Abstract: The system and method for actuator monitoring of an electric aircraft is illustrated. The system includes a plurality of flight components, a computing device attached to each rotor component, and a flight controller. The plurality of flight components are coupled to the electric aircraft. A computing device is communicatively coupled to each rotor component and is configured to detect an input health datum associated with each rotor component of the plurality of flight components and transmit the input health datum to a flight controller. The flight controller is communicatively connected to the computing devices and is configured to receive the health datum from the computing devices, generate an updated health datum as a function of the input health datum, and transmit the updated health datum to each rotor component of the plurality of flight components.

Abstract: A vertical landing apparatus comprises a body, at least three legs, and at least three leg locks coupled to the body. The body comprises a body lower end and at least three leg housings. Each leg housing comprises a passage extending longitudinally upwardly from a leg housing lower opening. Each leg is translatable within the passage of a respective leg housing between deployed and leg locking positions. Each leg comprises a leg lower end that is longitudinally outboard of the body lower end. Each leg comprises a longitudinally outboard extent from the body lower end to the lower leg end that is longer when in the deployed position than the leg locking position. Each leg lock is associated with a respective leg and configured to move between a locked position in which translation of the leg is prevented and a disengaged position in which translation of the leg is allowed.

Abstract: The invention is intended for the organization of an automated process for spraying of liquid means of chemical treatment from unmanned vehicles, for example, in precise farming systems. The invention provides the use of a replaceable, marked and hermetically sealed liquid subsystem with integrated pumping chambers in a spraying device together with an integrated self-diagnosis system allowing to ensure personnel safety and the accounting of the resources of main components of the spraying device. All this in combination enables to create fully automated spraying systems.

Abstract: Disclosed is an instrument panel designed to be integrated into an aircraft cockpit, the instrument panel comprising a main structure, extending longitudinally and having a concave shape defining a cavity, this cavity being configured to receive a plurality of navigation command and/or control units, and at least one inner wall, configured to delimit at least two recesses each intended to receive at least one of the plurality of navigation command and/or control units, the instrument panel being characterized in that the main structure is made from a single piece made from a composite material.

Abstract: An item to write on a surface of a celestial body that has less atmosphere than Earth is received at a communications station and from a user device. An instruction that triggers the robot to write the item on the surface of the celestial body is provided by the communications station and to a robot on the surface of the celestial body. An image of the item written on the surface of the celestial body is received by the communications station and from the robot. The image of the item written on the surface of the celestial body is provided by the communications station and to the user device.

Abstract: An infrastructure is provided for improving the safety of autonomous systems. An autonomous vehicle management system (AVMS) controls one or more autonomous functions or operations performed by a vehicle or machine such that the autonomous operations are performed in a safe manner. The AVMS is capable of dynamically controlling the behavior of sensors associated with a vehicle. For example, for a sensor, the AVMS can dynamically change and control what sensor data is captured by the sensor and/or communicated from the sensor to the AVMS (e.g., granularity/resolution, field of view, control zoom), when the data is captured by the sensor and/or communicated by the sensor to the AVMS (e.g., on-demand, according to a schedule), and how the data is captured by the sensor and/or communicated from the sensor to the AVMS (e.g., communication format, communication protocol, rate of data communication).

Abstract: The invention provides a locking device for preventing movement between two elements (11, 12) that are mounted to move relative to each other, the locking device including a lock (31) mounted to rotate relative to one of the elements in order to present successive angular positions for locking and for release in which the lock alternates between preventing and allowing relative movement between the two elements, the lock being constrained to rotate with a selector (55) of an angular indexing mechanism (50) actuated by a pulse-controlled actuator (70, 71) arranged to push the selector against a spring member (58) in order to cause it to turn on each pulse and thereby cause the lock to pass from one angular position to the other.

Abstract: A method 300 for deploying an aircraft landing gear including: receiving an aircraft landing gear deployment signal 310, receiving an aircraft position signal indicative of a distance of the aircraft from an aircraft landing site 320, receiving one or more flight signals indicating one or more dynamic conditions or parameters relating to the flight of the aircraft 330, determining, based at least on the one or more flight signals, a first aircraft position, relative to the aircraft landing site, at which the landing gear deployment should commence 340, and deploying the landing gear (a) when the aircraft reaches the first aircraft position, in the event that the deployment signal is received before the aircraft reaches the first aircraft position, or (b) immediately, in the event that the deployment signal is received when the aircraft has passed the first aircraft position 350.

Abstract: A system for flight control configured for use in an electric aircraft includes a sensor configured to capture an input datum. The system 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.

Abstract: An in-vehicle data collection and processing device receives real-time data from a plurality of sensors relating to at least one of a current vehicle condition and a current driver condition. The device then predicts, by processing at least a portion of the real-time data through a pre-trained pattern recognition algorithm, a likelihood of occurrence of at least one of a plurality of incidents involving the vehicle. In response, the device outputs one or more types of warnings and/or conducts a vehicle evasive maneuver if the likelihood is predicted to be above one or more thresholds.

