composite and selected from a graded metal liner, a graded ceramic liner, a graded metal-ceramic hybrid liner, a graded metallic core, a graded cooling channel structure, and a graded environmental barrier coating. 
     In yet another example, a method is provided for manufacturing a multilayered material system. The method comprises providing a graded multilayered composite, and joining at least one layer to the graded multilayered composite to provide the multilayered material system. 
     In still another example, a method is provided for manufacturing a multilayered material system. The method comprises providing a non-graded multilayered composite, and joining at least one graded layer to the non-graded multilayered composite to provide the multilayered material system. 
     In one example, a multilayered material system includes at least one of a liner sheet and a cellular core, and a multilayered composite (e.g., a multilayered metal matrix composite) joined to the at least one of a liner sheet and a cellular core. The multilayered composite includes hollow microspheres dispersed within a metallic matrix material. 
     In another example, a method for manufacturing a multilayered composite includes providing a first layer of a first powder having first hollow microspheres dispersed therein, providing a second layer of a second powder adjacent the first layer of first powder, and heating the first layer of first powder and the second layer of second powder. The second layer of second powder has second hollow microspheres dispersed therein. 
     In yet another example, a method for manufacturing a multilayered material system includes providing a first layer of a first powder having first hollow microspheres dispersed therein, providing a second layer of a second powder adjacent the first layer of first powder, sintering the first layer of first powder and the second layer of second powder, providing at least one of a liner sheet and a cellular core, and joining the first layer of sintered first powder with the at least one of a liner sheet and a cellular core. The second layer of the second powder has second hollow microspheres dispersed therein. 
     Other examples of the disclosed multilayered material systems and methods of the present description will become apparent from the following detailed description, the accompanying drawings and the appended claims. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    is a cross-sectional view of an example of a graded multilayered composite according to the present description. 
         FIG.  2 A  is a cross-sectional view of the graded multilayered composite of  FIG.  1    joined to a single-layer structure to form a graded multilayered material system. 
         FIG.  2 B  is a cross-sectional view of a non-graded multilayered composite joined to a graded single-layer structure to form a graded multilayered material system. 
         FIG.  3 A  is a cross-sectional view of the graded multilayered composite of  FIG.  1    joined to a multiple-layer structure to form a graded multilayered material system. 
         FIGS.  3 B- 3 E  are cross-sectional views similar to  FIG.  3 A , and show the graded multilayered composite of  FIG.  1    joined to different multiple-layer structures to provide different graded multilayered material systems. 
         FIG.  4    is a flow diagram representing a method for manufacturing a multilayered material system. 
         FIG.  5    is a flow diagram representing a method for manufacturing a multilayered material system. 
         FIG.  6    is a perspective view of a vehicle that includes a multilayered material system including a cellular sandwich panel and a multilayered composite joined to the cellular sandwich panel according to the present description. 
         FIG.  7    is a cross-sectional view of an example of the multilayered material system of  FIG.  6   . 
         FIG.  8    is a zoomed-in cross-sectional view of a portion of the multilayered material system of  FIG.  7   . 
         FIG.  9    is a cross-sectional view of another example of the multilayered material system of  FIG.  6   . 
         FIG.  10    is a zoomed-in cross-sectional view of a portion of the multilayered material system of  FIG.  9   . 
         FIG.  11    is flow diagram representing a method for manufacturing the multilayered composite of  FIG.  6   . 
         FIG.  12    is a flow diagram representing a method for manufacturing the multilayered material system of  FIG.  6   . 
         FIG.  13    is a flow diagram of an aircraft manufacturing and service methodology. 
         FIG.  14    is a block diagram of an aircraft. 
     
    
    
     DETAILED DESCRIPTION 
       FIG.  1    is a cross-sectional view of an example of a multilayered composite  1100  according to the present description. The multilayered composite  1100  is a graded multilayered composite that includes a metal matrix material  1110  having a first side  1112  and a second side  1114  opposite the first side  1112 . The graded multilayered composite  1100  also includes a first layer  1120  of microspheres dispersed on the first side  1112  of the metal matrix material  1110 , and a second layer  1122  of microspheres dispersed on the second side  1114  of the metal matrix material  1110 . 
     The multilayered composite  1100  is graded based upon a combination of grading factors. As an example, a first portion of the multilayered composite  1100  may have a density that is different from a density of a second portion of the multilayered composite  1100 . As another example, the metal matrix material  1110  may comprise a compositionally-graded material, such as a hybrid titanium-based and nickel-based material system. 
     As still another example, the microspheres of the first layer  1120  of microspheres may be spatially distributed relative to each other based upon a first spatial gradation, and the microspheres of the second layer  1122  of microspheres may be spatially distributed relative to each other based upon a second spatial gradation which is different from the first spatial gradation. In an example implementation, the first and second spatial gradations may be based upon number of microspheres. In another example implementation, the first and second spatial gradations may be based upon size of microspheres. Other grading factors and any combination of grading factors associated with the multilayered composite  1100  are possible. 
     The graded multilayered composite  1100  further comprises a first buffer region  1140  defined between the first layer  1120  of microspheres and a first edge  1113  on the first side  1112  of the metal matrix material  1110 . The graded multilayered composite  1100  also comprises a second buffer region  1142  defined between the second layer  1122  of microspheres and a second edge  1115  on the second side  1114  of the metal matrix material  1110 . Each of the first buffer region  1140  and the second buffer region  1142  is substantially void of microspheres. The first buffer region  1140  and the second buffer region  1142  ensure that no partial microsphere is in the vicinity of the first edge  1113  and the second edge  1115 , which could result in a weak material stress point. 
       FIG.  2 A  is a cross-sectional view of the graded multilayered composite  1100  of  FIG.  1    joined to a single-layer structure  1150  to form a graded multilayered material system  1200 . The single-layer structure  1150  may be selected from a metallic liner (e.g., a monolithic metal, metal alloy, metal matrix composite, intermetallic alloy, intermetallic matrix composite, complex concentrated alloy, or complex concentrated matrix composite), a ceramic liner (e.g. monolithic ceramic, ceramic matrix composite, or complex concentrated ceramic alloy), a metallic-ceramic hybrid liner, a metallic core, a cooling channel structure (which defines one or more cooling channels), and an environmental barrier coating. The single-layer structure  1150  may comprise a graded material (e.g., a graded metallic or a graded ceramic or a graded hybrid). 
