Systems and methods for facilitating climate control for aerial vehicles are provided. A system includes a climate control infrastructure with devices configured to facilitate climate control operations for aircraft at an aerial facility. The system obtains data associated with a multi-modal transportation service, and aerial vehicles and facilities for providing the service. The vehicle data can include thermal parameters associated with an aerial vehicle that indicate a temperature for aerial components such as a power source, a cabin, or hardware components within the cabin. The system can determine a climate control configuration for a climate control infrastructure of an aerial facility at which the aerial vehicle is located based on the obtained data. The climate control configuration can identify a desired temperature for a component of the aerial vehicle. The system can generate and communicate command signals for controlling the climate control infrastructure to implement the climate control configuration.

According to some embodiments, system and methods are provided, comprising receiving one or more mission objectives for an aircraft mission, and condition data at a mission execution module; generating, via the mission execution module, a mission plan executable to address at least one of the one or more mission objectives via manipulation of a power-thermal management system (PTMS); receiving the generated mission plan at the PTMS directly from the mission execution module; and automatically executing the generated mission plan to operate an aircraft. Numerous other aspects are provided.

A cooling system for a vehicle includes an inlet configured to receive a medium and a compression device including a shaft, a compressor connected to the shaft and having a compressor outlet, an electric motor connected to the shaft and configured to drive the compressor, and a turbine connected to the shaft and also configured to drive the compressor upon receipt of a compressed medium (to create an expanded medium). The turbine includes a turbine inlet and a turbine outlet. A load heat exchanger is connected to the turbine outlet and receives expanded medium therefrom. The load heat exchanger has a load heat exchanger outlet. At least one cooling heat exchanger has a heated flow inlet connected to the compressor outlet, a heated flow outlet connected to the turbine inlet, and a cooling flow inlet that receives a cooling medium from the load heat exchanger outlet.

A battery thermal management system for an air vehicle includes a first heat exchange circuit, a battery in thermal communication with the first heat exchange circuit, and a heat exchanger positioned on the first heat exchange circuit. The heat exchanger is operatively connected to a second heat exchange circuit. The system includes a controller operatively connected to the second heat exchange circuit. The controller is configured to variably select whether heat will be rejected to the second heat exchange circuit. A method for controlling a thermal management system for an air vehicle includes determining an expected fluid temperature of fluid in a fluid heat exchange circuit. The method includes commanding a flow restrictor at least partially closed or commanding the flow restrictor at least partially open.

A vertical takeoff and landing unmanned aerial vehicle and a cooling system for the unmanned aerial vehicle. Heat dissipation in an arm of an unmanned aerial vehicle is achieved by providing a forward-facing opening at the front end of each of a left linear support and a right linear support of the unmanned aerial vehicle, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.

The system can include an on-board thermal management subsystem. The system 100 can optionally include an off-board (extravehicular) infrastructure subsystem. The on-board thermal management subsystem can include: a battery pack, one or more fluid loops, and an air manifold. The system 100 can additionally or alternatively include any other suitable components.

An additively manufactured component includes an outer shell, the outer shell enclosing a space therein. An inner lattice structure is in the space of the outer shell. Interspaces are formed in the inner lattice structure. A method of forming an additively manufactured component includes evacuating a chamber in which the additively manufactured component will be formed, and forming in the chamber layer by layer an outer shell enclosing a core. The core includes a lattice structure with interspaces formed in the lattice structure.

A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.

An aircraft comprising a fuselage (1) subdivided by a floor (2) into a top volume (3) and a bottom value (4) in which girders (5) extend supporting the floor and co-operating with the fuselage and the floor to define two lateral housings (6) that are of substantially triangular cross-section and that extend parallel to a longitudinal axis of the fuselage. Calculation units (100) are arranged in the lateral housings and each comprises a box (101) defining a main compartment containing calculation modules (122) insertable into the main compartment along an insertion axis through an opening in the compartment and connectable to the connectors (115) carried by a back wall (116) of the compartment so as to extend into the main compartment opposite from the opening, the insertion axis being substantially parallel to the longitudinal axis of the fuselage.

A ground-based cryogenic cooling system includes a means for cooling an airflow and producing chilled air responsive to a power supply. A liquid air condensate pump system is operable to condense the chilled air into liquid air and urge the liquid air through a feeder line. A cryogenic cartridge includes a coupling interface configured to detachably establish fluid communication with the feeder line and a cryogenic liquid reservoir configured to store the liquid air under pressure. The cryogenic cartridge can be coupled to a cryogenic liquid distribution system on an aircraft. The liquid air can be selectively released from the cryogenic cartridge through the cryogenic liquid distribution system for an aircraft use.