Abstract: A bicycle front shifting system includes operable to transmit a wireless signal, a crank assembly with two crank arms and a pedal on each of the two crank arms. The crank assembly is rotatable about a rotation axis. A front shift unit is coupled to the crank assembly and is rotatable about the rotation axis. The front shift unit includes a chain ring component with a big chain ring and a small chain ring. The small chain ring has a small diameter and the big chain ring has a big diameter that is larger than the small diameter. A shift mechanism is coupled to and rotatable with the chain ring component about the rotation axis. The shift mechanism is configured to receive the wireless signal from the shifter and to shift a chain between the big chain ring and the small chain ring according to the wireless signal.

Abstract: A cavitation load-reduction device for an underwater vehicle has adjustable water-entry angles. It contains a cavitator disposed at a head end of an underwater vehicle, a front end of the cavitator being detachably connected to a head fairing device that is coaxially arranged with the cavitator. The head fairing device comprises a head fairing, a plurality of notches are arranged in a rear end of a side wall of the head fairing around an axis of the head fairing, fairing tiles hinged to the notches are arranged at the notches, and the fairing tiles are matched with the notches. Each fairing tile retractable arm is separately hinged to the fairing tile and the cavitator, and the fairing tile retractable arms are used to drive the fairing tiles to rotate around a hinge point of the fairing tiles and the head fairing.

Abstract: An automatically-separable suction anchor system including a plurality of pumps is disclosed. The system includes an opening/closing unit including a blocking plate provided at a suction pile while having a through hole and pull-up brackets, and a valve member to cause the interior of the suction pile to selectively communicate with an exterior of the suction pile, a suction device including an operation-supporting tubular body with a suction hole and a pressing opening/closing part configured to enable the suction hole to communicate with the suction pile, a frame including clamps to be selectively coupled to the pull-up brackets, and first and second supports, and an operating pump coupled to the operation-supporting tubular body, the operating pump including a first pump of high capacity and a second pump of high head configured to penetrate the suction pile, and a third pump configured to draw the suction pile, and a control module.

Abstract: Mechanical joints and processes for using same. The mechanical joint can include a gimbal table that can define a first and second bearing surface and include a first and second trunnion extending from a pair of opposing sides. The arm can include a third and fourth trunnion disposed toward a second end thereof. The third and fourth trunnion can be aligned along a first axis and the first and second trunnion can be aligned along a second axis. The first and second axes can be substantially orthogonal or substantially perpendicular to one another. The third trunnion and the first bearing surface and the fourth trunnion and the second bearing surface, respectively, can be engaged with one another. The arm can be rotatable relative to the gimbal table about the first axis, and at least a portion of the arm can be disposed through an aperture defined by the gimbal table.

Abstract: Systems and processes for recovering condensate from a conduit. The system can include a buoy that can include a fluid swivel assembly. The system can also include a first surface conduit and first and second gas transfer conduits that can be in fluid communication with the fluid swivel assembly and configured to transfer a gas discharged from a vessel storage tank to a gas pipeline. The system can also include first and second liquid transfer conduits in fluid communication with the fluid swivel assembly and configured to transfer a liquid from a liquid pipeline to the vessel storage tank. The system can also include a condensation conduit configured to transfer at least a portion of any condensate that accumulates within an internal volume of the first surface conduit or the first gas conduit into a fluid flow path defined by the fluid swivel assembly or the second liquid transfer conduit.

Abstract: The present disclosure relates to methods, apparatuses, and systems for a compact, low-cost drift buoy for use in a variety of applications. An example includes a drift buoy including a body defining a payload cavity; a float; and a controller, where the controller is configured to cause the drift buoy to release a payload when one or more predetermined conditions are satisfied. According to some embodiments, the controller is configured to establish a location of the drift buoy. According to certain embodiments, the one or more predetermined conditions include a location condition, where in response to the location of the drift buoy being within a target location, the controller causes the drift buoy to release the payload from the payload cavity.

