# US 2025/0368317 A1 · Systems, methods, and devices for operation of a vehicle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2025/0368317 A1 - Document ID: US20250368317A1 - Status: Published application - Kind: A1 - Application number: 18/872,192 - Filed: 2023-08-04 - Published: 2025-12-04 - Earliest claimed: 2022-08-05 - Assignees: Supernal, LLC - Applicants: Supernal, LLC - Inventors: Awais RAZA; Benjamin Douglas NARAVAGE; Martin Wesley SHUBERT, JR.; Sean Patrick PITONIAK; Jonathan TOTH; David GUERRERO - Web page: https://patentgrep.com/patent/US20250368317A1 ## CPC - B64C 13/042: {operated by hand} - B64C 13/0421: {control sticks for primary flight controls} - B64C 13/24: Transmitting means - B64C 13/503: {Fly-by-Wire} - B64C 29/0025: {the propellers being fixed relative to the fuselage} - B64C 29/0033: {the propellers being tiltable relative to the fuselage} - B64D 31/04: actuated personally - B64D 31/16: for electric power plants - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT ## Abstract The present disclosure generally provides for a control system for controlling an aircraft. The control system may comprise an input device configured to be manipulated by a user, the input device having a first orientation and a second orientation, at least one rotor, at least one control surface; and a controller coupled with the input device, the at least one rotor, and the at least one control surface. The controller may be configured to determine a speed profile of the aircraft, determine the orientation of the input device, send a command to the at least one rotor and/or the at least one control surface based in part on the speed profile and the orientation of the input device; and adjust the at least one rotor and/or the at least one control surface. ## Claims ### Claim 1 An aircraft control system for controlling an aircraft at a first speed and a second speed comprising: an input device configured to be manipulated by a user, the input device having a first orientation and a second orientation; at least one rotor operably coupled to a body of the aircraft; at least one control surface operably coupled to the body of the aircraft; and a controller coupled with the input device, the at least one rotor, and the at least one control surface, wherein the controller is configured to: determine a speed profile of the aircraft based on a speed which the aircraft is traveling; determine whether the input device is in the first orientation or the second orientation; send a command to one or both of the at least one rotor and the at least one control surface based at least in part on the speed profile and the orientation of the input device; and adjust at least one of the at least one rotor or the at least one control surface. ### Claim 2 (depends on 1) The aircraft control system of claim 1, wherein, when the aircraft is in the speed profile corresponding to a first speed and the input device is in the first orientation, a first command is sent to the at least one rotor and/or the at least one control surface. ### Claim 3 (depends on 2) The aircraft control system of claim 2, wherein, when the aircraft is in the speed profile corresponding to a second speed and the input device is in the first orientation, a second command is sent to the at least one rotor and/or the at least one control surface. ### Claim 4 (depends on 3) The aircraft control system of claim 3, wherein, when the aircraft is in the speed profile corresponding to the first speed and the input device is in the second orientation, a third command is sent to the at least one rotor and/or the at least one control surface. ### Claim 5 (depends on 4) The aircraft control system of claim 4, wherein, when the aircraft is in the speed profile corresponding to the second speed and the input device is in the second orientation, a fourth command is sent to the at least one rotor and/or the at least one control surface. ### Claim 6 (depends on 5) The aircraft control system of claim 5, wherein each of the first command, the second command, the third command, and the fourth command are different from each other. ### Claim 7 (depends on 5) The aircraft control system of claim 5, wherein the first command and the second command are the same, and the third command and the fourth command are different from the first command and the second command. ### Claim 8 (depends on 7) The aircraft control system of claim 7, wherein the third command and the fourth command are different from one another. ### Claim 9 (depends on 5) The aircraft control system of claim 5, further comprising a speed profile corresponding to a third speed; and wherein, when the input device is in the first orientation and the controller has determined that the aircraft is in the speed profile corresponding to the third speed, a fifth command is sent to the at least one rotor and/or at least one control surface. ### Claim 10 (depends on 1) The aircraft control system of claim 1, wherein the input device is two input devices. ### Claim 11 (depends on 10) The aircraft control system of claim 10, wherein the controller is further configured to: determine the orientation of the first input device; determine the orientation of the second input device; and send a command to the at least one rotor and/or the at least one control surface based on the speed profile and the orientation of the first input device and the orientation of the second input device. ### Claim 12 (depends on 10) The aircraft control system of claim 10, wherein the two input devices are a first inceptor and a second inceptor. ### Claim 13 (depends on 1) The aircraft control system of claim 1, wherein the second orientation of the input device is different from the first orientation of the input device. ### Claim 14 An aircraft control system, comprising: a first input device and a second input device, wherein each of the first input device and the second input device is configured to be manipulated by a user, the first input device and the second input device each having a first orientation and a second orientation different from the first orientation; at least one rotor operatively connected with a body of an aircraft; at least one control surface operatively connected to the body of the aircraft; a controller electrically coupled with the first input device, the second input device, the at least one rotor, and the at least one control surface, wherein the controller is configured to: determine a speed profile of the aircraft based on a speed of the aircraft; determine an orientation of the first input device; determine an orientation of the second input device; send a command to the at least one rotor and/or the at least one control surface based on the speed profile and the orientation of the first input device and the orientation of the second input device; and adjust the at least one rotor and/or the at least one control surface. ### Claim 15 (depends on 14) The aircraft control system of claim 14, wherein the first input device is a first inceptor and the second input device is a second inceptor. ### Claim 16 (depends on 14) The aircraft control system of claim 14, wherein, when the aircraft is in a first speed profile, the first input device is in the first orientation and the second input device is in the first orientation, a first command is sent to the at least one rotor and/or the at least one control surface. ### Claim 17 (depends on 16) The aircraft control system of claim 16, wherein, when the aircraft is in the first speed profile, the first input device is in the first orientation and the second input device is in the second orientation, a second command is sent to the at least one rotor and/or the at least one control surface. ### Claim 18 (depends on 17) The aircraft control system of claim 17, wherein, when the aircraft is in a second speed profile, the first input device is in the first orientation, and the second input device is in the second orientation, a third command is sent to the at least one rotor and/or the at least one control surface. ### Claim 19 (depends on 18) The aircraft control system of claim 18, further comprising a third speed profile; and wherein, when the input device is in the first orientation and the controller has determined that the aircraft is in the third speed profile, a fourth command is sent to the at least one rotor and/or the at least one control surface. ### Claim 20 (depends on 14) The aircraft control system of claim 14, wherein the first input device provides planform control of the aircraft and the second input device provides flight path angle control of the aircraft.