     Although the graded multilayered material system  1200  of  FIG.  2 A  is formed using the graded multilayered composite  1100  of  FIG.  1   , it is conceivable that a graded multilayered material system be formed using a substantially uniform (i.e., non-graded) multilayered composite and a graded single-layer structure such as shown in  FIG.  2 B . 
     As shown in  FIG.  2 B , a multilayered material system  1250  comprises a non-graded multilayered composite  1260  (i.e., a substantially uniform multilayered composite) joined to a graded single-layered structure  1280 . The non-graded multilayered composite  1260  comprises a metal matrix material  1262  having a non-graded layer  1264  of microspheres dispersed in the metal matrix material  1262 . First and second buffer regions  1266 ,  1268  are disposed on opposite sides of the non-graded layer  1264  of microspheres. The graded single-layered structure  1280  is joined to the first buffer region  1266 . 
     In some examples, the non-graded multilayered composite  1260  comprises a substantially uniform composition of the metal matrix material  1262 . In some examples, the graded single-layered structure  1280  is selected from a monolithic or graded metallic liner (e.g., a metal, metal alloy, metal matrix composite, intermetallic alloy, intermetallic matrix composite, complex concentrated alloy, or complex concentrated matrix composite), a monolithic or graded ceramic liner (e.g., ceramic, ceramic matrix composite, or complex concentrated ceramic alloy), or a monolithic or graded metallic-ceramic hybrid liner, a graded metallic core, a graded cooling channel structure (which defines one or more cooling channels), and a graded environmental barrier coating. 
       FIG.  3 A  is a cross-sectional view of the graded multilayered composite  1100  of  FIG.  1    joined to a multiple-layer structure to form a graded multilayered material system. Each of  FIGS.  3 B- 3 E  is a cross-sectional view similar to  FIG.  3 A , and shows the graded multilayered composite  1100  of  FIG.  1    joined to a different multiple-layer structure to provide a different graded multilayered material system. Each of the different multiple-layer structures may comprise a graded material structure. 
     Although each of the graded multilayered material systems of  FIGS.  3 A- 3 E  is formed using the graded multilayered composite  1100  of  FIG.  1   , it is conceivable that a multilayered material system be formed using a substantially uniform (i.e., non-graded) multilayered composite. For purposes of explanation, each of the graded multilayered material systems of  FIGS.  3 A- 3 E  will be described using the graded multilayered composite  1100  of  FIG.  1   . 
     As shown in graded multilayered material system  1300   a  of  FIG.  3 A , graded multilayered composite  1100   a  is sandwiched between cooling channel structure  1310   a  (which defines one or more cooling channels  1311   a ) and first liner sheet  1320   a . This sandwiched structure, in turn, is sandwiched between environmental barrier coating  1330   a  and cellular core  1340   a . Second liner sheet  1350   a  is disposed on opposite side of cellular core  1340   a . Environmental barrier coating  1330   a  may comprise a monolithic or graded metallic material (e.g., a metal, metal alloy, metal matrix composite, intermetallic alloy, intermetallic matrix composite, complex concentrated alloy, or complex concentrated matrix composite), a monolithic or graded ceramic material (e.g., ceramic, ceramic matrix composite, or complex concentrated ceramic alloy), or a monolithic or graded metallic-ceramic hybrid material. This environmental barrier coating  1330   a  can be provided for oxidation resistance, corrosion resistance, wear resistance, emissivity increase, etc. 
     As shown in graded multilayered material system  1300   b  of  FIG.  3 B , graded multilayered composite  1100   b  is sandwiched between cooling channel structure  1310   b  (which defines one or more cooling channels  1311   b ) and liner sheet  1320   b . Environmental barrier coating  1330   b  is disposed on opposite side of cooling channel structure  1310   b.    
     As shown in graded multilayered material system  1300   c  of  FIG.  3 C , graded multilayered composite  1100   c  is integrated with cooling channel structure  1310   c  (which defines one or more cooling channels  1311   c ). This integrated structure is sandwiched between first liner sheet  1320   c  and second liner sheet  1350   c . The first and second liner sheets  1320   c ,  1350   c  may comprise a monolithic or graded metallic material (e.g., a metal, metal alloy, metal matrix composite, intermetallic alloy, intermetallic matrix composite, complex concentrated alloy, or complex concentrated matrix composite), a monolithic or graded ceramic material (e.g., ceramic, ceramic matrix composite, or complex concentrated ceramic alloy), or a monolithic or graded metallic-ceramic hybrid material. Environmental barrier coating  1330   c  is disposed on opposite side of first liner sheet  1320   c.    
     As shown in graded multilayered material system  1300   f  of  FIG.  3 D , graded multilayered composite  1100   f  is sandwiched between cooling channel structure  1310   f  (which defines one or more cooling channels  1311   f ) and environmental barrier coating  1330   f . Cellular core  1340   f  is disposed on opposite side of cooling channel structure  1310   f . Liner sheet  1320   f  is disposed on opposite side of cellular core  1340   f.    
     As shown in graded multilayered material system  1300   g  of  FIG.  3 E , graded multilayered composite  1100   g  is integrated with cooling channel structure  1310   g  (which defines one or more cooling channels  1311   g ). This integrated structure is sandwiched first liner sheet  1320   g  and second liner sheet  1350   g . This sandwiched structure, in turn, is sandwiched between first cellular core  1340   g  and second cellular core  1360   g . This sandwiched structure, in turn, is sandwiched between third liner sheet  1370   g  and fourth liner sheet  1380   g . Environmental barrier coating  1330   g  is disposed on opposite side of third liner sheet  1370   g.    
     In each of  FIGS.  3 A- 3 E , it is conceivable that any number individual elements and any combination of the elements may be used to provide a graded multilayered material system. Moreover, it is conceivable that the multilayered composite may be integrated with any element. 
     Referring to  FIG.  4   , a flow diagram  1400  represents a method for manufacturing a multilayered material system. In block  1410 , a graded multilayered composite is provided. The process proceeds to block  1420  in which at least one layer is joined to the graded multilayered composite to provide the multilayered material system. The process then ends. 
