Multi-function air data probe having multi-hole ports used for determining angle of attack, total and static pressure values

Patent metadata

Field	Value
Publication number	US-2022120780-A1
Application number	US-202117562495-A
Country	US
Kind code	A1
Filing date	Dec 27, 2021
Priority date	Oct 16, 2019
Publication date	Apr 21, 2022
Grant date	—

Abstract

A multi-function air data probe comprises a probe stem having an outer surface that extends between a first end and an opposite second end, with the probe stem having a first cross-sectional diameter; and a probe head having an outer surface that extends between a proximal end and a distal end, wherein the proximal end of the probe head is coupled to the first end of the probe stem. The probe head has a second cross-sectional diameter that is larger than the first cross-sectional diameter of the probe stem. A plurality of multi-hole ports is located in the probe head, with the multi-hole ports extending into and through the probe stem. The air data probe is operative to make measurements used to determine one or more of angle of attack values, total pressure values, and static pressure values.

First claim

What is claimed is:

1 . A method of health management and assessment for an air data probe, the method comprising:
performing a calibration process for the air data probe prior to installation of the air data probe on a vehicle; performing an operational process after the air data probe is installed on the vehicle; computing residuals for individual pressure channels of the air data probe and an aggregated response function, based on outputs from the calibration process and the operational process; storing and trending the residuals over time; evaluating a trendline for the residuals against one or more threshold values; and announcing a message when one or more of the threshold values is exceeded, indicating that the health of the air data probe is compromised.

2 . The method of claim 1 , wherein the calibration process comprises:
measuring or calculating one or more calibration curves of pressure versus angle of attack for the air data probe; defining the one or more threshold values and associated actions; storing the one or more calibration curves and the one or more threshold values; and storing a ratio of specific heats.

3 . The method of claim 2 , wherein the operational process comprises:
measuring a pressure response of ports in the air data probe with respect to angle of attack during operation of the vehicle; determining a total pressure by curve fitting the measured pressure response of the ports and calculating a maximum value; measuring static pressure responses from independently located static pressure sensors during operation of the vehicle; and normalizing the measured responses for Mach number.

4 . The method of claim 1 , wherein the air data probe comprises:
a probe stem that extends between a first end and an opposite second end, the probe stem having a first cross-sectional diameter; a probe head coupled to the first end of the probe stem, wherein the probe head has a second cross-sectional diameter that is larger than the first cross-sectional diameter of the probe stem; a plurality of multi-hole ports in the probe head, the multi-hole ports extending into and through the probe stem; a base flange coupled to the probe stem at the opposite second end; and one or more static pressure ports in the base flange; wherein the probe stem and the probe head each have a substantially cylindrical shape.

5 . The method of claim 1 , wherein the vehicle is an aircraft.

6 . The method of claim 5 , wherein the air data probe is configured to provide measurement of angle of attack, static pressure, and total pressure, for the aircraft.

7 . The method of claim 1 , wherein the air data probe comprises:
a probe stem having an outer surface that extends along an axial direction between a first end and an opposite second end, the probe stem having a first cross-sectional diameter; a probe head having an outer surface that extends along the axial direction between a proximal end and a distal end, wherein the proximal end of the probe head is coupled to the first end of the probe stem, wherein the probe head has a second cross-sectional diameter that is larger than the first cross-sectional diameter of the probe stem; and a plurality of multi-hole ports located in the probe head, the multi-hole ports extending into and through the probe stem along the axial direction, the multi-hole ports defined by respective sensor manifold tubes each having a plurality of openings; wherein the outer surface of the probe head includes an array of sensor holes radially arranged in sensor hole rows along the axial direction; wherein each of the sensor manifold tubes respectively communicates with one of the sensor hole rows along the axial direction through respective port tubes coupled between each of the sensor holes and the plurality of openings in the respective sensor manifold tubes.

8 . An air data sensor system, comprising:
a multi-function air data probe on a vehicle, the air data probe configured to protrude into an airflow to collect air data; and an electronics housing coupled to the air data probe, the electronics housing containing at least one processor; wherein the at least one processor is operative to perform a method of health management and assessment for the air data probe, the method comprising:
computing residuals for individual pressure channels of the air data probe and an aggregated response function, based on outputs from a prior calibration process and operational process;
storing and trending the residuals over time;
evaluating a trendline for the residuals against one or more threshold values; and
announcing a message when one or more of the threshold values is exceeded, indicating that the health of the air data probe is compromised.

9 . The air data sensor system of claim 8 , wherein the air data probe is operative to make measurements used by the at least one processor to determine one or more of angle of attack values, total pressure values, and static pressure values.

10 . The air data sensor system of claim 8 , wherein the air data probe comprises:
a probe stem having an outer surface that extends along an axial direction between a first end and an opposite second end, the probe stem having a first cross-sectional diameter; a probe head having an outer surface that extends along the axial direction between a proximal end and a distal end, wherein the proximal end of the probe head is coupled to the first end of the probe stem, wherein the probe head has a second cross-sectional diameter that is larger than the first cross-sectional diameter of the probe stem; and a plurality of multi-hole ports located in the probe head, the multi-hole ports extending into and through the probe stem along the axial direction, the multi-hole ports defined by respective sensor manifold tubes each having a plurality of openings; wherein the outer surface of the probe head includes an array of sensor holes radially arranged in sensor hole rows along the axial direction; wherein each of the sensor manifold tubes respectively communicates with one of the sensor hole rows along the axial direction through respective port tubes coupled between each of the sensor holes and the plurality of openings in the respective sensor manifold tubes.

11 . The air data sensor system of claim 8 , wherein the vehicle is an aircraft.

12 . The air data sensor system of claim 11 , wherein the air data probe is implemented in a digital line replaceable unit (LRU) for the aircraft.

Assignees

• Honeywell Int Inc

Inventors

• Anderson Morris G
• Gordon Grant A

Classifications

• G01P13/025 Primary

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

• G01P5/165 Primary

  Arrangements or constructions of Pitot tubes · CPC title

• G01P21/025

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

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• B64D43/02

  for indicating aircraft speed or stalling conditions · CPC title