An automatic landing system for a vertical take-off and landing aircraft includes: a camera mounted on a vertical take-off and landing aircraft; a relative-position acquisition unit configured to perform image processing on an image captured by the camera, the image including a marker group provided at a target landing point, to acquire a relative position between the vertical take-off and landing aircraft and the target landing point; and a control unit configured to control the vertical take-off and landing aircraft such that the relative position becomes zero, in which the marker group includes a plurality of markers that are arranged side by side and that have different center positions from each other, the markers are larger as arranged farther away from the target landing point, and the relative-position acquisition unit acquires the relative position based on a distance between the marker recognized in the image and the target landing point.

A system for flight control configured for use in an electric aircraft includes an inertial measurement unit (IMU) and configured to detect an aircraft angle and an aircraft angle rate. The system includes a flight controller including an outer loop controller configured to receive the input datum from the sensor, receive the aircraft angle from the IMU, and generate a rate setpoint as a function of the input datum. The system includes an inner loop controller configured to receive the aircraft angle rate, receive the rate setpoint from the outer loop controller, and generate a moment datum as a function of the rate setpoint. The system includes a mixer configured to receive the moment datum, perform a torque allocation as a function of the moment datum, and generate a motor command datum as a function of the torque allocation.

Localization systems and methods for transmitting timestampable localization signals from anchors according to one or more transmission schedules. The transmission schedules may be generated and updated to achieve desired positioning performance. For example, one or more anchors may transmit localization signals at a different rate than other anchors, the anchor transmission order can be changed, and the signals can partially overlap. In addition, different transmission parameters may be used to transmit two localization signals at the same time without interference. A self-localizing apparatus is able to receive the localization signals and determine its position. The self-localizing apparatus may have a configurable receiver that can select to receive one of multiple available localization signals. The self-localizing apparatuses may have a pair of receivers able to receive two localization signals at the same time. A bridge anchor may be provided to enable a self-localizing apparatus to seamlessly transition between two localization systems.

A distributed control system with supplemental attitude adjustment including an aircraft control having an engaged state and a disengaged state. The system also including a plurality of flight components and a plurality of aircraft components communicatively connected to the plurality of flight components, wherein each aircraft component is configured to receive an aircraft command and generate a response command directing the flight components as a function of supplemental attitude. The supplemental attitude based at least in part on the engagement datum and generating a supplemental attitude includes choosing a position supplemental attitude if the aircraft control is disengaged and choosing a velocity supplemental attitude if the aircraft control is engaged. In generating the response command, the aircraft attitude is combined with the supplemental attitude to obtain an aggregate attitude, and the aircraft component is configured to generate the response command based on the aggregate attitude.

A system for controlling a flight boundary of an aircraft. The system includes a flight controller communicatively connected to the aircraft. The flight controller is configured to receive a plurality of flight data linked with the aircraft, determine a flight boundary for the aircraft as a function of the plurality of flight data, set an aircraft movement limit as a function of the flight boundary, receive a thrust envelope, and generate a control signal for the aircraft as a function of the aircraft movement limit and the thrust envelope. The control signal is limits the aircraft to remain within the flight boundary. A method for controlling a flight boundary of an aircraft is also provided.

A monitoring device monitors a state of a battery pack mounted on an eVTOL. The monitoring device includes: an acquisition unit configured to acquire information regarding the battery pack; an estimation unit configured to estimate a phase state of a latent heat storage material based on the acquired information; and an output unit configured to output information regarding the phase state. By using the monitoring device, a performance of the latent heat storage material required for cooling a battery can be obtained. Thus, flight safety can be effectively improved.

A rotor control device a vertical rotor control unit, a horizontal rotor control unit, and an allocation command value calculation unit. The vertical rotor control unit controls each VTOL rotor based on a first allocation command value. The horizontal rotor control unit controls each cruise rotor based on a second allocation command value. The allocation command value calculation unit sets, as the first allocation command value, a difference between a command value of a yaw moment and the second allocation command value, sets the magnitude of the second allocation command value to 0 when the command value of the yaw moment is less than a threshold, and sets the magnitude of the second allocation command value to a value greater than 0 when the command value of the yaw moment is equal to or greater than the threshold.

The disclosure relates to a battery driven flight vehicle. The battery-driven flight vehicle, comprising: a control unit; and a battery charged by a power supply device, wherein the control unit executes flight control in accordance with a charging speed of the battery. The disclosure also relates to a method of providing a Mobility as a Service (MaaS) in which the flight vehicle is used.

The position of a UAV within a three-dimensional space is changed based on a change in position of a controller of the UAV. First and second sensor data are produced using sensors of the controller to maintain stable altitude output for the UAV. The first sensor data indicates a geolocation of the controller, and the second sensor data indicates a barometric pressure of an environment in which the controller is located. The first and second sensor data are post-processed using a complementary filter based on respective altitude measurements of the first and second sensor data to determine an altitude of the controller. A position of the controller is determined within a three-dimensional space based on the altitude. Data indicative of the position of the controller within the three-dimensional space is then transmitted to the UAV to cause a change in a position of the UAV within the three-dimensional space.

Embodiments provide a method for land hazard communication. The method includes transmitting a first message to a landing site computing system based at least in part on determining that a pilotless aircraft is within a threshold range of a landing site, the first message comprising a first passcode. The method can further include determining whether a second message comprising a second passcode is received from the landing site computing system in response to the first message, the second passcode corresponding to the first passcode. The method can further include determining a subset of maneuvers for landing condition from a set of maneuvers based at least in part on determining whether the second message comprising a second passcode is received from the landing site computing system. The method can further include causing the pilotless aircraft to perform the subset of maneuvers for the landing condition.