     In some examples, the at least one layer is selected from a monolithic or graded metallic liner (e.g., a metal, metal alloy, metal matrix composite, intermetallic alloy, intermetallic matrix composite, complex concentrated alloy, or complex concentrated matrix composite), a monolithic or graded ceramic liner (e.g., ceramic, ceramic matrix composite, or complex concentrated ceramic alloy), or a monolithic or graded metallic-ceramic hybrid liner, a monolithic or graded metallic core, a monolithic or graded cooling channel structure, or a monolithic or graded environmental barrier coating. For example, the monolithic or graded metallic liner comprises a metal, metal alloy, metal matrix composite, intermetallic alloy, intermetallic matrix composite, complex concentrated alloy, or complex concentrated matrix composite, and the monolithic or graded ceramic liner comprises ceramic, ceramic matrix composite, or complex concentrated ceramic alloy. 
     Referring to  FIG.  5   , a flow diagram  1500  represents a method for manufacturing a tuned multilayered material system. In block  1510 , a non-graded multilayered composite is provided. The process proceeds to block  1520  in which the at least one monolithic or graded layer is joined to the non-graded multilayered composite to provide the tuned multilayered material system. The process then ends. 
     In some examples, the at least one graded layer is selected from a graded metal liner, a graded ceramic liner, a graded metal-ceramic hybrid liner, a graded metallic core, a graded cooling channel structure, and a graded environmental barrier coating. For example, the monolithic or graded metallic liner comprises a metal, metal alloy, metal matrix composite, intermetallic alloy, intermetallic matrix composite, complex concentrated alloy, or complex concentrated matrix composite, and the monolithic or graded ceramic liner comprises ceramic, ceramic matrix composite, or complex concentrated ceramic alloy. 
       FIG.  6    is a perspective view of a structure  1  that includes a multilayered material system  10  according to the present description. The structure  1  is shown as an aircraft, such as a hypersonic aircraft, but the structure  1  is not limited to vehicles and can include, for example, weapons, such as hypersonic weapons. The multilayered material system  10  can form an exterior surface of the structure  1  and can function as a thermal protection system for the structure  1 . It can also serve as other acreage skin structure, engine inlet structure, leading edge structure, control surface structure, thermo-mechanical isolator structure, or integrated thermal protection system for internal cold components. 
       FIG.  7    is a cross-sectional view of an example of the multilayered material system  10  of  FIG.  6   , and  FIG.  8    is a zoomed-in cross-sectional view of a portion of the multilayered material system of  FIG.  7   . As shown in  FIGS.  7  and  8   , the tuned multilayered material system  10  includes a cellular sandwich panel  100  and a multilayered composite  200  joined to the cellular sandwich panel  100 , in which the multilayered composite  200  includes hollow microspheres  210  dispersed within a metallic matrix material  220 . 
       FIG.  9    is a cross-sectional view of another example of the multilayered material system  10  of  FIG.  6   , and  FIG.  10    is a zoomed-in cross-sectional view of a portion of the tuned multilayered material system of  FIG.  9   . As shown in  FIGS.  9  and  10   , the multilayered material system  10  includes a cellular sandwich panel  100  and a multilayered composite  200  joined to the cellular sandwich panel  100 , in which the multilayered composite  200  includes a spatial distribution of hollow microspheres  210  dispersed within a metallic matrix material  220 . 
     The multilayered material systems  10  of  FIGS.  7  to  10    enable for the design of multifunctional and tunable structures that combine exceptional stiffness and strength-to-weight ratio with additional functional enhancements such as thermal protection and thermal management. The multilayered material system  10  includes two main constituents. First the cellular sandwich panel  100  can be optimized and tuned to meet specific extreme environment application requirements. Second, the multilayered composite  200  can be optimized and tuned to meet thermomechanical loading profile requirements. Further, the cellular sandwich panel  100  and the multilayered composite  200  can be joined together by a variety of methods to meet thermomechanical loading requirements. 
     In an example, the cellular sandwich panel  100  includes a first liner sheet  110 , a second liner sheet  120 , and a cellular core  130  between the first liner sheet  110  and the second liner sheet  120 . The thickness of the cellular core  130  is typically greater than the thickness of the first liner sheet  110  and second liner sheet  120  and the density of the cellular core  130  is typically less than the density of the first liner sheet  110  and second liner sheet  120 . The stiffness of the first liner sheet  110  and second liner sheet  120  is typically greater than the stiffness of the cellular core  130 . By attaching the thinner but stiffer first liner sheet  110  and second liner sheet  120  to the lightweight by thicker cellular core  130 , the cellular sandwich panel  100  is provided with high stiffness and low overall density. 
     The first liner sheet  110  can be formed from a variety of alloys, including but not limited to aluminum and aluminum alloys/metal matrix composites; titanium and titanium alloys/metal matrix composites; superalloys (including iron and iron alloys/metal matrix composites, nickel and nickel alloys/metal matrix composites, cobalt and cobalt alloys/metal matrix composites); refractory metals and alloys/metal matrix composites; copper and copper alloys/metal matrix composites; precious metals and alloys/metal matrix composites; zirconium and hafnium and their alloys/metal matrix composites; intermetallics; complex concentrated alloys/metal matrix composites (high entropy alloys/metal matrix composites, medium entropy alloys/metal matrix composites, multicomponent alloys/metal matrix composites). In an example, the first liner sheet  110  is formed from a titanium alloy. The first liner sheet  110  can be optimized and tuned to have a variety of thicknesses. 
     The second liner sheet  120  can be formed from a variety of alloys, including but not limited to aluminum and aluminum alloys/metal matrix composites; titanium and titanium alloys/metal matrix composites; superalloys (including iron and iron alloys/metal matrix composites, nickel and nickel alloys/metal matrix composites, cobalt and cobalt alloys/metal matrix composites); refractory metals and alloys/metal matrix composites; copper and copper alloys/metal matrix composites; precious metals and alloys/metal matrix composites; zirconium and hafnium and their alloys/metal matrix composites; intermetallics; complex concentrated alloys/metal matrix composites (high entropy alloys/metal matrix composites, medium entropy alloys/metal matrix composites, multicomponent alloys/metal matrix composites). In an example, the second liner sheet  120  is formed from a titanium alloy. The second liner sheet  120  can be optimized and tuned to have a variety of thicknesses. 
