Abstract: The disclosure provides an information processing apparatus, an information processing system, and an information processing method capable of allowing a user to approach a destination intuitively. An information processing apparatus according to the present technology includes a position-coordinate acquisition part, a direction acquisition part, a direction calculation part, and a haptic-feedback determining part. The position-coordinate acquisition part acquires a position coordinate of the information processing apparatus. The direction acquisition part acquires an apparatus direction that the information processing apparatus faces. The direction calculation part calculates a target direction being a direction of a target with respect to the information processing apparatus from a position coordinate of the target and the position coordinate of the information processing apparatus.

Abstract: A baggage processing system includes a storage array having a plurality of cells, each cell being configured to contain a single baggage item which is associated with a flight. The baggage processing system further includes a loading conveyor that receives baggage items retrieved from the storage array. A control system prepares a sequenced list of baggage items and controls the retrieval of baggage items from the storage array based on the sequenced list, whereby the retrieved baggage items are placed on the loading conveyor in an order conforming to the sequenced list. The baggage processing system also includes a queue of carts, where each cart is positionable to receive baggage items in sequence from a loading point on the loading conveyor, for transporting the baggage items to an aircraft. The sequenced list of baggage items defines a sequence of loading baggage items from the carts to the aircraft.

Abstract: A system for producing a control signal of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to obtain a requested aircraft force, generate an optimal command mix, wherein the optimal command mix includes a plurality of commands to a plurality of actuators as a function of the requested aircraft force, wherein generating further comprises receiving an ideal actuator model includes at least a performance parameter, producing a model datum as a function of the ideal actuator model, and generating the optimal command mix as a function of the request aircraft force and the model datum, and produce a control signal as a function of the optimal command mix.

Abstract: A system for anchoring unmanned aerial vehicles to surfaces includes a landing pad configured to be installed on an agricultural machine, with the landing pad defining a landing surface. Furthermore, the system includes an unmanned aerial vehicle (UAV) configured to land on the landing surface and a top surface of a field across which the agricultural machine is traveling. The UAV, in turn, includes an anchoring device configured to engage soil within the field to anchor the UAV to the field when the UAV has landed on the top surface of the field. Additionally, the anchoring device is further configured to engage the landing pad to anchor the UAV to the landing surface when the UAV has landed on the landing pad.

Abstract: An aircraft engine nacelle comprising an icing protection system and an icing protection method for such an aircraft engine nacelle. The aircraft engine nacelle comprises an air inlet comprising a lip, a tubular air inlet piece and an icing protection system. The icing protection system comprises an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip, a de-icing means powered by a second electrical energy source covering the tubular air inlet piece and a controller configured to acquire a current total air temperature value, and control the second electrical energy source as a function of the current total air temperature value.

Abstract: Braking systems and methods for an electrical vertical takeoff and landing aircraft are provided. A braking system may contain a pilot control device, brakes, wheels, sensors, and a controller. Pilot controls the pilot control device to transmit information to the controller such that the aircraft will slow down.

Abstract: An unmanned flight equipment according to an embodiment of the present invention includes: an aerial vehicle capable of flying in an unmanned manner; an abnormality recognition part-configured to recognize an abnormal situation in which a determination is made that it is difficult for the aerial vehicle to continue flight; and an alarm device held on the aerial vehicle and configured to be detached from the aerial vehicle and to warn neighborhood of abnormality when the abnormality recognition part recognizes the abnormal situation.

Abstract: The technology relates to developing a highly accurate understanding of a vehicle's sensor fields of view in relation to the vehicle itself. A training phase is employed to gather sensor data in various situations and scenarios, and a modeling phase takes such information and identifies self-returns and other signals that should either be excluded from analysis during real-time driving or accounted for to avoid false positives. The result is a sensor field of view model for a particular vehicle, which can be extended to other similar makes and models of that vehicle. This approach enables a vehicle to determine when sensor data is of the vehicle or something else. As a result, the detailed modeling allowing the on-board computing system to make driving decisions and take other actions based on accurate sensor information.

Abstract: In an aspect of the present disclosure is a computing device for predicting battery temperature in an electric aircraft, the computing device including a controller communicatively connected to the electric aircraft, the controller comprising: a battery model, the battery model configured to: receive a flight plan; instantiate a machine-learning model, wherein the machine-learning model is trained as a function of a training set correlating flight plan data to battery temperature labels.

Abstract: Embodiments in accordance with the invention address potential co-orbital threats to a spacecraft through the use of a plurality of evasion pattern maneuvers selected to prevent a rendezvous with a potential co-orbital threat from occurring within a finite horizon. Embodiments in accordance with the invention maintain separation from the potential co-orbital threat while minimizing a defending spacecraft's fuel consumption.

