Abstract: Embodiments provide an electric aircraft with a plurality of lift fan assemblies that are configured to provide vertical lift, and one or more pusher propellers that are configured to provide forward thrust. The lift fan assemblies may be coupled to the wings of the aircraft via one or more support structures, and the wings may be coupled to an upper region of the fuselage. The pusher propeller(s) may be coupled to a tailing end of the fuselage. The lift fan assemblies and the pusher propeller(s) may provide thrust and movement in directions that are orthogonal to one another. A control system coupled to the aircraft may control the lift fan assemblies and the one or more pusher propellers to activate, increase in power, and decrease in power. The lift fan assemblies and the one or more pusher propellers may be operated separately, and may be active at different times.

Abstract: A remote towing interface is used to couple a towbar to an aircraft having a fuselage and a steerable landing gear. The remote towing interface includes a towbar coupler mounted to the aircraft and configured to releasably couple a towbar to the aircraft. The remote towing interface further includes a sensor and a controller. The sensor is configured to sense a position of the towbar relative to the aircraft when the towbar is coupled to the towbar coupler, and the controller controls the steerable landing gear according to the sensed position of the towbar relative to the aircraft.

Abstract: Devices and methods of a pod that deploys from an aircraft or vehicle and descends to safely land. The pod is configured to be attached to an aircraft or vehicle. The pod includes walls that extend around and form a contained interior space that houses one or more travelers or cargo containers. During flight of the aircraft or vehicle, the pod deploys from the aircraft or vehicle while at an elevation above ground. A landing location is determined for the pod. While the pod is descending, the pod is steered towards and lands at the landing location.

Abstract: A canopy is configured to be mounted to a passenger seat of a passenger transport vehicle, in particular an aircraft. The canopy is foldable between a retracted storage configuration and an extended operational configuration. In the operational configuration, the canopy forms a hood establishing a passenger's personal space below the canopy. The canopy comprises at least one functional device which is configured for modifying a physical characteristics of the personal space. The at least one functional device in particular includes at least one of a lighting device configured for lighting the personal space and a venting device configured for venting the personal space.

Abstract: An aircraft monitoring system for an electric aircraft is disclosed. The monitoring system may include at least a sensor configured to generate a failure datum. The failure datum includes a datum regarding a condition of an electric motors. An electronic checklist may include a crew alerting system (CAS). A CAS may be in electronic communication a sensor, wherein the CAS is comprised of at least a computing device. A CAS may generate a plurality of remedy data as a function of the failure datum. A CAS then may display the plurality of remedy data using a pilot display. A pilot may be prompted to apply the remedy datum using a pilot display as a function of the plurality of remedy data. The CAS provides an indication of the condition of the electric motor using a pilot display as a function of the application of the plurality of remedy data.

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: A landing gear monitoring and alerting system includes a locking pin configured to be inserted into an aperture extending through a linkage of an extended landing gear assembly. When inserted into the aperture, the locking pin inhibits movement of the linkage to establish a locked state of the extended landing gear assembly. This system further includes a magnetic sensor and a communication module. The magnetic sensor is disposed proximate the aperture and is configured to sense a magnetic response indicative of the locking pin being disposed within the aperture. The magnetic sensor is configured to generate a sensor output indicative of the locking pin being disposed within the aperture. The communication module has a transmitter coupled to the magnetic sensor so as to receive the sensor output and is configured to responsively transmit a signal indicative of the locking pin being disposed within the aperture.

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: A transport system identifies an attribute of a ground on the basis of sensing data obtained by sensing the ground in a transport destination area, which is performed in flight by an Unmanned Aerial Vehicle transporting an article, and determines a region in the ground as an arrangement place of the article on the basis of the identified attribute.

Abstract: A movement space information processing system includes moving bodies and an information processing device. The information processing device determines one or more moving bodies that are movably located within a predetermined movement range in the space from the moving bodies, and performs an identification task of identifying, from the determined one or more moving bodies, at least one moving body to accordingly perform a setting task of setting the identified at least one moving body as the at least one representative moving body. At least one moving body identified as the at least one representative moving body acquires an image of the space and extracts, from the image, probe information related to the space. The information processing transmits device The moving-body information item including the probe information and performs development of the spatial information based on the probe information.

