# US 12,600,455 B2 · Aircraft cargo door actuation system with first actuator and second actuator > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,600,455 B2 - Document ID: US12600455B2 - Status: Granted - Kind: B2 - Application number: 18/926,793 - Filed: 2024-10-25 - Published: 2025-05-01 - Granted: 2026-04-14 - Earliest claimed: 2023-10-27 - Assignees: Airbus SAS; Airbus Operations GmbH - Applicants: Airbus (S.A.S.); Airbus Operations GmbH; Airbus Operations (S.A.S.) - Inventors: Mayur K V; Nishith Ramaraja; Marc Antonio Bentivoglio; Cristobal Federico Brito Maur; Benoit Thomas; Dominique Grisel; Jayaparthan Jagadeesan; Marco Lutz - Web page: https://patentgrep.com/patent/US12600455B2 ## CPC - B64C 1/1415: {Cargo doors, e.g. incorporating ramps} - B64C: AEROPLANES; HELICOPTERS ## Abstract An actuation system for a cargo door of an aircraft. The cargo door covers an opening into a cargo bay when it is in a closed position. The actuation system includes a first actuator configured to outwardly rotate the cargo door from the closed position to a first open position, and a second actuator configured to outwardly rotate the cargo door from the first open position to a second open position. ## Claims ### Claim 1 An actuation system for a cargo door of an aircraft, the actuation system comprising: a first actuator configured only to outwardly rotate the cargo door by more than 40 degrees from a closed position to a first open position; and a second actuator configured only to outwardly rotate the cargo door from the first open position to a second open position; wherein the cargo door covers an opening into a cargo bay when the cargo door is in the closed position; and wherein the first actuator and the second actuator are configured such that the first and second actuators are not powered simultaneously, such that only one of the first and second actuators operates to move the cargo door at any given time. ### Claim 2 (depends on 1) The actuation system according to claim 1, wherein the first actuator is configured to receive power from a power source that is different and independent from a power source from which the second actuator is configured to receive power. ### Claim 3 (depends on 1) The actuation system according to claim 1, further comprising: a first power source configured to supply power to the first actuator to outwardly rotate the cargo door between the closed position and the first open position; wherein the second actuator is configured to receive power from a second power source to outwardly rotate the cargo door between the first open position and the second open position. ### Claim 4 (depends on 3) The actuation system according to claim 3, wherein the first power source is configured for being carried by the aircraft and the second power source is configured for not being carried by the aircraft. ### Claim 5 (depends on 1) The actuation system according to claim 1, wherein: the first actuator comprises a rotary actuator; and the second actuator comprises a linear actuator. ### Claim 6 (depends on 5) The actuation system according to claim 5, wherein: the linear actuator has: a first end coupled to the rotary actuator; and a second end coupled to the cargo door; the rotary actuator is configured to rotate the cargo door between the closed position and the first open position by moving the first end of the linear actuator; and the linear actuator is configured to rotate the cargo door from the first open position to the second open position by increasing a distance between the first end of the linear actuator and the second end of the linear actuator. ### Claim 7 (depends on 1) The actuation system according to claim 1, wherein the first actuator is configured to receive electrical power from an electrical power source to rotate the cargo door between the closed position and the first open position. ### Claim 8 (depends on 1) The actuation system according to claim 1, wherein the second actuator is configured to receive electrical power from an electrical power source to rotate the cargo door between the first open position and the second open position. ### Claim 9 (depends on 1) The actuation system according to claim 1, wherein the first actuator is configured for being controlled independently of the second actuator. ### Claim 10 (depends on 1) An aircraft comprising: a cargo door; and the actuation system according to claim 1; wherein the actuation system is configured to open the cargo door. ### Claim 11 (depends on 10) The aircraft according to claim 10, further comprising: a body with an opening into a cargo bay of the aircraft; wherein the cargo door covers the opening when the cargo door is in the closed position. ### Claim 12 (depends on 10) The aircraft according to claim 10, further comprising: a first power source configured to supply power to the first actuator to outwardly rotate the cargo door towards the first open position; wherein the second actuator is configured to receive power from a second power source not carried by the aircraft. ### Claim 13 (depends on 10) The aircraft according to claim 10, wherein the first and second actuators are configured to be carried by the aircraft in flight. ### Claim 14 A method of opening a cargo door of an aircraft with an actuation system for the cargo door, the actuation system comprising: a first actuator; and a second actuator: the method comprising: outwardly rotating, using the first actuator, the cargo door by more than 40 degrees, from a closed position to a first open position; then outwardly rotating, using the second actuator, the cargo door from the first open position to a second open position; wherein the cargo door covers an opening into a cargo bay when the cargo door is in the closed position; and wherein the first actuator and the second actuator are not powered simultaneously, such that only one of the first and second actuators operates to move the cargo door at any given time. ### Claim 15 (depends on 14) The method according to claim 14, wherein the first actuator receives power from a power source that is different and independent from a power source from which the second actuator receives power. ### Claim 16 (depends on 14) The method according to claim 14, wherein: the first actuator receives power from a first power source to rotate the cargo door between the closed position and the first open position; and the second actuator receives power from a second power source to rotate the cargo door between the first open position and the second open position. ### Claim 17 (depends on 16) The method according to claim 16, wherein the first power source is carried by the aircraft and the second power source is not carried by the aircraft. ### Claim 18 (depends on 14) The method according to claim 14, wherein the first actuator is controlled independently of the second actuator. ### Claim 19 (depends on 18) The method according to claim 18, wherein: the first actuator is controlled by a first control signal; and the second actuator is controlled by a second control signal. ### Claim 20 An actuation system for a cargo door of an aircraft, the actuation system comprising: a rotary actuator configured to outwardly rotate the cargo door between a closed position and a first open position; and a linear actuator configured to outwardly rotate the cargo door between the first open position and a second open position; wherein the linear actuator has: a first end coupled to the rotary actuator; and a second end coupled to the cargo door; wherein the rotary actuator is configured to rotate the cargo door between the closed position and the first open position by moving the first end of the linear actuator; the linear actuator is configured to rotate the cargo door between the first open position and the second open position by increasing a distance between the first end of the linear actuator and the second end of the linear actuator; and wherein the cargo door covers an opening into a cargo bay when the cargo door is in the closed position.