Abstract: A propulsion unit for an aircraft, includes a support structure, a nacelle and a turbomachine. The support structure is configured to independently support, on the one hand, the turbomachine and, on the other hand, preferably by a cradle, an air inlet and/or a rear section of the nacelle.

Abstract: A drone port is portable to be disposed on a landing surface for a drone and includes a covering section configured to cover the landing surface and provided with markers of different sizes. The covering section includes a restraining section configured to restrain the drone on the covering section. The restraining section includes a first hook-and-loop fastener disposed on the covering section. The first hook-and-loop fastener is configured to join with a second hook-and-loop fastener configured to be disposed on the drone.

Abstract: A device is described for cooling air and directing it onto a hive. As the hive cools, pollinators within have reduced mobility and are not able to move aggressively to attack the remover. A temperature sensor within the device allows the remover to identify when air is sufficiently cooled to reduce pollinator activity without being lethal. As the cold air is blowing, the remover uses attached sharp edges to cut down the hive. As the hive falls on the ground away from the blower where the temperature is warmer, pollinators regain their muscle movement, and can soon resume their normal activities. However, by then the remover is gone and is not attacked.

Abstract: A transformable Unmanned Aerial Vehicle (UAV), can operate as a coplanar hexacopter or as an omnidirectional multirotor based on different operation modes. The UAV has 100% force efficiency for launching or landing tasks in the coplanar mode. In the omnidirectional mode, the UAV is fully actuated in the air for agile mobility in six degrees of freedom (DOFs). Models and control design are developed to characterize the motion of the transformable UAV. Simulation results are presented to validate the transformable UAV design and the enhanced UAV performance, compared with a fixed structure.

Abstract: Bait stations are disclosed that include a housing having an upper casing and a lower casing coupled to form an interior cavity. A pad, gel, or variations thereof that carry food are disposed within the interior cavity. The lower casing includes a base having a peripheral flange that defines an outer edge, an outer wall that is spaced apart from the outer edge and extends upwardly from the peripheral base flange to a top edge, and an inner wall that extends from the top edge to a first surface to define a receiving space therein. The upper casing includes a plurality of apertures that are configured to allow insects therethrough into the interior cavity.

Abstract: A power system for an aircraft includes one or more gas turbine engines arranged to burn a fuel so as to provide power to the aircraft; a plurality of fuel tanks each arranged to contain a fuel to be used to provide power to the aircraft; and a fuel manager. At least two of the fuel tanks contain different fuels, which have different proportions of a sustainable aviation fuel. The fuel manager is arranged to store information on the fuel contained in each fuel tank; and to control fuel supply so as to select a specific fuel accordingly to power at least the majority of operations on the ground. The fuel manager may additionally identify which tank contains the fuel with the highest proportion of a sustainable aviation fuel; and that fuel may be used to power at least the majority of operations on the ground.

Abstract: The present invention relates to a brush for pets that includes a handle part configured to be grasped by a user and a brush part coupled to the handle part and configured to brush pet hair, wherein the brush part includes a floor plate, a comb teeth array which consists of a plurality of comb teeth that extend in a state of being embedded in the floor plate, and a brush shade which is connected to the floor plate and configured to wrap around the comb teeth array, and a height of the brush shade is larger than a height of the comb teeth, and thus, when the brush shade is brought into contact with an epidermis of the pet to perform brushing, a closed space is formed inside the brush shade.

Abstract: An aircraft assembly is disclosed including an aircraft panel, a channel attached to the aircraft panel, a fuel line for carrying cryogenic fuel, the fuel line disposed in the channel, and a sealed containment space around the fuel line for containing cryogenic fuel leaked from the fuel line, the containment space defined between the channel, the fuel pipe, and the aircraft panel.

Abstract: A lure having a body with a line tie and one or more hooks attached to the body. The body includes pockets which are reflective such as by attaching a reflective material to the back wall of the pockets to make the lure more visible to a fish. Some prior art lures are not designed to reflect light or reflect light in one or a small number of directions.

Abstract: A barrier door to control movement of persons through an opening within a cabin area of an aircraft. The barrier door includes a body comprising an upper side, a lower side, and lateral sides. A lock is connected to the body and includes an elongated member and a pin. The pin is movable between a disengaged position with a distal end retracted and an engaged position with the distal end extending outward beyond the elongated member. A release mechanism is threaded on the elongated member and is rotatable relative to the elongated member to adjust a position of the elongated member and pin relative to the body.

Abstract: In order to suppress aeroelastic instabilities on a transonically operating aircraft comprising a pair of wing halves at which a transonic flow forms spatially limited supersonic flow regions that each, in a main flow direction of the flow, end in a compression shock, a boundary layer of the flow is temporarily thickened-up in at least one supersonic flow region at at least one of the two wing halves, when approaching a flight envelope of the aircraft with increasing flight Mach number of the aircraft. The boundary layer of the flow is thickened-up to such an extent that the compression shock at the end of the respective supersonic flow region at the present flight Mach number of the aircraft induces a separation of the boundary layer of the flow from the wing half.

