Acoustic air data systems

Patent metadata

Field	Value
Publication number	US-2020333371-A1
Application number	US-201916391192-A
Country	US
Kind code	A1
Filing date	Apr 22, 2019
Priority date	Apr 22, 2019
Publication date	Oct 22, 2020
Grant date	—

Abstract

An ultrasonic air data system can include a pole having a length longer than a boundary layer thickness of a boundary layer flow such that at least a distal end of the pole is configured to extend outwardly from an aircraft surface to be at least partially outside of the boundary layer flow. The system can include a transmitter disposed on or in the pole at or near the distal end of the pole such that the transmitter is located at least partially outside of the boundary layer flow when in use, wherein the transmitter is configured to output a transmitter signal. The system can include one or more receivers disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.

First claim

What is claimed is:

1 . An ultrasonic air data system, comprising:
a pole having a length longer than a boundary layer thickness of a boundary layer flow such that at least a distal end of the pole is configured to extend outwardly from an aircraft surface to be at least partially outside of the boundary layer flow; a transmitter disposed on or in the pole at or near the distal end of the pole such that the transmitter is located at least partially outside of the boundary layer flow when in use, wherein the transmitter is configured to output a transmitter signal; and one or more receivers disposed downstream of the pole as defined by the boundary layer flow and configured to receive the transmitter signal.

2 . The system of claim 1 , further comprising a controller configured to receive one or more signals from the one or more receivers and/or to operate the transmitter.

3 . The system of claim 1 , wherein the length of the pole is between about 1 inch and about 5 inches.

4 . The system of claim 1 , wherein the transmitter is configured to face backward along the aircraft for providing at least one of reduced susceptibility to icing, optimized directivity towards the one or more receivers, or extension of the signal just outside of the boundary layer.

5 . The system of claim 1 , wherein an axial distance between the pole and the one or more receivers is defined based on at least one of a frequency of the transmitter signal, a transmitter efficiency, and a maximum sound pressure level output.

6 . The system of claim 1 , wherein the transmitter is configured to vibrate radially with compression of the pole.

7 . The system of claim 1 , further comprising one or more receivers upstream of the pole.

8 . The system of claim 1 , wherein the one or more receivers include a plurality of receivers.

9 . The system of claim 8 , wherein the plurality of receivers are installed on a single plate.

10 . The system of claim 1 , wherein the pole includes a heater configured to prevent icing.

11 . The system of claim 1 , wherein the pole extends outwardly perpendicular to the aircraft surface.

12 . A transmitter assembly for an acoustic air data system, comprising:
a pole having a length longer than a maximum boundary layer thickness of a boundary layer flow on an aircraft of a predetermined cruise speed such that at least a distal end of the pole is configured to extend outwardly from an aircraft surface to be at least partially outside of the boundary layer flow; and a transmitter disposed on or in the pole at or near the distal end of the pole such that the transmitter is located at least partially outside of the boundary layer flow when in use, wherein the transmitter is configured to output a transmitter signal.

13 . The assembly of claim 12 , wherein the length of the pole is between about 1 inch and about 5 inches.

14 . The assembly of claim 12 , wherein the transmitter is configured to face backward along the aircraft for providing at least one of reduced susceptibility to icing, optimized directivity towards the one or more receivers, or extension of the signal just outside of the boundary layer.

15 . The assembly of claim 12 , wherein the transmitter can be configured to vibrate radially with compression of the pole.

16 . The assembly of claim 12 , wherein the pole includes a heater configured to prevent icing.

17 . A method for determining air data, comprising:
transmitting a transmitter signal outside of a boundary layer flow in a flow field into the boundary layer flow to be received by one or more receivers within the boundary layer flow.

18 . The method of claim 17 , further comprising receiving a received signal at the one or more receivers.

19 . The method of claim 18 , further comprising determining at least one of airspeed, temperature, and/or direction of the flow field based on at least one quality of the received signal compared to the transmitted signal.

20 . The method of claim 19 , wherein the at least one quality of the received signal includes time-of-flight between the transmitter and the one or more receivers.

Assignees

• Rosemount Aerospace Inc

Inventors

• Sly Jaime
• Shannon Daniel W
• Matheis Brian Daniel
• Ell Todd Anthony
• Kunik William
• Koushik Sudarshan N

Classifications

• G01P1/06

  Indicating or recording devices, e.g. for remote indication (indicating or recording in general G01D; registering or indicating working conditions of vehicles G07C5/00) · CPC title

• B64D43/02

  for indicating aircraft speed or stalling conditions · CPC title

• G01P5/245

  by measuring transit time of acoustical waves (measuring propagation velocity of acoustical waves per se G01H5/00) · CPC title

• G01P13/025 Primary

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

• G01P3/14 Primary

  by exciting one or more mechanical resonance systems · CPC title