In some examples, an unmanned aerial vehicle (UAV) may determine, based on a three-dimensional (3D) model including a plurality of points corresponding to a scan target, a scan plan for scanning at least a portion of the scan target. For instance, the scan plan may include a plurality of poses for the UAV to assume to capture images of the scan target. The UAV may capture with one or more image sensors, one or more images of the scan target from one or more poses of the plurality of poses. Further, the UAV may determine an update to the 3D model based at least in part on the one or more images. Additionally, the UAV may update the scan plan based at least in part on the update to the 3D model.

In some examples, an unmanned aerial vehicle (UAV) may determine, based on a three-dimensional (3D) model including a plurality of points corresponding to a scan target, a scan plan for scanning at least a portion of the scan target. For instance, the scan plan may include a plurality of poses for the UAV to assume to capture images of the scan target. The UAV may capture with one or more image sensors, one or more images of the scan target from one or more poses of the plurality of poses. Further, the UAV may determine an update to the 3D model based at least in part on the one or more images. Additionally, the UAV may update the scan plan based at least in part on the update to the 3D model.

A method of electrically powering a non-voltage-regulated electricity network, and also to an electrical architecture. The electrical architecture comprises: a plurality of sources of electrical energy including both at least one rechargeable electrical energy storage device and also an electrical power generation device a main electricity network electrically connected directly to the sources of electrical energy; and pieces of electrical equipment electrically powered by the main electricity network. The method comprises both a first powering step for electrically powering the main electricity network by the rechargeable electrical energy storage device and also a second powering step for electrically powering the main electricity network by the electrical power generation device, followed by a regulating step for regulating an internal voltage of the electrical power generation device as a function of the first power delivered by the rechargeable electrical energy storage device.

A method of electrically powering a non-voltage-regulated electricity network, and also to an electrical architecture. The electrical architecture comprises: a plurality of sources of electrical energy including both at least one rechargeable electrical energy storage device and also an electrical power generation device a main electricity network electrically connected directly to the sources of electrical energy; and pieces of electrical equipment electrically powered by the main electricity network. The method comprises both a first powering step for electrically powering the main electricity network by the rechargeable electrical energy storage device and also a second powering step for electrically powering the main electricity network by the electrical power generation device, followed by a regulating step for regulating an internal voltage of the electrical power generation device as a function of the first power delivered by the rechargeable electrical energy storage device.

An engine system for an aircraft includes a gas turbine engine and a control system. The control system is configured to motor the gas turbine engine, absent fuel burn, during a taxi mode of the aircraft. The control system is further configured to accelerate a motoring speed of the gas turbine engine, absent fuel burn, above an idle speed of the gas turbine engine to provide propulsion during the taxi mode. The control system is configured to decrease the motoring speed of the gas turbine engine, absent fuel burn, based on a change in a starting mode of the gas turbine engine or the aircraft reaching a targeted new position.

An engine system for an aircraft includes a gas turbine engine and a control system. The control system is configured to motor the gas turbine engine, absent fuel burn, during a taxi mode of the aircraft. The control system is further configured to accelerate a motoring speed of the gas turbine engine, absent fuel burn, above an idle speed of the gas turbine engine to provide propulsion during the taxi mode. The control system is configured to decrease the motoring speed of the gas turbine engine, absent fuel burn, based on a change in a starting mode of the gas turbine engine or the aircraft reaching a targeted new position.

A communication adapter of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine, a memory system, and processing circuitry. The processing circuitry is configured to receive an engine control dynamic data recording request from the offboard system, confirm an authentication between the communication adapter and the engine control, transfer the engine control dynamic data recording request received at the communication adapter from the offboard system to the engine control based on the authentication, and transmit an update completion confirmation of the engine control from the communication adapter to the offboard system based on a confirmation message from the engine control.

A communication adapter of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine, a memory system, and processing circuitry. The processing circuitry is configured to receive an engine control dynamic data recording request from the offboard system, confirm an authentication between the communication adapter and the engine control, transfer the engine control dynamic data recording request received at the communication adapter from the offboard system to the engine control based on the authentication, and transmit an update completion confirmation of the engine control from the communication adapter to the offboard system based on a confirmation message from the engine control.

Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to shutdown at least one engine of the multiple engines during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine.

Systems and methods of aircraft thrust management are provided. For example, a propulsion system for an aircraft comprises a fuel cell assembly comprising a fuel cell, a turbomachine, and a controller comprising memory and one or more processors. The memory stores instructions that, when executed by the one or more processors, cause the propulsion system to perform operations including receiving data indicative of a propulsion system thrust discrepancy and modifying an output of the fuel cell in response to receiving data indicative of the propulsion system thrust discrepancy. Modifying the fuel cell output may include modifying output products, an electrical power output, or both of the fuel cell to balance the thrust provided by the propulsion system.