# US 11,442,470 B2 · Method of and system for displaying an aircraft control input > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,442,470 B2 - Document ID: US11442470B2 - Status: Granted - Kind: B2 - Application number: 16/185,612 - Filed: 2018-11-09 - Published: 2019-03-28 - Granted: 2022-09-13 - Earliest claimed: 2016-05-11 - Assignees: Bombardier Inc. - Applicants: Bombardier Inc. - Inventors: Laurence Casia; Mathieu St-Cyr; Gervais Arel - Web page: https://patentgrep.com/patent/US11442470B2 ## CPC - G05D 1/101: {specially adapted for aircraft} - B64C 13/503: {Fly-by-Wire} - B64D 43/00: Arrangements or adaptations of instruments - B64D 45/00: Aircraft indicators or protectors not otherwise provided for - B64D 45/0005: {Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear} - G01C 23/005: {Flight directors (indicating arrangements specially adapted for rotary gyroscopes G01C19/32)} - G02B 27/01: Head-up displays - B64C 13/04: actuated personally - B64C 13/18: using automatic pilot - G05D: SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES - 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 - G01C: MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY (measuring liquid level G01F; radio navigation, determining distance or velocity by use of propagation effects, e.g. Doppler effects, propagation time, of radio waves, analogous arrangements using other waves G01S) - G02B: OPTICAL ELEMENTS, SYSTEMS OR APPARATUS ## Abstract A method of and a system for displaying an aircraft control input. The method comprises accessing a first indication indicative of an aircraft control input, the aircraft control input being associated with an orientation and an amplitude of the aircraft control input; generating, by a processing unit, a first single visual indication based on the first indication, the first single visual indication being reflective of the orientation and the amplitude of the aircraft control input; and causing the display of the first single visual indication on a display surface, the display of the first single visual indication providing a user viewing the first single visual indication with an understanding of the orientation and the amplitude of the aircraft control input. ## Claims ### Claim 1 A computer-implemented method for displaying an aircraft control input, the method comprising: accessing, from a non-transitory computer-readable medium, a first indication indicative of an aircraft control input, the aircraft control input being associated with an orientation and an amplitude of the aircraft control input; generating, by a processing unit, a first single visual indication based on the first indication, the first single visual indication being reflective of the orientation and the amplitude of the aircraft control input; and causing the display of the first single visual indication on a display surface, the display of the first single visual indication providing a user viewing the first single visual indication with an understanding of the orientation and the amplitude of the aircraft control input, wherein causing the display of the first single visual indication on the display surface is in response to an event relating to the operation of an aircraft, and wherein the event comprises a dual input received from a first aircraft controller and a second aircraft controller, wherein the first single visual indication comprises a dot and the display surface further displays a target-like graphical component, the target-like graphical component comprising circular graphical patterns, and wherein a first input from the first aircraft controller and a second input from the second aircraft controller are displayed simultaneously on the target-like graphical component. ### Claim 2 (depends on 1) The method of claim 1, wherein causing the first single visual indication to be displayed comprises causing the first single visual indication to be displayed in relation to at least one of a graphical amplitude scale and a graphical orientation scale. ### Claim 3 (depends on 1) The method of claim 1, wherein the target-like graphical component is configured to ease understanding of the orientation and the amplitude. ### Claim 4 (depends on 1) The method of claim 1, wherein the orientation is associated with (1) a first axis of the display surface and (2) a second axis of the display surface and the amplitude is associated with (3) a first distance of the first single visual indication to the first axis and (4) a second distance of the first single visual indication to the second axis. ### Claim 5 (depends on 4) The method of claim 4, wherein a first quantitative value is associated with the first axis of the display surface and a second quantitative value is associated with the second axis, the first quantitative value being reflective of a first axis amplitude of the aircraft control input along a longitudinal axis and the second quantitative value being reflective of a second axis amplitude of the aircraft control input along a vertical axis. ### Claim 6 (depends on 5) The method of claim 5, wherein the first quantitative value and the second quantitative value reflect values of the aircraft control input provided to a fly-by-wire system. ### Claim 7 (depends on 6) The method of claim 6, wherein the first quantitative value and the second quantitative value are one of absolute values and relative values. ### Claim 8 (depends on 6) The method of claim 6, wherein the first distance is proportional to the first quantitative value and the second distance is proportional to the second quantitative value. ### Claim 9 (depends on 1) The method of claim 1, wherein the aircraft control input is generated by the first aircraft controller. ### Claim 10 (depends on 9) The method of claim 9, wherein the first aircraft controller is one of a side stick, a yoke, a rudder pedal and an autopilot. ### Claim 11 (depends on 9) The method of claim 9, wherein the first indication indicative of the aircraft control input is a numerical value generated based on a raw digital signal of the first aircraft controller. ### Claim 12 (depends on 1) The method of claim 1, wherein the display surface is at least a part of a multifunction display, a primary flight display and a head-up display. ### Claim 13 (depends on 1) The method of claim 1, wherein causing the display of the first single visual indication on the display surface in response to the event relating to the operation of an aircraft comprises temporarily displaying the first single visual indication on the display surface. ### Claim 14 A computer-implemented method for displaying an aircraft control input, the method comprising: in response to an aircraft control input being inputted via a first aircraft controller, receiving a raw signal from the first aircraft controller; converting, by a processing unit, the raw signal from the first aircraft controller into numerical values, the numerical values being reflective of an orientation and an amplitude of the aircraft control input; generating, by the processing