     The cellular core  130  can be formed from a variety of alloys, including but not limited to aluminum and aluminum alloys/metal matrix composites; titanium and titanium alloys/metal matrix composites; superalloys (including iron and iron alloys/metal matrix composites, nickel and nickel alloys/metal matrix composites, cobalt and cobalt alloys/metal matrix composites); refractory metals and alloys/metal matrix composites; copper and copper alloys/metal matrix composites; precious metals and alloys/metal matrix composites; zirconium and hafnium and their alloys/metal matrix composites; intermetallics; complex concentrated alloys/metal matrix composites (high entropy alloys/metal matrix composites, medium entropy alloys/metal matrix composites, multicomponent alloys/metal matrix composites). In an example, the cellular core  130  is formed from a titanium alloy. The cellular core  130  can be optimized and tuned to have a variety of thicknesses. 
     The cellular core  130  can be produced using a variety of additive manufacturing technologies, including melting processes, such as powder bed fusion or directed energy deposition; sintering processes, such as binder jetting, material extrusion, and material jetting; and solid state processes, such as additive friction stir processing, ultrasonic additive processing, cold spray, etc. 
     The cellular core  130  can have a variety of architectures. In an example, cellular core  130  can have an open cellular architecture. In another example, the cellular core  130  can have a closed cellular architecture. In another example, the cellular core  130  can have a honeycomb architecture. The architecture of the cellular core  130  can be tuned and optimized to meet application requirements. 
     The cellular core  130  can be bonded to the first liner sheet  110  and second liner sheet  120  by a variety of methods, such as by welding, brazing, fastening, diffusion bonding (with or without interlayer foils/coatings) or additive manufacturing. 
     In an example, the cellular core  130  includes one or more third liner sheets. In another example, the cellular core  130  includes one or more third liner sheets  132  that are superplastically formed and are diffusion bonded to the first liner sheet  110  and the second liner sheet  120 . Superplastic forming and diffusion bonding (SPF/DB) is a technique for forming complex-shaped hollow cellular sandwich panels. It combines superplastic forming with diffusion bonding to create the cellular sandwich panels. Typically, three or more liner sheets are welded together at their edges, then heated within the confines of a female mold tool. At high temperatures, the three or more liner sheets become extremely malleable, i.e. superplastic. When in the superplastic state, an inert gas is injected between the three or more liner sheets to form the three or more liner sheets to the shape of the mold. Superplastic forming and diffusion bonding is useful for complex shapes. Thus, the architecture of the one or more third liner sheets  132  of the cellular core  130  can be tuned and optimized to meet a wide variety of application requirements. In the illustrated example, the cellular core  130  includes a double core structure having two third liner sheets  132 . 
     The cellular sandwich panel  100  can provide a thermal protection gradient functionality. In an example, the melting point or thermal microstructural stability point of the first liner sheet  110  is greater than the melting point or thermal microstructural stability point of the second liner sheet  120 . In another example, the melting point or thermal microstructural stability point of the first liner sheet  110  is greater than the melting point or thermal microstructural stability point of the cellular core  130 . In yet another example, the melting point or thermal microstructural stability point of the cellular core  130  is greater than the melting point or thermal microstructural stability point of the second liner sheet  120 . In yet another example, the melting point or thermal microstructural stability point of the first liner sheet  110  is greater than the melting point or thermal microstructural stability point of the cellular core  130 , which is greater than the melting point or thermal microstructural stability point of the second liner sheet  120 . By way of providing the above-described thermal protection gradient functionality, the cellular sandwich panel  100  has a hot side with higher resistance to high temperatures and a cold side with lower resistance to high temperatures. 
     In addition, by relaxing the requirements for high resistance to high temperatures at the cold side, the cold side can be formed from materials having lower cost or superior properties, such as increased strength, increased damage tolerance, increased resistance to environmentally assisted cracking, increased formability, increased joinability or increased producibility, than the materials at the hot side. Accordingly, by way of example, the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the second liner sheet  120  is greater than the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the first liner sheet  110 . In another example, the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the second liner sheet  120  is greater than the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the cellular core  130 . In yet another example, the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the cellular core  130  is greater than the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the first liner sheet  110 . In yet another example, the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the second liner sheet  120  is greater than the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the cellular core  130 , which is greater than the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the first liner sheet  110 . By way of providing the above-described thermal protection gradient functionality, the cellular sandwich panel  100  can have a hot side with higher resistance to high temperatures but lower strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility and a cold side with lower resistance to high temperatures but higher strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility. 
     The first liner sheet  110  can include a first liner layer  112  proximate to the cellular core  130  and a second liner layer  114  proximate to the multilayered composite  200 . The first liner layer  112  and the second liner layer  114  can provide a thermal protection gradient functionality. In an example, a melting point or thermal microstructural stability point of the second liner layer  114  is greater than a melting point or thermal microstructural stability point of the first liner layer  112 . The first liner sheet  110  can further include third or further liner layers intermediate to the first liner layer  112  and the second liner layer  114 , which the third or further liner layers have a melting point or thermal microstructural stability points intermediate to the first liner layer  112  and the second liner layer  114 . By way of providing the above-described thermal protection gradient functionality of the first liner sheet  110 , the first liner sheet  110  has a hot side with higher resistance to high temperatures and a cold side with lower resistance to high temperatures. 
     The first liner sheet  110  can provide for a compatibility with the multilayered composite  200 . In an aspect, the first liner layer  112  is compatible with the second liner layer  114 , which is compatible with the multilayered composite  200 , but the first liner layer  112  is incompatible or less compatible with the multilayered composite  200 . The first liner sheet  110  can further include third or further liner layers intermediate to the first liner layer  112  and the second liner layer  114 , in which the third or further liner layers are compatible with the first liner layer  112  and the second liner layer  114  but the first liner layer  112  and second liner layer  114  are incompatible or less compatible with each other. 
     In an example, a composition of the first liner layer  112  includes an element that is detrimental to the properties of the multilayered composite  200 , or a composition of the multilayered composite  200  includes an element that is detrimental the properties of the first liner layer  112 , and the second liner layer  114  excludes the detrimental element. Accordingly, the first liner sheet  110  can provide for an improved compatibility of the cellular sandwich panel  100  with the multilayered composite  200 . 
