Abstract: A pressure bulkhead assembly for an aircraft includes an aft pressure bulkhead and a plurality of splice angles. The aft pressure bulkhead includes a bulkhead interface surface and aft-pressure-bulkhead holes, pre-drilled through the bulkhead interface surface. The plurality of splice angles is configured to be coupled to the aft pressure bulkhead. Each one of the plurality of splice angles includes a flange surface, configured to mate with the bulkhead interface surface. Each one of the plurality of splice angles also includes splice-angle holes, drilled through the flange surface. Each one of the plurality of splice angles further includes a splice surface, extending from the flange surface. With the splice-angle holes aligned with the aft-pressure-bulkhead holes, a plurality of splice surfaces forms a circumferential splice surface with an optimized shape.

Abstract: An aircraft door mounted in a fuselage in a reference frame X, Y, Z, having a casing, a door leaf and a support arm enabling the door leaf to be installed and the position thereof to be adjusted relative to the fuselage by a pair of fasteners. Each fastener (10, 40) includes a pivot (16, 46) rotatable about a common axis parallel to the axis Z, a base (13, 43) fastened to the casing (3), and a trolley (14, 44) movable on this base (13, 43), the base (13, 43) and the trolley (14, 44) of each fastener (10, 40) forming two translational adjustment links in directions parallel to the X and Y axes, these directions determining adjustment axes (11, 12; 41, 42) secant in a plane parallel to the plane XY.

Abstract: An aircraft wing is disclosed having a main fixed wing portion and a wing tip device at a tip thereof. The wing tip device is configurable between a flight configuration and a ground configuration, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. A hinge arrangement connects the main fixed wing portion and the wing tip device and enables the wing tip device to rotate between the ground configuration and the flight configuration. The hinge arrangement protrudes beyond an outer surface of the main fixed wing portion and wing tip device. A fairing covers at least part of the hinge arrangement on at least a suction side of the wing.

Abstract: A roller for a control surface of an aircraft includes a roller shaft, a primary roller coupled to the shaft, and a roller assembly coupled to the shaft. The shaft includes a longitudinal axis, a mounting end that couples with a roller fitting of the control surface, and a roller end. The primary roller can rotate about the longitudinal axis, and can engage and roll along a first surface of a track. The roller assembly includes a secondary roller having a longitudinal roller axis and configured to engage and roll along a second surface of the track. The roller assembly also includes a housing that retains the secondary roller while allowing the secondary roller to rotate about the longitudinal roller axis. The housing is movably coupled to the roller end of the roller shaft with three degrees of rotational freedom relative to the roller end of the roller shaft.

Abstract: A thrust generating device includes a propeller unit including a propeller and a duct covering the periphery of the propeller. The duct includes a cylinder disposed around the propeller, a hub disposed inside the cylinder, and a plurality of duct stators extending radially from the hub to the cylinder. The hub and each of the duct stators are disposed rearward of the propeller.

Abstract: Provided is a method for controlling the directional orientation of a flying object so that the flying object faces in a direction that increases the efficiency of flight over the immediately preceding state based on predetermined information. To provide a method of flight control whereby a flying object having directional characteristics according to such a configuration can fly in an attitude suitable for the relative wind direction and wind speed in flight in order to actively utilize lift, reduce drag, and the like. According to such a configuration, the optimal flight attitude can be obtained by adjusting the wind direction and aircraft direction, thereby increasing safety while improving fuel efficiency.

Abstract: A combined cyclic and teeter system for an electric vertical takeoff and landing (eVTOL) aircraft is disclosed. In some embodiments, the eVTOL aircraft may include a motor and a propulsor driven by the motor, wherein the propulsor may include a propeller with a rigid blade and configured to propel the eVTOL aircraft. In some embodiments, the eVTOL aircraft may include a cyclic attached to the propeller and configured to change a pitch of blades of the propeller. In some embodiments, the eVTOL aircraft may include a passive flap attached to the propeller and configured to passively control flight transients, wherein the passive flap may include a base rotatably affixed to the propulsor and configured to rotate about a rotational axis and a hinge connecting the base and the propeller and configured to allow the propeller to pivot about a pivot point of the hinge.

