Abstract: A rolling type vehicle includes a pair of left and right arm members supported in a swingable manner by a vehicle body on inner sides in the transverse direction for supporting a pair of left and right front wheels in a steerable manner on outer sides in the transverse direction, respectively. A shock absorber support arm of which a central portion in the transverse direction is supported in a swingable manner by the vehicle body and is connected to the pair of left and right arm members through shock absorber units on outer sides in the transverse direction, respectively. The left and right shock absorber units are disposed on outer circumference sides of turning trajectories of the pair of left and right front wheels, respectively.

Abstract: A portable conveyance has a deck, a front drive wheel proximately disposed to a first end of the deck and a rear drive wheel attached proximate to a second end of the deck. A guide roller assembly attached proximate to the rear drive wheel. The guide roller assembly has a first rotational axis and the rear drive wheel rotates about a second rotational axis different from the first rotational axis and parallel to the first rotational axis, such that the guide roller assembly is not in contact with a substantially flat surface when the first and rear drive wheels are in contact with the substantially flat surface, and the guide roller assembly is in rotational contact with the surface when the deck is lifted into a towing position.

Abstract: Provided is an activity monitoring and recording device which may include a smartphone, a pollution sensor, a Global Positioning System (GPS) device, a microprocessor and proprietary software supported to a bicycle.

Abstract: A bicycle fork includes a pair of fork leg assemblies, each of the leg assemblies having an upper leg telescopingly engaged with a lower leg. A damping assembly is provided in at least one of the legs. The damping assembly includes lock-out and blow-off compression circuits. These compression circuits are externally adjustable without tools. Furthermore, these two compression circuits may be adjusted independently of each other.

Abstract: A bicycle rim brake comprises a first brake arm, a second brake arm, and a pivotal cam member. The first brake arm is configured to pivot about a first pivot axis. The first brake arm includes a first mounting portion and a first follower. The second brake arm is configured to pivot about a second pivot axis which is different from the first pivot axis. The second brake arm includes a second mounting portion and a second follower. The pivotal cam member is configured to pivot about a third pivot axis which is different from the first pivot axis and the second pivot axis to guide the first follower and the second follower so that the first brake arm pivots about the first pivot axis and the second brake arm pivots about the second pivot axis.

Abstract: Some embodiments of the present invention disclose a bicycle propulsion system. The propulsion system includes a frame. The propulsion system includes a wheel rotably coupled to the frame. The propulsion system includes a drive wheel for rotating the wheel. The propulsion system has a pedal. The propulsion system includes a crank lever having a proximate end coupled to the frame and a distal end coupled to the pedal. The propulsion system includes a cam rotably coupled to the crank lever between the distal and proximate ends, wherein the cam comprises a pair of connecting members that when connected form a shaft positioned away from a center of the cam. The propulsion system includes a drive lever having a proximate end comprising a cam follower interfaced to the cam and a distal end coupled to the drive wheel.

Abstract: Wheel hub motor (1) for an electric bicycle, comprising: a fixed shaft (2) which can be associated with a frame of an electric bicycle; a hub shell (3) which is rotatable with respect to said fixed shaft (3) and can be incorporated in a wheel structure (100) of said electric bicycle; an electric motor (4) being housed inside said hub shell (3), said motor having an internal stator (40) rigidly connected to the fixed shaft (2) and an external rotor (41) rotatably movable with respect thereto, and a reduction unit (5) which kinematically connects the rotation of said external rotor (41) to that of said hub shell (3) and which comprises two reduction stages arranged alongside each other in the axial direction inside the hub shell (3): a first reduction stage (50) comprising at least one first pinion (51), rigidly connected to the external rotor (41) and coaxial with the fixed shaft (2) and meshing with at least one first gear (52) rigidly connected to an eccentric shaft (53) mounted on an intermediate member; an

Abstract: In the present invention, one or both of an active wheel or a passive wheel is composed of an eccentric transmission wheel and is combined with a synchronous transmission belt for forming an eccentric wheel transmission wheel series, so that when the feet input forces at different angles from the treadle shafts of the treadles to an active wheel shaft combined on the active wheel through cranks, the active wheel forms different transmission speed ratios relative to the passive wheel according to the treadle angle, and random inward packing is performed to the transmission belt (100) of the engage end of the eccentric passive wheel (413) during the transmission for stabling the operation.