Abstract: A supporting arrangement for a carried load, more particularly a load carried on a ship such as, for example, a container, is provided. The supporting arrangement provides for connecting, in a non-rigid manner, the carried load to a bearing structure integral with the ship and to this aim it comprises a plurality of movement dampers interposed between the carried load and the bearing structure. The dampers can be directly interposed between the load and the bearing structure; alternatively, the supporting arrangement further comprises a supporting frame and the movement dampers are applied to the supporting frame. Owing to the fact that the carried load is not rigidly connected to the structure of the ship, the movements to which the ship is subjected during sea travel, especially because of wave movement, are not transmitted to the carried load, which therefore does not risk falling overboard.

Abstract: Example systems and methods are provided herein for controlling a watercraft in response to a bite on a fishing line. A system includes a memory and a processor, and the processor is configured to receive data via user input or one or more sensors to determine whether a fish has bitten on a fishing line. In response to a determination that the fish has bitten on the fishing line, the processor causes the watercraft to operate according to a fish-on operation, which includes at least one of altering a speed of the watercraft, altering a direction of the watercraft, altering a rate of change of the speed of the watercraft, altering a direction of a trolling motor, notifying other watercrafts, or engaging an autopilot to navigate the watercraft according to a preset route. The fish-on operation is designed to aid a user in catching the fish.

Abstract: A gyroscopic boat roll stabilizer for a boat comprises a gimbal, having a gimbal axis, an enclosure mounted to the gimbal and configured to precess about a gimbal axis, a flywheel assembly rotatably mounted inside the enclosure for generating a torque that is applied to counter a rolling motion of the boat, and a braking system for controlling precession of the enclosure.

Abstract: A marine vessel comprising a hull, a control unit, a hydrofoiling arrangement, and a motion sensor system. The motion sensor system includes a radar transceiver control unit and at least one radar transceiver arranged to transmit a radar signal in a boresight direction pointing at the sea surface, where the radar transceiver control unit is arranged to determine at least a current heave of the hull relative to the water surface based on radar backscatter from the sea surface. The control unit is arranged to control the hydrofoiling arrangement to reduce a difference between the current heave of the hull and a desired heave of the hull.

Abstract: A method of estimating a sea state, in particular wave spectrum, a offshore wind turbine has been subjected to includes: measuring a response quantity responding to the sea state, using at least one sensor associated with the offshore wind turbine; processing the response quantity to derive a measured response spectrum; deriving a calculated response spectrum based on a previously estimated wave spectrum; deriving an error between the measured response spectrum and the calculated response spectrum; adjusting the previously estimated wave spectrum based on the error, in order to derive an adjusted estimated wave spectrum.

Abstract: A rebreather (1) has at least the following components: a control unit (10), a low pressure system (77) with a breathing bag (3), a low pressure sensor (41), a valve arrangement (7), a hose line system (17), a breathing circuit (15), a mouthpiece (19), a CO2 absorber (13), a high pressure system (79) with a compressed gas supply (5), a pressure reducer (34), and a high pressure sensor (43). The control unit (10) is configured to carry out a procedure for checking the low-pressure system (77).

Abstract: A breathable mask is provided, which includes a body and a breathing tube in fluid communication with an interior thereof. The body includes a main frame, a lens, a waterproof skirt, a multi-channel connector, and intake and exhaust passages. The waterproof skirt has a partition dividing the interior of the body into upper and lower chambers, thereby accommodating the user's eyes and nose in the upper and lower chambers, respectively. The multi-channel connector has an upper end in fluid communication with the lower chamber. The intake passage is formed between the lower end portion of the breathing tube and the lower chamber. The exhaust passage is arranged upward along a periphery of the body to allow dirty air exhaled from the user to unidirectionally flow outward through the exhaust passage. The exhaust passage includes an exhaust tube with a bottom portion coupled to and communicating with the multi-channel connector.