Abstract: An inner middle rotor is rotated while an inner front rotor, an inner back rotor, and an outer rotor are not rotated. The inner middle rotor is surrounded by the inner front rotor, the inner back rotor, the outer rotor, and a fuselage. After rotating the inner middle rotor while not rotating the inner front rotor, the inner back rotor, and the outer rotor, the inner middle rotor, the inner front rotor, the inner back rotor, and the outer rotor are simultaneously rotated.

Abstract: A rotary shaft assembly includes a rotary shaft having a first end portion, a second end portion opposite the first end portion, a longitudinal axis extending centrally through the first and second end portions, and a shaft body that defines a bore between the first and second end portions. An anti-flailing mechanism is positioned within the bore of the shaft body. The anti-flailing mechanism is coupled to rotary shaft and extends at least partially between the first and second end portions to contain the rotary shaft about the longitudinal axis when the rotary shaft fails.

Abstract: A rotor blade for a rotary wing aircraft includes a leading edge and a trailing edge defining a chordwise direction. The leading edge defines a forward end of the rotor blade and the trailing edge defines an aft end of the rotor blade. The rotor blade has a center of gravity and an aerodynamic center along the chordwise direction. The center of gravity is aft of the aerodynamic center.

Abstract: An autonomous vehicle that is equipped with image capture devices can use information gathered from the image capture devices to plan a future three-dimensional (3D) trajectory through a physical environment. To this end, a technique is described for image-space based motion planning. In an embodiment, a planned 3D trajectory is projected into an image-space of an image captured by the autonomous vehicle. The planned 3D trajectory is then optimized according to a cost function derived from information (e.g., depth estimates) in the captured image. The cost function associates higher cost values with identified regions of the captured image that are associated with areas of the physical environment into which travel is risky or otherwise undesirable. The autonomous vehicle is thereby encouraged to avoid these areas while satisfying other motion planning objectives.

Abstract: A method for an aerial vehicle includes generating a control signal that controls multiple actuators of the aerial vehicle each including a corresponding one of multiple propellers. The multiple propellers are configured to be mounted in multiple actuators, respectively. The method also includes controlling the multiple actuators to operate based on the control signal; obtaining status information of the aerial vehicle when the multiple actuators are operating in response to the control signal; and determining whether at least one of the multiple propellers is abnormally mounted according to the status information.

Abstract: This disclosure is directed to a payload attachment and payload management and control device for an unmanned aircraft for supporting a payload having a payload handle, the payload attachment device. The payload attachment device including a receiver for receiving the payload handle and a releasable latch in the receiver having an engaged position and disengaged position, the latched biased to the engaged position restraining a payload handle. The payload attachment device includes a manual release connected to the latch for overcoming the bias and moving the cam to the disengaged position and an automated release connected to the latch for overcoming the bias and moving the cam to the disengaged position, the automated release connected to a controller of the unmanned aircraft. The payload attachment device may also receive payload telemetry data and electrical power from the payload using a disconnectable electrical communication connection.

Abstract: A suspension and control head apparatus for an aerial firefighting bucket comprising: a rigid frame member having an upper cargo attachment portion that is removably connectable to a cargo hook of a hover capable aircraft, the frame member including lower spaced apart cable attachment portions that are removably connectable to support cables that support the bucket; the frame member defining bilateral opposite sides, one side being a solenoid side and the opposite side being a reel side; a solenoid mounted on the solenoid side, the solenoid being coupled to an electrical source and a switch that energizes and deenergizes the solenoid; a spring-loaded reel rotatably mounted on the reel side, the reel having wound thereon a cable when the reel is in a relaxed or nearly relaxed state, the cable having a stop member, wherein the solenoid and the reel are adjacent to each other on the opposite sides; a latch that interferes with the stop member when the latch is in a latched position and the latch being moveable t

Abstract: A modular water storing and jettisoning system which can be easily introduced into and removed from a host firefighting aircraft. To that end, the water storing and jettisoning system for a host aircraft comprises a fluid tank and at least one tube. The tank is connected to said tube or to all of said tubes which extend(s) longitudinally from the tank such that, once installed in a host aircraft, the one or more tubes conduct the fluid to the longitudinal end of a rear door of the aircraft in an open position. Also an aircraft fitted with such a system.

