# US 11,077,627 B2 · Multi-functional protective assemblies, systems including protective assemblies, and related methods > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,077,627 B2 - Document ID: US11077627B2 - Status: Granted - Kind: B2 - Application number: 16/103,428 - Filed: 2018-08-14 - Published: 2019-02-14 - Granted: 2021-08-03 - Earliest claimed: 2017-08-14 - Assignees: Northrop Grumman Systems Corporation - Applicants: Northrop Grumman Systems Corporation - Inventors: Steven F. Stone; Matt Armentrout; Christopher Deemer; Carl Madsen; Brian Barber - Web page: https://patentgrep.com/patent/US11077627B2 ## CPC - B29C 66/73754: {the to-be-joined areas of both parts to be joined being partially cured} - B29C 66/71: {characterised by the composition of the plastics material of the parts to be joined (welding bar compositions B29C65/125)} - B29C 66/721: {Fibre-reinforced materials (B29C66/729 takes precedence)} - B29C 66/72321: {consisting of metals or their alloys} - B29C 66/727: {being porous, e.g. foam} - B29C 66/7314: {Electrical and dielectric properties} - B29C 66/7315: {Mechanical properties} - B29C 66/7392: {characterised by the material of at least one of the parts being a thermoplastic} - B64D 7/00: Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraft; Adaptations of armament mountings for aircraft (dropping bombs or the like B64D1/00) - B64G 1/226: {Special coatings for spacecraft} - B64G 1/54: Protection against radiation - B64G 1/56: Protection against meteoroids or space debris - B64G 1/58: Thermal protection, e.g. heat shields - F41H 5/0435: {the additional layers being only fibre- or fabric-reinforced layers} - F41H 5/0464: {the additional layers being only fibre- or fabric-reinforced layers} - F41H 5/0471: {Layered armour containing fibre- or fabric-reinforced layers (in combination with ceramic layers F41H5/0428, with metal layers F41H5/0457)} - F41H 5/0492: {Layered armour containing hard elements, e.g. plates, spheres, rods, separated from each other, the elements being connected to a further flexible layer or being embedded in a plastics or an elastomer matrix} - B29L 2031/3076: {Aircrafts (blades, propellers B29L2031/08)} - B32B 15/02: {Layer formed of wires, e.g. mesh} - B32B 37/10: characterised by the pressing technique, e.g. using action of vacuum or fluid pressure - B32B 2037/0092: {in which absence of adhesives is explicitly presented as an advantage} - B32B 2274/00: Thermoplastic elastomer material - B32B 2305/022: Foam - B32B 2305/08: Reinforcements - B32B 2305/38: Meshes, lattices or nets - B32B 2305/74: Partially cured - B32B 2307/212: Electromagnetic interference shielding - B32B 2307/306: Resistant to heat - B32B 2307/558: Impact strength, toughness - B32B 2309/12: Pressure - B32B 2309/68: Vacuum - B32B 2323/16: EPDM, i.e. ethylene propylene diene monomer - B32B 2327/18: PTFE, i.e. polytetrafluoroethylene - B32B 2398/20: Thermoplastics - B32B 2605/18: Aircraft - G21F 1/106: {metallic dispersions} - B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR - F41H: ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL - B29L: INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES - B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM - G21F: PROTECTION AGAINST X-RADIATION, GAMMA RADIATION, CORPUSCULAR RADIATION OR PARTICLE BOMBARDMENT; TREATING RADIOACTIVELY CONTAMINATED MATERIAL; DECONTAMINATION ARRANGEMENTS THEREFOR (radiation protection by pharmaceutical means A61K8/00, A61Q17/04; in cosmonautic vehicles B64G1/54; combined with a reactor G21C11/00; combined with X-ray tubes H01J35/16; combined with X-ray apparatus H05G1/02) ## Abstract A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process. ## Claims ### Claim 1 A protective assembly, comprising: a first region comprising a composite of particles and polymer, the first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation; a second region comprising a composite of fibers and polymer, the second region formulated and configured to provide protection from ballistic impact; and a third region comprising a composite of particles, fibers, and polymer, the third region formulated and configured to provide protection from thermal radiation; wherein each of the first region, the second region, and the third region comprises a common polymer. ### Claim 2 (depends on 1) The protective assembly of claim 1, further comprising an additional region comprising at least one of a metallic mesh or a metallic foil, wherein the additional region is formulated and configured to provide protection from at least one of electrostatic discharge and electromagnetic discharge. ### Claim 3 (depends on 2) The protective assembly of claim 2, wherein the at least one of the metallic mesh or the metallic foil comprises at least one of silver, copper, aluminum, nickel, and iron. ### Claim 4 (depends on 2) The protective assembly of claim 2, wherein the additional region comprises the metallic mesh and a polymer, the polymer of the additional region comprising the common polymer of the first region, the second region, and the third region. ### Claim 5 (depends on 2) The protective assembly of claim 2, wherein the common polymer is continuous at a bond interface between adjacent regions of the first region, the second region, the third region, and the additional region to form a substantially indistinct interface therebetween. ### Claim 6 (depends on 2) The protective assembly of claim 2, wherein a bond interface between adjacent regions of the first