Apparatuses and systems for controlling autoflight systems
First Claim
1. An apparatus for use with an aircraft having an autoflight system capable of controlling the attitude of the aircraft in pitch, roll and yaw axes, the apparatus comprising:
- an autoflight performance selector configured to limit the response of the autoflight system to flight guidance instructions in at least two of the pitch, roll and yaw axes, the autoflight performance selector having at least a first selection and a second selection different than the first selection, wherein selecting the first selection causes the response of the autoflight system to not exceed a first level angle about a first one of the at least two axes and a second angle about a second one of the at least two axes, and wherein selecting the second selection causes the response of the autoflight system to not exceed a third angle about the first one of the at least two axes and a fourth angle about the second one of the at least two axes.
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Accused Products
Abstract
Apparatuses and methods for controlling autoflight systems are disclosed herein. An apparatus for use with an aircraft having an autoflight system can include an autoflight performance selector configured to limit the response of the autoflight system to flight guidance instructions in at least two of the pitch, roll and yaw axes. The autoflight performance selector has at least a first selection and a second selection different than the first selection. Selecting the first selection causes the response of the autoflight system to flight guidance instructions to not exceed a first level in the at least two axes, and selecting the second selection causes the response of the autoflight system to the flight guidance instructions to not exceed a second level in the at least two axes different than the first level.
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Citations
22 Claims
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1. An apparatus for use with an aircraft having an autoflight system capable of controlling the attitude of the aircraft in pitch, roll and yaw axes, the apparatus comprising:
an autoflight performance selector configured to limit the response of the autoflight system to flight guidance instructions in at least two of the pitch, roll and yaw axes, the autoflight performance selector having at least a first selection and a second selection different than the first selection, wherein selecting the first selection causes the response of the autoflight system to not exceed a first level angle about a first one of the at least two axes and a second angle about a second one of the at least two axes, and wherein selecting the second selection causes the response of the autoflight system to not exceed a third angle about the first one of the at least two axes and a fourth angle about the second one of the at least two axes. - View Dependent Claims (2, 5, 6, 7, 8, 9, 10)
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3. An apparatus for use with an aircraft having an autoflight system capable of controlling the attitude of the aircraft in pitch, roll and yaw axes, the apparatus comprising:
an autoflight performance selector configured to limit the response of the autoflight system to flight guidance instructions in at least two of the pitch, roll and yaw axes, wherein the autoflight performance selector includes a rotary knob having at least a min position and a max position, wherein selecting the min position limits the response of the autoflight system to a first angle about the pitch axis and a second angle about the roll axis, and wherein selecting the max position limits the response of the autoflight system to a third angle about the pitch axis greater than the first angle, and a fourth angle about the roll axis greater than the second angle.
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4. An apparatus for use with an aircraft having an autoflight system capable of controlling the attitude of the aircraft in pitch, roll and yaw axes, the apparatus comprising:
an autoflight performance selector configured to limit the response of the autoflight system to flight guidance instructions in at least two of the pitch, roll and yaw axes, wherein the autoflight performance selector includes a rotary knob having at least a min position and a max position, wherein selecting the min position limits the response of the autoflight system to a first rate of pitch change about the pitch axis and a second rate of roll about the roll axis, and wherein selecting the max position limits the response of the autoflight system to a third rate of pitch change about the pitch axis greater than the first rate, and a fourth rate of roll about the roll axis greater than the second rate.
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11. An apparatus for use with an aircraft having an autothrottle and an autopilot capable of controlling the attitude of the aircraft in pitch, roll and yaw axes, the apparatus comprising:
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a flight management computer operably connected to the autothrottle and the autopilot; a data entry device configured to transmit flight guidance instructions from a pilot to the flight management computer, wherein the flight management computer controls the autothrottle and the autopilot in response to the flight guidance instructions; and an autoflight performance selector configured to limit the dynamic response of the autothrottle and the autopilot to the flight guidance instructions in at least two of the pitch, roll and yaw axes, the autoflight performance selector having at least a first selection and a second selection different than the first selection, wherein selecting the first selection causes the flight management computer to control the autothrottle and the autopilot to not exceed a first rate of rotation about a first one of the at least two axes and a second rate of rotation about a second one of the at least two axes, and wherein selecting the second selection causes the flight management computer to control the autothrottle and the autopilot to not exceed a third rate of rotation about the first one of the at least two axes and a fourth rate of rotation about the second one of the at least two axes. - View Dependent Claims (13, 14, 15)
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12. An apparatus for use with an aircraft having an autothrottle and an autopilot capable of controlling the attitude of the aircraft in pitch, roll and yaw axes, the apparatus comprising:
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a flight management computer operably connected to the autothrottle and the autopilot; a data entry device configured to transmit flight guidance instructions from a pilot to the flight management computer, wherein the flight management computer controls the autothrottle and the autopilot in response to the flight guidance instructions; and an autoflight performance selector configured to limit the dynamic response of the autothrottle and the autopilot to the flight guidance instructions in at least two of the pitch, roll and yaw axes, wherein the autoflight performance selector includes at least a min position and a max position, wherein selecting the min position limits the dynamic response of the autothrottle and the autopilot to a first rate of pitch change about the pitch axis and a second rate of roll about the roll axis, and wherein selecting the max position limits the dynamic response of the autothrottle and the autopilot to a third rate of pitch change about the pitch axis greater than the first rate, and a fourth rate of roll about the roll axis greater than the second rate.
