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WO/2024/080006A1 |
Provided is a system comprising: a plurality of switching units connected in parallel with a bus to which power generation units and loads are connected and each switching between connection and disconnection of battery packs to and from...
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WO/2024/080060A1 |
A control device (60) controls flight of an eVTOL comprising: rotating blades (13) which are driven by a drive apparatus (15) and which generate a rotational lifting force; a fixed blade for generating a glide lifting force; and a liftin...
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WO/2024/080181A1 |
Provided is a transmission device for an unmanned aerial vehicle, wherein arms that drive propellers can be positioned so as not to interfere with an air cleaner and a radiator. A transmission device for an unmanned aerial vehicle in w...
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WO/2024/077668A1 |
The present invention relates to the technical field of unmanned aerial vehicles. Disclosed are a variable topdressing device based on a six-rotor multispectral unmanned aerial vehicle and a use method therefor. The device comprises: an ...
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WO/2024/081443A1 |
An apparatus for an inertial separation of air in an electric aircraft, wherein the apparatus includes an intake duct configured to intake an airflow, an inertial air separator configured to separate the airflow into a clean airflow and ...
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WO/2024/077308A1 |
A VTOL aircraft includes a plurality of lift propellers configured to rotated by lift motors to provide vertical thrust during takeoff, landing and hovering operations. The lift propellers are configured to generate a cooling airflow to ...
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WO/2024/076966A1 |
A system for an aircraft includes a tiltable proprotor that is tiltable between a lift position for providing lift for the aircraft and a forward flight position for providing forward propulsion for the aircraft is provided. The system i...
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WO/2024/077213A1 |
In one embodiment, an electrical propulsion system includes an electrical motor configured to drive one or more propellers of the aircraft, a capacitor configured to stabilize a direct current (DC) bus voltage, a first inverter circuit c...
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WO/2024/077280A1 |
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 su...
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WO/2024/076965A1 |
A system includes a first frame for mounting to the aircraft; a second frame for mounting the proprotor, the second frame being rotatably mounted to the first frame; a first gear located along the rotation axis of the second frame and fi...
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WO/2024/077260A1 |
A tilt propeller for a vertical takeoff and landing (VTOL) aircraft includes a tilt actuation assembly for moving a tilt propeller between a lift configuration and a cruise configuration. The tilt actuation assembly may comprise multiple...
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WO/2024/077248A1 |
An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed ci...
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WO/2024/069095A1 |
Device (210) for measuring a rotational speed of an aircraft propeller (211), comprising: - an optical speed sensor (220); - an optical fiber (230) connected to the optical speed sensor and intended to be connected to a control unit of t...
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WO/2024/063791A1 |
Described is a fan assembly for an electrical aircraft motor having an axial fan with an inner hub of a first diameter and an outer hub of a second diameter. The outer hub may be concentrically aligned with the inner hub. A plurality of ...
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WO/2024/060585A1 |
The present invention relates to a wing system integrated with a power battery module. The wing system comprises: a wing box, the wing box comprising a plurality of wing support members, and the plurality of wing support members being co...
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WO/2024/062928A1 |
The present technology relates to an unmanned aircraft and a propeller in which it is possible to improve stability in a state in which a foldable unmanned aircraft propeller is opened. This unmanned aircraft comprises a propeller and a ...
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WO/2024/060567A1 |
An integrated electric propulsion system for electric aircrafts. A distributed electric propulsion system and a fly-by-wire flight control actuation system which are integrated on aircraft wings can be unified, thereby providing for the ...
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WO/2024/060633A1 |
An aircraft wing (10) having an integrated distributed ducted fan, the aircraft wing (10) being attached to a fuselage (20) and being provided with a ducted fan power set (30), wherein the ducted fan power set (30) is provided on an inbo...
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WO/2024/064270A1 |
An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that ...
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WO/2024/058566A1 |
The present invention relates to a way to prevent the deterioration of batteries in drones, and in particular, provides a power distribution circuit for preventing the deterioration of a battery due to an instantaneous high output power ...
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WO/2024/058619A1 |
The present invention relates to an airship capable of easily switching directions, the airship comprising an aerial vehicle (mother ship) formed in a disc or polygonal shape provided with a jet engine, a rotating body having a jet engin...
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WO/2024/059181A1 |
Systems and methods relate to a vehicle, such as a vertical takeoff and landing (VTOL) platform, which can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotate...
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WO/2024/058565A1 |
The present invention relates to a method for preventing drone battery degradation, and in particular, provides: an apparatus for preventing battery degradation caused by a momentary high output exceeding the rating of the battery, where...
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WO/2024/055900A1 |
The present invention relates to the technical field of unmanned aerial vehicles, and provides a battery management system having a plurality of backup communication main units, and an aircraft. In the battery management system provided ...
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WO/2024/056549A1 |
The present invention relates to a system (10; 20; 30) for reconfiguring power distribution in an aircraft, the system comprises at least two propulsion units (3), at least two energy storage units (13) and an interconnecting network (15...
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WO/2024/056929A1 |
The present invention relates to a smart device (100) for supplying ammonia and hydrogen for mixed combustion in aircraft, as shown in Figure 1, for propulsion. The smart device comprises a subassembly (120) that stores ammonia and suppl...
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WO/2024/053375A1 |
Provided are a flight device and a method for controlling the same, by which it is possible to accurately measure the power remaining in a battery with a simple configuration. A flight device 10 is provided with a rotor 11, a motor 12,...
