Abstract: A system for scaling lag based on flight phase of an electric aircraft is presented. The system include a sensor connected to an electric aircraft configured to detect measured aircraft data, identify a flight phase of the electric aircraft, and generate a flight datum. The system further comprises a computing device communicatively connected to the sensor, wherein the computing device is configured to receive the flight datum and the flight phase, identify an input latency as a function of the flight datum, select a lag frame as a function of the input latency, wherein the lag frame further comprises a lag threshold, and transmit the flight datum to a user device as a function of the lag frame. The system further includes a remotely located user device configured to receive the flight datum.

Abstract: A system for airspeed estimation utilizing propulsor data in electric vertical takeoff and landing (eVTOL) aircraft is provided. The system generally comprises at least a propulsor, at least one sensor and a flight controller. The at least a propulsor is mechanically coupled to a body of an eVTOL aircraft, wherein the at least a propulsor is configured to propel the eVTOL aircraft. The at least one sensor is configured to detect a torque of the at least a propulsor, and transmit the torque of the at least a propulsor. The flight controller is configured to receive the torque of the at least a propulsor and determine an airspeed of the eVTOL aircraft as a function of the torque of the at least a propulsor. A method for airspeed estimation utilizing propulsor data in electric vertical takeoff and landing (eVTOL) aircraft is also provided.

Abstract: A braking control system and method to synchronize the operation of the braking system of a towed vehicle with the braking system of a towing vehicle to match the deceleration and acceleration of the towed vehicle with the deceleration and acceleration of the towing vehicle wherein the braking control system includes a braking device comprising an electrically driven linear actuator coupled between an electric motor and the brake pedal of the towed vehicle and a control device coupled to the electric motor and including logic to control operation of the electrically driven linear actuator to selectively extend and retract the electrically driven linear actuator to selectively depress and release the brake pedal of the towed vehicle as the towing vehicle decelerates and accelerates.

Abstract: An electric aircraft with flight trajectory planning. The electric aircraft includes a sensor. The sensor is coupled to the electric aircraft. The sensor is configured to detect a plurality of weather measurements. The electric aircraft includes a processor. The processor is communicatively connected to the sensor. The processor is configured to receive, from the sensor, a weather measurement of the plurality of weather measurements. The processor is configured to receive, from a user, a destination datum and a desired altitude datum. The processor is configured to determine an optimal trajectory of the electric aircraft as a function of the destination datum, weather datum, and altitude datum.

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: In an aspect, a system for vibration monitoring of an electric aircraft. A system include a propulsor. A system includes a sensor coupled to a propulsor. A sensor is configured to measure a vibration datum of a propulsor and transmit the vibration datum to a flight controller. A flight controller is configured to receive a vibration datum from a sensor. A flight controller is configured to generate a throttle datum as a function of a vibration datum. A flight controller is configured to transmit a throttle datum to a propulsor.

Abstract: A rover can include a spherical shall and an avionics hub. The spherical shell defines a spherical volume and having an inner surface and an outer surface. The avionics hub is disposed within the spherical volume. The avionics hub includes an avionics shell, a data acquisition unit, and a plurality of motortrain assemblies. The avionics shell is disposed with the spherical volume of the spherical shell. The data acquisition unit is disposed within the avionics shell. Each motortrain assembly includes a motorized wheel extending at least partially through the avionics shell and in contact with the inner surface of the spherical shell, the plurality of motortrain assemblies configured to rotate the spherical shell relative to the avionics shell to move the rover.

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 computing system for landing and storing vertical take-off and landing (VTOL) aircraft can be configured to receive aircraft data, passenger data, or environment data associated with a VTOL aircraft and determine a landing pad location within a landing facility based on the aircraft data, passenger data, and/or environment data. The landing facility can include a lower level and an upper level. The lower level can include a lower landing area and a lower storage area. The upper level can include an upper landing area. At least a portion of the upper level can be arranged over the lower storage area. The landing pad location can include a location within the lower landing area or the upper landing area of the landing facility. The computing system can communicate the landing pad location to an operator or a navigation system of the VTOL aircraft.

Abstract: To facilitate assembly of an aircraft cockpit, a cockpit module includes an instrument panel to support at least one screen and an air conditioning distribution block bordering the instrument panel and integral with a rear face of it. The air conditioning distribution block includes an air distributor, an excess air collector, and air distribution channels each including a first end communicating with the air distributor and a second end communicating with the excess air collector, each distribution channel being equipped with an air outlet arranged between its first and second ends.

