# US 10,871,360 B1 · Method for cooling missiles > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,871,360 B1 - Document ID: US10871360B1 - Status: Granted - Kind: B1 - Application number: 15/911,065 - Filed: 2018-03-02 - Granted: 2020-12-22 - Earliest claimed: 2017-03-02 - Applicants: Herbert U. Fluhler - Inventors: Herbert U. Fluhler - Web page: https://patentgrep.com/patent/US10871360B1 ## CPC - B64D 7/08: Arrangement of rocket launchers - F42B 15/34: Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements {(thermal protection fitted in or to cosmonautic vehicles B64G1/58)} - B64F 5/50: Handling or transporting aircraft components - F25B 21/02: using Peltier effect; using Nernst-Ettinghausen effect - F41F 3/04: for rockets - F41F 3/055: Umbilical connecting means {(means for facilitating disengagement of electric line connector coupling parts in general H01R13/633)} - B64D 13/006: {the air being used to cool structural parts of the aircraft} - F25B 2321/02: using Peltier effects; using Nernst-Ettinghausen effects - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F42B: EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION (explosive compositions C06B; fuzes F42C; blasting F42D) - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - F25B: REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS - F41F: APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS (smallarms F41C); LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS (functional features or details common to both smallarms and ordnance, mountings therefor F41A; projecting missiles without use of explosive or combustible propellant charge F41B) ## Abstract A system and method for cooling a missile includes an assembly of Peltier tiles configured to be reversibly attached to the skin of the missile with the cold sides of the Peltier tiles against the skin. The Peltier tiles are electrically powered to cool a portion of the missile skin. A thermally conductive paste or sheets of a heat conductive material may be placed between the Peltier tiles and missile skin. When the missile is launched, the assembly of Peltier tiles detach from the missile. ## Claims ### Claim 1 A method for cooling at least a portion of a stationary missile in a ready-to launch standby mode of operation, said method comprising: applying a cold side of a cooling assembly comprising a plurality of Peltier cooling tiles to an application site in apposition to, or in contact with, the skin of the missile under which a component of the missile is to be cooled while the missile is in said ready to launch standby state; attaching the cooling assembly to the application site using attaching means to retain the cooling assembly at the application site; electrically powering the cooling assembly to cool the application site, thereby cooling the component of the missile to be cooled; and connecting a detaching means to the cooling assembly such that, upon a launch of the missile, the cooling assembly is removed from the application site without interfering with the launch of the missile; wherein said attaching means are configured to retain the cooling assembly at the application site during transport and handling of the missile and said detaching means are configured to detach the cooling assembly from the application site during a launch of the missile. ### Claim 2 (depends on 1) The method of claim 1, further comprising assembling the plurality of Peltier cooling tiles into the cooling assembly. ### Claim 3 (depends on 1) The method of claim 1, wherein the cooling assembly conforms to a curved surface on the skin of the missile. ### Claim 4 (depends on 1) The method of claim 1, wherein the plurality of Peltier cooling tiles are in direct contact with the skin of the missile. ### Claim 5 (depends on 1) The method of claim 1, wherein the cooling assembly comprises a frame or holder that holds the plurality of Peltier cooling tiles in a shape that conforms to a shape of the application site. ### Claim 6 (depends on 1) The method of claim 1, wherein the application site faces a launch rail for guiding said missile during launch and the cooling assembly is retained within a space between the missile and the launch rail by said attaching means. ### Claim 7 (depends on 1) The method of claim 1, further comprising applying a thermal paste or a metal foil to either the application site or to the cold side of the cooling assembly before applying the cold side of the cooling assembly to the application site. ### Claim 8 (depends on 7) The method of claim 7, comprising applying a thermal paste to either the application site or to the cold side of the cooling assembly before applying the cold side of the cooling assembly to the application site and wherein the thermal paste acts as an adhesive attaching means. ### Claim 9 (depends on 1) The method of claim 1, wherein said electrically powering the cooling assembly is provided by electrical connection of the cooling assembly to an umbilical cord of the missile and said umbilical cord acts as the detaching means. ### Claim 10 (depends on 1) The method of claim 1, wherein said electrically powering the cooling assembly is provided by electrical connection of the cooling assembly to a power cord configured for, and comprising a tensile strength sufficient, to pull the cooling assembly off of the application site when the missile is launched. ### Claim 11 (depends on 1) The method of claim 1, wherein the detaching means comprises an anchored cord having sufficient tensile strength to pull the cooling assembly from the application site. ### Claim 12 (depends on 1) The method of claim 1, wherein the plurality of Peltier cooling tiles are contained within a heat conductive mesh that holds the cooling tiles together in a flexible assembly that is applied at the application site. ### Claim 13 (depends on 1) The method of claim 1, wherein the cooling assembly comprises a plurality of Peltier cooling tiles cast as a solid assembly in a rigid matrix material to conform to a surface of the application site. ### Claim 14 (depends on 13) The method of claim 13, wherein the rigid matrix material comprises an epoxy resin, fiberglass, a rubber, metal particles, or combinations of these.