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WO/2024/052190A1 |
During the transition of a vertical take-off and landing (VTOL) aircraft (1) from hover flight to cruise flight and vice versa, a method for controlling this transition is configured to push propulsion units (2) of the VTOL aircraft (1) ...
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WO/2024/048342A1 |
This EPU (50) has a motor device (60), an inverter device (80), a unit housing (101), and a cooling device (800). The motor device (60) has a motor (61) and a motor housing (70). The inverter device (80) has an inverter (81) and an inver...
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WO/2024/046050A1 |
Disclosed in the present invention are a device power source system of an aircraft, and an aircraft. The system comprises: a first power manage unit (PMU), a second PMU, a third PMU and a power control unit (PCU), which are connected to ...
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WO/2024/043092A1 |
A malfunction indicator diagnosing device (20) diagnoses a malfunction indicator of a battery (106) provided to an eVTOL (100). The malfunction indicator diagnosis device (20) comprises: a malfunction indicator determination unit (23); a...
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WO/2024/042293A1 |
The present application relates to a blade (3) of a static vane assembly (2) of a turbine engine (1) comprising: - a blade root (8) comprising a fibrous reinforcer (13) comprising a first skin (12) and a second skin (12) separated by a c...
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WO/2024/043093A1 |
This prediction device (20) predicts the required performance and/or state of a battery, which is a driving apparatus installed in an eVTOL. The prediction device (20) comprises: an acquisition unit (21) that acquires information includi...
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WO/2024/038189A1 |
The present invention relates to a system (40) for redistributing power in an aircraft with at least two electrical powertrain units (10), each powertrain unit (10) comprises a propulsion unit (15) powered by an energy storage unit (13);...
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WO/2024/038634A1 |
Provided is a flight method that makes it possible to prevent a collision of a drone and entanglement of a power supply cable. This flight control system relating to flight control of an electrically driven drone 3 that is connected to a...
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WO/2024/035711A1 |
An aircraft indudes a fuselage, a forward wing assembly, a mid-body wing assembly, and an aft wing assembly, and a hybrid propulsion system. The hybrid propulsion system includes a plurality of primary thrust assemblies and a plurality o...
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WO/2024/032907A1 |
An electric vertical take-off and landing aircraft comprises a fuselage (1) and a tilt wing (7). The tilt wing (7) is tiltable relative to the fuselage (1) in a range of tilt wing angles. Control surfaces (13) are arranged at the tilt wi...
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WO/2024/033589A1 |
The invention relates to an electrical system (100) having: - an electric circuit (102) having a electrically insulating flat support (104) and two electric conductors (106, 108) secured to the flat support, the two electric conductors (...
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WO/2024/028671A1 |
Aircraft (1) capable of hovering comprising a fuselage (2), at least one rotor (3a, 3b, 4) that is rotatable with respect to the fuselage (2), electrical drive means adapted to rotate the rotor (3a, 3b, 4) and electrically powered by a b...
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WO/2024/023462A1 |
The invention relates to a method for monitoring a propulsion system (102) of an aircraft (100), comprising: - computing a margin of a parameter (NG, T4x) of a thermal chain (TH), this margin being taken as margin (PMD1, PMT1) of the the...
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WO/2024/023316A1 |
The invention relates to a thermal management system (1, 1a, 1b, 41, 51, 61) comprising a fluid cooling circuit (2) comprising a cooling channel (3) in a thermal load (4), a cooling pump (5) arranged to circulate cooling fluid inside the...
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WO/2024/022556A1 |
The present invention relates to a propulsion system (1) for an aircraft (50), having a first propulsion unit (11) which has a first power generator (21) for outputting a first electric power (P1) and a first thrust unit (31) connected t...
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WO/2024/023305A1 |
The present invention relates to an energy distribution system (20) for an aircraft with at least two electrical powertrain units, each comprising a propulsion unit (1) powered by energy storage units (13) each configured to supply a fir...
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WO/2024/018392A1 |
A rotorcraft type UAV drone comprises a main body (1) which supports at least one rotor (2, 4) with blades (6) and at least one compressor (18, 20), integrated with each other and operated by the same driving force (10, 12), to generate ...
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WO/2024/018988A1 |
This aircraft hybrid motive power source system is installed in an aircraft and comprises: a gas turbine engine (20) that includes a low-pressure shaft (27) and a high-pressure shaft (28) as rotating shafts; a first electric generator (3...
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WO/2024/018459A1 |
The present disclosure provides a thrusting assembly for mounting on an aerial platform and configured for generating thrusting power to allow a controllable accelerated air mass flow in and out the thrusting assembly. The thrusting asse...
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WO/2024/020222A1 |
A system for an electrically powered aircraft can comprise: a truss configured to couple to a structure of an aircraft; a battery system supported by the truss, the battery system including a first array of battery modules and a second a...
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WO/2023/229790A9 |
In an aspect this disclosure is directed at a propulsor assembly powered by a dual motor system. The aircraft may comprise a propulsors. The electric aircraft may also include a driveshaft that is mechanically coupled to the propulsor, w...
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WO/2024/020423A1 |
A hydrogen boiloff capture system. The hydrogen boiloff capture system having a cryogenic tank for storing liquid hydrogen. The hydrogen boiloff capture system also includes an intermediate tank fluidically coupled with the cryogenic tan...
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WO/2024/014135A1 |
[Problem] To rapidly return an aerial vehicle to normal after a sudden change in position thereof due to a disturbance. [Solution] This position control device is provided to an aerial vehicle 30 that produces thrust corresponding to a c...
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