US 12,534,187 B2Granted

Mode-dependent tactile feedback profiles for an inceptor

AssigneeLockheed Martin Corporation

InventorMatthew T. Luszcz

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Abstract

Systems and methods for providing tactile feedback via an inceptor. A control system for an aircraft includes an inceptor and a controller. The inceptor includes a grip portion moveable between a plurality of positions and one or more motors to apply a variable force to the grip portion. The controller is coupled to the one or more motors. The controller includes an electronic processor and a memory. The controller is configured to operate in a first operating mode, select a first tactile feedback profile associated with the first operating mode, and control the one or more motors based on the first tactile feedback profile. The controller is further configured to detect a transition from the first operating mode to a second operating mode, select a second tactile feedback profile associated with the second operating mode, and control the one or more motors based on the second tactile feedback profile.

Claims20

Dependent claims

A control system for an aircraft, the control system comprising:

an inceptor including a grip portion moveable between a plurality of positions and one or more motors connected to the grip portion to apply a variable force to the grip portion;
and
a controller coupled to the one or more motors, the controller including an electronic processor and a memory, the controller configured to:
operate in a first operating mode,
select a first tactile feedback profile associated with the first operating mode,
control the one or more motors based on the first tactile feedback profile,
detect a transition from the first operating mode to a second operating mode,
select a second tactile feedback profile associated with the second operating mode, and
control the one or more motors based on the second tactile feedback profile,
wherein the first operating mode is an attitude command mode and wherein the second operating mode is a rate command mode,
wherein, in the attitude command mode, a displacement of the grip portion corresponds to a set attitude of the aircraft, and
wherein, in the rate command mode, a displacement of the grip portion corresponds to a set angular rate of the aircraft,
wherein an amount of maximum displacement distance of the grip portion is dependent on the mode of operation.

10 more elements

Dependencies are inferred from the claim text.