Abstract: A system and method for flight control compensation for component degradation is illustrated. The system comprises a first flight component mechanically coupled to the electric aircraft and a second flight component mechanically coupled to the electric aircraft. A sensor is also coupled to both the first flight component and the second flight component, wherein the sensor is configured to detect a performance degradation datum in one of the first flight component and the second flight component and transmit the performance degradation datum to a flight controller. The system also comprises a flight controller communicatively coupled to the sensor, wherein the flight controller is configured to receive the performance degradation datum from the sensor and adjust operation of either the first flight component or the second flight component as a function of the performance degradation datum.

Abstract: An exploration method includes: a step of exploring a natural resource on a satellite, a minor planet, or a planet; a step of acquiring the natural resource detected by the exploration; and a step of storing the acquired natural resource.

Abstract: A trajectory setting device that sets a trajectory of a host vehicle includes a first path generation unit configured to generate a first path by assuming all obstacles around the host vehicle to be stationary obstacles, a second path generation unit configured to generate a second path when the moving obstacle is assumed to move independently, a third path generation unit configured to generate a third path when the moving obstacle is assumed to move while interacting with at least one of the other obstacles or the host vehicle, a reliability calculation unit configured to calculate reliability of the second path and reliability of the third path, and a trajectory setting unit configured to set the trajectory for traveling from the first path, the second path, and the third path based on the reliability of the second path and the reliability of the third path.

Abstract: Processes and systems for determining that a piece of luggage has been left behind in an overhead bin of a vehicle. When a passenger places a piece of luggage into the overhead bin, it is associated with that passenger by detecting that the passenger has sat down in a particular seat after the luggage has been placed into the overhead bin. When it has been determined that the passenger has deboarded the vehicle, and the luggage has not been removed, reminder signals are sent.

Abstract: A system for stowable propulsion in an electric aircraft that includes at least a propulsor mounted on at least a structural feature that includes at least a rotor and at least a motor mechanically coupled to the at least a rotor, where the motor is configured to cause the rotor to rotate as a function of an activation datum, at least a sensor communicatively coupled to the at least a propulsor configured to detect a position datum as a function of the configuration, generate a clearance datum as a function of the position datum, transmit the clearance datum to a flight controller, and a flight controller communicatively coupled to the at least a propulsor and the at least a sensor configured to receive the clearance datum from the at least a sensor and generate the activation datum as a function of the clearance datum.

Abstract: A system detects a maneuver of at least one space object by receiving a first data set relating to orbital characteristics of at least one space debris object. The system trains a model, using the first data set, in order to model orbital behaviors of the at least one space debris object. The system then receives a second data set relating to orbital characteristics of the at least one space object, and detects a maneuver of the at least one space object using the trained model and the second data set.

Abstract: Disclosed is an aircraft and a method of controlling an aircraft. The aircraft comprises a continuous wing assembly extending from port to starboard sides of the aircraft. The aircraft is controlled partially by flexing portions of the wing, and partially or totally by mechanical systems that alter the position of a fuselage with respect to the wing. The fuselage is attached to the wing by a wing/fuselage joint structure that permits at least two mutually orthogonal axes of rotation of the fuselage relative to the wing. The aircraft includes a sensors, a telemetry system linked to a remote server, and a control system for programming flight information and aircraft control instructions and a plurality of actuators responsive to the control system for rotating the fuselage relative to the wing and flexing the wing for controlling the flight of the aircraft in response to instructions from the control system.

Abstract: In an embodiment, a system includes a frame configured to support a load, a first set of wheels provided on the frame, a second set of wheels provided on the frame, and a controller. The first set of wheels is configured to descend or ascend in response to the controller, and is oriented to move in a first direction. The second set of wheels is configured to descent or ascend in response to the controller, and is oriented to move in a different direction from the first direction. The controller configured to control the descent and ascent of the second set of wheels and the first set of wheels.

Abstract: Disclosed is an apparatus and method for operating a gliding parachute/kite. The gliding parachute/kite has a wing with a flexible material, and a set of suspension lines adapted for coupling a load to the wing, such that the coupling is configurable in any one of a plurality of possible states based on relative lengths of the suspension lines. In some implementations, the possible states include a first state enabling gliding in a first direction, and a second state enabling gliding in a second direction that is opposite to the first direction. Reversing direction is possible with the first and second states. Additionally, or alternatively, the possible states include a spinning state enabling spinning of the gliding parachute/kite. Adjusting a rate of decent is possible with the spinning. Reversing direction and/or spinning operations can be used to improve control of trajectory.

Abstract: A system for the prioritization of flight controls in an electric aircraft is illustrated. The system includes a plurality of flight components, a sensor, and a computing device. The plurality of flight components are coupled to the electric aircraft. The sensor is coupled to each flight component of the plurality of flight components. Each sensor of the plurality of sensors is configured to detect a failure event of a flight component of the plurality of flight components and generate a failure datum associated to the flight component of the plurality of flight components. The computing device is communicatively connected to the sensor and is configured to receive the failure datum associated to the flight component of the plurality of flight component from the sensor, determine a prioritization element as a function of the failure datum, and restrict at least a flight element as a function of the prioritization element.