A cargo hold of an aircraft having cladding elements and at least one housing element for accommodating electronic components and/or cables. The cladding elements are attached to supports, in particular structural elements, of the aircraft and have a plurality of cladding holes with predefined cladding hole spacings for attachment. The at least one housing element has at least one pair of housing holes for receiving fastening devices. The housing holes have a housing hole spacing which corresponds to at least one pair of cladding hole spacings.

Systems and methods associated with electrical systems of aircraft are disclosed. A method disclosed herein comprises generating electricity using an electric generator operatively coupled to an engine of the aircraft, supplying the electricity generated using the electric generator to a baseline power bus; generating electricity using an electric starter generator operatively coupled to the engine; and supplying the electricity generated using the electric starter generator to a supplemental power bus independent from the baseline power bus.

Renewable fuel power systems for vehicles, such as aircraft, are provided. For example, a system includes a storage tank, a reactor module, a heat exchanger unit, and a combustion engine. The storage tank is configured to store ammonia in liquid form. The reactor module is in fluid communication with the storage tank. The reactor module is configured to extract hydrogen from the ammonia, and output fuel which includes the extracted hydrogen. The heat exchanger unit is configured to heat the ammonia which flows from the storage tank to an input of the reactor module, using heat which is extracted from the fuel that is output from the reactor module. The combustion engine is configured to combust the fuel provided by the reactor module, to thereby produce mechanical power.

An unmanned aerial vehicle (“UAV”) system for energy transport includes a UAV having an energy tank configured to transport energy, a processor, and a memory. The memory includes instructions which, when executed by the processor, may cause the system to receive a first location for collecting or releasing the energy, determine an energy level of the energy tank, and transport the energy by the UAV to or from the first location based on the determined energy level.

An unmanned aerial vehicle (“UAV”) system for energy transport includes a UAV having an energy tank configured to transport energy, a processor, and a memory. The memory includes instructions which, when executed by the processor, may cause the system to receive a first location for collecting or releasing the energy, determine an energy level of the energy tank, and transport the energy by the UAV to or from the first location based on the determined energy level.

A quick attach bracket includes a first portion and a second portion aligned substantially perpendicular with the first portion, a retaining ridge disposed across the first portion and extending in the direction of the second portion, and a hub disposed on the second portion and extending in the direction of the first portion. The retaining ridge is configured to receive a flange of a structure. The hub includes a sidewall that extends from the second portion in the direction of the first portion, a façade aligned with the second portion, and a rounded portion connecting the sidewall and the façade to assist with installation of the hub into a recess or through-hole of the structure. The quick attach bracket is installable by hand via hooking of the retaining ridge on the flange and insertion of the hub into the recess or through-hole.

A quick attach bracket includes a first portion and a second portion aligned substantially perpendicular with the first portion, a retaining ridge disposed across the first portion and extending in the direction of the second portion, and a hub disposed on the second portion and extending in the direction of the first portion. The retaining ridge is configured to receive a flange of a structure. The hub includes a sidewall that extends from the second portion in the direction of the first portion, a façade aligned with the second portion, and a rounded portion connecting the sidewall and the façade to assist with installation of the hub into a recess or through-hole of the structure. The quick attach bracket is installable by hand via hooking of the retaining ridge on the flange and insertion of the hub into the recess or through-hole.

An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

A boundary layer ingestion-open rotor system for use with an aircraft having a fuselage, wings, and an empennage includes an open rotor assembly, one or more energy storage systems, and an electronic control unit (ECU). The open rotor assembly includes fan blades connected to and extending radially from a rotor hub, and a linkage assembly connecting the hub to the fuselage aft of the empennage within a predefined boundary layer of airflow around the fuselage. The energy storage systems are connectable to the rotor hub. In response to an electronic control signal, the system(s) selectively energize the open rotor assembly to cause rotation of the hub to occur within the boundary layer. The ECU selectively generates the electronic control signals to energize the open rotor assembly during one or more predetermined flight operating phases of the aircraft, e.g., cruise, takeoff, landing, and descent.