System and method for controlling a pressure field around an aircraft in flight

Patent metadata

Field	Value
Publication number	US-2016257397-A1
Application number	US-201414459488-A
Country	US
Kind code	A1
Filing date	Aug 14, 2014
Priority date	Aug 14, 2014
Publication date	Sep 8, 2016
Grant date	—

Abstract

A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to measure the pressure field. The system further includes, but is not limited to, a controller that is communicatively coupled with the plurality of pressure sensors. The controller is configured to receive information that is indicative of the pressure field from the plurality of pressure sensors. The controller is also configured to determine when the pressure field deviates from a desired pressure field based on the information. The controller is also configured to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.

First claim

What is claimed is:

1 . A system for controlling a pressure field around an aircraft in flight, the system comprising:
a plurality of pressure sensors arranged on the aircraft to measure the pressure field; and a controller communicatively coupled with the plurality of pressure sensors, the controller configured to receive information indicative of the pressure field from the plurality of pressure sensors, to determine when the pressure field deviates from a desired pressure field based on the information, and to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.

2 . The system of claim 1 , wherein the controller is configured to transmit the instruction to a primary controller configured to control the movable component.

3 . The system of claim 1 , wherein the movable component comprises a propulsion system component.

4 . The system of claim 1 , wherein the movable component comprises a flight control surface.

5 . The system of claim 1 , wherein the pressure field deviates from the desired pressure field when a pressure gradient of the pressure field exceeds a pressure gradient of the desired pressure field.

6 . A system for controlling a pressure field around an aircraft in flight, the system comprising:
a plurality of pressure sensors arranged on the aircraft, each pressure sensor of the plurality of pressure sensors positioned to measure a respective air pressure proximate a respective portion of an external surface of the aircraft proximate a propulsion system of the aircraft; a first movable component mounted on the aircraft and disposed in a position that alters the pressure field when the first movable component moves while the aircraft is in flight; and a controller communicatively coupled with the plurality of pressure sensors and communicatively connected with the first movable component, the controller configured to receive information from each pressure sensor indicative of the respective air pressure, to compute the pressure field along the external surface of the aircraft based on the information, to detect a deviation between the pressure field and an anticipated pressure field caused by the propulsion system of the aircraft, and to send a first instruction to the first movable component to move in a manner that diminishes the deviation when the deviation is detected.

7 . The system of claim 6 , wherein the plurality of pressure sensors are arranged on the external surface of the aircraft.

8 . The system of claim 6 , wherein the first movable component comprises a flight control surface.

9 . The system of claim 6 , wherein the first movable component comprises a propulsion system component.

10 . The system of claim 6 , wherein the controller is communicatively coupled with a primary controller configured to control the movable component and wherein the controller sends the first instruction to the primary controller.

11 . The system of claim 6 , wherein detecting the deviation comprises comparing a pressure gradient of the pressure field with a corresponding pressure gradient of the anticipated pressure field.

12 . The system of claim 6 , wherein the controller is further configured to send the first instruction when the deviation exceeds a predetermined deviation.

13 . The system of claim 6 , further comprising a second movable component mounted on the aircraft and disposed in a second position that alters the pressure field when the second movable component moves while the aircraft is in flight,
wherein the controller is communicatively connected with the second movable component and is further configured to send a second instruction to the second movable component to move in a manner that diminishes the deviation when the deviation is detected.

14 . The system of claim 13 , wherein the controller is further configured to send the second instruction when movement of the first movable component fails to diminish the deviation by a predetermined amount.

15 . The system of claim 13 , wherein the controller is further configured to send the second instruction when the first movable component does not move in response to the first instruction.

16 . The system of claim 6 , wherein at least one pressure sensor of the plurality of pressure sensors is positioned to measure the respective air pressure proximate a propulsion system inlet.

17 . The system of claim 6 , wherein at least one pressure sensor of the plurality of pressure sensors is positioned to measure the respective air pressure proximate a propulsion system nozzle.

18 . The system of claim 6 , wherein at least one pressure sensor of the plurality of pressure sensors is positioned to measure the respective air pressure proximate a portion of the external surface where a shock generated by a structure of the aircraft intercepts the external surface.

19 . The system of claim 6 , further comprising an electronic data storage unit communicatively coupled with the controller and configured to store information indicative of a plurality of anticipated pressure fields,
wherein the controller is configured to retrieve the information from the electronic data storage unit and to use the information to detect the deviation between the pressure field and the anticipated pressure field.

20 . A method for controlling a pressure field around an aircraft in flight, the method comprising:
measuring the pressure field with a plurality of pressure sensors arranged on the aircraft; receiving, at a controller, information from the plurality of pressure sensors indicative of the pressure field; determining, with the controller, when the pressure field deviates from a desired pressure field based, at least in part, on the information from the plurality of pressure sensors; and transmitting, with the controller, an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Conners Timothy
• Knight Michael
• Cowart Robert

Classifications

• B64D33/02

  of combustion air intakes · CPC title

• G01L19/0084

  to the outside of the housing (other details about the housing see G01L19/14) · CPC title

• B64D31/06

  actuated automatically · CPC title

• G01L19/14

  Housings {(G01L19/0007, G01L19/0084, G01L19/0092, G01L19/04, G01L19/06 take precedence)} · CPC title

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title