초록 ▼

A system for controlling aircraft boundary layer airflow comprising a frame structure configured to be coupled or integral to an inner surface of an aircraft nacelle, the frame configured to support to the nacelle, and/or a modular plenum configured to be received by the frame structure, the modular

A system for controlling aircraft boundary layer airflow comprising a frame structure configured to be coupled or integral to an inner surface of an aircraft nacelle, the frame configured to support to the nacelle, and/or a modular plenum configured to be received by the frame structure, the modular plenum comprising a truncated tetrahedron intersected at its apex by a duct. The frame may comprise a plurality of sub-frames. The system may further comprise a plurality of modular plenums, each configured to fit within a sub-frame. The system may further comprise a flexible material configured to couple a first duct to a second duct. The system may further comprise a nacelle configured to receive the system.

대표청구항 ▼

1. A system for controlling aircraft boundary layer airflow comprising: a frame structure configured to be coupled to an inner surface of an aircraft nacelle, the frame configured to provide support to the nacelle;a plurality of modular plenums configured to be received by the frame structure, the m

1. A system for controlling aircraft boundary layer airflow comprising: a frame structure configured to be coupled to an inner surface of an aircraft nacelle, the frame configured to provide support to the nacelle;a plurality of modular plenums configured to be received by the frame structure, the modular plenum comprising a truncated tetrahedron intersected tangentially at its apex by a pipe duct,wherein the frame structure comprises a plurality of sub-frames;each modular plenum configured to fit within a sub-frame; andthe sub-frames each comprising a geometry complementary to the geometry of the sub-frames. 2. The system of claim 1, further comprising a flexible material configured to couple a first duct to a second duct. 3. The system of claim 1, further comprising the nacelle configured to receive the system. 4. The system of claim 3, wherein the nacelle comprises a perforated outer surface, wherein air enters the modular plenum through the perforated outer surface. 5. The system of claim 1, further comprising a pump that draws air into the modular plenum. 6. A system for controlling aircraft boundary layer airflow comprising: a frame structure configured to be coupled to an inner surface of an aircraft nacelle, the frame configured to provide support to the nacelle;a modular plenum configured to be received by the frame structure, the modular plenum comprising a truncated tetrahedron intersected tangentially at its apex by a pipe duct. 7. The system of claim 6, wherein the frame comprises a plurality of sub-frames. 8. The system of claim 7, wherein the modular plenum is configured to fit within a sub-frame. 9. The system of claim 6, further comprising the nacelle configured to receive the system. 10. The system of claim 9, wherein the nacelle comprises a perforated outer surface, wherein air enters the modular plenum through the perforated outer surface. 11. The system of claim 10, further comprising a pump that draws air into the modular plenum. 12. The system of claim 11, wherein the pump draws air into the modular plenum through the perforated outer surface formed in the aircraft nacelle. 13. The system of claim 7, wherein the plurality of sub-frames are configured to provide support to the aircraft nacelle.