Abstract: A method for autonomously controlling electric power supplied to a thruster of a spacecraft during electric orbit raising includes determining a state of charge of a battery onboard the spacecraft at an entry into an eclipse during each orbit of a plurality of orbits during the electric orbit raising of the spacecraft. The method also includes determining an electric power level used to fire each thruster of a plurality of thrusters during each orbit beginning after the eclipse, based at least on the state of charge of the battery, and that will provide a shortest electric orbit raising duration and minimize thruster propellant usage during electric orbit raising.

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: There is provided a pivot turn load alleviation (PTLA) brake system for alleviating structural loads on a pivoting main landing gear of an aircraft in a pivot turn maneuver. The PTLA brake system includes a brake control system operatively coupled to at least two main landing gear, each having two or more wheels. The PTLA brake system further includes a PTLA brake inhibit subsystem coupled to the brake control system. The subsystem inhibits braking of one or more of the two or more wheels of the pivoting main landing gear, in the pivot turn maneuver, so that at least one wheel of the two or more wheels is in an unbraked state, and a remaining number of the two or more wheels are in a braked state. The PTLA brake system alleviates structural loads, and reduces wear on the at least one wheel that is in the unbraked state.

Abstract: An apparatus includes a communication device affixed to or placed within a transport container. The apparatus further includes processing circuitry configured to initiate display, via the communication device, of first routing information indicating a first destination along a geographic route from a first location to a second location and to, in response to a condition indicating movement of the container from the first location to an intermediate location, initiate display, via the at least one communication device, of second routing information indicating a second destination or a final destination that is different than the first destination.

Abstract: Methods of determining a final space reservation for a new aircraft are disclosed. The methods include using parametric definitions of potential payloads to generate a population of representative payloads for use in creating an initial space reservation. The methods include accounting for and applying a variety of margins on each potential payload and taking the union of potential payloads. Alternatively, the union can be taken first and then the margins applied. A homogenous space reservation can be determined based upon a variety of differently shaped or sized payloads, including a margin build-up to mitigate risk of unknowns associated with future changes in specific payload shapes and sizes, build tolerances, environmental conditions, and/or loading and unloading motions and clearances. Once this space reservation is known, it is possible to design an external shape of a carrying vehicle by staying outside of this space reservation.

Abstract: An automatically adjustable landing light circuit and method for an aircraft approaching a target are provided. The circuit includes a memory having therein an auto adjustable landing light program, and a processor operationally coupled to a source of real-time navigation data, a source of intended approach information, a source of target geometry, and a source of environmental information including cross-wind data. The processor executes the auto adjustable landing light program, to: determine a course correction, as a function of the cross-wind data, upon determining each occurrence of deviations exceeding respective thresholds for the current heading and an intended heading, the current pitch and an intended pitch, and the current yaw and an intended yaw. The processor generates control motor commands for a landing lights assembly that generates a landing light projection. The control motor commands adjust the landing light projection in accordance with each determined course correction.

Abstract: A vehicle seat can be configured to selectively provide support to a vehicle occupant in conditions when lateral acceleration is experienced. An actuator can be located within the vehicle seat. When activated, the actuator cause a portion of the seat to morph into an activated configuration. The actuator can be activated based on vehicle speed, steering angle, and/or lateral acceleration. The actuator can include end members connected by a shape memory material connecting member. Actuator blocks with sliding surfaces can be located between the end members. The actuator can be configured such that, in response to an activation input, the shape memory material connecting member contracts, which draws the end members toward each other and causes corresponding sliding surfaces of the plurality of actuator blocks to engage and slide relative to each other. In this way, the actuator morphs into an activated configuration in which its overall height increases.

Abstract: A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.

Abstract: Systems and methods of searching stored flight plan information using a custom search query including at least one aircraft parameter condition or environmental parameter condition. The systems and method include receiving, using a user interface module, a custom search query comprising an aircraft parameter condition or an environmental condition; searching, using a processor module, stored flight plan information for instances in the stored flight plan information that satisfy the aircraft parameter condition or environmental condition; and displaying, using a display module, the instances in the stored flight plan information that satisfy the aircraft parameter condition or environmental condition.

Abstract: A Passenger Service Unit (PSU) including an outer plate having an aperture therethrough. The outer plate has symmetry about at least one outer plate axis. The outer plate is configured to be couplable to a passenger compartment at a first position and a second position nonadjacent to the first position. The PSU also includes a first insert configured to be coupled to the outer plate and includes at least one component to be manipulated by a passenger in the passenger compartment. The first insert has symmetry about at least one insert axis and at least a portion of the first inner plate fits within the aperture. Further, the inner plate is rotatable with respect to the outer plate such that the inner plate can be coupled to the outer plate in a first orientation and a second orientation offset by substantially 180 degrees from the first orientation.