Abstract: A control apparatus includes a controller configured to acquire weather information including a wind speed on a scheduled spraying date and time at which an unmanned aircraft is to spray an agricultural chemical on a field, determine a flight altitude of the unmanned aircraft according to the wind speed, and generate a plan for spraying of the agricultural chemical by the unmanned aircraft, the plan for spraying including the determined flight altitude.

Abstract: A technique for validating a presence of a package carried by an unmanned aerial vehicle (UAV) includes: capturing an image of a scene below the UAV with a camera mounted to the UAV and oriented to face down from the UAV; analyzing the image to identify whether the package is present in the image; and determining whether the package is attached to the UAV, via a tether extending from an underside of the UAV, based at least on the analyzing of the image.

Abstract: A vehicle lavatory monument assembly that includes an enclosure having a plurality of walls that cooperate to define a lavatory interior, an entry door, and a toilet positioned in the lavatory interior. The enclosure includes an inlet and the toilet includes an outlet. An air replenishment system is configured to move a first volume of air from the lavatory interior and through the outlet and a second volume of air through the inlet an into the lavatory interior to replenish the air in the lavatory interior.

Abstract: A cabin monument having a monument body and a transparent film which is connected to the monument body. The transparent film has a large number of light-emitting elements. Further provided is an aircraft having at least one such cabin monument and a control device.

Abstract: An endurance haptic system is disclosed herein. The endurance haptic system includes a plurality of tactors, a plurality of air bladders, a tactor driver operably coupled to the plurality of tactors and configured to send vibration commands to the plurality of tactors in response to a first signal received from an aircraft controller, and an air bladder driver operably coupled to the plurality of air bladders and configured to inflate and deflate the plurality of air bladders in response to a second signal received from the aircraft controller.

Abstract: An environmental control system of a vehicle includes an inlet for receiving a medium, an outlet for delivering a conditioned form of the medium to a load, a primary heat exchanger fluidly coupled to the inlet and a secondary heat exchanger. A thermodynamic device is fluidly coupled to the primary heat exchanger and the secondary heat exchanger. A first bypass conduit has a first bypass inlet arranged upstream from the primary heat exchanger and a first bypass outlet arranged upstream from the secondary heat exchanger. A first bypass valve is operable to control a flow of medium through the first bypass conduit. During operation in a first mode, the medium is configured to flow through the primary heat exchanger and the secondary heat exchanger in series. During operation in a second mode, the medium is configured to flow through the primary heat exchanger and the secondary heat exchanger in parallel.

Abstract: A system is disclosed herein, including a cushion including a plurality of tactors and a plurality of air bladders disposed adjacent the plurality of tactors, a pump assembly operably connected to the plurality of bladders, a processor, and a memory operatively coupled to the processor. The memory includes instructions stored thereon that, when executed by the processor, cause the processor to determine an inflation sequence for the plurality of air bladders, determine a deflation sequence for the plurality of air bladders, output commands to the pump assembly corresponding to the inflation sequence and the deflation sequence, and output vibrate commands to the plurality of tactors.

Abstract: A technical object of the present invention is to provide a supplementary thrust generating apparatus which may apply additional force to an object in a thrust direction while applying a thrust to an object by a propulsion device, wherein the supplementary thrust generating apparatus as a supplementary thrust generating apparatus used for an object having a propulsion device is provided on an outer surface of the object, and converts an external pressure applied to the object while the object is propelled by the propulsion device, and generates a supplementary thrust in the same direction as a thrust direction of the propulsion device.

