Dynamic center of gravity determination

Patent metadata

Field	Value
Publication number	US-2016209290-A1
Application number	US-201514598986-A
Country	US
Kind code	A1
Filing date	Jan 16, 2015
Priority date	Jan 16, 2015
Publication date	Jul 21, 2016
Grant date	—

Abstract

A computer-implemented method for determining center of gravity of a tiltrotor aircraft includes storing a multi-dimensional matrix mapping multiple tiltrotor aircraft parameters to a plurality of three-dimensional (3D) centers of gravity of the tiltrotor aircraft, where each 3D center of gravity includes a respective longitudinal center of gravity, lateral center of gravity, and vertical center of gravity. The method includes receiving input signals from corresponding on-board sensors, where the input signals represent characteristics of the tiltrotor aircraft, determining tiltrotor aircraft parameters from the input signals, identifying, from the multi-dimensional matrix mapping, a longitudinal center of gravity, a lateral center of gravity, and a vertical center of gravity that corresponds to the determined tiltrotor aircraft parameters, and providing the identified longitudinal center of gravity, the identified lateral center of gravity, and the identified vertical center of gravity in response to receiving the input signals.

First claim

What is claimed is:

1 . An on-board tiltrotor aircraft system for determining center of gravity of the tiltrotor aircraft, the system comprising:
one or more computers; and a computer-readable medium storing instructions executable by the one or more computers to perform operations comprising:
storing a multi-dimensional matrix mapping a plurality of tiltrotor aircraft parameters to a plurality of three-dimensional (3D) centers of gravity of the tiltrotor aircraft, each 3D center of gravity comprising a respective longitudinal center of gravity, lateral center of gravity, and vertical center of gravity;
receiving a plurality of input signals from a corresponding plurality of on-board sensors, the plurality of input signals representing characteristics of the tiltrotor aircraft;
determining one or more tiltrotor aircraft parameters from the plurality of input signals;
identifying, from the multi-dimensional matrix mapping, a longitudinal center of gravity, a lateral center of gravity, and a vertical center of gravity that corresponds to the determined one or more tiltrotor aircraft parameters; and
providing the identified longitudinal center of gravity, the identified lateral center of gravity, and the identified vertical center of gravity in response to receiving the plurality of input signals.

2 . The system of claim 1 , wherein the plurality of on-board sensors comprises at least one of a nacelle settings sensor, a flap settings sensor, a weight sensor, a flight sensor, a flight control sensor, an engine state sensor, or a mode sensor.

3 . The system of claim 1 , wherein the multi-dimensional matrix comprises a longitudinal center of gravity matrix, and wherein the operations further comprise:
identifying, for the tiltrotor aircraft operating in a helicopter mode, a first plurality of longitudinal centers of gravity corresponding to a first plurality of gross weight-fuselage direction pairs; identifying, for the tiltrotor aircraft operating in an airplane mode, a second plurality of longitudinal centers of gravity corresponding to a second plurality of gross weight-fuselage direction pairs; storing, in the longitudinal center of gravity matrix, the first plurality of gross weight-fuselage direction pairs and the second plurality of gross weight-fuselage direction pairs as tiltrotor aircraft parameters; and storing, in the longitudinal center of gravity matrix, the first plurality of longitudinal centers of gravity and the second plurality of longitudinal centers of gravity corresponding to the first plurality of gross weight-fuselage direction pairs and the second plurality of gross weight-fuselage direction pairs, respectively, in the helicopter mode and the airplane mode, respectively.

4 . The system of claim 1 , wherein the multi-dimensional matrix comprises a lateral center of gravity matrix, and wherein the operations further comprise:
determining lateral center of gravity limits for the tiltrotor aircraft based on one or more of the plurality of tiltrotor aircraft parameters; and storing the lateral center of gravity limits in the lateral center of gravity matrix.

