초록 ▼

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

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.

대표청구항 ▼

We 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 ins

We 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.