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WO/2024/095853A1 |
In the present invention, an air conditioning control unit acquires vehicle internal environment information, vehicle external environment information, and flight information via steps S101-S103 of an air conditioning control process. Th...
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WO/2024/094949A1 |
Aeronautical thruster (40) having a longitudinal axis (X) and comprising an upstream rotor row and a downstream stator row (16) having unducted blades (18). Two adjacent blades of the downstream stator row (16) have between them, about t...
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WO/2024/094352A1 |
Disclosed is an aircraft power system (800) comprising a hydraulic reservoir (801, 803), a bidirectional hydraulic pump (212) for pumping hydraulic fluid to and from the reservoir, and an electric motor (230), wherein the hydraulic pump ...
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WO/2024/094948A1 |
Aeronautical thruster (40) having a longitudinal axis (X) and comprising an upstream rotor row and a downstream stator row (16) having unducted blades (18). Two adjacent blades of the downstream stator row (16) have between them, about t...
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WO/2024/094351A1 |
Disclosed is an aircraft power system 800 comprising a first driveable component 120, 130 of the aircraft, and a mechanical flywheel 250, wherein the mechanical flywheel is connectable to the first driveable component such that the mecha...
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WO/2024/095581A1 |
Propulsion　systems,　methods　and　aircraft　relatedã€
€to　boundary　layer　ingestion　are　described.　Inã€
€some　embodiments,　an　aircraft　may　include　a　f
uselage　with　a　plurality　of　boundary　layer...
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WO/2024/096879A1 |
A gas turbine engine including a turbomachine. The turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine including an inlet duct defining an engine inlet,...
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WO/2024/088901A1 |
A system (1) for an aircraft (2, 2') comprises: an electric machine (10) which defines an axis of rotation (D), and an even number of elements (11) which each have a housing (110) and are arranged in pairs on opposite sides of the axis o...
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WO/2024/089375A1 |
The invention relates to a pitch-change mechanism (70), which comprises a frame (72), a control actuator (74) including a stationary portion (100) rigidly connected to the frame (72) and a movable portion (102) translatable along a longi...
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WO/2024/090524A1 |
This hybrid rotor drive system comprises: a gas turbine engine which includes a compressor, a combustor, a turbine, and a first output shaft mechanically connecting the compressor to the turbine; an electric motor including a second outp...
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WO/2024/089376A1 |
The invention relates to a pitch-change mechanism (70), which comprises a frame (72), an actuating cylinder (74), and a locking device (160). The actuating cylinder (74) comprises a cylinder block (104) and a piston (106), of which one i...
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WO/2024/089377A1 |
The invention relates to a pitch-change mechanism (70), which comprises a frame (72) and an actuating cylinder (74) including a movable portion (102) that is translatable relative to the frame (72). The mechanism also comprises a connect...
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WO/2024/089670A1 |
A frame device (100) for a propulsion unit (200a…200n) of a flight device (300), comprises annular elements (10a…10n) for a fixation of a fuel tank (210) of the propulsion unit (200a…200n), a retaining element (60) being arranged b...
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WO/2024/088472A1 |
The invention relates to an aircraft (1) having a fuel-cell propulsion system (2), wherein the fuel-cell propulsion system (2) comprises - a fuel cell (3) for supplying electricity to an electric propulsion apparatus (4) of the aircraft ...
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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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