Abstract: An aircraft controller configured to determine a period and/or distance over which deployment of a landing gear can be initiated for landing including a determined first portion during which landing gear deployment can be safely initiated and a determined second portion, closer to aircraft landing than the first portion, during which the landing gear deployment can be safely initiated in an efficient landing mode; issue a first pilot feedback when the first portion is entered by the aircraft; issue a second pilot feedback when the second portion of the determined; and initiate landing gear deployment when the aircraft is in the determined period and/or distance in response to receiving a deployment signal from the pilot.

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: An aircraft glazing unit including a body of transparent material and at least one subsurface thickness indicator at a predetermined depth within the material. The provision of a subsurface thickness indicator allows for the unit to be re-polished to remove erosion, whilst providing a visual indicator to ground crew of the remaining thickness of material in the unit. In this way, the service lifetime of the glazing unit can be extended.

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: A method for monitoring a condition of a VTOL-aircraft (1), preferably an electrically propelled, more particularly an autonomous, more particularly a multi-rotor aircraft, with a plurality of spatially distributed actuators (2i, 2o), preferably propulsion units, wherein a primary control (4.1) is used for controlling a flight state of the VTOL-aircraft (1) and at least one secondary control (4.2) is used for controlling the actuators (2i, 2o) of the VTOL-aircraft (1), preferably the propulsion units (2i, 2o); during operation. The primary control (4.1) generates a primary data set, which is subject to a first uncertainty, and is entered into an estimation algorithm, and the secondary control generates a secondary data set, which is subject to a second uncertainty, and is also entered into the estimation algorithm.

Abstract: Systems and methods for minimizing an aircraft turn radius are disclosed. For example, a method to minimize an aircraft turn radius may include receiving an activation signal from an activation switch. The activation switch may be configured allow a selected turn. The method may also include receiving a turn command in a direction of the selected turn. The method may also include transmitting a turn signal to an actuator operatively coupled to a nosewheel assembly. The actuator may rotate a shaft in the direction of the selected turn to move at least one nosewheel from a first angle to a second angle with reference to a longitudinal axis of the aircraft. The method may also include transmitting a thrust signal to at least one of a plurality of thrust-producing devices operatively coupled to a first wing and a second wing operatively coupled to the aircraft.

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: In an aspect an apparatus for determining a most limiting parameter of an electric aircraft is presented. An apparatus includes at least a processor and a memory communicatively connected to the at least a processor. A memory contains instructions configuring at least a processor to receive aircraft data from a sensing device. A sensing device is configured to measure a parameter of an electric aircraft and generate aircraft data. At least a processor is configured to determine a most limiting parameter of an electric aircraft as a function of aircraft data. At least a processor is configured to communicate a most limiting parameter to a pilot indicator in communication with the at least a processor and memory communicatively connected to the at least a processor. A pilot indicator is configured to display a most limiting parameter to a user.

Abstract: [Object] To provide a technique for reducing the fluctuation of an airplane when an airplane enters turbulence without using prior information of two-dimensional or more airflow vectors. [Solving Means] A system includes: a measurement unit 10 that emits electromagnetic waves toward a planned flight direction of the airplane, receives scattered waves of the emitted electromagnetic waves in atmosphere, and measures a remote wind speed in a radiation axis direction of the emitted electromagnetic waves based on a Doppler shift amount of a frequency between the emitted electromagnetic waves and the scattered electromagnetic waves; a spoiler 221 that controls a lift of the airplane; and a control calculation unit 30 that calculates an angle of attack with less lift inclination and calculates an angle of the spoiler 221 that controls the lift so that the lift does not change when it is determined that the airplane will receive a gust, based on a measurement result of the measurement unit 10.

Abstract: A field planting system for planting seeds of at least two plant genotypes in a field includes a multi-variety planter operable to plant the seeds of the at least two plant genotypes in the field. The field planting system also includes a controller in operable communication with the multi-variety planter. The controller is configured to receive georeferenced field information for the field and plant information for the at least two plant genotypes, and generate a planting map for the field based on the georeferenced field information and the plant information, the planting map including a planting pattern for interplanting the seeds of the at least two plant genotypes. The controller is further configured to monitor a location of the multi-variety planter in the field, and control the multi-variety planter to plant the seeds of the at least two plant genotypes in the field according to the planting map.