Line replaceable, fly-by-wire control columns with push-pull interconnect rods
First Claim
1. A control system including:
- first and second control columns for receiving pitch and roll control inputs from a pilot for an aircraft, each control column having a control grip moveable along a pitch axis to adjust the pitch control input to the aircraft and moveable along a roll axes to adjust the roll control input to the aircraft;
a roll interconnect rod operably coupling the first and second control columns for coordinated movement of the control grips along each control grips roll axis when an input is provided to either of the control grips; and
a pitch interconnect rod operably coupling the first and second control columns for coordinated movement of the control grips along each control grips pitch axis when an input is provided to either of the control grips;
further including a disconnect device interposed between the grip of the first control column and the grip of the second column for a selected one of pitch or roll, the disconnect device having a coupled state fixedly coupling the grips for coordinated movement along a selected one of the pitch axis or roll axis and a decoupled state in which the disconnect device does not fixedly couple the grips such that movement of one grip along the selected one of the pitch axis or roll axis is not translated to the other grip, the disconnect device including a solenoid actuated latch for transitioning the disconnect device from the coupled state to the decoupled state.
1 Assignment
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Accused Products
Abstract
A control input system is provided. The system includes a pair of control columns that are selectively interconnected such that manipulation of one of the control columns is translated to the other one of the control columns. The system includes a disconnect arrangement for each of the degrees of freedom (pitch and roll) of the system that operably disconnects the two control columns such that the two control columns can operate independently such as in the event of failure of one of the control columns. The system may also include a discontinuous force profile for a restoring force mechanism that provides tactile feedback to the pilots simulating resistance provided by control surfaces of the aircraft. The system may also include an autopilot lockout mechanism that increases the force profile experienced by the pilots when autopilot mode is entered.
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Citations
19 Claims
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1. A control system including:
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first and second control columns for receiving pitch and roll control inputs from a pilot for an aircraft, each control column having a control grip moveable along a pitch axis to adjust the pitch control input to the aircraft and moveable along a roll axes to adjust the roll control input to the aircraft; a roll interconnect rod operably coupling the first and second control columns for coordinated movement of the control grips along each control grips roll axis when an input is provided to either of the control grips; and a pitch interconnect rod operably coupling the first and second control columns for coordinated movement of the control grips along each control grips pitch axis when an input is provided to either of the control grips; further including a disconnect device interposed between the grip of the first control column and the grip of the second column for a selected one of pitch or roll, the disconnect device having a coupled state fixedly coupling the grips for coordinated movement along a selected one of the pitch axis or roll axis and a decoupled state in which the disconnect device does not fixedly couple the grips such that movement of one grip along the selected one of the pitch axis or roll axis is not translated to the other grip, the disconnect device including a solenoid actuated latch for transitioning the disconnect device from the coupled state to the decoupled state. - View Dependent Claims (15)
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2. A control system including:
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first and second control columns for receiving pitch and roll control inputs from a pilot for an aircraft, each control column having a control grip moveable along a pitch axis to adjust the pitch control input to the aircraft and moveable along a roll axes to adjust the roll control input to the aircraft; a roll interconnect rod operably coupling the first and second control columns for coordinated movement of the control grips along each control grips roll axis when an input is provided to either of the control grips; a pitch interconnect rod operably coupling the first and second control columns for coordinated movement of the control grips along each control grips pitch axis when an input is provided to either of the control grips; and further including a disconnect device interposed between the grip of the first control column and the grip of the second column for a selected one of pitch or roll, the disconnect device having a coupled state fixedly coupling the grips for coordinated movement along a selected one of the pitch axis or roll axis and a decoupled state in which the disconnect device does not fixedly couple the grips such that movement of one grip along the selected one of the pitch axis or roll axis is not translated to the other grip; wherein the disconnect device includes; a pivot link that is operably coupled to the grip of one of the control columns for movement about a pivot axis; a connection link pivotably coupled to the pivot link about a release axis that is offset from the pivot axis; a clevis link pivotable relative to the pivot link about the pivot axis, the clevis link selectively engageable with the connection link to fix the clevis link relative to the pivot link, the clevis link being operably coupled to the pitch interconnect rod. - View Dependent Claims (3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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16. A control system including:
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first and second control columns for receiving pitch and roll control inputs from a pilot for an aircraft, each control column having a control grip moveable along a pitch axis to adjust the pitch control input to the aircraft and moveable along a roll axes to adjust the roll control input to the aircraft; a roll interconnect rod operably coupling the first and second control columns for coordinated movement of the control grips along each control grips roll axis when an input is provided to either of the control grips; and a pitch interconnect rod operably coupling the first and second control columns for coordinated movement of the control grips along each control grips pitch axis when an input is provided to either of the control grips; further including an autopilot lockout mechanism associated with a selected one of pitch or roll, the autopilot lockout mechanism providing increased resistance that must be overcome to manipulate the first and second control columns along the selected one of the pitch axis or roll axis when autopilot is activated; and wherein the autopilot lockout includes; first and second autopilot plates being pivotable about an autopilot axis; an autopilot resistance spring biasing ends of the first and second autopilot plates angularly toward one another about the autopilot axis; a main link pivotable about the autopilot axis, the interconnect rod coupled to the control stick through the main link, the main link operably engaging the first autopilot plate when rotated angularly in a first direction and operably engaging the second autopilot plate when rotated angularly in a second direction, opposite the first direction; a grounding arrangement, when autopilot is activated, selectively grounding the second autopilot plate when the main link is rotated in the first direction and selectively grounding the first autopilot plate when the main link is rotated in the second direction. - View Dependent Claims (17, 18, 19)
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Specification