Abstract: Braking systems for aircraft are disclosed. An example braking system includes a fan cowl having a leading edge and a trailing edge. The braking system includes a hinge assembly coupled between the leading edge and a fan cage of an aircraft engine to enable the fan cowl to move between a stowed position and a deployed position. An actuator is coupled to the leading edge of the fan cowl, and the actuator is to move the fan cowl via the hinge from the stowed position to the deployed position in a direction away from the aircraft engine and toward a fore end of the aircraft to provide an air brake during a braking event.

Abstract: A compact inlet design including a single bulkhead and/or an acoustic panel extending into nacelle lip region for noise reduction. The compact inlet is used with a low power fluid ice protection system capable of preventing ice build-up on the acoustic panel in the nacelle lip region.

Abstract: An airflow disruptor for a gas turbine engine bleed air exhaust port employs a disruptor plate rotatably mounted upstream from an exhaust port of an exhaust duct. An actuator is coupled to the disruptor plate and adapted to rotate the disruptor plate into an external airflow responsive to temperature of exhaust flow in the exhaust port whereby the external airflow is turbulated upstream of the exhaust port.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to move the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is moved away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet and a compressor outlet. The compressor inlet to receive airflow from a first air supply source. An air mixing device having a first mixer inlet to receive compressed air from the compressor outlet and a second mixer inlet to receive bleed air from a bleed air system. The bleed air to provide a motive fluid to enable the air mixing device to mix the bleed air and the compressed air to produce mixed air for the anti-icing system.

Abstract: Hybrid propulsion engines for aircraft are described herein. An example hybrid propulsion engine includes a propulsor and a gas turbine engine having a first drive shaft. The hybrid propulsion engine also includes an electric motor having a second drive shaft, and the propulsor is coupled to the second drive shaft. The hybrid propulsion engine further includes a clutch coupled between the first drive shaft and the second drive shaft to enable the gas turbine engine to drive the propulsor, via the clutch, during a first mode of operation and to enable the electric motor to drive the propulsor during a second mode of operation.

Abstract: Method, system, and aircraft for providing anti-ice protection including a supply of ferrofluid that is flowed out of orifices along a first region of an aerodynamic surface. The flowed ferrofluid is urged toward an aperture on a second region. The aperture is arranged relative to a magnetic field generator. A magnetic field generated by the magnetic field generator attracts the ferrofluid into the aperture while water droplets carried by the ferrofluid continue past the aperture.

Abstract: A method for controlling compressed air sent to pneumatic systems. The method includes acquiring a set of performance demands for each of a plurality of pneumatic systems in a platform, where the performance demands indicate needs for the compressed air supplied to each of the pneumatic systems, identifying a maximum allowable air discharge temperature limit of a variable speed air compressor configured to supply compressed air to the pneumatic systems, and controlling an operation of the compressor to supply the compressed air to the pneumatic systems to meet the acquired performance demands for at least one of the pneumatic systems while operating the compressor below the maximum allowable air discharge temperature limit.

Abstract: An aircraft engine system has a turbofan engine with a lubricating oil system. An oil pump is connected to pump oil from the oil tank through a cooling circuit to the turbofan engine. The cooling circuit has a bleed air boosted engine oil cooler assembly with a liquid/air heat exchanger (LAHEX) connected to an oil inlet conduit and receiving fan air from a high bypass fan of the turbofan engine as the cooling working fluid. The LAHEX is connected to an oil exit conduit. An ejector downstream of the LAHEX receives bleed air from a compressor section of the turbofan engine. The ejector draws the fan air through the LAHEX.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: Aircraft cooling and heating systems and related methods are disclosed. An example apparatus includes an air compressor operatively coupled to a turbine engine. The air compressor is configured to generate compressed air at a first temperature. A vapor cycle system configured to reduce the first temperature of the compressed air provided by the air compressor to a second temperature that is less than the first temperature.

Abstract: Compressor valves for aircraft are described herein. An example valve for a compressor includes a first end plate, a second end plate, and a first sleeve valve disposed between the first and second end plates. The first the first sleeve valve is operable between a closed state and an open state. The example valve also includes a second sleeve valve disposed between the first and second end plates and within the first sleeve valve such that a plenum is formed between the first end plate, the second end plate, the first sleeve valve, and the second sleeve valve. The plenum is to receive outlet air from an outlet of the compressor. A passageway is formed through a center of the valve to be fluidly coupled to an inlet of the compressor. The second sleeve valve is operable between a closed state and an open state.

Abstract: Hybrid propulsion engines for aircraft are described herein. An example hybrid propulsion engine includes a propulsor and a gas turbine engine to drive the propulsor during a first mode of operation. The gas turbine engine has a core air intake. The hybrid propulsion engine also includes an electric motor to drive the propulsor during a second mode of operation and a damper disposed in the core air intake of the gas turbine engine to block airflow through the core air intake during the second mode of operation.

Abstract: Flow multiplier systems for aircraft are described herein. A flow multiplier system includes a turbo-compressor having a compressor, a turbine, and a drive shaft coupled between the compressor and the turbine. A compressor outlet of the compressor is fluidly coupled to an ejector in a gas turbine engine. The system also includes a supply line fluidly coupling a compressed air tank and a turbine inlet and a valve coupled to the supply line. The system includes a controller configured to, based on an input signal requesting to increase output power of the gas turbine engine, send a command signal to open the valve to enable a flow of pressurized air from the compressed air tank to the turbine inlet. The turbine drives the compressor to create high pressure air at the compressor outlet, which is provided into the gas turbine engine to increase the output power.

Abstract: Pressurized air systems for aircraft and related methods are described herein. An example pressurized air system includes a compressor having a compressor inlet and a compressor outlet. The compressor inlet receives air from a first air source and the compressor outlet supplies pressurized air to an environmental control system (ECS). The pressurized air system includes a turbine having a turbine inlet to receive air from a second air source, a first overrunning clutch operatively coupled between an output shaft of an accessory gearbox and the compressor, the accessory gearbox operatively coupled to a drive shaft extending from an engine of the aircraft, and a second overrunning clutch operatively coupled between the compressor and the turbine. The first and second overrunning clutches enable the accessory gearbox to drive the compressor during a first mode of operation and enable the turbine to drive the compressor during a second mode of operation.

Abstract: A ground service vehicle system employs autonomous vehicles that can be reconfigured with interchangeable service modules to provide different services. The autonomous service vehicles can be remotely controlled and dispatched in swarms to provide different services at a location.

Abstract: A pre-cooler system employs a powered pre-cooler fan assembly having a fan adapted to receive bypass engine fan air through an inlet plenum with an outlet guide vane array (OGVA) adapted to control airflow from the inlet plenum and fan, with a rotational power source operationally connected to the fan. A shroud directs airflow from the inlet plenum, fan and OGVA into a pre-cooler disposed downstream of the fan and OGVA.

Abstract: An aircraft launching system and method include a first lifting sub-system including a first tether that removably couples to an aircraft, and a second lifting sub-system including a second tether that couples the first lifting sub-system to the second lifting sub-system.

Abstract: A method for controlling compressed air sent to pneumatic systems. The method includes acquiring a set of performance demands for each of a plurality of pneumatic systems in a platform, where the performance demands indicate needs for the compressed air supplied to each of the pneumatic systems, identifying a maximum allowable air discharge temperature limit of a variable speed air compressor configured to supply compressed air to the pneumatic systems, and controlling an operation of the compressor to supply the compressed air to the pneumatic systems to meet the acquired performance demands for at least one of the pneumatic systems while operating the compressor below the maximum allowable air discharge temperature limit.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.