Abstract: A semi-submersible offshore platform for operations in a body of water includes a buoyant hull configured to be at least partially submerged in the water. In addition, the platform includes an equipment deck coupled to the hull and configured to be positioned above the water. The hull includes a first vertical column and a second vertical column horizontally spaced from the first vertical column. Each column has a longitudinal axis, an upper end, a lower end, and a tapered section axially positioned between the upper end and the lower end. Further, the hull includes a horizontal pontoon having a longitudinal axis, a first end coupled to the lower end of the first column, and a second end coupled to the lower end of the second column.

Abstract: A universal hydrofoil comprises a hydrofoil assembly, a universal mount assembly and a plurality of lateral connectors. The hydrofoil assembly has a longitudinal axis and includes a centerfoil having first and second longitudinal ends. A foil assembly is disposed at the centerfoil second end and includes a fuselage, a wing at a fuselage first end and a tail at a fuselage second end. The universal mount assembly comprises a base having first and second mounting surfaces. The second mounting surface defines a mounting interface configured to reversibly mate with the centerfoil first end. Lateral supports having a pair of arms projecting from a central beam are selectively engageable with the base. The lateral connectors are adjustably secured within the lateral channel and configured to engage a structural feature of a craft.

Abstract: An anti-piracy device for ships comprises a blocking device, such as a metal plate, to block an opening from the exterior to the interior of a ship, such as a window or porthole. The anti-piracy device also includes mounts, which are mounted permanently to the interior wall of the ship, to which the blocking device can be removably fastened, by nuts or the like. This allows the device to be installed when entering dangerous waters, but removed and stored when traversing safe waters.

Abstract: A canopy assembly for a marine vessel having at least two U-shaped canopy support members each removably coupled to a first side section and a second side section of a marine vessel, a cover coupled to the at least two U-shaped canopy support members, with an upper surface providing a water barrier to, and in an overlapping relationship with, an upper surface of a bow of the marine vessel, spanning from the first and second ends of each of the at least two U-shaped canopy support members, and having a cover zipper assembly with a plurality of teeth. The assembly also includes a track zipper assembly having a plurality of teeth removably interlocked with the plurality of teeth of the cover zipper assembly to form a joint contouring a portion of the marine vessel that includes the first and second side sections and the fore section of the marine vessel.

Abstract: The present invention relates to a monohull offshore drilling vessel comprising a hull with a bow and a stern and a moonpool extending through the hull, the hull having an upper deck. A firing line hoist system comprising a mast is mounted on the hull. A drill floor is provided at a firing line side of the mast, which covers a portion of the moonpool while the firing line extends through an opening in said drill floor. Furthermore marine equipment and drilling equipment for performing auxiliary operations for the drilling or drilling related operations is provided, which equipment is mainly provided in the hull of the vessel below the upper deck. According to the invention, the drill floor is flush with the upper deck.

Abstract: Systems, devices, and methods for providing a swinging system and platform assembly that deploys a swim platform from the front of a pontoon boat which is mounted underneath the deck between the pontoons in a raised position adjacent to the underside of the pontoon deck. The platform assembly, when deployed, provides a safe method for users of pontoon boat vessels to access the front deck area from land or from a body of water. The platform deploys from two pivoting frames affixed to the bottom of the deck, which is powered by an actuator with the push of a button on the control panel. For deployment, the platform is both lowered and extended out from the pontoon boat. A powered actuator positions the platform in the deployed position for use and then retracts the platform for storage.

Abstract: A water vessel is provided. The water vessel includes a hull, a deck, and a ramp. The hull has a front end, an aft end, a starboard side, a port side, a bottom, a bow at the front end, and a stem at the aft end. The bow is movable between a closed configuration and an open configuration. The deck is in the region of the bow. The ramp is located between the bottom of the hull and the deck in a retracted position. When the bow is in the open configuration, the ramp is movable to an extended position in which the ramp extends from the front end of the hull.