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16. An autoflight system for use with an aircraft, the autoflight system comprising:
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an autothrottle and an autopilot capable of controlling the attitude of the aircraft in pitch, roll and yaw axes; a flight management computer operably connected to the autothrottle and the autopilot; a data entry device configured to receive flight guidance instructions from a pilot and transmit the flight guidance instructions to the flight management computer, wherein the flight management computer controls the autothrottle and the autopilot in response to the flight guidance instructions; a display device operatively connected to the flight management computer and configured to exchange information with the flight management computer, wherein the display device includes; a first display screen configured to provide autoflight mode information related to airspeed; a second display screen positioned at least approximately adjacent to the first display screen, the second display screen configured to provide autoflight mode information related to vertical guidance; and a third display screen positioned at least approximately adjacent to at least one of the first and second display screens, the third display screen configured to provide autoflight mode information related to lateral guidance; and an autoflight performance selector configured to limit the dynamic response of the autothrottle and the autopilot to the flight guidance instructions in at least two of the pitch, roll and yaw axes, the autoflight performance selector having at least a first position and a second position, wherein selecting the first position limits the autothrottle and the autopilot to a first rate of rotation about the at least two axes, a first angle about a first one of the at least two axes, and a second angle about a second one of the at least two axes, and wherein selecting the second position limits the autothrottle and the autopilot to a second rate of rotation, greater than the first rate of rotation, about the at least two axes, a third angle about the first one of the at least two axes, and a fourth angle about the second one of the at least two axes. - View Dependent Claims (17, 19, 20)
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18. An autoflight system for use with an aircraft, the autoflight system comprising:
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an autothrottle and an autopilot capable of controlling the attitude of the aircraft in pitch, roll and yaw axes; a flight management computer operably connected to the autothrottle and the autopilot; a data entry device configured to receive flight guidance instructions from a pilot and transmit the flight guidance instructions to the flight management computer, wherein the flight management computer controls the autothrottle and the autopilot in response to the flight guidance instructions; a display device operatively connected to the flight management computer and configured to exchange information with the flight management computer, wherein the display device includes; a first display screen configured to provide autoflight mode information related to airspeed; a second display screen positioned at least approximately adjacent to the first display screen, the second display screen configured to provide autoflight mode information related to vertical guidance; and a third display screen positioned at least approximately adjacent to at least one of the first and second display screens, the third display screen configured to provide autoflight mode information related to lateral guidance; and an autoflight performance selector configured to limit the dynamic response of the autothrottle and the autopilot to the flight guidance instructions in at least two of the pitch, roll and yaw axes, the autoflight performance selector having at least a first position and a second position, wherein selecting the first position of the autoflight performance selector limits the autothrottle and the autopilot to a first rate of rotation about the at least two axes, a first angle about the pitch axis and a second angle about the roll axis, and wherein selecting the second position of the autoflight performance selector limits the autothrottle and the autopilot to a second rate of rotation, greater than the first rate of rotation, about the at least two axes, a third angle about the pitch axis greater than the first angle, and a fourth angle about the roll axis greater than the second angle.
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21. An apparatus for use with an aircraft having an autoflight system capable of controlling the attitude of the aircraft in pitch, roll and yaw axes, the apparatus comprising:
an autoflight performance selector configured to limit the response of the autoflight system to flight guidance instructions in at least two of the pitch, roll and yaw axes, the autoflight performance selector having at least a first selection and a second selection different than the first selection, wherein selecting the first selection limits the response of the autoflight system to a first rate of rotation about a first one of the at least two axes and a second rate of rotation about a second one of the at least two axes, and wherein selecting the second selection limits the response of the autoflight system to a third rate of rotation about the first one of the at least two axes and a fourth rate of rotation about the second one of the at least two axes. - View Dependent Claims (22)
Specification