Abstract: The present disclosure relates to the technical field of autonomous underwater vehicles, in particular to an unmanned cable-free operation type autonomous underwater vehicle. The unmanned cable-free operation type autonomous underwater vehicle includes a bow, a middle and a stern, each of the bow, the middle and the stern is of a hollow structure, the middle is provided with a manipulator lifting device and a cabin door opening and closing mechanism, the bow is provided with a first horizontal channel propeller and a first vertical channel propeller, and the stern is provided with two second vertical channel propellers and four main propellers. High-speed cruising of the unmanned cable-free operation type autonomous underwater vehicle can be achieved, and stable and precise hovering needed by the operation of the unmanned cable-free operation type autonomous underwater vehicle can also be achieved.

Abstract: According to the present invention there is provided an underwater vessel comprising: a body; a thruster operable to produce thrust, wherein the thruster is deployable from the body; an actuator assembly connected to the thruster and operable to deploy the thruster, wherein the actuator assembly is operable to deploy the thruster in a first configuration in which the thruster is oriented to produce a thrust having a vertical component when the thruster is operated.

Abstract: The ballast tank (65) is a cylindrical pressure chamber (86) with an end cap (81) that has a central opening for receiving and connecting to the venting input (67) from the pump system (66) and the venting path (68) to the outlet (70) that vents with the outside environment to the submersible. The ballast tank includes a rubber bladder (85) within the solid pressure chamber (86) that is fed by a manifold (83) leading from the end cap (81) opening and feeds through spaced holes into the bladder at spaced distances. This ensures a constant pressure buildup or release of the whole bladder rather than distorted expansion or reduction. Generally, pumps are notorious for being strong in one direction but not in the other. Further there is substantial weight and size limitation in submersibles of the size of less than 5 meters. A novel solution to this problem is to use a one-way pump with a switching valve system.

Abstract: A drive unit for propulsion and trim control of a marine vessel. The drive unit extends in use from the vessel along a vertical axis to a base plane normal to the vertical axis, and spanned by orthogonal longitudinal and lateral axes. The drive unit includes a first propulsion unit and a second propulsion unit arranged separated along the lateral axis and intersected by the base plane. The first propulsion unit and the second propulsion unit are jointly rotatable about the vertical axis, where the first propulsion unit and the second propulsion unit are individually rotatable about the lateral axis.

Abstract: This disclosure relates generally to controlling movement of at least one steering device on a watercraft.

Abstract: Resilient elongated tubular seals that are flexible and that comprise selected geometric cross-sections and that can absorb compressive forces to seal gaps between adjacently positioned aircraft cabin structure and that can further expand outwardly as compressive forces change or abate and methods of installation of such tubular seals are disclosed.

Abstract: A door assembly for an aircraft includes a door, a door hinge, and a support assembly rotatably mounting the door hinge to the door. The support assembly includes a forearm and at least one link. The forearm is rotatably mounted to the door hinge along a first rotational axis. The forearm extends along the first rotational axis between and to an upper end and a lower end. The at least one link extends between and to an inner end and an outer end. The at least one link is rotatably mounted to the forearm at the inner end. The at least one link is rotatable relative to the forearm about a second rotational axis. The at least one link is rotatably mounted to the door at the outer end. The at least one link is rotatable about the second rotational axis between and to a lowered position of the door and a raised position of the door.

Abstract: A door assembly for an aircraft includes a door, an interior door handle and an exterior door handle, and a clutch assembly. The interior door handle and the exterior door handle are rotatable about a door handle rotational axis. The clutch assembly includes a shaft, an exterior coupling body, an exterior handle body, and a clutch lever. The shaft includes an interface portion. The interface portion includes a handle tooth. The exterior coupling body includes a fixed body portion disposed adjacent the interface portion. The exterior handle body is rotatably mounted to the exterior coupling body. The exterior handle body is rotatable between and to an engaged position and a disengaged position. The clutch lever is rotatably mounted to the exterior coupling body. The clutch lever is pivotable between and to an engaged pivot position and a disengaged pivot position. In the engaged pivot position, the handle tooth is positioned circumferentially between the clutch lever and the fixed body portion.