Abstract: Disclosed herein are folding tables for use on small boats like kayaks and canoes, including inflatable kayaks. Such tables are secured to the gunwales or topsides of such small boats and have various devices for organizing and securing sportsman's gear for fishing, hunting, photographing and the like. The tables are readily detachable from the boats and foldable for compact storage.

Abstract: An elevated seat for a kayak. A floor of the kayak generally defines a reference plane. The seat may include a first support bar configured to be releasably attached to the kayak at a first location and a second support bar configured to be releasably attached to the kayak at a second location spaced along a bow-stern direction of the kayak relative to the first location. The seat may also include a seating member extending from a distal end of the first support bar to a distal end of the second support bar. The seating member may be inclined at a non-perpendicular angle relative to the floor. When in use, the first and second support bars are configured to position the seating member above the floor by a sufficient distance to support a user substantially standing on the floor.

Abstract: A passively stable personal hydrofoil watercraft that has a flotation device, wherein a user can ride in a prone, kneeling, or standing position. The watercraft includes a strut having an upper end interconnected with the flotation device and lower end connected with a hydrofoil. The hydrofoil greatly reduces the power required to travel at higher speed. The watercraft also includes a propulsion system connected to the hydrofoil. Both longitudinal and directional control of the watercraft is via weight shift, eliminating the need of any movable surfaces. The flotation device, strut, and hydrofoil may be permanently interconnected or may be detachable.

Abstract: A gyroscopic roll stabilizing device for a marine vehicle includes a base communicating with a gyroscopic component which includes a rotor rotatable about an axis, a motor for rotating the rotor about the axis, a swing container swinging about a swing axis and having the rotor communicating thereto, a first support member and a second support member being opposite to the first support member for swingingly supporting the swing container. An actuating member rotates the gyroscopic component about an axis around which the rotor does not swing in its free state.

Abstract: A device comprising a first plate disposed on top of a second plate where the first and second plates are parallel and separated by a fixed distance with a spacer, and wherein the spacer fits around the perimeter of the first and second plates creating a void space, and wherein the second plate has a plurality of pin-sized holes, and wherein a pump sits in the void space and is operably coupled to the plates, wherein the plates are operably coupled to the bottom, exterior hull of an Unmanned Underwater Vehicle (UUV), and wherein the pump is configured to pump liquid into the void space between the parallel plates.

Abstract: A paddle device configured with adjustable paddle-blades at both a first end and a second end is described. The paddle device is equipped with a center padded grip area, which functions as a center extender couple for adapting to conventional oars or paddles in an alternate embodiment described. The paddle device is configured to conjoin two paddles or oars together such to create a larger alternating paddle, configured to effectively expedite the paddling process on paddle boards and other similar small single-paddle, manual craft by eliminating the need to alternate hands while paddling.

Abstract: There is provided an intake apparatus of an engine for an outboard motor. An intake manifold, a throttle body and an intake silencer box are arranged at one of right and left sides of an engine block which is configured such that an axial direction of a cylinder coincides with a front and rear direction of the outboard motor. An intake duct communicating with an intake introduction port provided at an upper part of an engine cover is coupled to an upstream end of the intake silencer box. A first water separation part is arranged between the intake introduction port and the intake duct. A second water separation part is provided below a duct part of the intake duct. The second water separation part is formed by providing a drain hole at a bottom part of a resonator chamber part communicating with the duct part to reduce an intake noise.

Abstract: A vessel propulsion system includes an engine that provides a propulsive force to a vessel, a throttle valve to adjust an air amount supplied to the engine, an accelerator operation unit operated by an operator to adjust a throttle opening degree, the throttle opening degree corresponding to an operation amount of the accelerator operation unit, and a control unit programmed to vary an engine output even when the throttle opening degree is maintained at a fixed value other than an idling opening degree, the engine output corresponding to the operation amount of the accelerator operation unit as a reference output.

Abstract: A method for controlling the hybrid drive system of a water craft, comprising a combustion engine (1), an electric engine/generator (2), a drive train (5) having a propeller (7) and a storage battery (3), a control unit (8) and a clutch (4). In order to increase efficiency, during travel in the upper power range the electric engine (2) is additionally operated as a generator, and during travel in the middle and lower power ranges the electric engine (2) is operated with current from a storage battery (3). The drive train is designed so that the characteristic (20) thereof lies by a defined charging capacity below the point of minimum specific fuel consumption (e.g. 25), or is steeper than the characteristic (16) of a conventional construction.

