The dual inlet exhaust design for the flying device incorporates easy-to-assemble designs with low number of components, suitable for limited space and small volume requirements, good performance. The exhaust is designed as a three-chamber cylinder with two coaxial inlet pipes running through the two chambers on both sides, extending into the middle compartment. The width of the two inlet tubes in the middle compartment is different. The inlet pipe at the two compartments on both sides has a bore. The outlet tube is located in the middle compartment, deviating to the side with a smaller expansion inlet, with the longitudinal axis of the outlet tube passing through the inlet tube.

An acoustic treatment panel includes at least one acoustically resistive layer, a reflective layer and at least one cellular structure interposed between the acoustically resistive layer and the reflective layer. The cellular structure includes cylindrical and identical main tubes which are closed at one end by the acoustically resistive layer and at the other end by the reflective layer, spacer zones between the main tubes, the spacer zones being sealed relative to one another, cutouts made at an end of certain main tubes, in contact with the reflective layer, and/or secondary tubes positioned in the main tubes and/or in the spacer zones, the cutouts and/or the secondary tubes being configured to generate acoustic cells of different dimensions from identical main tubes.

Lobed mixer nozzles for supersonic and subsonic aircraft, and associated systems and methods are disclosed herein. A representative lobe mixer nozzle includes a fan flow duct aligned along a longitudinal axis, and a core flow duct, also aligned along the longitudinal axis. At least one duct wall, for example, a splitter, forms, at least in part, a radially inner boundary of the fan flow duct, and a radially outer boundary of the core flow duct. The duct wall terminates at a reference exit plane, and has multiple first lobes extending radially inwardly, and multiple second lobes extending radially outwardly. At least one lobe is canted forward relative to the reference exit plane, and at least one lobe is canted aft relative to the reference exit plane.

Dissimilarly shaped aircraft nozzles with tandem mixing devices, and associated systems and methods are disclosed. An ejector nozzle in a representative embodiment includes a nozzle duct having a nozzle flow axis, a first axial position and a second axial position. The nozzle duct has a first cross-sectional shape at the first axial position, and a second cross-sectional shape at the second axial position, with the second shape being geometrically non-similar to the first shape. The nozzle further includes a fan flow duct portion and a core flow duct portion, both upstream of the first axial position. An ejector duct is positioned in fluid communication with the nozzle duct, and has at least one portion with a cross-sectional shape geometrically similar to the second cross-sectional shape. A first mixing device is positioned proximate to the first axial position to mix fan flow in the fan flow duct portion with core flow in the core flow duct portion, and a second mixing device is positioned downstream of the first mixing device to mix the fan flow and the core flow with flow through the ejector duct, and direct the combined flow generally along the nozzle flow axis. A representative design technique can include selecting an axial position for, and tailoring the shape of, the second mixing device, such as, their spanwise spacings, to enhance flow characteristics of interest, e.g., identified via computational fluid dynamic techniques, that may appear at (e.g., only at) a downstream position.

A thrust reverser track beam is disclosed. The thrust reverser track beam may comprise a recess defined by a reception surface and/or a perimeter surface surrounding the reception surface and extending away from the reception surface, wherein the reception surface and the perimeter surface bound a recess that is configured to receive a noise suppressing structure. The thrust reverser track beam may further comprise the noise suppressing structure. The recess is generally triangular in shape and may extend away from a plane. The noise suppressing structure may be generally triangular in shape and may extend away from a plane. The noise suppressing structure may be coupled within the recess of the track beam and/or to the track beam.

A mixer is mounted in an aircraft. A rear end part of a cylindrical portion of the mixer is divided by a guide vane into a plurality of divided tubular portions. In the plurality of divided tubular portions, a notch nozzle is formed on an outer wall of the cylindrical portion. A plurality of guide holes are formed to extend from the outer wall of the cylindrical portion to a rear end surface of the guide vane.

An active noise cancellation system (1) for cancelling environment noise perceived by a driver or passenger seated in a seat (3) mounted in a cabin of a vehicle, in combination with said seat, the seat comprising a seat cushion (19), a seat back (21) coupled to the seat cushion at a bottom end and extending upwards to a seat shoulder (23), and a headrest (22) coupled to the seat back, extending upwardly from the seat shoulder, the active noise cancellation system comprising an active noise cancellation circuit (ANC) (30), a plurality of microphones (10) mounted in the headrest and connected electrically to the ANC, and a plurality of speakers (16) mounted in the seat and connected electrically to the ANC circuit. The plurality of microphones comprises at least one first microphone mounted on a right side of the headrest and at least one second microphone mounted on a left side of the headrest, and the plurality of speakers comprises at least one first speaker mounted in the seat shoulder on a left side and at least one second speaker mounted in the seat shoulder on a right side, the right speaker configured to generate a noise cancellation sound from a noise signal picked up by the right microphone processed by the ANC circuit and the left speaker configured to generate a noise cancellation sound from a noise signal picked up by the left microphone processed by the ANC circuit.

An aircraft propulsion system apparatus includes a first skin, a second skin, an intermediate layer between the first skin and the second skin, a first cellular core and a second cellular core. The first cellular core is connected to the first skin and the intermediate layer. The first cellular core includes a plurality of first core chambers, where a first of the first core chambers is fluidly coupled with one or more first perforations in the first skin and one or more first perforations in the intermediate layer. The second cellular core is connected to the intermediate layer and the second skin. The second cellular core includes a plurality of second core chambers and a plurality of corrugations, where a first of the second core chambers is fluidly coupled with the first of the first core chambers through the one or more first perforations in the intermediate layer.

An arrowhead aircraft includes a pair of counter-rotating propellers, a jet engine module, and an exhausted module, wherein the counter-rotating propellers propel the aircraft but does not have angular momentum, and the exhausted module deployed around the exhausted end of the jet engine module, which reuses the waste heat from the exhausted end and reduces the noise. Wherein, the airflow system includes a shutter deployed at the bottom side of the body that controls the streamlines of airflow through the aircraft and a plurality of airfoils that will force the aircraft tilted to the desired direction. The present invention resolved the helicopter's vulnerabilities, such as its intricate mechanism, dragging response, dangers blades, hard to control angular momentum, high cost, and high training level.

An aerial vehicle that can comprise a housing comprising an outer wall at least partially defining an interior space, a mechanical power source at least partially located in the interior space of the housing, an exhaust header in communication with the mechanical power source for communicating exhaust fluid from the mechanical power source, and an exhaust system comprising at least an exhaust chamber extending at least partially in the interior space of the housing. The exhaust chamber can be in communication with the exhaust header, and the exhaust system can comprise an exhaust outlet for communicating the exhaust fluid from the exhaust system outside the aerial vehicle.