# US 10,479,510 B2 · Modular environmental control chamber > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,479,510 B2 - Document ID: US10479510B2 - Status: Granted - Kind: B2 - Application number: 15/292,102 - Filed: 2016-10-12 - Published: 2018-04-12 - Granted: 2019-11-19 - Earliest claimed: 2016-10-12 - Assignees: The Boeing Company - Applicants: The Boeing Company - Inventors: Khashayar Borumand; David C. Hass; Randall S. Smith; Karl E. Schuster - Web page: https://patentgrep.com/patent/US10479510B2 ## CPC - B64F 5/60: Testing or inspecting aircraft components or systems - F25D 15/00: Devices not covered by group F25D11/00 or F25D13/00, e.g. non-self-contained movable devices - B64C 1/00: Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like - 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 - F25D: REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR (refrigerated showcases A47F3/04; thermally-insulated vessels for domestic use A47J41/00; refrigerated vehicles, see the appropriate subclasses of classes B60 - B64; containers with thermal insulation in general B65D81/38; heat-transfer, heat-exchange or heat-storage materials, e.g. refrigerants, or materials for the production of heat or cold by chemical reactions other than by combustion C09K5/00; thermally-insulated vessels for liquefied or solidified gases F17C; air-conditioning or air-humidification F24F; refrigeration machines, plants, or systems F25B; cooling of instruments or comparable apparatus without refrigeration G12B) - B64C: AEROPLANES; HELICOPTERS ## Abstract An example modular environmental control chamber (MECC) includes an outer chamber formed by an outer chamber housing section enclosing an outer face of a section of fuselage and an inner chamber formed by an inner chamber housing section enclosing an inner face of the section of fuselage. An outer chamber airflow delivery and return system includes an outer chamber blower for directing temperature-controlled air to the outer chamber through an air inflow aperture of the outer chamber housing section and an outer chamber air return duct connected to an air outflow aperture of the outer chamber housing section. An inner chamber airflow delivery and return system includes an inner chamber blower for directing humidity-controlled air to the inner chamber through an air inflow aperture of the inner chamber housing section and an inner chamber air return duct connected to an air outflow aperture of the inner chamber housing section. ## Claims ### Claim 1 A modular environmental control chamber (MECC) comprising: an outer chamber formed by an outer chamber housing section enclosing an outer face of a section of fuselage, and wherein the outer chamber housing section comprises an air inflow aperture and an air outflow aperture; an inner chamber formed by an inner chamber housing section enclosing an inner face of the section of fuselage, wherein the inner chamber housing section comprises an air inflow aperture and an air outflow aperture, wherein the section of fuselage separates the outer chamber and the inner chamber, and wherein the outer chamber housing section and the inner chamber housing section are connected to form an outer boundary of the MECC; an outer chamber airflow delivery and return system comprising i) an outer chamber blower for directing temperature-controlled air to the outer chamber through the air inflow aperture of the outer chamber housing section and ii) an outer chamber air return duct connected to the air outflow aperture of the outer chamber housing section; and an inner chamber airflow delivery and return system comprising i) an inner chamber blower for directing humidity-controlled air to the inner chamber through the air inflow aperture of the inner chamber housing section and ii) an inner chamber air return duct connected to the air outflow aperture of the inner chamber housing section. ### Claim 2 (depends on 1) The MECC of claim 1, wherein the air inflow aperture of the outer chamber housing section is in fluid connection with an air inflow manifold on an inner surface of the outer chamber housing section, wherein the air inflow manifold comprises a first plurality of openings positioned to direct airflow from the air inflow aperture across the outer face of the section of fuselage toward the air outflow aperture of the outer chamber housing section. ### Claim 3 (depends on 2) The MECC of claim 2, wherein the first plurality of openings is positioned to direct airflow approximately tangential to the outer face of the section of fuselage. ### Claim 4 (depends on 1) The MECC of claim 1, wherein the air outflow aperture of the outer chamber housing section is in fluid connection with an air outflow manifold on an inner surface of the outer chamber housing section, and wherein the air outflow manifold comprises a second plurality of openings. ### Claim 5 (depends on 1) The MECC of claim 1, wherein the outer chamber airflow delivery and return system comprises a refrigerant for cooling the temperature-controlled air that is directed to the outer chamber through the air inflow aperture of the outer chamber housing section. ### Claim 6 (depends on 5) The MECC of claim 5, wherein the refrigerant comprises liquid nitrogen. ### Claim 7 (depends on 1) The MECC of claim 1, wherein the inner chamber airflow delivery and return system comprises a humidifier for conditioning the humidity-controlled air that is directed to the inner