Abstract: A parallel or redundant hybrid drive of a marine drivetrain of a propulsion unit includes an input shaft, which is configured to be driven by a primary drive source; a clutch unit attached to the input shaft with which rotation of the input shaft can be either connected, reversed, or disconnected; a countershaft transverse to the input shaft and driven by the input shaft via a gear; and a secondary drive source arranged via an interconnected clutch at an end of the countershaft, so that upon driving of the input shaft by the primary drive source, the secondary drive source drives the countershaft either on its own or in cooperation with the primary drive source.

Abstract: A splice assembly may include a first splice bracket including first longitudinal axis, a first connecting member, and a first mating member extending from the first connecting member along the first longitudinal axis, the first mating member including a first mating surface disposed as a non-zero first angle relative to the first longitudinal axis. The disclosed slice assembly may further include a second splice bracket including second longitudinal axis, a second connecting member, and a second mating member extending from the second connecting member along the second longitudinal axis, the second mating member including a second mating surface disposed as a non-zero second angle relative to the second longitudinal axis. The first mating surface and the second mating surface are complementary. Surface contact between the first mating surface and the second mating surface defines a fastening location for connecting the first splice bracket and the second splice bracket.

Abstract: A fuselage cell structure for an aircraft includes at least two skin panels including at least one double shell skin panel and at least one monolithic skin panel. At least one longitudinal brace or a transverse brace is disposed so as to form at least one of longitudinal seam or a transverse seam between the double shell skin panel and the monolithic skin panel. The fuselage cell structure includes at least one of a longitudinal bracket and a load transfer point. The longitudinal bracket is disposed in a region of the longitudinal seam and includes a first and a second longitudinal flanges disposed offset with respect to one another and connected by a web. The load transfer point is disposed in a region of the transverse seam so as to connect the longitudinal brace disposed on the monolithic skin panel to the double shell skin panel.

Abstract: An aircraft window assembly includes a pressure pane. A bezel is proximate a periphery of the pressure pane and defines an inner opening. The bezel includes an inner wall with a channel. An electro-optic element is disposed in the inner opening and is configured for reception in the channel of the inner wall. The electro-optic element is capable of operation between a transmissive condition and a dimmed condition. A dust cover is proximate the bezel. The dust cover includes an interior substrate and an exterior substrate. The interior substrate and the exterior substrate generally define a gap therebetween. A thermally absorbent liquid is disposed in the gap.

Abstract: A windshield mounting assembly, comprising a windshield that is adapted to be arranged on an associated vehicle frame, the windshield comprising at least one edge that is provided with at least one lateral recess; at least one mounting frame that is attached to the windshield and adapted for mounting of the windshield to the associated vehicle frame, the mounting frame comprising at least one fastener receiving opening that is arranged in the region of the lateral recess and adapted to receive an associated frame fastener; and a bonding interface that is arranged at least partially between the edge of the windshield and the mounting frame, the bonding interface attaching the edge to the mounting frame.

Abstract: The invention relates to a unitary floor panel (1) for a means of transportation, comprising a self-supporting plate (2) having a smallest dimension, called the thickness, extending along a first direction of the self-supporting plate (2), and two larger dimensions extending along two directions that are orthogonal to each other and orthogonal to the thickness; the self-supporting plate (2) having two opposite sides, called main sides, that extend substantially parallel to the two orthogonal directions; characterized in that the panel comprises at least one beam (5) securely fastened to the self-supporting plate (2) and having an axis of elongation parallel to at least one first main side of the self-supporting plate (2), each beam (5) being designed to increase the flexural strength of the unitary panel (1) along the axis of elongation of the beam (5).

Abstract: A high-lift device of a flight vehicle includes: a flap main body provided at a trailing edge portion of a main wing of the flight vehicle so as to be extracted from and be retracted in the trailing edge portion and extending in a wing span direction of the main wing; and a vortex suppressing portion provided at a tip end portion of the flap main body in a wing span direction of the flap main body and configured to suppress a vortex rolling up from a lower surface of a tip end portion of the flap main body to an upper surface of the tip end portion.