     In another example, a temperature for processing the multilayered composite  200  exceeds the melting point or thermal microstructural stability point of the first liner layer  112  rendering the first liner layer  112  and the multilayered composite  200  incompatible, and the melting point or thermal microstructural stability point of the second liner layer  114  exceeds the temperature for processing the multilayered composite  200  rending the second liner layer  114  and the multilayered composite  200  more compatible. The temperature for processing the multilayered composite  200  can include, for example, a joining temperature, a sintering temperature, or a heat treatment temperature. Accordingly, the first liner sheet  110  can provide for an improved compatibility of the cellular sandwich panel  100  with the multilayered composite  200 . 
     In yet another example, a coefficient of thermal expansion of the first liner layer  112  greatly varies from a coefficient of thermal expansion of the multilayered composite  200  and a coefficient of thermal expansion the second liner layer  114  varies less from the coefficient of thermal expansion of the multilayered composite  200 . Accordingly, the first liner sheet  110  can provide for an improved compatibility of the cellular sandwich panel  100  with the multilayered composite  200 . 
     In addition, the first liner layer  112  can be formed from alloys having lower cost or superior properties, such as increased strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility. Accordingly, by way of example, the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the first liner layer  112  is greater than the strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility of the second liner layer  114 . Thus, by providing the above-described compatibility of the cellular sandwich panel  100  with the multilayered composite  200 , the cellular sandwich panel  100  can be provided with a higher overall strength, damage tolerance, resistance to environmentally assisted cracking, formability, joinability or producibility while remaining compatible with the multilayered composite  200 . 
     As previously mentioned, the multilayered composite  200  includes hollow microspheres  210  dispersed within a metallic matrix material  220 . The hollow microspheres  210  can provide the multilayered composite  200  with lightweight characteristics and insulative, conductive, and/or noise/impact attenuating properties. The metallic matrix material  220  can provide the multilayered composite  200  with durability and resistance to failure. 
     The metallic matrix material  220  can be formed from a variety of materials. In an example, the metallic matrix material  220  is formed from at least one of an alloy material, including but not limited to aluminum and aluminum alloys/metal matrix composites; titanium and titanium alloys/metal matrix composites; superalloys (including iron and iron alloys/metal matrix composites, nickel and nickel alloys/metal matrix composites, cobalt and cobalt alloys/metal matrix composites); refractory metals and alloys/metal matrix composites; copper and copper alloys/metal matrix composites; precious metals and alloys/metal matrix composites; zirconium and hafnium and their alloys/metal matrix composites; intermetallics; complex concentrated alloys/metal matrix composites (high entropy alloys/metal matrix composites, medium entropy alloys/metal matrix composites, multicomponent alloys/metal matrix composites) and a ceramic material. By forming the metallic matrix material  220  from at least one of an alloy material and a ceramic material, the metallic matrix material  220  can be provided with resistance to high temperatures. In a specific example, the metallic matrix material  220  is formed from a nickel-based superalloy. In another specific example, the metallic matrix material is formed from a titanium-based superalloy. 
     The hollow microspheres  210  can be formed from a variety of materials. In an example, the hollow microspheres  210  are formed from a ceramic material. By forming the hollow microspheres  210  from a ceramic material, the hollow microspheres  210  can be provided with resistance to high temperatures and resistance against deformation to maintain their shape around the hollow interior thereof. In a specific example, the ceramic material is formed from yttria-stabilized zirconia or alumina-silica-iron glass. The architecture of the hollow microspheres  210  can be tuned and optimized to enable the multilayered composite  200  to meet application requirements. This architecture includes material, coating size, shell thickness, coating thickness, and type/material. In some implementations, the material of the hollow microspheres  210  is ceramic-based or metallic-based, and the size range is between 5 microns and 500 microns in diameter with average wall thickness between 2% to 30% of the diameter. In some implementations, the hollow microspheres  210  are coated with a coating made of metallic, ceramic, or hybrid metal-ceramic material combinations and having a coating thickness between 2 microns and 200 microns. The microspheres can also be solid. These example implementations tune the multilayered composite  200  for a particular application. 
     In an example, the hollow microspheres  210  are included in the metallic matrix material  220  in a volume fraction in a range of between about 1 and 60 percent. Volume fraction of the hollow microspheres  210  is defined as the volume of all the hollow microspheres  210  within the metallic matrix material  220  divided by the total volume of the hollow microspheres  210  and the metallic matrix material  220 . A higher volume fraction of hollow microspheres  210  increases lightweight characteristics and insulative, conductive, and/or noise/impact attenuating properties of the multilayered composite  200 . A lower volume fraction of hollow microspheres  210  increases durability and resistance to failure of the multilayered composite  200 . 
     In an example, the multilayered composite  200  includes a first layer  202  proximate to the first liner sheet  110  and a second layer  204  adjacent to first layer  202 . The first layer  202  has a first matrix  222  that includes first hollow microspheres  212 , and the second layer  204  has a second matrix  224  that includes second hollow microspheres  214 . 
     The first layer  202  and second layer  204  can provide a thermal protection gradient functionality. In an example, a melting point or thermal microstructural stability point of the second matrix  224  is greater than a melting point or thermal microstructural stability point of the first matrix  222 . The multilayered composite  200  can further include third or further layers intermediate to the first layer  202  and the second layer  204 , in which the third or further layers have matrixes with melting point or thermal microstructural stability points that are intermediate to the melting point or thermal microstructural stability points of the first matrix  222  and second matrix  224 . By way of providing the above-described thermal protection gradient functionality of the multilayered composite  200 , the multilayered composite  200  has a hot side with higher resistance to high temperatures and a cold side with lower resistance to high temperatures. 
     The multilayered composite  200  can provide for a compatibility with the cellular sandwich panel  100 . In an example, the first matrix  222  is compatible with the second liner layer  114  of the cellular sandwich panel  100 , but the second matrix  224  is incompatible or less compatible with the second liner layer  114  of the cellular sandwich panel  100 . The multilayered composite  200  can further include third or further layers intermediate to the first layer  202  and the second layer  204 , in which the third or further layers are compatible with the first layer  202  and the second layer  204  but the first layer  202  and second layer  204  are incompatible or less compatible with each other. 
