An aircraft comprises a fuselage, a front wing and a rear wing that extends laterally from the fuselage for generating lift during cruise, a boom extending in a front-back direction supported by these wings to be spaced apart from the fuselage, at least one VTOL rotor supported on the boom and having one or more blades for generating thrust in a vertical direction during take-off and landing, and a cooling system within the boom including two radiators stored between an inlet and an outlet provided on the boom, to cool an element with a low control temperature and an element with a high control temperature, for example, a motor and an inverter, respectively, among electric elements of the at least one VTOL rotor by using a first radiator that is positioned on the inlet side and a radiator that is positioned on the outlet side among the two radiators.

A method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.

A directional control system for a rotorcraft having a tail boom including a no-tail-rotor apparatus configured to control rotorcraft yaw using forced air ejected from the tail boom and a duct configured to deliver the forced air to the no-tail-rotor apparatus. The directional control system comprises a heat exchanger having air passages and fluid passages, the air passages in fluid communication with the duct, the fluid passages in heat exchange relationship with the air passages and configured for receiving a cooling fluid, and a forced air driver in fluid communication with the duct for driving the forced air through the duct to the no-tail-rotor apparatus. Methods of providing directional control in a rotorcraft are also discussed.

A heat exchanger which may be used in an engine, such as a vehicle engine for an aircraft or orbital launch vehicle. is provided. The heat exchanger may be configured as generally drum-shaped with a multitude of spiral sections, each containing numerous small diameter tubes. The spiral sections may spiral inside one another. The heat exchanger may include a support structure with a plurality of mutually axially spaced hoop supports, and may incorporate an intermediate header. The heat exchanger may incorporate recycling of methanol or other antifreeze used to prevent blocking of the heat exchanger due to frost or ice formation.

A heat dissipation structure includes a housing configured to receive a heat generating device. The housing includes a first air inlet, a first air outlet, and an alloy heat dissipation device disposed in the housing and including heat dissipation fins disposed in parallel. A heat dissipation air channel is formed between two adjacent heat dissipation fins. The heat dissipation air channel includes a second air inlet and a second air outlet, the second air outlet being connected with the first air outlet. The heat dissipation structure further includes a heat dissipation fan configured to provide a heat dissipation air flow to an inside space of the housing. The heat dissipation fan is disposed inside the housing, and includes a third air inlet and a third air outlet. The third air inlet is connected with the first air inlet and the third air outlet is connected with the second air inlet.

An aircraft includes a battery, an airfoil and heat conducting elements, and the heat conducting elements connect the battery thermally to the airfoil in such a way that heat which is produced in the battery is distributed to the airfoil.

An aircraft includes a battery, an airfoil and heat conducting elements, and the heat conducting elements connect the battery thermally to the airfoil in such a way that heat which is produced in the battery is distributed to the airfoil.

Systems and methods for expanding an operating speed range of a high speed flight vehicle include providing an engine with an inlet air duct, and positioning a heat exchanger in the inlet air duct to cool at least a portion of duct air flow associated with an engine core. Additionally or alternatively, a nozzle assembly includes a cowl fluidly communicating with the engine and having a cowl internal surface defining a cowl orifice, and a plug defines a primary thrust surface. The plug is supported relative to the cowl so that a portion of the primary thrust surface is disposed within the cowl orifice to define a throat therebetween. An actuator is coupled to at least one of the cowl or the plug, and is configured to generate relative movement between the cowl and the plug, thereby to modify the throat.

Systems and methods of operating systems are provided. For example, a system comprises a fuel cooling loop including a cold fuel flowpath having a fuel flowing therethrough, a fuel cooler heat exchanger for cooling the fuel in fluid communication with the cold fuel flowpath, and a cold fuel tank disposed along the cold fuel flowpath for accumulating at least a portion of the cooled fuel. The system further comprises a fuel heating loop including a hot fuel flowpath for a flow of the fuel, a fuel heater heat exchanger for heating the fuel in fluid communication with the hot fuel flowpath, and a hot fuel tank disposed along the hot fuel flowpath for accumulating at least a portion of the heated fuel. The fuel cooling loop is coupled to the fuel heating loop such that the fuel circulates through both the fuel cooling loop and the fuel heating loop.

A method of cooling an aircraft power plant having a combustion engine is disclosed. The method comprises in a first operating mode, inducing a cooling air flow through a heat exchanger in an air conduit via a flow inducing device fluidly connected to the air conduit, the heat exchanger connected in heat exchange relationship with the power plant of the aircraft. The method comprises, in a second operating mode, bypassing the cooling air flow from the flow inducing device via a selectively closable air outlet of the air conduit downstream of the heat exchanger. A cooling system for an aircraft power plant is also disclosed.