Deployable noise shield panels
Technologies for providing noise shielding are described herein. In some examples, noise shields are installed proximate to one or more of the main engines of the aircraft. The noise shields can be extended during terminal operations and retracted during flight operations.
1. A blended wing body aircraft, comprising:
a fuselage comprising a port wing and a starboard wing continuously coupled to a nose section of the aircraft;
a first main engine housed within a first nacelle;
a second main engine housed within a second nacelle adjacent to the first nacelle;
a first shield panel located proximate to the first nacelle laterally disposed between the first main engine and the port wing, the first shield panel configured to be deployed to reduce at least a portion of noise emanating from the first main engine; and
a second shield panel located proximate to the second nacelle laterally disposed between the second main engine and the starboard wing, the second shield panel configured to be deployed to reduce at least a portion of noise emanating from the second main engine,
wherein the fuselage further comprises a first cavity to receive the first shield panel when the first shield panel is retracted into the fuselage, and a second cavity to receive the second shield panel when the second shield panel is retracted into the fuselage.
2. The aircraft of claim 1 , wherein the first shield panel comprises a first piston rotatably affixed to the first shield panel and the second shield panel comprises a second piston rotatably affixed to the second shield panel, wherein the first piston is extended to deploy the first shield panel and the second piston is extended to deploy the second shield panel.
3. The aircraft of claim 2 , wherein the first piston or the second piston are extended using a hydraulic system, a pneumatic system, or an electrical motor.
4. The aircraft of claim 1 , wherein the first shield panel comprises an exterior surface and an interior surface, wherein the interior surface comprises a curvature that reduces drag.
5. A method of operating a blended wing body aircraft, the method comprising:
commencing, using a blended wing body aircraft including a fuselage comprising a port wing and a starboard wing continuously coupled to a nose section of the aircraft, terminal operations;
deploying a shield panel located proximate to a first nacelle laterally disposed between a first main engine and the port wing to shield at least a portion of noise emanating from the first main engine housed within the first nacelle of the aircraft;
commencing takeoff operations; and
retracting the shield panel, wherein the fuselage comprises a cavity to receive the shield panel when the shield panel is retracted into the fuselage.
6. The method of claim 5 , wherein the shield panel comprises a piston rotatably affixed to the shield panel, wherein the piston is extended to deploy the shield panel.
7. The method of claim 6 , wherein the piston is extended using a hydraulic system, a pneumatic system, or an electrical motor.
8. The method of claim 5 , wherein the shield panel comprises an exterior surface and an interior surface, wherein the interior surface comprises a curvature that reduces drag.
9. An aircraft, comprising:
a fuselage;
a first main engine housed within a first nacelle; and
a first shield panel located proximate to the first nacelle laterally disposed between the
first main engine and a port wing, the first shield panel configured to be deployed to reduce at least a portion of noise emanating from the first main engine,
wherein the fuselage comprises a first cavity to receive the first shield panel when the first shield panel is retracted into the fuselage.
10. The aircraft of claim 9 , wherein the aircraft is a blended wing body aircraft.
11. The aircraft of claim 9 , further comprising:
a second main engine housed within a second nacelle; and
a second shield panel located proximate to the second nacelle between the second main engine and a starboard wing, the second shield panel configured to be deployed to reduce at least a portion of noise emanating from the second main engine.
12. The aircraft of claim 11 , wherein the fuselage comprises a second cavity to receive the second shield panel when the second shield panel is retracted into the fuselage.
13. The aircraft of claim 11 , wherein the first shield panel comprises a first piston rotatably affixed to the first shield panel and the second shield panel comprises a second piston rotatably affixed to the second shield panel, wherein the first piston is extended to deploy the first shield panel and the second piston is extended to deploy the second shield panel.
14. The aircraft of claim 13 , wherein the first piston or the second piston are extended using a hydraulic system, a pneumatic system, or an electrical motor.
15. The aircraft of claim 11 , wherein the first shield panel comprises an exterior surface and an interior surface, wherein the interior surface comprises a curvature that reduces drag.