unit, a first single visual indication based on the numerical values; and causing the display of the first single visual indication on a display surface, the display of the first single visual indication providing a user viewing the first single visual indication with an understanding of the orientation and the amplitude of the aircraft control input, wherein causing the display of the first single visual indication on the display surface is in response to an event relating to the operation of an aircraft, and wherein the event comprises a dual input received from the first aircraft controller and a second aircraft controller, wherein the first single visual indication comprises a dot and the display surface further displays a target-like graphical component, the target-like graphical component comprising circular graphical patterns, and wherein a first input from the first aircraft controller and a second input from the second aircraft controller are displayed simultaneously on the target-like graphical component. ### Claim 15 A computer-implemented system for displaying an aircraft control input, the system comprising: a non-transitory computer-readable medium; a processor configured to perform: accessing, from the non-transitory computer-readable medium, a first indication indicative of an aircraft control input, the aircraft control input being associated with an orientation and an amplitude of the aircraft control input; generating, by the processor, a first single visual indication based on the first indication, the first single visual indication being reflective of the orientation and the amplitude of the aircraft control input; and causing the display of the first single visual indication on a display surface, the display of the first single visual indication providing a user viewing the first single visual indication with an understanding of the orientation and the amplitude of the aircraft control input, wherein causing the display of the first single visual indication on the display surface is in response to an event relating to the operation of an aircraft, and wherein the event comprises a dual input received from a first aircraft controller and a second aircraft controller, wherein the first single visual indication comprises a dot and the display surface further displays a target-like graphical component, the target-like graphical component comprising circular graphical patterns, and wherein a first input from the first aircraft controller and a second input from the second aircraft controller are displayed simultaneously on the target-like graphical component. ### Claim 16 (depends on 15) The system of claim 15, wherein causing the first single visual indication to be displayed comprises causing the first single visual indication to be displayed in relation to at least one of a graphical amplitude scale and a graphical orientation scale. ### Claim 17 (depends on 15) The system of claim 15, wherein the first single visual indication is configured to ease the understanding of the orientation and the amplitude. ### Claim 18 (depends on 15) The system of claim 15, wherein the orientation is associated with (1) a first axis of the display surface and (2) a second axis of the display surface and the amplitude is associated with (3) a first distance of the first single visual indication to the first axis and (4) a second distance of the first single visual indication to the second axis. ### Claim 19 (depends on 18) The system of claim 18, wherein a first quantitative value is associated with the first axis of the display surface and a second quantitative value is associated with the second axis, the first quantitative value being reflective of a first axis amplitude of the aircraft control input along a longitudinal axis and the second quantitative value being reflective of a second axis amplitude of the aircraft control input along a vertical axis. ### Claim 20 (depends on 19) The system of claim 19, wherein the first quantitative value and the second quantitative value reflect values of the aircraft control input provided to a fly-by-wire system. ### Claim 21 (depends on 20) The system of claim 20, wherein the first quantitative value and the second quantitative value are one of absolute values and relative values. ### Claim 22 (depends on 19) The system of claim 19, wherein the first distance is proportional to the first quantitative value and the second distance is proportional to the second quantitative value. ### Claim 23 (depends on 15) The system of claim 15, wherein the aircraft control input is generated by the first aircraft controller. ### Claim 24 (depends on 23) The system of claim 23, wherein the first aircraft controller is one of a side stick, a yoke, a rudder pedal and an autopilot. ### Claim 25 (depends on 23) The system of claim 23, wherein the first indication indicative of the aircraft control input is a numerical value generated based on a raw digital signal of the first aircraft controller. ### Claim 26 (depends on 15) The system of claim 15, wherein the display surface is at least a part of a multi-function display, a primary flight display and a head-up display. ### Claim 27 (depends on 15) The system of claim 15, wherein causing the display of the first single visual indication on the display surface in response to the event relating to the operation of an aircraft comprises temporarily displaying the first single visual indication on the display surface. ### Claim 28 A computer-implemented system for displaying an aircraft control input, the system comprising: a non-transitory computer-readable medium; a processor configured to perform: in response to an aircraft control input being inputted via a first aircraft controller, receiving a raw signal from the first aircraft controller; converting, by the processor, the raw signal from the first aircraft controller into numerical values, the numerical values being reflective of an orientation and an amplitude of the aircraft control input; generating, by the processor, a first single visual indication based on the numerical values; and causing the display of the first single visual indication on a display surface, the display of the first single visual indication providing a user viewing the first single visual indication with an understanding of the orientation and the amplitude of the aircraft control input, wherein causing the display of the first single visual indication on the display surface is in response to an event relating to the operation of an aircraft, and wherein the event comprises a dual input received from the first aircraft controller and a second aircraft controller, wherein the first single visual indication comprises a dot and the display surface further displays a target-like graphical component, the target-like graphical component comprising circular graphical patterns, and wherein a first input from the first aircraft controller and a second input from the second aircraft controller are displayed simultaneously on the target-like graphical component.