Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

The invention discloses a propeller-driven helicopter or airplane which comprises a fuselage and a propeller comprising a plurality of blades, wherein a plurality of pressure pipes are uniformly distributed between windward sides and leeward sides of the blades; a plurality of first inlets are formed in the windward sides and are communicated with outside via first channels in the blades and second outlets at tails of the blades; a high-pressure fluid of a low-speed fluid layer formed when a fluid flows through the leeward sides in a widthwise direction flows towards a low-pressure fluid of a high-speed fluid layer formed when the fluid flows through the first inlets, the first channels and the second outlets; and an upward pressure generated by the high-pressure fluid is opposite to a downward pressure generated by an external fluid above the windward sides, so that a fluid pressure above the propeller is decreased.

Disclosed is an aircraft having an aircraft electric motor; a motor controller; a structure having ribs and spars defining a wingbox of the aircraft; a feeder cable connecting the motor controller and the aircraft electric motor through the wingbox; and a grommet defining an orifice by an inner perimeter sized to receive the feeder cable, the passage housing a thermoelectric cooler having a cooled side thermally conductive with the inner perimeter at a thermal conductivity greater than 100 watts per meter-kelvin at one ° C. and a heated side thermally conductive with the structure at the thermal conductivity.

Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

Fluid systems are described herein. An example fluid system includes a main body and a heating member attached to the main body. The main body has a leading edge, a trailing edge, an injection opening, a suction opening, a channel, a first passageway, a second passageway, a first opening, a second opening, and a third opening. The channel extends from the injection opening to the suction opening. The first passageway extends from the first opening to the second opening. The first opening is in communication with the channel and the second opening is in communication with the second passageway. The second passageway is in communication with the first passageway and extends to the third opening, which is in communication with a first environment exterior to the second passageway. The heating member is sized and configured to heat fluid traveling through the second passageway.

An aircraft wing has a wing body with a span and a chord. A skin of the wing body has a leading edge portion with an inner surface delimiting a cavity of the wing body. A wing ice protection system includes a curved flow guide disposed within the cavity and spaced apart from the leading edge portion to define a fluid channel, A bleed air supply is operable to convey bleed air to the fluid channel. Turbulence-generating members are positioned within the leading edge portion to engage the bleed air in the fluid channel. The members are spaced apart along the fluid channel in a chordwise direction and/or in a spanwise direction. A thermal barrier may be disposed on the curved flow guide to thermally insulate the leading edge interior from the fluid channel.

A wing comprising a fixed main part and a leading edge slat with upper and lower surface rear edges. The wing main part has an upper surface wall, which extends downstream and in alignment with the upper surface rear edge, and a lower surface wall, which extends downstream and in alignment with the lower surface rear edge. The wing has an upper surface gap between the end of the upper surface rear edge and the end of the upper surface wall and a lower surface gap between the end of the lower surface rear edge and the end of the lower surface wall. The wing has an upper surface channel downstream of the upper surface gap and a lower surface channel downstream of the lower surface gap. The wing comprises a suction system connected to each channel and arranged to suck the air contained in the channel.

The present invention provides a propulsion system for an aircraft. The system includes one or more thrust producing portions, wherein the one or more thrust producing portions include one or more duct means. The duct means are at least partially formed or defined by two or more substantially parallel wall members. At least one flapping or waving wing member is provided, at least partially located or positioned substantially within the one or more duct means, wherein the flapping or waving motion of the at least one wing member creates thrust, enabling the aircraft to fly in use.

The invention discloses a lift source for an aircraft comprising a fuselage and wings, wherein first channels are formed in the wings, a plurality of first inlets are formed in upper surfaces of the wings, a plurality of first pressure ports are formed in lower surfaces of the wings and are communicated with the first inlets via the first channels; and spoiler devices are arranged in the first channels and under the effect of the spoiler devices, form high-speed fluid layers on the upper surfaces of the wings, thereby generating a pressure difference from the lower surfaces of the wings which counteracts an external fluid pressure on the upper surfaces of the wings in the opposite direction, so a lift is generated by reduction of fluid resistance when fluid flows through the upper and lower surfaces of the wings, thereby developing a high-speed aircraft with a larger lift and thrust.

Embodiments described herein relate to a vertical take-off and landing aircraft, specifically an electric or hybrid electric aircraft having a plurality of ducted fans. The aircraft includes a plurality of axially oriented fans, laterally oriented fans, forward air intakes, side exit ports and rear exhaust ports. The air-craft achieves flight by capturing air in the intakes and diverting the air through the axially oriented fans or the laterally oriented fans through the channels selectively.