Architecture for providing enhanced altitude functionality to aircraft air data system

Patent metadata

Field	Value
Publication number	US-10913545-B2
Application number	US-201816009911-A
Country	US
Kind code	B2
Filing date	Jun 15, 2018
Priority date	Jun 15, 2018
Publication date	Feb 9, 2021
Grant date	Feb 9, 2021

Abstract

A system and method of augmenting an existing air data system includes a multi-function probe (MFP) having a portion extending into an oncoming airflow about an exterior of an aircraft. A plurality of pressure sensing ports in the portion includes at least first and second static pressure ports. A first electronics channel of the MFP includes pressure sensors communicating with the first and second static pressure ports and is configured to determine first and second altitude values based on sensed static pressures at the first and second static pressure ports, respectively, that are independent of the existing air data system.

First claim

The invention claimed is:

1. A method of augmenting an existing air data system of an aircraft, the method comprising:
attaching a multi-function probe (MFP) to an exterior of the aircraft that is independent of the existing air data system of the aircraft, wherein the existing data system lacks one or more of at least two altitude values determined independently and multiple altitude values compensated for sideslip and/or angle of attack, and wherein the probe comprises a plurality of pressure sensing ports positioned to sense pressure of an oncoming airflow about an aircraft exterior, and wherein the plurality of pressure sensing ports includes a first static pressure port and a second static pressure port operatively associated with a first electronics channel; and
electrically coupling the first electronics channel to the existing air data system for displaying a first altitude value based on a first static pressure of an oncoming airflow about the aircraft exterior measured at the first static pressure port and displaying a second altitude value based on a second static pressure of the oncoming airflow measured at the second static pressure port.

2. The method of claim 1 , wherein attaching the MFP to the aircraft exterior includes:
locating the MFP on the aircraft exterior such that the first static pressure port and the second static pressure port have an installed location able to detect angle of sideslip.

3. The method of claim 1 , wherein attaching the MFP to the aircraft exterior includes:
locating the MFP on a side of the aircraft such that the first static pressure port and the second static pressure port have an installed location able to detect angle of attack.

4. A system comprising:
an existing air data system for an aircraft, the existing air data system comprising:
a pressure sensing probe having a pressure sensing port; and
an air data computer (ADC) electrically or pneumatically coupled to the pressure sensing probe, wherein the ADC is configured to determine a first altitude value based on a first pressure of an oncoming airflow about an exterior of the aircraft sensed at the pressure sensing port;
wherein the existing data system lacks one or more of at least two altitude values determined independently and multiple altitude values compensated for sideslip and/or angle of attack;

a multi-function probe (MFP) attached to the exterior of the aircraft, the MFP comprising:
a barrel portion extending into the oncoming airflow;
a plurality of pressure sensing ports in the barrel portion that includes at least a first static pressure port and a second static pressure port disposed on the barrel portion; and
a first electronics channel configured to determine a second altitude value based on the sensed first static pressure and a third altitude value based on the sensed second static pressure, wherein the second and third altitude values are determined independently of the existing air data system.

5. The system of claim 4 , wherein the first static pressure port is disposed on an opposite side of the barrel portion relative to the second static pressure port.

6. The system of claim 5 , wherein:
the first electronics channel includes a differential pressure sensor communicating with the first and second static pressure ports;
the first electronics channel is configured to determine one of an angle of sideslip and an angle of attack based on a differential pressure sensed by the differential pressure sensor; and
the first electronics channel is configured to compensate the first and second altitude values based on the determined angle of sideslip or angle of attack.

7. The system of claim 5 , wherein:
the plurality of pressure sensing ports includes a third static pressure sensing port and a fourth static pressure sensing port in the barrel of the MFP, and
each of the third and fourth pressure sensing ports are spaced circumferentially between the first and second static pressure sensing ports.

8. The system of claim 7 , wherein:
the first electronics channel includes a first differential pressure sensor communicating with the first and second static pressure ports and a second differential pressure sensor communicating with the third and fourth static pressure sensing ports;
the first electronics channel is configured to determine an angle of sideslip based on a first differential pressure sensed by the first differential pressure sensor and to determine an angle of attack based on a second differential pressure sensed by the second differential pressure sensor; and
the first electronics channel is configured to compensate the first and second altitude values based on the determined angle of sideslip and angle of attack.

Assignees

• Rosemount Aerospace Inc

Inventors

• Boelke Joel
• Naslund Brian Brent
• Langemo Benjamin John

Classifications

• G01P21/025 Primary

  for measuring speed of fluids; for measuring speed of bodies relative to fluids (for measuring volume flow G01F25/10) · CPC title

• B64D45/00 Primary

  Aircraft indicators or protectors not otherwise provided for · CPC title

• G01P13/025

  indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw · CPC title

• G01C23/00

  Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration · CPC title

• B64D43/00 Primary

  Arrangements or adaptations of instruments · CPC title