System for noise control in air mobility unitizing an array of acoustic scatterers

Patent metadata

Field	Value
Publication number	US-12492012-B2
Application number	US-202217897391-A
Country	US
Kind code	B2
Filing date	Aug 29, 2022
Priority date	Aug 29, 2022
Publication date	Dec 9, 2025
Grant date	Dec 9, 2025

Abstract

A system for isolating sound generated by an aircraft utilizing a helipad may include a plurality of acoustic scatterers being disposed adjacent to at least a portion of a perimeter of the helipad. Each of the plurality of acoustic scatterers include channels having an open end and a terminal end. Additionally, each of the plurality of acoustic scatterers has an acoustic monopole response and an acoustic dipole response with a resonant frequency that is substantially similar to one another.

First claim

What is claimed is:

1 . A system for isolating sound generated by an aircraft utilizing a helipad, the system comprising:
a plurality of acoustic scatterers being disposed adjacent to at least a portion of a perimeter of the helipad, the plurality of acoustic scatterers extending upward from a landing surface of the helipad and being free standing cylindrical devices without using a reflective vertical surface; wherein the plurality of acoustic scatterers include a plurality of channels; and wherein the plurality of acoustic scatterers has an acoustic monopole response and an acoustic dipole response, wherein the acoustic dipole response and the acoustic monopole response of the plurality of acoustic scatterers have a resonant frequency that is substantially similar.

2 . The system of claim 1 , wherein the plurality of acoustic scatterers are separated from one another by a distance less than approximately twice a wavelength of the sound generated by the aircraft utilizing the helipad.

3 . The system of claim 2 , wherein the distance is between approximately 0.5 and 1.0 of the wavelength of the sound generated by the aircraft utilizing the helipad.

4 . The system of claim 1 , wherein the resonant frequency of the acoustic monopole response and the acoustic dipole response is substantially similar to a frequency of the sound generated by the aircraft utilizing the helipad.

5 . The system of claim 1 , wherein the plurality of channels each have an open end and a terminal end, the terminal ends of the plurality of channels being separate from each other.

6 . The system of claim 5 , wherein the plurality of channels of the plurality of acoustic scatterers are in a zigzag formation.

7 . The system of claim 5 , wherein a cross-section along a width of the plurality of acoustic scatterers defines a symmetrical shape having at least one line of symmetry, the symmetrical shape having an outer perimeter, wherein the open end of the plurality of channels are adjacent to the outer perimeter.

8 . The system of claim 1 , wherein each channel of the plurality of channels of the plurality of acoustic scatterers have a substantially similar volume.

9 . The system of claim 1 , wherein each channel of the plurality of channels of the plurality of acoustic scatterers have a substantially similar shape across a width of the plurality of acoustic scatterers.

10 . A system for isolating sound generated by an aircraft utilizing a helipad, the system comprising:
a plurality of acoustic scatterers being disposed adjacent to at least a portion of a perimeter of the helipad, wherein the plurality of acoustic scatterers are separated from one another by a distance less than approximately twice a wavelength of the sound generated by the aircraft utilizing the helipad, the plurality of acoustic scatterers extending upward from a landing surface of the helipad and being free standing cylindrical devices without using a reflective vertical surface; wherein the plurality of acoustic scatterers include a plurality of channels; and wherein the plurality of acoustic scatterers has an acoustic monopole response and an acoustic dipole response, wherein the acoustic dipole response and the acoustic monopole response of the plurality of acoustic scatterers have a resonant frequency that is substantially similar, the resonant frequency being substantially similar to the sound generated by the aircraft utilizing the helipad.

11 . The system of claim 10 , wherein the plurality of channels each have an open end and a terminal end, the terminal ends of the plurality of channels being separate from each other.

12 . The system of claim 11 , wherein the plurality of channels of the plurality of acoustic scatterers are in a zigzag formation.

13 . The system of claim 11 , wherein a cross-section along a width of the plurality of acoustic scatterers defines a symmetrical shape having at least one line of symmetry, the symmetrical shape having an outer perimeter, wherein the open end of the plurality of channels are adjacent to the outer perimeter.

14 . The system of claim 10 , wherein each channel of the plurality of channels of the plurality of acoustic scatterers have a substantially similar volume.

15 . The system of claim 10 , wherein each channel of the plurality of channels of the plurality of acoustic scatterers have a substantially similar shape across a width of the plurality of acoustic scatterers.

16 . A system for absorbing a target sound, the system comprising:
a plurality of acoustic scatterers that include a plurality of channels; the plurality of acoustic scatterers being separated from one another by a distance less than approximately twice a wavelength of the target sound, the plurality of acoustic scatterers extending upward from a landing surface of a helipad and being free standing cylindrical devices without using a reflective vertical surface; and wherein the plurality of acoustic scatterers has an acoustic monopole response and an acoustic dipole response, wherein the acoustic dipole response and the acoustic monopole response of the plurality of acoustic scatterers have a resonant frequency that is substantially similar, the resonant frequency being substantially similar to a frequency of the target sound.

17 . The system of claim 16 , wherein the plurality of channels each have an open end and a terminal end, the terminal ends of the plurality of channels being separate from each other.

18 . The system of claim 17 , wherein a cross-section along a width of the plurality of acoustic scatterers defines a symmetrical shape having at least one line of symmetry, the symmetrical shape having an outer perimeter, wherein the open end of the plurality of channels are adjacent to the outer perimeter.

19 . The system of claim 16 , wherein each channel of the plurality of channels of the plurality of acoustic scatterers have a substantially similar volume.

20 . The system of claim 16 , wherein each channel of the plurality of channels of the plurality of acoustic scatterers have a substantially similar shape across a width of the plurality of acoustic scatterers.

Assignees

• Toyota Eng & Mfg North America
• Toyota Motor Co Ltd

Inventors

• Sakamoto Mizuki
• Miwa Tomohiro
• EMOTO Reimi
• Su Xiaoshi
• Banerjee Debasish

Classifications

• E01F3/00

  Landing stages for helicopters, e.g. located above buildings (layout of airfields B64F; buildings or like structures for special purposes E04H) · CPC title

• B64F1/26 Primary

  for reducing engine or jet noise; Protecting airports from jet erosion · CPC title