公开(公告)号：US20220221878A1

公开(公告)日：2022-07-14

申请号：US17149445

申请日：2021-01-14

Applicant: Bell Textron Inc.

Inventor： Steven G. Hagerott ,  Jonathan Andrew Toth

IPC: G05D1/08 ,  B64C29/00

Abstract: There is disclosed in one example an inner loop controller for an aircraft flight computer, including: a stall protection circuit to compute, for an attitude angle θ, an attitude limit θmax as a function of a flight path angle (γ) and an angle of attack limit (αmax); a transfer function circuit to convert θ to an attitude rate {dot over (θ)}, wherein {dot over (θ)} is a time derivative of θ; and a load protector circuit to compute a limit on {dot over (θ)} ({dot over (θ)}max) as a function of a load factor limit (Nz,max) and a true airspeed (v).

公开(公告)号：US20220388672A1

公开(公告)日：2022-12-08

申请号：US17338236

申请日：2021-06-03

Applicant: Bell Textron Inc.

Inventor： Kip Gregory Campbell ,  Kristen Stuart ,  Steven G. Hagerott

IPC: B64D31/00 ,  B64D27/24 ,  B64C27/68 ,  B64C39/02 ,  B64C27/635

Abstract: A system can include a flight controller for an aircraft that includes an electric motor that drives blades with a variable pitch, where the flight controller receives a command to change a flight characteristic of the aircraft and creates a torque command and a revolutions per minute (RPM) command. The system can also include a propulsion assembly, where the propulsion assembly creates a current command based at least in part on the torque command and the RPM command, creates a blade pitch command based at least in part on the torque command and the RPM command, communicates the current command to the electric motor to change a mechanical output of the electric motor, and communicates the blade pitch command to blade actuators to control the pitch of the blades. The current command and the blade pitch command cause the blades of the aircraft to rotate at a predetermined RPM.

公开(公告)号：US11733714B2

公开(公告)日：2023-08-22

申请号：US17149445

申请日：2021-01-14

Applicant: Bell Textron Inc.

Inventor： Steven G. Hagerott ,  Jonathan Andrew Toth

IPC: G05D1/08 ,  B64C29/00 ,  G05D1/00 ,  B64C13/50

CPC classification number: G05D1/0808 ,  B64C29/0033 ,  G05D1/0055 ,  B64C13/503

Abstract: There is disclosed in one example an inner loop controller for an aircraft flight computer, including: a stall protection circuit to compute, for an attitude angle θ, an attitude limit θmax as a function of a flight path angle (γ) and an angle of attack limit (αmax); a transfer function circuit to convert θ to an attitude rate {dot over (θ)}, wherein {dot over (θ)} is a time derivative of θ; and a load protector circuit to compute a limit on {dot over (θ)} ({dot over (θ)}max) as a function of a load factor limit (Nz,max) and a true airspeed (v).

公开(公告)号：US12043398B2

公开(公告)日：2024-07-23

申请号：US17338236

申请日：2021-06-03

Applicant: Bell Textron Inc.

Inventor： Kip Gregory Campbell ,  Kristen Stuart ,  Steven G. Hagerott

IPC: B64D31/00 ,  B64C27/635 ,  B64C27/68 ,  B64C39/02 ,  B64D27/24 ,  B64U30/20 ,  B64U50/19

CPC classification number: B64D31/00 ,  B64C27/635 ,  B64C27/68 ,  B64C39/024 ,  B64D27/24 ,  B64U30/20 ,  B64U50/19 ,  B64U2201/00

Abstract: A system can include a flight controller for an aircraft that includes an electric motor that drives blades with a variable pitch, where the flight controller receives a command to change a flight characteristic of the aircraft and creates a torque command and a revolutions per minute (RPM) command. The system can also include a propulsion assembly, where the propulsion assembly creates a current command based at least in part on the torque command and the RPM command, creates a blade pitch command based at least in part on the torque command and the RPM command, communicates the current command to the electric motor to change a mechanical output of the electric motor, and communicates the blade pitch command to blade actuators to control the pitch of the blades. The current command and the blade pitch command cause the blades of the aircraft to rotate at a predetermined RPM.

公开(公告)号：US20220350347A1

公开(公告)日：2022-11-03

申请号：US17245446

申请日：2021-04-30

Applicant: Bell Textron Inc.

Inventor： Steven G. Hagerott ,  Jonathan Andrew Toth

IPC: G05D1/10 ,  G05D1/08 ,  G05B11/42

Abstract: Embodiments are directed to systems and methods for utilizing a two-degree-of-freedom model-following control law within an architecture of nested loop functions. This allows for the separation of command and feedback path requirements and enables the restrictions of the inner loops to be applied to the outer loop feedbacks. This method of restriction allows a better allocation of coordinated authority between the loops.

公开(公告)号：US20220324558A1

公开(公告)日：2022-10-13

申请号：US17571936

申请日：2022-01-10

Applicant: Bell Textron Inc.

Inventor： Brent C. Ross ,  Kirk L. Groninga ,  Steven R. Ivans ,  Steve R. Schafer ,  Brad Joseph Passe ,  Nicholas Ralph Carlson ,  Kip Gregory Campbell ,  Bradley Paul Regnier ,  Steven G. Hagerott

IPC: B64C29/00

Abstract: One embodiment is an aircraft including a fuselage; a wing connected to the fuselage; first and second booms connected to the wing on opposite sides of the fuselage; first and second forward propulsion systems attached to forward ends of the first and second booms; first and second aft propulsion systems fixedly attached proximate aft ends of the first and second booms; and first and second wing-mounted propulsion systems connected to outboard ends of wings; wherein the first and second wing-mounted propulsion systems are tiltable between a first position when the aircraft is in a hover mode and a second position when the aircraft is in a cruise mode.