Acoustic probe array for aircraft

1. An aerial vehicle comprising:

an aircraft sensor probe to detect an audio signal, the aircraft sensor probe comprising:

a nosecone including a tip and a body portion, wherein a diameter of the body portion of the nosecone is smaller than a length of the nosecone and the nosecone is configured to mitigate drag of the sensor probe in an airflow;

a mount assembly downstream of the nosecone and positioned rearward of the tip and including a mount aperture in fluid communication within an external environment of the sensor probe and configured to direct airflow from the external environment rearward;

a microphone positioned downstream of the mount assembly and secured in a perpendicular orientation relative to a direction of airflow exiting the mount aperture; and

an acoustic corridor to transmit the audio signal extending from an opening at an external environment of the sensor probe to the microphone via the mount aperture, wherein the opening is defined by a side of the nosecone.

2. The aircraft sensor probe of claim 1 , further comprising an intermediary filtering media arranged between the external environment and the microphone.

3. The aircraft sensor probe of claim 2 , wherein the intermediary filtering media is a fabric.

4. The aircraft sensor probe of claim 2 , wherein the intermediary filtering media is porous.

5. The aircraft sensor probe of claim 1 , wherein the nosecone comprises a hydrophobic material.

6. The aircraft sensor probe of claim 1 further comprising:

a flexible wiring harness electrically coupled to the microphone, wherein the flexible wiring harness electrically couples the microphone to the aerial vehicle.

7. The aircraft sensor probe of claim 1 , wherein the microphone assembly mount is defined by a cylindrical and hollow body that is at least partially closed at one end, the mount aperture extending through the one end.

8. The aircraft sensor probe of claim 1 , further comprising:

an elongated member having a hollow interior extending from the aerial vehicle and coupled to the aircraft sensor probe;

wherein the elongated member dampens oscillation of the aircraft sensor probe relative to the aircraft.

9. The aircraft sensor probe of claim 8 , further comprising:

a nosecone mount coupled to a distal end of the nosecone, wherein a sealing element is positioned between the nosecone mount and the nosecone; and

wherein the nosecone mount is coupled to an end of the elongated member opposite the aerial vehicle.

10. An aircraft sensor probe to detect an audio signal comprising:

a nosecone including a tip and a body portion, wherein a diameter of the body portion of the nosecone is smaller than a length of the nosecone and the nosecone is configured to mitigate drag of the sensor probe in an airflow;

a mount assembly downstream of the nosecone defining a mount aperture extending therethrough;

an audio sensor coupled to the mount assembly and positioned rearward of the tip and downstream of the nosecone;

an acoustic corridor to transmit the audio signal extending from an external environment of the sensor probe to the audio sensor;

an opening defined by the nosecone and fluidly coupled with the acoustic corridor;

an intermediary media positioned at the acoustic corridor arranged between the nosecone and the audio sensor; and

wherein the sensor probe receives the airflow for a plurality of local flow angles and reduces noise from direct flow for the audio signal.

11. The aircraft sensor probe of claim 10 , wherein the mount assembly positions the audio sensor in a perpendicular orientation to a direction of the airflow encountered by the nosecone.

12. The aircraft sensor probe of claim 10 , wherein the opening is defined along an exterior of the nosecone.

13. The aircraft sensor probe of claim 10 , wherein the opening is configured reduce an impact of airflow to assist with noise reduction.

14. The aircraft sensor probe of claim 10 , wherein:

the intermediary media is a fabric; and

the intermediary media at least one of filters the airflow or selectively attenuates the audio signal.

15. The aircraft sensor probe of claim 10 , wherein the nosecone may guide the airflow along the nosecone to limit direct entry of the airflow into the acoustic corridor.

16. The aircraft sensor of claim 10 , wherein a direction or shape of the opening is configured to reduce an impact of airflow in certain directions to assist with noise reduction.

17. An aircraft comprising:

a fuselage;

a first wing extending from the fuselage;

a second wing extending from the fuselage opposite the first wing;

a propeller; and

one or more sensor probes to detect an audio signal comprising:

a nosecone including a tip and a body portion, wherein the nosecone is configured to mitigate drag of the sensor probes in an airflow,

an audio sensor positioned rearward of the tip and downstream of the nosecone,

an acoustic corridor to transmit the audio signal extending from an opening at an external environment of the sensor probes to the audio sensor, and

a mount assembly downstream of the nosecone and defining a mount aperture extending therethrough, the microphone assembly mount coupled with the audio sensor.

18. The aircraft of claim 17 , wherein the one or more sensor probes further comprise:

an intermediary filtering media positioned at the acoustic corridor and arranged between the nosecone and the audio sensor, and

wherein the intermediary media is a fabric.

19. The aircraft of claim 17 , wherein:

the one or more sensor probes include a first sensor probe and a second sensor probe;

the first sensor probe extends from a leading edge of the first wing; and

the second sensor probe extends from a leading edge of the second wing.

20. The aircraft of claim 17 , wherein:

the audio sensor is positioned distal to the microphone mount; and

the mount aperture at least partially defines the acoustic corridor.