     In an example, a composition of the second matrix  224  includes an element that is detrimental to the properties of the second liner layer  114 , or a composition of the second liner layer  114  includes an element that is detrimental the properties of the second matrix  224 , and the second matrix  224  excludes the detrimental element. Accordingly, the multilayered composite  200  can provide for an improved compatibility with the cellular sandwich panel  100 . 
     In another example, a temperature for processing the second matrix  224  exceeds the melting point or thermal microstructural stability point of the second liner layer  114  rendering the second matrix  224  and the second liner layer  114  incompatible, and the melting point or thermal microstructural stability point of the second liner layer  114  exceeds a temperature for processing the first matrix  222  rendering the first matrix  222  and the second liner layer  114  more compatible. The temperature for processing the first matrix  222  and the second matrix  224  can include, for example, a joining temperature, a sintering temperature, or a heat treatment temperature. Accordingly, the multilayered composite  200  can provide for an improved compatibility with the cellular sandwich panel  100 . 
     In yet another example, a coefficient of thermal expansion of the second layer  204  greatly varies from a coefficient of thermal expansion of the second liner layer  114  and a coefficient of thermal expansion of the first layer  202  varies less from the coefficient of thermal expansion of the second liner layer  114 . Accordingly, the multilayered composite  200  can provide for an improved compatibility with the cellular sandwich panel  100 . 
     In addition, the second matrix  224  can be formed from materials having lower cost or superior properties, such as higher resistance to high temperatures. Accordingly, by way of example, the melting point or thermal microstructural stability point of the second matrix  224  is greater than the melting point or thermal microstructural stability point of the first matrix  222 . Thus, by providing the above-described compatibility of the multilayered composite  200  with the cellular sandwich panel  100 , the multilayered composite  200  can be provided with a higher resistance to high temperatures while remaining compatible with the cellular sandwich panel  100 . 
     As shown in  FIGS.  9  and  10   , the first layer  202  and the second layer  204  provide a spatial distribution of the hollow microspheres  210 . Although  FIGS.  9  and  10    show the first layer  202  and the second layer  204  providing a graded spatial distribution of the hollow microspheres  210 , it is conceivable that the first layer  202  and the second layer  204  provide a substantially uniform (i.e., non-graded) spatial distribution of the hollow microspheres  210 . For the purpose of explanation, only the graded spatial distribution of the hollow microspheres  210  will be described herein. 
     As illustrated in  FIGS.  9  and  10   , a volume fraction of the second hollow microspheres  214  within the second layer  204  is higher than a volume fraction of the first hollow microspheres  212  within the first layer  202 . By way of example, the volume fraction of the second hollow microspheres  214  within the second layer  204  is at least 5 percent greater than the volume fraction of the first hollow microspheres  212  within the first layer  202 , preferably at least 10 percent greater, more preferably at least 20 percent greater, even more preferably at least 50 percent greater, even more preferably at least 100 percent greater. Accordingly, the first layer  202  can have a higher durability and resistance to failure while the second layer  204  can have a lower overall density and higher insulative, conductive, and/or noise/impact attenuating properties. Additionally, the first layer  202  having a lower volume fraction of first hollow microspheres  212  can be more compatible for joining with the second liner layer  114  than the second layer  204  having a higher volume fraction of second hollow microspheres  214 . By way of a specific example, the first layer  202  has a volume fraction of about 10% first hollow microspheres  212 , and the second layer  204  has a volume fraction of about 45% second hollow microspheres  214 . The first liner sheet  110  can further include third or further liner layers intermediate to the first liner layer  112  and the second liner layer  114 , which the third or further liner layers have a melting point or thermal microstructural stability points intermediate to the first liner layer  112  and the second liner layer  114 . The multilayered composite  200  can further include third or further layers intermediate to the first layer  202  and the second layer  204 , in which the third or further layers having third or further hollow microspheres having different volume fractions of hollow microspheres. 
     Although  FIGS.  9  and  10    show the first layer  202  and second layer  204  as generally planar layers, in which the first layer  202  covers the surface of the cellular sandwich panel  100  and the second layer  204  covers the surface of the first layer  202 , other arrangements of the first layer  202  and second layer  204  are included in the present description. For example, the first layer  202  and second layer  204  each cover adjacent portions of the cellular sandwich panel  100 . Accordingly, the first layer  202  can be more compatible for fastening with the second liner layer  114  of the cellular sandwich panel  100  than the second layer  204 . Thus, the first layer  202  can be positioned on the second liner layer  114  where fasteners connect the second liner layer  114  with the multilayered composite  200 . 
     In another example, a composition of the second hollow microspheres  214  within the second layer  204  is different than a composition of the first hollow microspheres  212  within the first layer  202 . For example, a composition of the second hollow microspheres  214  are selected to provide higher insulative, conductive, and/or noise/impact attenuating properties than the insulative, conductive, and/or noise/impact attenuating properties of the composition of the first hollow microspheres  212 . Accordingly, the first layer  202  can have varying properties, such as insulative, conductive, and/or noise/impact attenuating properties, from the second layer  204 . 
     In yet another example, a size of the second hollow microspheres  214  within the second layer  204  is different than a size of the first hollow microspheres  212  within the first layer  202 . Accordingly, the first layer  202  can have a varying insulative, conductive, and/or noise/impact attenuating properties from the second layer  204 . 
     Referring back to  FIGS.  7  to  10   , the multilayered material system  10  further includes a barrier coating  300  on a surface of the multilayered composite  200  to protect against environmental exposure and increase emissivity. The barrier coating  300  can have a variety of architectures, compositions, and thicknesses. 
     The cellular sandwich panel  100  and a multilayered composite  200  are joined together by a variety of methods to form joint  400 , exemplary methods including welding, brazing, diffusion bonding, and fastening. In a specific example, the cellular sandwich panel  100  and a multilayered composite  200  are joined together to form joint  400  using a compositionally graded braze joint. In an example, the compositionally graded braze joint includes a first brazing layer adjacent to the cellular sandwich panel  100  and a second brazing layer adjacent to the multilayered composite  200 , wherein the first brazing layer has a coefficient of thermal expansion that is compatible with the cellular sandwich panel  100  and the second brazing layer has a coefficient of thermal expansion that is compatible with the multilayered composite  200 . In additional, the compositionally-graded braze joint can include third or additional brazing layer intermediate to the first brazing layer and second brazing layer having coefficients of thermal expansion that are intermediate to the coefficient of thermal expansion of the first brazing layer and the second brazing layer. Thus, the compositionally-graded braze joint can accommodate a coefficient of thermal expansion mismatch between the cellular sandwich panel  100  and a multilayered composite  200 . 
