A controller for an aerial vehicle, the aerial vehicle comprising a fuselage, fixed wings, and a multi-rotor assembly, the fixed wings disposed on both sides of the fuselage, and the multi-rotor assembly comprising at least two rotors disposed on either the fuselage or the fixed wings. The controller may comprise at least one memory storing at least one instruction set configured to control the vehicle, and at least one processor, communicatively coupled to the at least one memory. When the aerial vehicle operates, the at least one processor executes the at least one instruction set to, during cruise of the aerial vehicle, control at least a portion of the rotors of the multi-rotor assembly to actively rotate to provide a force in a vertical direction so that the multi-rotor assembly and the fixed wings together provide lift for the aerial vehicle.

A technique for detecting and avoiding obstacles by an unmanned aerial vehicle (UAV) includes: querying a knowledge graph having information related to a dynamic obstacle that may be in proximity to the UAV when traveling along a planned route; comparing the location of the dynamic obstacle to the UAV to detect conflicts; and in response to detecting a conflict, performing an action to avoid conflict with the dynamic obstacle. The knowledge graph can be updated by receiving a VHF radio signal containing the information related to the dynamic obstacle in the audible speech format; translating the audible speech format to a text format using speech recognition; analyzing the text format for relevant information related to the dynamic obstacle; comparing the relevant information related to the dynamic obstacle of the text format to the knowledge graph to detect changes; and updating the knowledge graph.

A control system for a powered lift aircraft includes a pilot input device, at least one powered lift element configured to provide powered lift support to the aircraft, and a processor. The processor is configured to receive, from the pilot input device, an input indicative of one of a powered lift enabled mode or a powered lift disabled mode and control the at least one powered lift element to operate the aircraft in a selected one of the powered lift enabled mode or the powered lift disabled mode based on the received input. When the aircraft is in the powered lift enabled mode, the at least one processor is configured to control the at least one powered lift element based on a state of the aircraft. When the aircraft is in the powered lift disabled mode, the at least one processor is configured to control the at least one powered lift element to disable powered lift.

Disclosed is a flight control system for a VTOL aircraft comprising a first and a second manual control apparatus for inputting control commands by an operator, a flight control computer, which is connected to the first and second manual control apparatuses and configured to output flight control instructions based on pivot positions of the first and second stick members with respect to the first to fourth control axes, wherein the flight control computer is adapted to derive and output flight control instructions, while at least partially eliminating cross-coupling between the individual directions of motion for longitudinal motion control based on the pivot position of the first stick member with respect to the first control axis.

A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive prioritization data including a prioritization datum corresponding to each of the plurality of attitude command, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the prioritization data, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

An electrical system for an aircraft is disclosed, comprising: at least one processor configured to: receive first sensor data from at least one inertial sensor of the aircraft, wherein the first sensor data is indicative of a state of the aircraft, receive second sensor data from at least one of an airspeed sensor indicating an airspeed of the aircraft or a propeller speed sensor indicating a propeller speed of at least one propeller of the aircraft, and determine the state of the aircraft based on the first sensor data, wherein determining the state of the aircraft comprises filtering aircraft state measurements based on the second sensor data to lessen influence of propeller vibrations on at least one aircraft signal. The at least one processor is further configured to control the aircraft based on a pilot input command and the determined state of the aircraft.

A flight control device performs a flight control process for causing an eVTOL to fly. In a step of the flight control process, the flight control device determines whether the eVTOL is capable of maintaining a stable attitude. In the step, it is determined whether the eVTOL is capable of maintaining the stable attitude even if driving of an abnormal motor is stopped. In the step, it is determined whether the eVTOL is capable of maintaining the stable attitude even if the abnormal motor continues driving. When it is determined that the eVTOL is capable of maintaining the stable attitude, the flight control device performs output adjustment of at least one of a normal motor and the abnormal motor to maintain the eVTOL at the stable attitude.

A flying apparatus, an aircraft, and a method for controlling flight of a flying apparatus are provided. The flying apparatus may include a frame, comprising a front section and a rear section; a front tiltrotor, disposed on the front section of the frame; and a rear tiltrotor, disposed on the rear section of the frame; wherein the front tiltrotor is configured to tilt at a front tilt angle to a gravity direction to control a flight of the flying apparatus, and the rear tiltrotor is configured to tilt at a rear tilt angle to the gravity direction to control the flight of the flying apparatus.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for command prioritization in an aircraft is disclosed. The method comprises receiving a pilot command, analyzing the pilot command to determine characteristics associated with the pilot command, wherein the characteristics to airspeed and climb of an aircraft, assigning weights to characteristics associated with the pilot command based on constraint data, determining priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command, calculating a correction factor to be applied to the characteristics associated with the pilot command based on determined priority and generating at least one actuator command to control the aircraft based on determined priority of execution.

Disclosed embodiments generally relate to systems and methods for flight control of aircrafts. In some embodiments, a flight control system is configured to determine desired commands for the electric aircraft, determine at least one reference command for an effector based on the desired commands and one or more aircraft conditions, monitor energy states of the plurality of battery packs, where at least a first battery pack of the plurality of battery packs is electrically isolated from at least a second battery pack of the plurality of battery packs, adjust the at least one reference command based on the monitored energy states of the plurality of battery packs, generate control commands for the plurality of effectors based on the adjusted at least one effector reference command, and control the plurality of effectors according to the generated control commands to meet the one or more desired commands of the electric aircraft.