Abstract: A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle ?PROP from the propeller indexer, and a sensor coupled to the motor and positioned to detect the sensor trigger so that the propeller indexer may be positioned at the propeller offset angle ?PROP from the sensor through rotation of the shaft so that said sensor is proximate to the sensor trigger.

Abstract: A retractable rotor system for an aircraft includes a rotor blade with a leading edge, a trailing edge, and an internal collapsible web. The leading edge includes a flexible portion whose lower edge contacts but is not structurally joined to the lower skin. When the leading edge is peeled forward from the lower skin, the blade elastically collapses to the thickness of its constituent layers. The rotor blade extends through a support frame connectable to the aircraft to secure the rotor blade to a spool. Rotating the spool retracts the rotor blade through the support frame while pulling the rotor blade over a fixed actuating member, placing the rotor blade in the collapsed condition and winding the rotor blade onto the spool. Rotating the spool in the opposite direction unwinds the rotor blade from the spool, through the frame, causing the rotor blade to relax into the expanded condition.

Abstract: A secondary actuation mechanism for arresting movement of a control surface may include a secondary actuator, a drive link coupled to the secondary actuator, and a secondary connecting rod coupled between the drive link and the control surface, wherein the control surface is movable to a default position in response to actuation of the secondary actuator, and the secondary actuator retains the control surface at the default position.

Abstract: Provided are mechanisms and processes for a pneumatic shaft positioning system. According to various examples, the pneumatic shaft positioning system includes a pyrotechnic valve that is configured to control the flow of gas from a pressurized gas source into a pressure chamber. The pressure chamber includes a first piston that is slidably coupled to the pressure chamber. When gas from the pressurized gas source fills the pressure chamber, the piston is configured to slide through the pressure chamber and force a shaft into a predetermined position.

Abstract: For establishment of a laminar attachment line flow, an aircraft wing includes a leading edge including an attachment line, where air impinging on the region flows in a boundary layer spanwise along the leading edge. The leading edge and the attachment line are at least partially formed at first and second slats. The second slat is located adjacent to the first slat in the downstream direction of the attachment line flow, so that the leading edge includes a slat-to-slat junction, where a slat cavity is formed. A duct has a duct entrance at the slat-to-slat junction for receiving spanwise flow along the leading edge of the wing. The duct entrance extends around the leading edge and over the range of positions of the attachment line at the slat-to-slat junction.

Abstract: The present disclosure provides devices and methods related to park brake systems and methods. In various embodiments, a park brake system may comprise a motor shaft having a first diameter portion and a second diameter portion, the second diameter portion having a greater diameter than the first diameter portion. A park brake system may further comprise a spring disposed at least partially around a circumference of the motor shaft, a wire coil disposed at least partially around a circumference of a bobbin, a one-way clutch disposed at least partially within the bobbin and coaxial to the motor shaft, an annular magnet disposed coaxial to the motor shaft and distal to at least a portion of the bobbin, and a clutch release mechanism disposed coaxial to the motor shaft and around the first diameter portion.

Abstract: A helicopter main rotor control system includes a trunnion head mountable to a rotatable helicopter mast wherein the trunnion head has a control bar pivot supported by the trunnion head and pivotal about an axis substantially at a right angle to the helicopter mast. A control bar extends through the control bar pivot at a right angle thereto, and a pair of opposing leaf hinges are pivotal about the control bar and centered about said trunnion head. Each leaf hinge has a hinge plate extending from the control bar and defines a rotor blade mount hole therethrough.

Abstract: An abutment mechanism for limiting the flapping of the blades of a rotor (1). High abutment members (6) can be moved into an engagement position by return means (13) exerting an intrinsic return force (R), and into a disengagement position by a flyweight (10) exerting a centrifugal force (C) under the effect of the rotor (1) rotating. At least one magnetic type bistable latch (15) is in selective engagement with the high abutment members (6). When the rotor (1) is stationary and while it is starting to rotate, an engagement latch (15) engages with the high abutment member (6) to prevent it passing from the engagement position towards the disengagement position. At a predetermined centrifugal force threshold, the engagement of the engagement latch (15) with the high abutment member (6) is broken, and the high abutment member (6) quickly passes into the disengagement position.