     Although the multilayered material system  10  is illustrated in a planar configuration, the overall form of the multilayered material system  10  can vary. For example, curved or complex curved surfaces of acreage skin structure, engine inlet structure, leading edge structure, control surface structure, thermo-mechanical isolator structure, or integrated thermal protection systems for internal cold components can be formed from multilayered material system  10 . 
       FIG.  11    is flow diagram representing a method  600  for manufacturing the multilayered composite  200  of  FIG.  6   . The method  600  includes, at block  610 , providing a first layer of a first powder having first hollow microspheres  212  dispersed therein, and at block  620 , providing a second layer of a second powder adjacent the first layer of first powder, the second layer of second powder having second hollow microspheres  214  dispersed therein. The method  600  further includes, at block  630 , heating the first layer of first powder and the second layer of second powder. The heating can occur under various levels of sustained stress and for various durations. 
     In an example, a melting point or thermal microstructural stability point of the second layer of second powder is greater than a melting point or thermal microstructural stability point of the first layer of first powder. According, a multilayered composite  200  can be provided with a thermal protection gradient functionality as previously described above. 
     In another example, a volume fraction of hollow microspheres within the second layer of second powder is higher than a volume fraction of hollow microspheres within the first layer of first powder. According, a multilayered composite  200  can be provided with a graded spatial distribution of the hollow microspheres  210  dispersed within a metallic matrix material  220 , as previously described. 
     The first layer of first powder having first hollow microspheres  212  dispersed therein and the second layer of second powder having second hollow microspheres  214  dispersed therein may be provided in various ways. In an example, the first hollow microspheres  212  and second hollow microspheres  214  are pre-mixed into respective first powder and second powder. In another example, the first powder are provided as a first layer in a tool and then the first hollow microspheres  212  are placed within the first layer and the second powder are provided as a second layer in the tool and then the second hollow microspheres  214  are placed within the second layer. 
     The second layer of second powder can be placed adjacent to the first layer of first powder by a variety of methods. In an example, the first layer of first powder is provided to a tool and then pressed with or without heat. Then the second layer of second powder is provided to the tool on the first layer and then pressed and heated together with the first layer of first powder. In another example, the first layer of first powder is provided to a tool and then an interlayer material, such an interlayer foil or interlayer mesh, is provided on the first layer. Then, the second layer of second powder is provided to the tool on the interlayer material and heated together with the first layer of first powder and the interlayer material. In yet another example, a mold is provided with an interlayer barrier separating a first compartment and second compartment. The first layer of first powder is provided to the first compartment and the second layer of second powder is provided to the second compartment, and then the first layer and second layer are heated together with the interlayer barrier. Thus, the first layer of first powder and second layer of second powder may be placed adjacent to each in various configurations. 
     In an example, heating the first layer of first powder and the second layer of second powder includes heating the first layer of first powder and the second layer of second powder to a sintering temperature. The heating may include a consolidation process, such as hot isostatic pressing, spark plasma sintering, or cold isostatic pressing and sintering. In another example, heating the first layer of first powder and the second layer of second powder includes heating the first layer of first powder and the second layer of second powder to a heat treatment temperature. 
     In an aspect, the first layer or the second layer are sintered, consolidated, or heat treated prior to a providing of the other of the first layer or the second layer. For example, the second layer of second powder can have a processing temperature, such as a sintering temperature, consolidation temperature, or heat treatment temperature, that is higher than a melting point or thermal microstructural stability point of the first layer of first powder. Thus, the second layer of second powder can be processed prior to providing of the first layer of first powder, then the first layer of first powder can be subject to processing, such as sintering, consolidation, or heat treatment. Accordingly, a multilayered composite  200  can be provided with a thermal protection gradient functionality as previously described above by separate processing of the first layer of first powder and second layer of second powder. 
       FIG.  12    is a flow diagram representing a method  700  for manufacturing the multilayered material system  10  of  FIG.  6   . The method  700  includes, at block  710 , providing a first layer of a first powder having first hollow microspheres  212  dispersed therein, at block  720 , providing a second layer of a second powder adjacent the first layer of first powder, the second layer of second powder having second hollow microspheres  214  dispersed therein, and, at block  730 , sintering the first layer of first powder and the second layer of second powder. The method  700  further includes, at block  740 , providing at least one of a liner sheet and a cellular core, and, at block  750 , joining the first layer of sintered first powder to the at least one of a liner sheet and cellular core. In some implementations, the first layer of first powder and the second layer of second powder are sintered under necessary stress for necessary length of time. 
     In an example, a melting point or thermal microstructural stability point of the second layer of second powder is greater than a melting point or thermal microstructural stability point of the first layer of first powder. According, a multilayered composite  200  can be provided with a thermal protection gradient functionality as previously described above. 
     In another example, a volume fraction of hollow microspheres within the second layer of second powder is higher than a volume fraction of hollow microspheres within the first layer of first powder. According, a multilayered composite  200  can be provided with a graded spatial distribution of the hollow microspheres  210  dispersed within a metallic matrix material  220 , as previously described. 
     The first layer of first powder having first hollow microspheres  212  dispersed therein and the second layer of second powder having second hollow microspheres  214  dispersed therein may be provided in various ways. In an example, the first hollow microspheres  212  and second hollow microspheres  214  are pre-mixed into respective first powder and second powder. In another example, the first powder are provided as a first layer in a tool and then the first hollow microspheres  212  are placed within the first layer and the second powder are provided as a second layer in the tool and then the second hollow microspheres  214  are placed within the second layer. 