Abstract: An aircraft includes a gas turbine engine, an electric motor, and a propulsion device. The gas turbine engine and the electric motor are configured to provide a target cumulative output to the propulsion device. An electronic control unit is configured to set the gas turbine engine to a first engine mode to provide a first engine output to the propulsion device, set the electric motor to a first motor mode to provide a first motor output to the propulsion device, a sum of the first engine output and the first motor output being within a predetermined range of the target cumulative output, and in response to a speed of the aircraft reaching a target speed and the first engine output increasing to a second engine output, set the electric motor to a second motor mode.

Abstract: A hybrid engine including features to meet aircraft thrust, passenger airflow, and fuel cell requirements. The engine includes a combustor burning the same fuel as the fuel cell. The engine has electric motors to utilize the power output of the fuel cell. The engine shafts have sprags to allow motors to drive the compressors and over run the turbines. The engine has variable flowpath geometry to bypass the combustor.

Abstract: Example engine apparatus and associated control methods are disclosed. An example engine apparatus includes: a frame; a lug to attach the frame to an aircraft; a mount cover positioned over the lug; and a heating mechanism to regulate a temperature of the lug under the mount cover.

Abstract: A system and method for controlling an aircraft engine is provided. The method includes a) producing first sensor data using a first sensor sensing a first parameter during operation of the aircraft engine on a flight mission; b) producing other sensor data using a plurality of second sensors sensing a plurality of other parameters, during operation of the aircraft engine; c) providing the first and other sensor data to a control unit during operation of the aircraft engine; d) storing the first and other sensor data during operation of the aircraft engine; e) using an artificial intelligence (AI) model that is trained using the stored first and other sensor data produced during operation of the aircraft engine, to produce one or more derived first parameter values; and f) selectively providing the one or more derived first parameter values to the control unit for use in controlling the aircraft engine.

Abstract: Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, and a voltage regulator. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.

Abstract: A system for estimating percentage torque produced by a propulsor configured for use in an electric aircraft, the system including a propulsor, the propulsor configured to generate output torque. The system including a sensor, the sensor configured to detect the output torque and generate an output torque datum. The system including a flight controller including a computing device configured to receive an output torque datum, receive an ideal propulsor model, the ideal propulsor model including at least a performance parameter, generate a model torque datum, including a model torque datum threshold, as a function of the at least a performance parameter, generate a percentage datum as a function of the output torque datum and model torque datum, and determine, at least an obstruction datum correlated to the torque percentage datum, and display torque percentage datum and the at least an obstruction datum.

Abstract: Inlet systems are described. An example inlet system has a first wall, a second wall, and a compressor. The first wall has a first end, a second end, and defines a passageway, a first passageway opening, and a second passageway opening. The passageway extends from the first passageway opening to the second passageway opening. The first wall and the second wall cooperatively define an inlet, an outlet, and a channel. The channel extends from the inlet to the outlet. The compressor is disposed within the passageway and is configured to pressurize fluid that passes through the passageway. The first end of the first wall is disposed outside of the channel. The passageway is in fluid communication with the channel.

Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective plate fastened to the frame and positioned between the casing and the supply pipe. With such an arrangement, if a blade of the turbine became detached it would meet the protective plate blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

Abstract: A powerplant for an aircraft, comprising a frame, a propulsion system comprising a core enclosed in a casing and comprising a combustion chamber and a turbine, a supply pipe for conveying dihydrogen to the combustion chamber and that snakes outside the casing running along the turbine before dropping down into the combustion chamber through the casing, and a protective cylinder fastened to the frame or to the casing by fastening means and positioned around the casing and between the supply pipe and the turbine. With such an arrangement, if a blade of the turbine became detached it would meet the protective cylinder blocking its path to the dihydrogen pipe and would thus be diverted or stopped.

Abstract: There is a remote control device or drone, which has software and a combination of lights or LED on an lighting ring or apparatus that can move independently of the drone; the drone can be programmed or be reactive to sound or other stimulus to create the effect of writing shapes or words in the air and typically at nighttime against a dark sky.

Abstract: A system for airborne storage, assembly and launch of aircraft and spacecraft.

