Systems and methods for correcting acoustic error in pressure sensors

• US 10,323,997 B2
• Filed: 07/03/2017
• Issued: 06/18/2019
• Est. Priority Date: 07/03/2017
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Chuck, Chen, Sato, Sho
• Primary Examiner(s): Ha, Nguyen Q.
• Application Number:
  US15/641,148
• Publication Number:
  US 20190003912A1
• Time in Patent Office: 715 Days
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: G01L 19/0092 Pressure sensor associated with other sensors, e.g. for measuring acceleration or temperature G01L9/025, G01L9/045, G01L9/065, G01L9/085, G01L9/105, G01L9/125, G01L19/02, G01L19/04 take precedence; measuring two or more variable G01D21/02; temperature sensors with pressure compensation G01K1/26
• CPC Class Codes: G01L 27/002 Calibrating, i.e. establishing true relation between transducer output value and value to be measured, zeroing, linearising or span error determination
• CPC Class Codes: G01M 9/06 Measuring arrangements specially adapted for aerodynamic testing
• CPC Class Codes: G01M 9/08 Aerodynamic models
• CPC Class Codes: G01P 13/025 indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw

Abstract

Various techniques are provided for correcting error in static pressure data. In one example, a system includes an aircraft component. The aircraft component can include a port disposed within the aircraft component. A static pressure sensor is disposed within the port. The static pressure sensor is configured to provide primary pressure data in response to environmental air pressure. The data provided can include error due to acoustic disturbance. The system can also include an acoustic sensor configured to provide acoustic data in response to the acoustic disturbance. Data from the static pressure sensor and the acoustic sensor can be provided to a processor communicatively coupled to the static pressure sensor and the acoustic sensor. The processor can be configured to determine corrected static pressure data using the provided primary pressure data and the provided acoustic data. Additional systems and similar methods are also provided.

Claims

1. A system comprising:

an aircraft component;

a port disposed within the aircraft component;

a static pressure sensor disposed within the port and configured to provide primary pressure data in response to at least environmental air pressure and an acoustic disturbance;

an acoustic sensor configured to provide acoustic data in response to the acoustic disturbance; and

a processor communicatively coupled to the static pressure sensor and the acoustic sensor and configured to determine corrected static pressure data using the provided primary pressure data and the provided acoustic data.

2. The system of claim 1, wherein the acoustic data corresponds to at least an amplitude and a frequency of the acoustic disturbance.

3. The system of claim 1, wherein the processor is configured to determine an acoustic modifier from the provided acoustic data and apply the acoustic modifier to the provided primary pressure data to determine the corrected static pressure data, and wherein the acoustic modifier is configured to correct for an acoustic component of the provided primary pressure data.

4. The system of claim 1, wherein the static pressure sensor is a first pressure sensor and the system further comprises:

a second pressure sensor configured to provide dynamic and/or total pressure data in response to at least movement of an aircraft, wherein the processor is further configured to use the dynamic and/or total pressure data to determine the corrected static pressure data.

5. The system of claim 4, wherein the processor is configured to determine modified pressure data using the provided primary pressure data and the provided dynamic and/or total pressure data and use the modified pressure data to determine the corrected static pressure data, wherein the modified pressure data is configured to correct for a dynamic pressure component of the provided primary pressure data.

6. The system of claim 1, wherein the acoustic sensor is disposed within 2 feet of the port.

7. The system of claim 1, wherein the system is an aircraft.

8. The system of claim 1, wherein the aircraft component is a portion of an intake of an aircraft propulsor or a portion of a fuselage or a wing, and wherein the acoustic disturbance comprises acoustic noise generated by operation of the aircraft propulsor and/or movement of the aircraft component.

9. The system of claim 1, wherein the aircraft component is a scale wind tunnel model.

10. The system of claim 1, further comprising:

a plurality of ports disposed within the aircraft component;

a plurality of static pressure sensors, each static pressure sensor disposed within a corresponding one of the ports and configured to provide corresponding primary pressure data in response to at least corresponding environmental air pressure and a corresponding acoustic disturbance associated with the corresponding static pressure sensor; and

a plurality of acoustic sensors, each acoustic sensor associated with a corresponding one of the ports and configured to provide corresponding acoustic data in response to the corresponding acoustic disturbance associated with the corresponding static pressure sensor, wherein the processor is communicatively coupled to each of the plurality of static pressure sensors and acoustic sensors and the corrected static pressure data is determined using the plurality of corresponding provided primary pressure data and the plurality of corresponding provided acoustic data.

11. A method comprising:

receiving primary pressure data from a static pressure sensor in response to at least environmental air pressure and an acoustic disturbance, wherein the static pressure sensor is disposed within a port, and wherein the port is disposed within an aircraft component;

receiving acoustic data from an acoustic sensor in response to the acoustic disturbance; and

determining corrected static pressure data using the received primary pressure data and the received acoustic data.

12. The method of claim 11, wherein the acoustic data corresponds to at least an amplitude and a frequency of the acoustic disturbance.

13. The method of claim 11, wherein determining the corrected static pressure data further comprises determining an acoustic modifier from the received acoustic data and applying the acoustic modifier to the received primary pressure data, and wherein the acoustic modifier is configured to correct for an acoustic component of the received primary pressure data.

14. The method of claim 11, wherein the static pressure sensor is a first pressure sensor and the method further comprises:

receiving dynamic and/or total pressure data from a second pressure sensor in response to at least movement of an aircraft, wherein determining the corrected static pressure data also uses the received dynamic and/or total pressure data.

15. The method of claim 14, wherein determining the corrected static pressure data further comprises determining modified pressure data using the received primary pressure data and the received dynamic and/or total pressure data, and wherein the modified pressure data is configured to correct for a dynamic pressure component of the received primary pressure data.

16. The method of claim 11, wherein the acoustic sensor is disposed within 2 feet of the port.

17. The method of claim 11, wherein static pressure sensor and the acoustic sensor are disposed on an aircraft.

18. The method of claim 17, wherein the static pressure sensor and/or the acoustic sensor are disposed on a portion of an intake of an aircraft propulsor or a portion of a fuselage or a wing, and wherein the acoustic disturbance comprises acoustic noise generated by operation of the aircraft propulsor and/or movement of the aircraft component.

19. The method of claim 11, wherein the aircraft component is a scale wind tunnel model.

20. The method of claim 11, further comprising:

receiving primary pressure data from a plurality of static pressure sensors, each of the plurality of static pressure sensors disposed within a corresponding one of a plurality of ports, wherein the plurality of ports are disposed within the aircraft component; and

receiving acoustic data from a plurality of acoustic sensors, each of the plurality of acoustic sensors associated with a corresponding port, wherein the corrected static pressure data is determined using the plurality of corresponding received primary pressure data and the plurality of corresponding received acoustic data.