region, the second region, the third region, and the additional region comprises a chemical bond interface. ### Claim 7 (depends on 2) The protective assembly of claim 2, wherein the first region, the additional region, the second region, and the third region are provided sequentially over an outer surface of an aerospace structure, the first region comprising an innermost region of the protective assembly and the third region comprising an outermost region of the protective assembly. ### Claim 8 (depends on 1) The protective assembly of claim 1, wherein the common polymer comprises an ethylene acrylic elastomer. ### Claim 9 (depends on 8) The protective assembly of claim 8, wherein at least one of the first region, the second region, and the third region comprises an ethylene acrylic elastomer foam. ### Claim 10 (depends on 1) The protective assembly of claim 1, wherein the fibers of the second region and the third region comprise aramid fibers. ### Claim 11 (depends on 1) The protective assembly of claim 1, wherein the particles of the first region comprise particles of a high-Z metal. ### Claim 12 A protective assembly, comprising: a first region comprising a composite of reinforcing material in a matrix material, the first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation; a second region comprising a composite of reinforcing material in a matrix material, the second region formulated and configured to provide protection from ballistic impact; and a third region comprising a composite of particles and fiber in a matrix material, the third region formulated and configured to provide protection from thermal radiation; wherein the matrix material of at least two of the first region, the second region, or the third region comprises a substantially similar material. ### Claim 13 (depends on 12) The protective assembly of claim 12, wherein the matrix material of the at least two of the first region, the second region, and the third region comprises a substantially continuous material at an interface between the at least two of the first region, the second region, and the third region. ### Claim 14 An aerospace structure comprising: an aerospace structure body; and a protective assembly formed on an exterior surface of the aerospace structure body, the protective assembly comprising: a first region comprising a composite of particles and polymer, the first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation; a second region comprising a composite of fibers and polymer, the second region formulated and configured to provide protection from ballistic impact; and a third region comprising a composite of particles, fiber, and polymer, the third region formulated and configured to provide protection from thermal radiation; wherein at least two of the first region, the second region, or the third region comprises a common polymer. ### Claim 15 (depends on 14) The aerospace structure of claim 14, wherein the protective assembly is co-cured such that a chemical bond exists at an interface between adjacent regions of the first region, the second region, and the third region. ### Claim 16 (depends on 14) The aerospace structure of claim 14, wherein the aerospace structure body comprises a fiber-reinforced composite body. ### Claim 17 (depends on 16) The aerospace structure of claim 16, wherein the protective assembly is co-cured to the aerospace structure such that a chemical bond exists at an interface between the aerospace structure body and the protective assembly. ### Claim 18 A method of forming a protective assembly for an aerospace structure, comprising: mounting a protective assembly over an aerospace structure body, the protective assembly comprising: a first region comprising a composite of particles and polymer, the first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation; a second region comprising a composite of fibers and polymer, the second region formulated and configured to provide protection from ballistic impact; and a third region comprising a composite of particles, fiber, and polymer, the third region formulated and configured to provide protection from thermal radiation; wherein the first region, the second region, and the third region are each provided in an at least partially uncured state; and co-curing the protective assembly to form a chemical bond between adjacent regions of the first region, the second region, and the third region and to attach the protective assembly to the aerospace structure body. ### Claim 19 (depends on 18) The method of claim 18, further comprising positioning a fourth region comprising a metallic mesh and polymer over the aerospace structure body, the fourth region formulated and configured to provide protection from electrostatic pulses. ### Claim 20 (depends on 19) The method of claim 19, wherein mounting the protective assembly over the aerospace structure body comprises mounting at least one of the first region, the second region, the third region, and the fourth region to an at least partially uncured fiber-reinforced composite structure using a hand lay-up process. ### Claim 21 (depends on 18) The method of claim 18, further comprising applying a compressive force on the protective assembly toward the aerospace structure body while co-curing the protective assembly. ### Claim 22 (depends on 18) The method of claim 18, further comprising selecting the polymer of each of the first region, the second region, and the third region to comprise an ethylene acrylic elastomer.