chamber through the air inflow aperture of the inner chamber housing section. ### Claim 8 (depends on 1) The MECC of claim 1, wherein the inner chamber airflow delivery and return system further comprises a dehumidifier for conditioning the humidity-controlled air that is directed to the inner chamber through the air inflow aperture of the inner chamber housing section. ### Claim 9 (depends on 1) The MECC of claim 1, wherein the air inflow aperture of the inner chamber is in fluid connection with an air inflow manifold within the inner chamber, and wherein the air inflow manifold comprises a first plurality of openings. ### Claim 10 (depends on 9) The MECC of claim 9, wherein the air outflow aperture of the inner chamber is in fluid connection with an air outflow manifold within the inner chamber, and wherein the air outflow manifold comprises a second plurality of openings. ### Claim 11 (depends on 1) The MECC of claim 1, wherein the outer face of the section of fuselage is convex, and wherein the outer chamber housing section is approximately parallel to the outer face of the section of fuselage. ### Claim 12 (depends on 11) The MECC of claim 11, wherein the outer chamber comprises an approximately uniform depth between the outer face of the section of fuselage and an inner surface of the outer chamber housing section, and wherein the depth is within a range of two to ten inches. ### Claim 13 (depends on 1) The MECC of claim 1, wherein the inner chamber housing section and the outer chamber housing section are removably connected. ### Claim 14 (depends on 1) The MECC of claim 1, wherein the section of fuselage encompasses an arc spanning at least ninety degrees. ### Claim 15 A method of assembling a modular environmental control chamber (MECC) comprising: connecting an inner chamber housing section to a section of fuselage, wherein the inner chamber housing section and an inner face of the section of fuselage form an inner chamber, and wherein the inner chamber housing section comprises an air inflow aperture and an air outflow aperture; connecting an outer chamber housing section to the inner chamber housing section such that an outer face of the section of fuselage and the outer chamber housing section form an outer chamber, wherein the section of fuselage separates the inner chamber and the outer chamber, wherein the outer chamber housing section comprises an air inflow aperture and an air outflow aperture, and wherein the outer chamber housing section and the inner chamber housing section form an outer boundary of the MECC; connecting, to the air inflow aperture of the outer chamber housing section, an outer chamber airflow delivery and return system comprising an outer chamber blower for directing temperature-controlled air to the outer chamber through the air inflow aperture of the outer chamber housing section; and connecting, to the air inflow aperture of the inner chamber housing section, an inner chamber airflow delivery and return system comprising an inner chamber blower for directing humidity-controlled air to the inner chamber through the air inflow aperture of the inner chamber housing section. ### Claim 16 (depends on 15) The method of claim 15, further comprising: connecting an outer chamber air return duct to the air outflow aperture of the outer chamber housing section; and connecting an inner chamber air return duct to the air outflow aperture of the inner chamber housing section. ### Claim 17 (depends on 15) The method of claim 15 further comprising: connecting an air inflow manifold to the inner surface of the outer chamber housing section such that the air inflow manifold is in fluid connection with the air inflow aperture of the outer chamber housing section, wherein the air inflow manifold comprises a plurality of openings positioned to direct airflow from the air inflow aperture across the outer face of the section of fuselage toward the air outflow aperture of the outer chamber housing section. ### Claim 18 A method of simulating environmental conditions in an aircraft comprising: directing temperature-controlled air into an outer chamber through an air inflow aperture of an outer chamber housing section, wherein the outer chamber housing section encloses an outer face of a section of fuselage thereby forming the outer chamber, and wherein the temperature-controlled air is directed across the outer face of the section of fuselage toward an air outflow aperture in the outer chamber housing section; and directing humidity-controlled air into an inner chamber through an air inflow aperture of an inner chamber housing section, wherein the inner chamber housing section encloses an inner face of the section of fuselage thereby forming the inner chamber, wherein the section of fuselage separates the outer chamber and the inner chamber, wherein the inner chamber housing section comprises an air outflow aperture through which the humidity-controlled air is drawn from the inner chamber, and wherein the outer chamber housing section and the inner chamber housing section are connected to form an outer boundary of a modular environmental control chamber. ### Claim 19 (depends on 18) The method of claim 18 comprising: determining a condensation rate of moisture in the inner chamber. ### Claim 20 (depends on 19) The method of claim 19 wherein determining the condensation rate of moisture in the inner chamber comprises determining a rate of frost build-up in the inner chamber.