Abstract: An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

Abstract: Disclosed is a digital device controlling an unmanned aerial vehicle to provide a flight trajectory feedback based on at least one of an application and a task of the application. The digital device includes a communication unit configured to communicate with an unmanned aerial vehicle, a display unit, and a processor configured to control the communication unit and the display unit. The processor is further configured to transmit application data including information of at least one of an application executed by the digital device and/or a task of the application to the unmanned aerial vehicle through the communication unit. The application data causes the unmanned aerial vehicle to provide a flight trajectory feedback determined based on the application data. The flight trajectory feedback is one of plural predetermined flight trajectory feedbacks and displays at least one of the application and the task pairing with the unmanned aerial vehicle.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a thrusting motor and propeller assembly that is oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, it may be determined if the horizontal airspeed of the UAV exceeds an airspeed threshold. If the horizontal airspeed exceeds the airspeed threshold, the thrusting motor may be engaged and the thrusting propeller will aid in the horizontal propulsion of the UAV.

Abstract: An electrically powered unmanned aircraft system (UAS or drone) including a propeller including a core formed by battery material layers as a power source and integrated as a structural component of the drone. The battery material layers can be a graphene super capacitor or a nanopore battery structure. Power available from the integrated battery material layers can be used to power an electric motor included with the drone and operating to rotate the propeller.

Abstract: A modular potable water distribution manifold for an aircraft water supply and drainage system includes a tubular element with a first manifold quick connector adapted to mate with a flexible hose connector and having a flow control poppet, a second manifold quick connector having a flow control poppet, the second manifold quick connector adapteded mate with a terminating self-venting/self-draining device, and a rotating ferrule that mates the second manifold with the self-venting/self-draining device.

Abstract: The present invention generally relates to passenger aircraft seats. Some examples provide systems for providing side support to seated passengers. Some examples include a passenger seat backrest having an extendable side support. An extendable side support may be integrated with a seat backrest and may be moved between a stowed position and a deployed position. When in a deployed position, the expandable side support may then provide additional side support to a seated passenger's body.

Abstract: Disclosed is a removable seat divider for placement in a seat. The removable seat divider includes a vertical structure configured to be placed on the seat along an approximate center of the seat. The vertical structure includes a first outer surface, second outer surface, top, and back portion, where the back portion of the vertical structure is configured to be placed adjacent to a back portion of the seat. The removable seat divider also includes a cavity located adjacent to the back portion, where the cavity connects the first outer surface to the second outer surface, and the cavity is configured to pass a seat belt through the cavity. The base back portion is configured to produce a restraining force against the seat that is proportional to a tension on the seat belt that passes through the cavity.

Abstract: An article of manufacture, a parachute harness with main risers, configured in vertical flight mode, further comprising a vertical-to-supine upper riser release mechanism integrated into the parachute harness, further comprising a lower cutaway release mechanism integrated into the parachute harness, wherein when the operator is in vertical flight mode and releases the vertical-to-supine upper release mechanism, the parachute harness transitions to supine flight mode is disclosed.

Abstract: A parachute device is provided with a bag containing a main parachute and a reserve parachute and with a propulsion assembly having a frame to which two arms are coupled; the two arms can be opened laterally by operating a control and support respective power units, which can be started by operating a further control.

Abstract: A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.

Abstract: A power plant (1) having two engine groups (10, 20) and a main gearbox (MGB) (2), and a rotary wing aircraft (30) having such a power plant (1). Each engine group (10, 20) drives said MGB (2) mechanically to rotate a main outlet shaft (3) and, consequently, a main rotor (31) of said aircraft (30) at a frequency of rotation NR. A first engine group (10) has two main engines (11, 12) and is by a first setpoint NR* for said frequency of rotation NR, while a second engine group (20) has one secondary engine (21) and is regulated by a second setpoint W1* for power from said second engine group (20). The first engine group (10) is also regulated by a third setpoint W2f* for anticipating power such that said first engine group (10) and said second engine group (20) deliver the power needed at said main rotor (31).