Abstract: A system for isolating sound generated by an aircraft utilizing a helipad may include a plurality of acoustic scatterers being disposed adjacent to at least a portion of a perimeter of the helipad. Each of the plurality of acoustic scatterers include channels having an open end and a terminal end. Additionally, each of the plurality of acoustic scatterers has an acoustic monopole response and an acoustic dipole response with a resonant frequency that is substantially similar to one another.

Abstract: The invention relates to a monolithic structure in composite material manufactured starting from a fiber-reinforced prepreg material and comprises two walls facing each other and at least one interconnection element extending transversely between the walls, connected to them and delimiting with the latter respective elongated cavities; wherein the walls extend symmetrically at opposite sides of a direction; the interconnection element is a rib extending transversely to the aforesaid direction; at least one wall has a sandwich configuration and comprises two panels facing each other and at least one spar member, which extends transversely between the panels, is connected to them, delimits with the latter respective elongated cavities and extends transversally to the rib.

Abstract: Provided is a steam jet multifunctional aircraft deicing vehicle with steam jet, includes a vehicle body, where a steam generating assembly is arranged in the vehicle body, and the steam generating assembly is connected with a steam conveying assembly. A moving assembly is rotatably connected above the vehicle body, and the moving assembly is rotatably connected with an execution assembly. The execution assembly includes a first spray head assembly and a second spray head assembly. The steam conveying assembly includes a first supercharger and a second supercharger arranged side by side, where an air outlet end of the first supercharger is communicated with one end of a first air outlet pipe, and an other end of the first air outlet pipe is communicated with spray heads of the second spray head assembly through a first air pipeline.

Abstract: A method includes obtaining, at a device, a first test matrix for a first aircraft system and a second test matrix for a second aircraft system. The method also includes, during a first operational test of the first test matrix, obtaining sensor data that includes first sensor data in a range specified by the first test matrix and second sensor data that is not specified by the first test matrix. The method includes evaluating, at the device, a second operational test of the second test matrix by processing the second sensor data using a second analytic model of the second aircraft system. The method also includes determining, based at least in part on a range of the second sensor data, a test coverage metric of the second test matrix. The method further includes providing an output to a display device, the output indicating the test coverage metric.

Abstract: An aerospike engine configured to be connected to a liquid methane tank, and to a liquid oxygen tank is provided. The aerospike engine comprises a centerbody including an aerospike nozzle, an external skirt, and a combustion chamber being defined between the external skirt and the centerbody. The centerbody is additively manufactured from one or more copper alloys and has a plurality of centerbody internal cooling channels. The external skirt is additively manufactured from one or more copper alloys and has a plurality of skirt internal cooling channels. The aerospike engine is configured to supply liquid methane and liquid oxygen through the internal cooling channels to the combustion chamber. Also disclosed are stages of a launch vehicle and a launch vehicle comprising such an aerospike engine, as well as methods for re-entry for a re-usable stage of a launch vehicle comprising an aerospike engine.

Abstract: A system for providing spacecraft-based services, preferably including one or more spacecraft and one or more ground control elements, wherein the spacecraft can include one or more payloads associated with one or more organizations. A method for providing spacecraft-based services, preferably including receiving service requests, determining request assignments, and/or controlling spacecraft.

Abstract: Provided are a method and apparatus for ground target precision orientation for satellite image acquisition, in which the method includes: receiving a desired satellite position (P) for imaging from a ground station, and receiving a ground plan imaging time (T) or an algorithm execution time (TA) from the ground station, in which the ground plan imaging time (T) is calculated according to the desired satellite position (P) for imaging at a ground-based orbit propagator, and the algorithm execution time (TA) is set to be earlier than the ground plan imaging time (T) by a predetermined amount of time; and determining, based on a position error (E) calculated by using a difference between the desired satellite position (P) for imaging and the predicted satellite position (Q) output from the satellite-based orbit propagator, a closest satellite position (QC) and a closest satellite time (TC) corresponding to when the satellite is closest to the desired satellite position (P) for imaging, and determining a correct