     The second layer of second powder can be placed adjacent to the first layer of first powder by a variety of methods. In an example, the first layer of first powder is provided to a tool and then pressed with or without heat. Then the second layer of second powder is provided to the tool on the first layer and then pressed and heated together with the first layer of first powder. In another example, the first layer of first powder is provided to a tool and then an interlayer material, such an interlayer foil or interlayer mesh, is provided on the first layer. Then, the second layer of second powder is provided to the tool on the interlayer material and heated together with the first layer of first powder and the interlayer material. In yet another example, a mold is provided with an interlayer barrier separating a first compartment and second compartment. The first layer of first powder is provided to the first compartment and the second layer of second powder is provided to the second compartment, and then the first layer and second layer are heated together with the interlayer barrier. Thus, the first layer of first powder and second layer of second powder may be placed adjacent to each in various configurations. 
     In an example, the sintering the first layer of first powder and the second layer of second powder includes a consolidation process, such as hot isostatic pressing, spark plasma sintering, or cold isostatic pressing and sintering. 
     In an aspect, the first layer or the second layer are sintered prior to a providing of the other of the first layer or the second layer. For example, the second layer of second powder can have a sintering temperature that is higher than a melting point or thermal microstructural stability point of the first layer of first powder. Thus, the second layer of second powder can be sintered prior to providing of the first layer of first powder, then the first layer of first powder can be subject to sintering. Accordingly, a multilayered composite  200  can be provided with a thermal protection gradient functionality as previously described above by separate processing of the first layer of first powder and second layer of second powder. 
     The cellular sandwich panel  100  can take a variety of forms at previously described and may be formed according to a variety of methods. In an example, the step of providing the at least one of a liner sheet and cellular core includes, at block  742 , and a step of providing a first liner sheet  110 , at block  744 , a step of providing a second liner sheet  120 . The step of providing the at least one of a liner sheet and cellular core further includes, at block  746 , providing one or more third liner sheets  132  between the first liner sheet  110  and the second liner sheet  120 , and, at block  748 , superplastically forming and diffusion bonding the one or more third liner sheets to the first liner sheet and the second liner sheet. 
     The step of joining the first layer of sintered first powder to the at least one of a liner sheet and cellular core may be performed by a variety of methods. Exemplary methods include welding, brazing, diffusion bonding, and fastening. In a specific example, the at least one of a liner sheet and cellular core and a multilayered composite  200  are joined together to form joint  400  using a compositionally-graded braze joint. In an example, the step of joining the first layer of sintered first powder to the at least one of a liner sheet and cellular core includes providing a first brazing layer adjacent to the at least one of a liner sheet and cellular core and a second brazing layer adjacent to the multilayered composite  200 . The first brazing layer can have a coefficient of thermal expansion that is compatible with the cellular sandwich panel  100  and the second brazing layer can have a coefficient of thermal expansion that is compatible with the multilayered composite  200 . In additional, the compositionally-graded braze joint can include third or additional brazing layer intermediate to the first brazing layer and second brazing layer having coefficients of thermal expansion that are positioned intermediate to the coefficient of thermal expansion of the first brazing layer and the second brazing layer. Thus, the compositionally-graded braze joint can accommodate a coefficient of thermal expansion mismatch between the at least one of a liner sheet and cellular core and a multilayered composite  200 . 
     The above description describes numerous materials. It should be understood that “metal/metallic” includes “metals and metal matrix composites”; “ceramic” includes “ceramics and ceramic matrix composites”; and “hybrid metal-ceramic” includes “metal-ceramic hybrid and metal matrix composite/ceramic matrix composite hybrid”. Also, metallic bases include aluminum and aluminum alloys/metal matrix composites; titanium and titanium alloys/metal matrix composites; superalloys (including iron and iron alloys/metal matrix composites, nickel and nickel alloys/metal matrix composites, cobalt and cobalt alloys/metal matrix composites); refractory metals and alloys/metal matrix composites; copper and copper alloys/metal matrix composites; precious metals and alloys/metal matrix composites; zirconium and hafnium and their alloys/metal matrix composites; intermetallics; complex concentrated alloys/metal matrix composites (high entropy alloys/metal matrix composites, medium entropy alloys/metal matrix composites, multicomponent alloys/metal matrix composites). 
     It should be apparent that each of the graded multilayered composite  1100  of  FIG.  1   , the graded multilayered material system  1200  of  FIG.  2   , the multilayered material systems  1300   a - 1300   g  of  FIGS.  3 A- 3 E , and the multilayered material systems  10  of  FIGS.  7 - 10    disclosed herein comprises either a tuned multilayered composite or a multilayered material system that can operate under stringent thermomechanical loading requirements, such as on an aircraft. 
     Examples of the present disclosure may be described in the context of an aircraft manufacturing and service method  1000 , as shown in  FIG.  13   , and an aircraft  1002 , as shown in  FIG.  14   . During pre-production, the aircraft manufacturing and service method  1000  may include specification and design  1004  of the aircraft  1002  and material procurement  1006 . During production, component/subassembly manufacturing  1008  and system integration  1010  of the aircraft  1002  takes place. Thereafter, the aircraft  1002  may go through certification and delivery  1012  in order to be placed in service  1014 . While in service by a customer, the aircraft  1002  is scheduled for routine maintenance and service  1016 , which may also include modification, reconfiguration, refurbishment and the like. 
     Each of the processes of method  1000  may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limitation any number of venders, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on. 
     Any combination of the graded multilayered composite  1100  of  FIG.  1   , the graded multilayered material system  1200  of  FIG.  2   , the multilayered material systems  1300   a - 1300   g  of  FIGS.  3 A- 3 E , and the multilayered material systems  10  of  FIGS.  7 - 10    may be employed during any one or more of the stages of the aircraft manufacturing and service method  1000 , including specification and design  1004  of the aircraft  1002 , material procurement  1006 , component/subassembly manufacturing  1008 , system integration  1010 , certification and delivery  1012 , placing the aircraft in service  1014 , and routine maintenance and service  1016 . 
     As shown in  FIG.  14   , the aircraft  1002  produced by example method  1000  may include an airframe  1018  with a plurality of systems  1020  and an interior  1022 . Examples of the plurality of systems  1020  may include one or more of a propulsion system  1024 , an electrical system  1026 , a hydraulic system  1028 , and an environmental system  1030 . Any number of other systems may be included. The multilayered material system  10  of the present disclosure may be employed for any of the systems of the aircraft  1002 . 
     Although various examples of the disclosed multilayered material systems and multilayered composites have been shown and described, modifications may occur to those skilled in the art upon reading the specification. The present application includes such modifications and is limited only by the scope of the claims.