# US 2019/0315487 A1 · System to accelerate and decelerate aircraft for take-off and landing > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0315487 A1 - Document ID: US20190315487A1 - Status: Published application - Kind: A1 - Application number: 16/453,820 - Filed: 2019-06-26 - Published: 2019-10-17 - Earliest claimed: 2014-11-19 - Assignees: The Boeing Company - Applicants: The Boeing Company - Inventors: Brett M. Hoffstadt; William A. Harkness; Royal E. Meservy - Web page: https://patentgrep.com/patent/US20190315487A1 ## CPC - B64F 1/06: using catapults - B64F 1/02: for arresting aircraft, e.g. nets or cables - B64F 1/22: for handling aircraft - Y02T 50/80: Energy efficient operational measures, e.g. ground operations or mission management - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A system for controlling aircraft movement includes a frame extending across a width of a runway. The system includes an attachment mechanism coupled to the frame and configured to be releasably connected to a portion of an aircraft. The system includes a conveying system configured to, with the aircraft coupled to the frame during take-off of the aircraft, accelerate the aircraft. The conveying system is further configured to, during landing of the aircraft, decelerate the aircraft. ## Claims ### Claim 1 A system for controlling aircraft movement, the system comprising: a frame extending across a width of a runway; an attachment mechanism coupled to the frame and configured to be releasably connected to a portion of an aircraft; and a conveying system configured to, with the aircraft coupled to the frame during take-off of the aircraft, accelerate the aircraft, and wherein the conveying system is configured to, during landing of the aircraft, decelerate the aircraft. ### Claim 2 (depends on 1) The system of claim 1, wherein the conveying system is further configured to accelerate the aircraft by moving a platform that is coupled to the aircraft, and wherein the conveying system comprises: a first rail positioned at a first side of the runway; a second rail positioned at a second side of the runway; and a power supply electrically coupled to the first rail and the second rail. ### Claim 3 (depends on 2) The system of claim 2, wherein the platform is configured to be moved within a recess during the take-off of the aircraft and the landing of the aircraft. ### Claim 4 (depends on 2) The system of claim 2, wherein a top surface of the platform is substantially parallel with a surface of a taxiway. ### Claim 5 (depends on 1) The system of claim 1, wherein the conveying system comprises: at least one rail; and a power supply electrically coupled to the at least one rail. ### Claim 6 (depends on 1) The system of claim 1, wherein the conveying system comprises a first rail positioned on a first side of a runway, a second rail positioned on a second side of the runway, and an electrical power supply coupled to the first rail and to the second rail, and further comprising a platform coupled to the frame and to the conveying system. ### Claim 7 (depends on 6) The system of claim 6, wherein the platform comprises a first magnet spaced apart from a second magnet, wherein the first magnet is configured to levitate over the first rail while the electrical power supply supplies electrical energy to the first rail, and wherein the second magnet is configured to levitate over the second rail while the electrical power supply supplies electrical energy to the second rail. ### Claim 8 (depends on 7) The system of claim 7, wherein the electrical power supply is configured to supply power, to the first rail and the second rail, to exert an electromagnetic force on the first magnet and on the second magnet, the electromagnetic force configured to cause linear movement of the platform. ### Claim 9 (depends on 1) The system of claim 1, further comprising a controller, wherein the frame comprises a first component, a second component spaced apart from the first component, and a third component spaced apart from the first component and the second component, wherein the attachment mechanism comprises a first clamp mechanism coupled to the first component, a second clamp mechanism coupled to the second component, and a third clamp mechanism coupled to the third component, and wherein the controller is in communication with the first clamp mechanism, the second clamp mechanism, the third clamp mechanism, and the conveying system. ### Claim 10 (depends on 1) The system of claim 1, wherein the conveying system comprises a propulsion driving mechanism coupled to the frame. ### Claim 11 (depends on 1) The system of claim 1, wherein the frame includes a surface configured to orient the aircraft at an angle with respect to a direction of movement of the frame. ### Claim 12 (depends on 1) The system of claim 1, wherein the attachment mechanism is configured to be coupled to a portion of the aircraft during acceleration or deceleration of the frame and decoupled from the portion of the aircraft to permit the aircraft to lift off of the frame during the take-off of the aircraft. ### Claim 13 (depends on 1) The system of claim 1, wherein the attachment mechanism includes a wheel block configured to be positioned on opposing sides of a wheel of the aircraft. ### Claim 14 (depends on 1) The system of claim 1, further comprising a controller configured to receive data from sensors on the frame and to control an orientation of a top surface of the frame based on the data and based on an orientation of the aircraft during the landing of the aircraft. ### Claim 15 (depends on 14) The system of claim 14, wherein, to facilitate receipt of the aircraft onto the frame, the controller is further configured to move the top surface of the frame based on a pitch, a yaw, a roll, or a combination thereof, of the aircraft. ### Claim 16 A runway system for controlling aircraft movement, the runway system comprising: first and second barriers in a recess that is adjacent to a surface of a taxiway; a platform including a top surface substantially parallel with a surface of the taxiway; and a securing mechanism coupled to the platform and configured to secure an aircraft to the platform during landing of the aircraft. ### Claim 17 (depends on 16) The runway system of claim 16, further comprising a conveying system comprising: multiple rails located in the recess; and an electrical power supply electrically connected to the multiple rails. ### Claim 18 (depends on 16) The runway system of claim 16, wherein the securing mechanism comprises a wheel block configured to be positioned on opposing sides of a wheel of the aircraft. ### Claim 19 (depends on 16) The runway system of claim 16, wherein the platform is configured to be positioned under the aircraft during the landing of the aircraft. ### Claim 20 A method for controlling aircraft movement, the method comprising: moving a frame to match a speed and position of an aircraft, the frame extending across a width of a runway; attaching an attachment mechanism coupled to the frame to a portion of the aircraft; during landing of the aircraft, decelerate the aircraft via a conveying system; and during take-off of the aircraft, accelerate the aircraft.