公开(公告)号：US11238200B2

公开(公告)日：2022-02-01

申请号：US16293425

申请日：2019-03-05

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael McNair ,  Brent Chadwick Ross ,  Christopher Stroncek ,  Kip Gregory Campbell ,  Joseph Scott Drennan ,  Brett Zimmerman ,  Carey Cannon

IPC: G06F30/33 ,  H01R13/66 ,  G06F30/15 ,  G06F30/367 ,  G09B9/42 ,  G09B9/00 ,  G09B9/12 ,  G09B19/16

Abstract: A method of operating a targeting system simulation tool (TSST) includes providing a TSST configured to receive an obstacle/effect parameterization, a simulation parameterization, a sensor parameterization, an aircraft parameterization, and an autonomy parameterization. The method further includes receiving by the TSST, at least one of each of an obstacle/effect parameterization and a simulation parameterization. The method further includes receiving by the TSST, either (1) a sensor parameterization or (2) an aircraft parameterization. The method further includes operating the TSST to apply the provided ones of the obstacle/effect parameterization, simulation parameterization, sensor parameterization, and aircraft parameterization to generate a value, value range, or value limit for the unprovided aircraft parameterization or unprovided sensor parameterization.

公开(公告)号：US20200348695A1

公开(公告)日：2020-11-05

申请号：US16399893

申请日：2019-04-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Kip Gregory Campbell

IPC: G05D1/06 ,  G08G5/00 ,  B64D45/00

Abstract: According to one implementation of the present disclosure, a method for determining angle-of-attack for an unpowered vehicle is disclosed. The method includes: determining a monotonic portion of a look-up curve of an angle-of-attack operating plot; during flight, determining, by an accelerometer disposed on the unpowered vehicle, first and second accelerometer outputs, where the first and second accelerometer outputs correspond to first and second body-fixed load factor measurements, respectively; determining an operating point on the monotonic portion by applying a quotient of the first and second accelerometer outputs to the angle-of-attack operating plot; and determining an angle-of-attack parameter corresponding to the determined operating point.

公开(公告)号：US20190100313A1

公开(公告)日：2019-04-04

申请号：US15724669

申请日：2017-10-04

Applicant: Bell Helicopter Textron Inc.

Inventor： Kip Gregory Campbell

IPC: B64D1/02

Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having a wing with oppositely disposed wing tips. Tip booms respectively extend longitudinally from the wing tips. Forward rotors are coupled to the forward ends of the tip booms and aft rotors are coupled to the aft ends of the tip booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the tip booms, and a forward thrust orientation, wherein the forward rotors are forward of the tip booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the tip booms, and a forward thrust orientation, wherein the aft rotors are aft of the tip booms. One of a plurality of payload modules is interchangeable coupled to the airframe, wherein each payload module has a respective function.

公开(公告)号：US20190100303A1

公开(公告)日：2019-04-04

申请号：US15724649

申请日：2017-10-04

Applicant: Bell Helicopter Textron Inc.

Inventor： Kip Gregory Campbell

IPC: B64C29/00

CPC classification number: B64C29/0033 ,  B64C15/12 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52

Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The tiltrotor aircraft includes a longitudinally extending fuselage with a wing extending laterally therefrom having oppositely disposed wing tips distal from the fuselage. Tip booms respectively extend longitudinally from the wing tips. Forward rotors are coupled to the forward ends of the tip booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the tip booms, and a forward thrust orientation, wherein the forward rotors are forward of the tip booms. An aft rotor is coupled to the aft end of the fuselage. The aft rotor is reversibly tiltable between a vertical lift orientation, wherein the aft rotor is below the fuselage, and a forward thrust orientation, wherein the aft rotor is aft of the fuselage.

公开(公告)号：US11061410B2

公开(公告)日：2021-07-13

申请号：US16399893

申请日：2019-04-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Kip Gregory Campbell

IPC: G05D1/06 ,  B64D45/00 ,  G08G5/00

Abstract: According to one implementation of the present disclosure, a method for determining angle-of-attack for an unpowered vehicle is disclosed. The method includes: determining a monotonic portion of a look-up curve of an angle-of-attack operating plot; during flight, determining, by an accelerometer disposed on the unpowered vehicle, first and second accelerometer outputs, where the first and second accelerometer outputs correspond to first and second body-fixed load factor measurements, respectively; determining an operating point on the monotonic portion by applying a quotient of the first and second accelerometer outputs to the angle-of-attack operating plot; and determining an angle-of-attack parameter corresponding to the determined operating point.

公开(公告)号：US20200026811A1

公开(公告)日：2020-01-23

申请号：US16293425

申请日：2019-03-05

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael McNair ,  Brent Chadwick Ross ,  Christopher Stroncek ,  Kip Gregory Campbell ,  Joseph Scott Drennan ,  Brett Zimmerman ,  Carey Cannon

IPC: G06F17/50 ,  H01R13/66

Abstract: A method of operating a targeting system simulation tool (TSST) includes providing a TSST configured to receive an obstacle/effect parameterization, a simulation parameterization, a sensor parameterization, an aircraft parameterization, and an autonomy parameterization. The method further includes receiving by the TSST, at least one of each of an obstacle/effect parameterization and a simulation parameterization. The method further includes receiving by the TSST, either (1) a sensor parameterization or (2) an aircraft parameterization. The method further includes operating the TSST to apply the provided ones of the obstacle/effect parameterization, simulation parameterization, sensor parameterization, and aircraft parameterization to generate a value, value range, or value limit for the unprovided aircraft parameterization or unprovided sensor parameterization.