Abstract: A vertical seat blocking/divider device includes a seat back connector and a seat cushion connector. The vertical seat blocking/divider device is disposed on the center of an aircraft seat to block occupancy of the aircraft seat and establish a barrier between neighboring seats. In a further aspect, the vertical seat blocking/divider device includes a spring element to apply a force to the fabric of the seat blocking/divider device. In a further aspect, the vertical seat blocking/divider device may include armrest connectors on opposing surfaces so that the vertical seat blocking/divider device can be disposed between occupied seats to create a barrier between passengers.

Abstract: A system for an unmanned aerial vehicle can include an altitude control system 320, which further includes a compressor assembly 400, a valve assembly 500, and an electronics control assembly 600. The compressor assembly may include a compressor housing 410 that includes a compressor inlet 402, an outlet 202, and a cavity 414 extending therethrough and joining the inlet to the outlet. A diffuser 408 may be coupled to the compressor housing. A motor housing 407 may be disposed within the central cavity at the inlet of the compressor housing, and a compressor motor 406 may be disposed within the motor housing. An impeller 412 disposed within the compressor housing may be coupled to a driveshaft 444 for rotation therewith. The valve assembly may be coupled to an opening 416 of the compressor inlet. The valve head 502 may be configured to move into and away from the inlet opening so as to change a size of the circumferential area of the inlet opening.

Abstract: An example system for controlling a target satellite includes: a satellite-control spacecraft including: a propulsion subsystem configured to propel and navigate the spacecraft proximate the target satellite; and a satellite-capture subsystem configured to: capture the target satellite; apply a control medium to the target satellite, the control medium including an electrically conducting and/or magnetic material; and release the target satellite; and an energization assembly configured to energize the control medium to release energy for controlling, propelling and navigating the target satellite.

Abstract: A propulsion unit having a propeller for an aircraft including a nacelle; a propeller mounted in the nacelle so as to be capable of rotating about a longitudinal axis of rotation, the propeller having blades mounted by a root so as to be capable of pivoting between a deployed position, in which they extend radially relative to the axis of rotation, and a folded position, in which they are longitudinally received against the nacelle; drive means that rotate the propeller; indexing means for stopping the propeller in at least one indexed angular position (? i) relative to the nacelle; the propulsion unit wherein the indexing means consist of a stepping electric motor including a rotor that is coupled to the propeller.

Abstract: A fishing tool includes a main body and a cutting assembly coupled to the main body. The cutting assembly includes a top jaw, a bottom jaw rotatable relative to the top jaw, and a scissor assembly including a top blade and a bottom blade rotatable relative to the top blade. The top blade and the bottom blade are removably coupled to the top jaw and the bottom jaw.

Abstract: A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises a plurality of capture arms attached to a grounding structure. In one embodiment, the capture arms are kinematically linked and are free to rotate with respect to the grounding structure using a single actuator, thereby synchronizing the rotation of the arms for any angular displacement of the actuator, thus the arms form a circle that is concentric with the boom axis. In a second embodiment, there are two sets of capture arms, with the arms in each set kinematically linked and independently actuated; thus, the two sets cooperatively form different grasping geometries. Further, the docking mechanism is configured to enable the host spacecraft to dock with the client spacecraft.

Abstract: An aerial vehicle configured for operation within indoor spaces has a meshed construction with a housing defined by upper and lower sections having meshes provided above and below propellers and motors of the aerial vehicle. The aerial vehicle also includes a suite of sensors such as LIDAR sensors, time-of-flight sensors, cameras, ultrasonic sensors, or others. Meshes of the upper and lower sections include central openings along with spokes and concentric rings provided about the central openings. Meshes of the lower section have substantially larger central openings than meshes of the upper section, but feature more dense spokes or concentric rings beneath tips of the rotating propellers, which may be hinged or foldable in nature. Data captured by sensors of the aerial vehicle may be utilized for any purpose, such as to generate environment maps of an indoor space, or to monitor the indoor space for adverse conditions or events.

Abstract: A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises one or more electromagnets spaced apart and suspended on a frame that may include means for compensating for any out of plane misalignments during capture. The client spacecraft includes a striker plate that covers an area, nominally larger than the footprint of the capture mechanism, that is sized to accommodate a capture envelope determined by the rendezvous and proximity sensing systems. The electromagnets attract the striker plate to capture the client spacecraft in order to provide on-orbit servicing. The docking system has multiple degrees of freedom that are independent of the capture system; docking is accomplished by mechanically coupling the two spacecrafts together, post capture.

Abstract: An aircraft includes a fuselage and a primary airfoil having a first upper surface. The first upper snake has a recess disposed therein. A conduit is in fluid communication with recess. An ejector is disposed within the recess. The ejector is configured to receive compressed air via the conduit. The ejector is further configured to produce a propulsive efflux stream. A secondary airfoil is coupled to the primary airfoil and has a second upper surface. The ejector is positioned such that the efflux stream flows over the second surface. The second surface is oriented so as to entrain the efflux stream to flow in a direction substantially perpendicular to the first upper surface.