Abstract: A leading-edge high-lift device according to an embodiment of the present invention is a leading-edge high-lift device that is deployable and retractable from/into a fixed leading edge of a main wing of an aircraft and includes: a leading edge portion; a trailing edge portion that forms a gap between a trailing edge portion and the main wing during deployment; a cusp portion formed at a lower edge of the leading edge portion; a lower surface portion formed between the cusp portion and the trailing edge portion; and a curved hump portion that is locally provided on a surface of the lower surface portion and protrudes toward the main wing in a cross-sectional shape perpendicular to a wing span direction of the main wing.

Abstract: A power system for an aircraft includes at least one power distribution unit. The at least one power distribution unit includes at least one input configured to receive electrical power from at least one energy source, and at least one output configured to provide electrical power from the at least one input to at least one electrical load. The at least one power distribution unit also includes a control system configured to detect a condition, and to perform an action based on the detected condition.

Abstract: Shaft connection (1) having a first shaft (5) which is rotatable about an axis of rotation (3), a second shaft (7) which is arranged coaxially with the first shaft (5) and which is movable axially relative to the first shaft (5), and at least one spring element pair (9), in each case having a first spring element (11) and a second spring element (13), wherein the first spring element (11) and the second spring element (13) are each fastened to the first shaft (5) and to the second shaft (7), and wherein the first spring element (11) and the second spring element (13) are arranged axially offset relative to one another.

Abstract: This aircraft flight compensator control system comprises a motor (3) and a variable-friction actuator (6) coupled with the motor and with an output shaft (8).

Abstract: Flow control ducted fans are disclosed. A disclosed example flow control apparatus for use with an aircraft includes a duct defining an inner cavity with a primary flow path, a fan disposed in the inner cavity, an aperture on an exterior surface of the duct and upstream from the fan, the aperture fluidly coupled to the inner cavity to define a secondary flow path, and a door to control a degree to which the aperture is opened.

Abstract: Aspects related to aircraft for commercial air travel and methods of manufacture. An aircraft includes a blended wing body, a single deck located within the blended wing body, wherein the single deck additionally includes a passenger compartment located in a lateral middle portion of the blended wing body and at least a cargo store located laterally outside the passenger compartment, and a landing gear, wherein the landing gear includes at least a nose gear located substantially forward of the single deck and at least a main gear located substantially aft of the single deck, wherein one or more of the at least a nose gear and the at least a main gear occupies a gear housing that overlaps with a plane coincident with at least a portion of the single deck.

Abstract: An aircraft includes a ground maneuver control system that automatically steers a nose landing gear wheel to compensate for asymmetrical braking of the wheels of the aircraft resulting from a failure on one side in comparison to the other. A control system detects such a failure in order to be able to effect such automatic steering. The system may be retrofitted by the installation of software on an existing aircraft, having a braking and steering computer system with a pre-existing steering control functional block and a pre-existing braking control functional block.

Abstract: A compound helicopter includes a fuselage including a fuselage airframe, a translational thrust system coupled to the fuselage airframe and a pylon assembly subject to vibration. The pylon assembly includes a transmission and a rotor system having a main rotor assembly. The compound helicopter also includes a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency. Each augmented liquid inertia vibration eliminator unit includes at least one active tuning element movable to tune the isolation frequency thereof.

Abstract: A rotor system for an aircraft includes a rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The aerial vehicle may have rear mounted rotors adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may be powered with electric motors.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle may have deployment mechanisms which deploy electric motor driven propellers from a forward facing to a vertical orientation. The aerial vehicle may be powered with electric motors.

