Described are novel composite structural panels and methods of forming such panels. In some examples, a method comprises wrapping a mandrel with a composite tape to form a composite tube. This wrapping operation allows forming composite tubular structures with any cross-sectional profiles defined by the mandrel. The wrapping is also used to control the fiber orientations in the composite tubular structures. The composite tube is then cut into composite tubular structures. In some examples, the composite tube is partially cured prior to the cutting, which allows removal of the mandrel while preserving the shape of the composite tube. This cutting operation allows forming composite tubular structures with different lengths, shapes, and orientations of the ends. The composite tubular structures are disposed on a support structure and are bonded to each other. In some examples, this bonding operation also involves final curing of the composite tubular structures.

Methods and systems to electrically assist an internal combustion engine of an aircraft may be provided. A first bladed rotor may be rotated by a first internal combustion engine. Electricity may be generated from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine. In response to a predetermined event, such as an engine failure, mechanical power may be generated from the first motor generator instead of electricity. The mechanical power may be transferred to the first bladed rotor. The mechanical power may be generated by applying electricity to the first motor generator. The electricity applied is received from a second motor generator, where the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine that powers a second bladed rotor.

Methods and systems to electrically assist an internal combustion engine of an aircraft may be provided. A first bladed rotor may be rotated by a first internal combustion engine. Electricity may be generated from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine. In response to a predetermined event, such as an engine failure, mechanical power may be generated from the first motor generator instead of electricity. The mechanical power may be transferred to the first bladed rotor. The mechanical power may be generated by applying electricity to the first motor generator. The electricity applied is received from a second motor generator, where the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine that powers a second bladed rotor.

A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, a first thermal bus, and a turbomachine including a compressor, a rotary pump, and a first turbine, with the compressor and rotary pump in serial flow arrangement and the rotary pump being fluidly coupled to the first thermal bus.

A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, a first thermal bus, and a turbomachine including a compressor, a rotary pump, and a first turbine, with the compressor and rotary pump in serial flow arrangement and the rotary pump being fluidly coupled to the first thermal bus.

Aspects of the disclosure are directed to a system associated with an engine of an aircraft comprising: a duct, an inlet coupled to the duct, and a fence coupled to the inlet or located upstream of the inlet. In some embodiments, the system further comprises a valve body coupled to the duct. In some embodiments, the valve body includes at least one valve that is configured to rotate between a closed state and an open state.

Aspects of the disclosure are directed to a system associated with an engine of an aircraft comprising: a duct, an inlet coupled to the duct, and a fence coupled to the inlet or located upstream of the inlet. In some embodiments, the system further comprises a valve body coupled to the duct. In some embodiments, the valve body includes at least one valve that is configured to rotate between a closed state and an open state.

Aspects of the disclosure are directed to a panel configured for use on an aircraft nacelle, comprising: a first skin, a second skin, a first core portion coupled to the first skin and the second skin, a second core portion coupled to the first skin and the second skin, and an insert coupled to the first skin, the second skin, the first core portion, and the second core portion, the insert forming a corner fitting between the first core portion and the second core portion.

Aspects of the disclosure are directed to a panel configured for use on an aircraft nacelle, comprising: a first skin, a second skin, a first core portion coupled to the first skin and the second skin, a second core portion coupled to the first skin and the second skin, and an insert coupled to the first skin, the second skin, the first core portion, and the second core portion, the insert forming a corner fitting between the first core portion and the second core portion.

An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.