Abstract: A device for determining an attitude of a satellite is disclosed, the satellite having an attitude control system comprising a gyroscopic actuator including a flywheel mounted so as to be rotatable around an axis of rotation and carried by a gimbal articulated to rotate around an axis of rotation. The device includes an attitude sensor configured to measure the attitude of the satellite, a position sensor configured to measure the angular position of the gimbal around its axis of rotation, a speed sensor configured to measure the rotational speed of the flywheel, and a processing circuit configured to determine the attitude of the satellite by using the measurement of the angular position of the gimbal, the measurement of the rotational speed of the flywheel, and the measurement of the attitude of the satellite.

Abstract: According to various aspects, an obstacle analyzer may include: one or more sensors configured to receive obstacle identification information representing one or more identification features of an obstacle and obstacle condition information associated with one or more conditions of the obstacle; and one or more processors configured to identify the obstacle based on the received obstacle identification information and generate an identification value corresponding to the identified obstacle, determine a rating value representing a risk potential of the identified obstacle based on the received obstacle condition information, and store the rating value assigned to the identification value of the identified obstacle in one or more memories.

Abstract: A multi-layer insulation includes a plurality of layers that are laminated on each other. A detection layer that is at least one of the plurality of layers has a piezoelectric film, and a pair of electrode parts installed on both surfaces of the piezoelectric film.

Abstract: An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, and a winch mounted to the chassis. The winch includes a reel and a motor. The reel has a line wound thereon, the line having a free end. The reel includes a circumferential channel in which a wound portion of the line is wound onto the reel. The circumferential channel includes an inner portion, an outer portion, and a passage connecting the inner portion and the outer portion. The motor is operable to rotate the reel under control of the control system to thereby cause the line to wind onto and off of the reel, thereby causing the free end of the line to raise and lower.

Abstract: A turnaround monitoring system and method are configured to monitor a turnaround of an aircraft at an airport. The turnaround monitoring system and method include receiving, by a turnaround analysis control unit, turnaround data regarding the aircraft at the airport, and determining, by the turnaround analysis control unit, a turnaround status of the aircraft based on the turnaround data.

Abstract: An assistance vehicle designed for supplying electrical energy to an electric taxiing device of an aircraft landing gear when the aircraft is moving over the ground. The assistance vehicle includes an autonomous energy source, a connector enabling it to be coupled to the aircraft and to electrically power the electric taxiing device. When an assistance instruction comprising the aircraft position is received, the assistance vehicle moves in an autonomous manner so as to reach the position of the aircraft, is automatically connected to the electric taxiing device when the assistance vehicle reaches the position of the aircraft and switches into freewheeling mode. When the assisted move has finished, the assistance vehicle is separated from the electric taxiing device and switches back into tractor mode. Thus, the electrical power supply system of the aircraft is simplified by externalizing the electrical supply of the electric taxiing device.

Abstract: Systems and methods are disclosed for vehicle integration of unmanned aircraft systems (UASs). Example methods may include coupling a landing dish of a vehicle integrated UAS to a ground station assembly; positioning the landing dish and the ground station assembly into a portion of a vehicle and a capping member of the vehicle integrated UAS; and coupling the landing dish to the capping member of the vehicle integrated UAS. In various embodiments, the vehicle integrated UAS may be configured to send and receive information (e.g., route information, power information, status information, etc.) between unmanned aerial vehicles (UAV) associated with the UAS to device(s) of a vehicle.

Abstract: Methods and apparatus for cooling a surface on a flight vehicle and/or generating power include advancing the flight vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A supercritical working fluid is circulated through a fluid loop that includes compressing the supercritical working fluid through a compressor, heating the supercritical working fluid through a heat intake that is thermally coupled to the surface, expanding the supercritical working fluid in a thermal engine to generate a work output, cooling the supercritical working fluid, and recirculating the supercritical working fluid to the compressor. The work output of the thermal engine is operably coupled to the compressor, and may optionally be coupled to a generator to produce power. The supercritical working fluid absorbs heat from the surface, eliminating hot spots and permitting use of lighter and/or less expensive materials.

Abstract: A protective cover for the protection of an aircraft having a fuselage and two wings, includes an anchoring system fixing the protective cover to the aircraft, a tarpaulin having a retracted position wherein it is gathered up and a deployed position wherein it is spread over the wing, a deployment device making the tarpaulin move from the retracted to the deployed position, an electromagnet fixed to the tarpaulin face against the wing, and having a deactivated state and an active state, a remote control, and a control system including a control unit in communication with the remote control. When the control unit receives activation information from the remote control, the control unit controls the deployment device, to make the tarpaulin move from the retracted position to the deployed position, and activates each electromagnet. When the control unit receives deactivation information from the remote control, the control unit deactivates each electromagnet.

Abstract: A reconnaissance rover configured for multiple agile and autonomous landings over a small body or moon. The reconnaissance rover comprises a detection unit, a processing unit, a control unit and a drive unit. The detection unit is configured to detect at least an environment in front of the reconnaissance rover, in the direction of a trajectory of the reconnaissance rover over a surface of the small body or moon. The detection unit is further configured to provide environmental data based on the detected environment. The processing unit is configured to update the trajectory based upon the provided environmental data. The control unit interacts with the drive unit to move the reconnaissance rover according to the updated trajectory.