Abstract: An electric fan includes a boss part; an outer peripheral part around the boss part; a rotor blade between the boss part and the outer peripheral part and rotatably supported about the boss part; a drive unit on the outer peripheral part to rotate the rotor blade; and a stator vane on a downstream side of the rotor blade in a flowing direction of fluid between the boss part and the outer peripheral part. The stator vane includes main bodies spaced apart in a peripheral direction, and one of the main bodies that is in a region where an obstacle is disposed on a radially outside is provided with a guide part that guides fluid to an inner diameter side, on a leading edge part on an upstream side in the flowing direction of fluid or an end portion on a suction surface side, on the inner diameter side.

Abstract: Vertical take-off aircraft provided with canards (1) and primary wings (2), which primary wings (2) are provided with two or more primary thrusters (20). The primary wings (2) are rotatable alternately in a vertical configuration for vertical flight mode and in a horizontal configuration for horizontal flight mode. The canards (1) in said vertical flight mode are arranged substantially parallel to a plane perpendicular to the flight direction, each canard (1) being provided with a secondary thruster (10) oriented for vertical flight mode and at least partially comprised in the profile of the canard (1) itself.

Abstract: Embodiments provide mechanisms for coupling rotor blade pitch to propulsion system tilt angle in an aircraft, and more specifically in electric aircrafts. A system may include a tiltable propulsion system configured to move between a first tilt angle and a second tilt angle, wherein the tiltable propulsion system includes a plurality of rotor blades each configured to move between a first pitch position and a second pitch position; a tilting mechanism coupled to the tiltable propulsion system and configured to move the tiltable propulsion system between the first tilt angle and the second tilt angle; a pitching mechanism coupled to one or more of the plurality of rotor blades and configured to move one or more of the plurality of rotor blades between the first pitch position and the second pitch position; and an actuator configured to operate both the tilting mechanism and the pitching mechanism simultaneously.

Abstract: A VTOL aircraft comprising a plurality of motor assemblies, each configured to generate thrust by movement of air past the motor assembly along a respective axis of thrust of the motor assembly, and a wing, wherein 1) the orientations of the axes of thrust are each fixed, during operation of the aircraft, at a constant respective pitch angle oblique to a pitch orientation of the wing; 2) the plurality of motor assemblies is operable together to both fully support the aircraft in a hovering mode, and to propel the aircraft forward in a forward flight mode; 3) the wing does not intersect with any right cylinder centered on any motor assembly and having a central longitudinal axis aligned with the axis of thrust of the motor assembly, and having a radius equal to a radius of a propeller of the motor assembly.

Abstract: Physical and logical components of a long line loiter control system address control of a long line loiter maneuver conducted beneath a carrier, such as a fixed-wing aircraft. Control may comprise identifying, predicting, and reacting to estimated states and predicted states of the carrier, a suspended load control system, and a long line. Identifying, predicting, and reacting to estimated states and predicted states may comprise determining characteristics of state conditions over time as well as response time between state conditions. Reacting may comprise controlling a hoist of the carrier, controlling thrusters of the suspended load control system, and or controlling or issuing flight control instructions to the carrier so as not to increase the response time and or to avoid a hazard.

Abstract: In various embodiments, specialized vehicle launch systems and methods are provided to enable personnel to launch and operate one or more UAVs from the safety of a vehicle or other mobile location. In various embodiments, a launch system comprises a launch device and an operator terminal. The launch device is adapted to be mounted on an exterior surface of a vehicle and is communicably coupled to the operator terminal, which is operable from the interior of the vehicle. The vehicle launch system allows an operator to control one or more UAVs from inside the vehicle, without requiring the operator to step outside of the vehicle to interact with the UAV or launch device.

Abstract: Embodiments of the present invention relate to a method for generating search information of an unmanned aerial vehicle (UAV) and a UAV. The method includes: controlling a gimbal camera apparatus of the UAV to perform surround shooting to obtain character image information when the UAV is in an input locked state; matching the character image information with internal image information of the UAV; and generating the search information of the UAV according to a matching result. Therefore, a user can find the UAV in time according to the search information. In this way, theft is prevented, reducing the user loss.

Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft. The blended wing body aircraft also includes a plurality of transparent panels located in the top surface of the main body, wherein the plurality of transparent panels are located in channels, wherein the plurality of transparent panels allow the transmission of visible light.

Abstract: An enclosed space, such as a lavatory within an internal cabin of a vehicle, includes one or both of: (a) a toilet moveably secured to one or both of a floor or one or more walls, wherein the toilet is configured to be moved between a toilet deployed position and a toilet retracted position, and/or (b) a sink moveably secured to one or both of the floor or the one or more walls, wherein the sink is configured to be moved between a sink deployed position and a sink retracted position.

Abstract: The invention relates to a seat unit including a seat, at least one surrounding element associated with the seat, and a noise attenuation panel fixed to one face of the surrounding element. The noise attenuation panel can include a soft trim cover, and a support plate comprising at least one sound-permeable portion provided with at least one through hole. The support plate can be arranged such that there is an empty space between said sound-permeable portion and the face of the surrounding element of the seat.

Abstract: A gasper assembly for use in a passenger aircraft. The gasper assembly includes an inlet comprising a socket configured to receive intake air; and an outlet comprising a body mounted in the socket that is manually adjustable to direct a stream of airflow received via the inlet in a first direction and in a second direction. The body is further configured by a first rotation to direct the stream of airflow in the first direction and by a second rotation to direct the stream of airflow in the second direction wherein the first direction is substantially perpendicular to the second direction.

Abstract: A gasper module for use in an aircraft. The gasper module including an inlet configured to receive intake air and a first outlet configured to direct a stream of an airflow from the intake air towards a passenger. Also, a second outlet configured to form an air curtain from the intake air between the passenger receiving the direct stream of airflow and an adjacent passenger.

Abstract: An air aircraft air circulation system including a duct adapter system for mounting an ion generator unit upon the exterior surface of a conduit of an air circulation system to dispose electrodes projecting from the housing of the ion generator into the interior of the conduit, and preferably having material clearance between the electrodes and the housing, between the electrodes the duct adaptor, and between the electrodes and the conduit.

Abstract: A compressing device for use in an environmental control system includes at least one turbine configured to provide energy by expanding one or more mediums. The one or more mediums provided at an outlet of the at least one turbine form a heat sink within the environmental control system. A compressor is configured to receive energy from the one or more mediums expanded across the at least one turbine. During a first mode of the compressing device, energy derived from a first medium and a second medium of the one or more mediums is used to compress a second medium at the compressor. During a second mode of the compressing device, energy derived from the first medium, the second medium, and a third medium of the one or more mediums is used to compress the second medium at the compressor.

Abstract: The present invention reduces a probability of condensation forming in a container for a flying object. Container 12 is a cabin of a gas balloon. Container 12 comprises Main Body 121 that is an airtight container filled with air and accommodating Crew Member H1, and Partition 122 that divides the space in Main Body 121 into Space S1 and Space S2. Partition 122 has one or more narrow Holes H. When the altitude of the flying object increases and Container 12 cools from the outside, air in Space S1 cools more slowly than the air in Space S2. A pressure difference between Space S1 and Space S2 is rapidly equalized by air flow through Holes H, but it takes a long time to equalize a temperature difference between Space S1 and Space S2. Therefore, a temperature in Space S1 becomes higher than a temperature in Space S2, and a temperature in Space S2 becomes higher than a temperature in the space outside Main Body 121.

Abstract: An ice protection system may comprise an electrical heating mat of an electrically resistive material, wherein the electrically resistive material defines at a first spanwise zone and a first chordwise zone, wherein at least one of the first spanwise zone or the first chordwise zone include a first busbar portion contiguous with the electrically resistive material.

Abstract: An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide forward propulsion of the aircraft and a respective electrical machine each configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

Abstract: An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.