5 . The system of claim 1 , wherein the multi-dimensional matrix comprises a vertical center of gravity matrix, and wherein the operations further comprise:
identifying, for the tiltrotor aircraft operating in a helicopter mode, a first plurality of vertical centers of gravity corresponding to a first plurality of nacelle tilt directions; identifying, for the tiltrotor aircraft operating in an airplane mode, a second plurality of vertical centers of gravity corresponding to a second plurality of nacelle tilt directions; storing, in the vertical center of gravity matrix, the first plurality of nacelle tilt directions and the second plurality of nacelle tilt directions; and storing, in the longitudinal center of gravity matrix, the first plurality of vertical centers of gravity and the second plurality of vertical centers of gravity corresponding to the first plurality of nacelle tilt directions and the second plurality of nacelle tilt directions, respectively, in the helicopter mode and the airplane mode, respectively.

6 . The system of claim 1 , wherein the identified longitudinal center of gravity, the identified lateral center of gravity and the identified vertical center of gravity are identified in real time during flight of the tiltrotor aircraft.

7 . The system of claim 1 , wherein the operations further comprise determining, at a flight time instant, a rate of fuel consumption of the tiltrotor aircraft based, in part, on the identified longitudinal center of gravity, the identified lateral center of gravity, and the identified vertical center of gravity, each identified at the flight time instant.

8 . The system of claim 7 , wherein the operations further comprise determining, at the flight time instant, flight mode adjustments based, in part, on the determined rate of fuel consumption.

9 . The system of claim 1 , wherein the on-board tiltrotor aircraft system is integrated into an existing computer system of the tiltrotor aircraft.

10 . A computer-implemented method for determining center of gravity of a tiltrotor aircraft, the method comprising:
storing a multi-dimensional matrix mapping a plurality of tiltrotor aircraft parameters to a plurality of three-dimensional (3D) centers of gravity of the tiltrotor aircraft, each 3D center of gravity comprising a respective longitudinal center of gravity, lateral center of gravity, and vertical center of gravity; receiving a plurality of input signals from a corresponding plurality of on-board sensors, the plurality of input signals representing characteristics of the tiltrotor aircraft; determining one or more tiltrotor aircraft parameters from the plurality of input signals; identifying, from the multi-dimensional matrix mapping, a longitudinal center of gravity, a lateral center of gravity, and a vertical center of gravity that corresponds to the determined one or more tiltrotor aircraft parameters; and providing the identified longitudinal center of gravity, the identified lateral center of gravity, and the identified vertical center of gravity in response to receiving the plurality of input signals.

11 . The method of claim 10 , wherein the plurality of on-board sensors comprises at least one of a nacelle settings sensor, a flap settings sensor, a weight sensor, a flight sensor, a flight control sensor, an engine state sensor, or a mode sensor.

12 . The method of claim 10 , further comprising:
identifying, for the tiltrotor aircraft operating in a helicopter mode, a first plurality of longitudinal centers of gravity corresponding to a first plurality of gross weight-fuselage direction pairs; identifying, for the tiltrotor aircraft operating in an airplane mode, a second plurality of longitudinal centers of gravity corresponding to a second plurality of gross weight-fuselage direction pairs; storing, in a longitudinal center of gravity matrix of the multi-dimensional matrix, the first plurality of gross weight-fuselage direction pairs and the second plurality of gross weight-fuselage direction pairs as tiltrotor aircraft parameters; and storing, in the longitudinal center of gravity matrix, the first plurality of longitudinal centers of gravity and the second plurality of longitudinal centers of gravity corresponding to the first plurality of gross weight-fuselage direction pairs and the second plurality of gross weight-fuselage direction pairs, respectively, in the helicopter mode and the airplane mode, respectively.

13 . The method of claim 10 , further comprising:
determining la

Assignees

• Bell Helicopter Textron Inc

Inventors

• Shue Shyhpyng Jack

Classifications

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title

• B64C19/00

  Aircraft control not otherwise provided for · CPC title

• B64C27/28

  with forward-propulsion propellers pivotable to act as lifting rotors · CPC title

• G01M1/127 Primary

  during the flight · CPC title