Abstract: A cold gas thruster having a two-stage solenoid is provided. Pressurized gas from the inlet flows to the back side of the piston to hold the piston closed. The pressure is maintained by a check ball held by the solenoid armature. When the solenoid is energized, the armature allows the check ball to move to bleed off the pressure holding the piston closed. The piston moves away from its seat and allows the pressurized gas to flow to the outlet creating thrust. When the solenoid coil is de-energized, the check ball is forced against its seat, which blocks the escape of pressure on the back side of the piston, so that it can re-pressurize back up to the inlet pressure. This creates a force imbalance and moves the piston to close the valve and stop the thrust. Different nozzles can be used for different thrust profiles without changing the solenoid.

Abstract: The present invention relates to a system for power delivery to satellites. More particularly, the present invention relates to a method and system for providing power to orbiting satellites from ground stations on Earth using laser light. Aspects and/or embodiments seek to provide a method of delivering power to artificial satellites from ground stations using electromagnetic energy, for example laser light.

Abstract: A workstation for microgravity environments is provided that prevents objects from floating around inside a spacecraft. The workstation includes a downdraft table that has a plenum chamber with an inlet and an outlet. A fan is disposed in the plenum chamber for drawing air into the plenum via the inlet, and exhausting air from the plenum via the outlet. A metal grate is disposed across the inlet, and an air resistive stack is disposed on an outer side of the metal grate. The air resistive stack includes an inner resistive layer disposed on the metal grate and an outer resistive layer disposed on the inner layer. The workstation improves a user's ability to perform many activities in a microgravity environment.

Abstract: A hybrid aircraft of the unmanned type configured for joint and optimized use of aerostatic and aerodynamic force is provided. The hybrid aircraft has an inflatable body having an outer shell and a load-bearing structure inside the outer shell, the inflatable body being adapted to assume a closed wing operating configuration.

Abstract: An image capturing system including a device that is capable of flying, and an image capturing apparatus that is attached to the device. The device includes a drive unit attached to the device that holds the image capturing apparatus and changes a position of the image capturing apparatus. The drive unit is controlled in a direction in which a lens of the image capturing apparatus is protected from an obstacle when image capturing is not performed by the image capturing apparatus.

Abstract: This invention relates generally to pet and child toys and drones. More specifically, the invention relates to an apparatus and method of operation for an autonomous or remotely controlled fetch toy drone for pets and children that is safe to operate and retrieve, extends the fetching range beyond that of a throw-type fetch toy, and also provides numerous other features, such as actuated shut-down and audio broadcast features, as well as video and audio recording capabilities, and supplemental stimuli features.

Abstract: A modular drone containment system including a plurality of modular stacked drone containers. Each modular drone container is configured to house a drone device and be removably disposed in a stacked orientation relative to one another. Each modular container includes a sidewall having a continuous upstanding wall defining a containment space configured to house a respective drone device. A topmost modular container in the stacked orientation further includes a top cover pivotally attached to a top portion of its sidewall. A bottommost modular container in the stacked orientation includes a bottom wall attached to a bottom portion of its sidewall. Further included is a charging system configured to simultaneously charge a battery provided in each drone housed in a stacked modular container.

Abstract: An injection system is provided. An injection pump is coupled to a fluid reservoir operable to create a flow of fluid. The injection pump can include an outlet through which the fluid is dispensed. A conduit is coupled with the injection pump. The conduit forms a channel operable to permit the fluid to flow therethrough. The channel extends linearly along a longitudinal axis.

Abstract: A system includes a gantry having an end-of-arm tool (EOAT). The gantry can include a first linear actuator that is configured to axially move the EOAT along a first axis and second linear actuator that is configured to axially move the EOAT along a second axis that is perpendicular to the first axis. The system can further include at least one input conveyor. Each input conveyor can have a plurality of pucks that are each configured to receive a prescription container and carry the prescription container to the gantry. The system can further include at least one output conveyor that is configured to receive the prescription container from the gantry. The gantry can be configured to move the prescription containers from the plurality of pucks to the output conveyor(s).