A method and device for generating an optimum aircraft vertical trajectory, including a unit performing iterative processing to determine, on each iteration, a next state from a computational state, by using an estimated overall cost for next states, each estimated overall cost, which is computed by a cost computation unit, being equal to the sum of a real cost computed up to the next state under consideration by using predetermined constraints and a cost estimated up to the current state of the aircraft. The estimated cost is computed using a deterministic neural network based on performance calculations for the aircraft without using energy constraints, allowing computation of this estimated cost and the estimated overall cost to be performed rapidly. The iterative processing is repeated until the determined state is situated in proximity to the current state of the aircraft, the corresponding trajectory part forming the optimum vertical trajectory.

A method of automatically determining a flight trajectory of a vertical take-off and landing aircraft having vectorable propulsion can be used to improve flight efficiency. The method includes receiving one or more aircraft flight constraints, inputting the aircraft flight constraints to a trajectory planning algorithm to determine a minimum energy aircraft transition trajectory, and outputting a control schedule to fly the aircraft to along the flight trajectory.

An aircraft mission calculation system is configured to calculate an environmental benefit index. The system includes an aircraft trajectory calculation engine, able to calculate at least one potential mission trajectory between a geographic point of origin and a geographic point of destination. The aircraft trajectory calculation engine comprises an environmental benefit index calculation module, able to activate the calculation engine. The environmental benefit index calculation module is able to determine an environmental benefit index (GI) of the potential trajectory from the first amount of carbon dioxide (Q1(TR1)) produced on a first reference trajectory defining a fastest mission, the second amount of carbon dioxide produced on a second reference trajectory (Q2(TR2)), defining a mission minimizing the amount of carbon dioxide produced, and the potential amount of carbon dioxide produced on the potential trajectory.

Embodiments of the present invention are a flight control method and device, and an unmanned aerial vehicle. The method comprises firstly acquiring the current flight velocity of the unmanned aerial vehicle, then obtaining the current optimum inclination angle corresponding to the unmanned aerial vehicle according to the current flight velocity, and further adjusting the flight state of the unmanned aerial vehicle according to the current optimum inclination angle. The method can relieve the restrictions on the flight freedom of unmanned aerial vehicles and make the user experience rapid flight pleasure.

A control apparatus includes a memory storing information on power consumption for flight of an aircraft flying by an electric rotor and a controller configured to instruct the aircraft to fly on a flight path passing through a power supply facility based on a remaining charge of the aircraft and the power consumption according to flight conditions when the aircraft flies to a destination.

Method and device for determining trajectory to optimal position of a follower aircraft with respect to vortices generated by a leader aircraft. The method includes controlling trajectory of a follower aircraft to an optimal position where the follower aircraft benefits from effects of at least one of the vortices of a leader aircraft. A first section control step controls flight of the follower aircraft using current measurements of flight parameters, from a safety position to a search position, along an approach section passing through an approach zone. A second section control step controls flight of the follower aircraft using current measurements of flight parameters, from the search position to a precision position, along a search section passing through a search zone, and a third section control step controls flight of the follower aircraft, from the precision position to the optimal position, along an optimization section passing through an optimization zone.

Systems, devices, and methods including at least one flight control computer (FCC) associated with at least one UAV, where the at least one FCC is configured to: determine a direction of travel of the at least one UAV relative to the Sun; adjust a UAV airspeed to a first airspeed if the determined direction of travel is towards the Sun; and adjust the UAV airspeed to a second airspeed if the determined direction of travel is away the Sun; where the first airspeed is greater than the second airspeed to maximize solar capture of a solar array covering at least a portion of the UAV.

A delivery system including: a plurality of autonomously-moving-type delivery vehicles each including a battery and configured to deliver an article to a delivery destination by electric power the battery is charged with; and a transportation vehicle configured to carry and transport the plurality of the delivery vehicles. For each of the plurality of the delivery vehicles, based on a route for delivering the article and a remaining amount of charge of the battery, a surplus or shortfall in the remaining amount of charge of the battery required for traveling along the route is calculated, and based on the result of the calculation of the surplus or shortfall in the remaining amount of charge, surplus electric power is supplied from the battery of a delivery vehicle having a surplus remaining amount of charge to the battery of a delivery vehicle having a shortfall in the remaining amount of charge.

Systems and methods for providing trajectory amendments are provided. In one embodiment, a method can include receiving, by one or more first computing devices, a plurality of parameters associated with an aircraft. The method can further include determining, by the one or more first computing devices, a trajectory amendment associated with the aircraft based at least in part on the plurality of parameters. The method can include determining, by the one or more first computing devices, a projected operations value associated with the trajectory amendment. The method can further include providing, by the one or more first computing devices to one or more second computing devices of an operator associated with the aircraft, a set of data identifying the trajectory amendment and the projected operations value associated with the trajectory amendment.

A system for redistributing electrical load in an electric aircraft. The system includes a ring bus and a controller communicatively connected to the ring bus. The ring bus includes a plurality of bus sections including a first bus section and a second bus section. The controller is configured to receive a fault datum indicative of a fault associated with one of a first energy source and a second energy source, actuate, as a function of the fault datum, at least a switch to electrically connect the first bus section and the second bus section so as to form an electrical merger of the first bus section and the second bus section, and redistribute the electrical load to compensate for the fault associated with one of the first energy source and the second energy source. A method of redistributing electrical load in an electric aircraft is also provided.