Flight control computer for an aircraft that includes an inertial sensor incorporated therein

Patent metadata

Field	Value
Publication number	US-2016221663-A1
Application number	US-201414574496-A
Country	US
Kind code	A1
Filing date	Dec 18, 2014
Priority date	Dec 18, 2014
Publication date	Aug 4, 2016
Grant date	—

Abstract

The disclosed embodiments relate to a flight control computer for an aircraft. The flight control computer includes an inertial sensor integrated or incorporated within the flight control computer.

First claim

1 . A flight control computer, comprising:
an inertial sensor incorporated within the flight control computer.

2 . The flight control computer according to claim 1 , wherein the inertial sensor comprises:
an accelerometer.

3 . The flight control computer according to claim 1 , wherein the inertial sensor comprises:
a gyroscope.

4 . The flight control computer according to claim 1 , further comprising:
a magnetometer incorporated within the flight control computer.

5 . The flight control computer according to claim 1 , further comprising:
a processor, and wherein the inertial sensor is integrated within the processor of the flight control computer.

6 . The flight control computer according to claim 1 , further comprising:
a processor, wherein the inertial sensor is configured to generate inertial signal data that is processed by the processor to generate control commands.

7 . The flight control computer according to claim 1 , wherein the flight control computer provides power to the inertial sensor.

8 . The flight control computer according to claim 1 , wherein the inertial sensor is a first inertial sensor, wherein the flight control computer further comprises:
an interface that is configured to be coupled to a second inertial sensor that is external to the flight control computer.

9 . The flight control computer according to claim 8 , wherein the first inertial sensor is a redundant version of the second inertial sensor.

10 . An aircraft, comprising:
a flight control computer, comprising:
an inertial sensor integrated within the flight control computer.

11 . The aircraft according to claim 10 , wherein the inertial sensor comprises:
an accelerometer.

12 . The aircraft according to claim 10 , wherein the inertial sensor comprises:
a gyroscope.

13 . The aircraft according to claim 10 , wherein the flight control computer further comprises:
a magnetometer integrated within the flight control computer.

14 . The aircraft according to claim 10 , wherein the flight control computer comprises:
a processor, and wherein the inertial sensor is integrated within the processor of the flight control computer.

15 . The aircraft according to claim 10 , wherein the flight control computer comprises:
a processor, wherein the inertial sensor is configured to generate inertial signal data that is processed by the processor to generate control commands that are used to control flight control surfaces of the aircraft.

16 . The aircraft according to claim 10 , further comprising:
a power supply that is configured to supply power to the flight control computer, and wherein the inertial sensor is configured to be powered by the power supplied to the flight control computer by the power supply.

17 . The aircraft according to claim 10 , wherein the inertial sensor is a first inertial sensor, and further comprising:
a second inertial sensor that is external to the flight control computer and that is coupled to the flight control computer via a wired connection.

18 . The aircraft according to claim 17 , wherein the first inertial sensor is a redundant version of the second inertial sensor.

19 . The aircraft according to claim 18 , wherein the flight control computer comprises:
a processor, wherein the first inertial sensor is configured to generate first inertial signal data, wherein the second inertial sensor is configured to generate second inertial signal data, and wherein the processor is configured to compare the first inertial sensor data to the second inertial sensor data to check validity of the second inertial sensor data.

20 . The aircraft according to claim 19 , further comprising:
at least one flight control surface, and wherein the processor is configured to process the first inertial sensor data, when the processor determines that the second inertial sensor data is unavailable, to generate control commands that are used to control the flight control surface of the aircraft.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Landers Thomas

Classifications

• G01C21/1654

  with electromagnetic compass · CPC title

• B64C13/503 Primary

  Fly-by-Wire · CPC title

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• G05D1/0077

  using redundant signals or controls · CPC title

• Y02T50/40

  Weight reduction · CPC title