# US 2021/0276723 A1 · Power assembly, power system and unmanned aerial vehicle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2021/0276723 A1 - Document ID: US20210276723A1 - Status: Published application - Kind: A1 - Application number: 17/321,498 - Filed: 2021-05-17 - Published: 2021-09-09 - Earliest claimed: 2018-11-30 - Assignees: Sz Dji Technology Co., Ltd. - Applicants: Sz Dji Technology Co., Ltd. - Inventors: Jiexing HAN - Web page: https://patentgrep.com/patent/US20210276723A1 ## CPC - B64U 50/34: In-flight charging (photovoltaics B64U50/31) - B60L 50/15: with additional electric power supply (with capacitors charged by engine-driven generators B60L50/40; with batteries charged by engine-driven generators B60L50/61) - B60L 50/16: with provision for separate direct mechanical propulsion - B64C 29/0025: {the propellers being fixed relative to the fuselage} - B64D 27/10: of gas-turbine type (jet aircraft B64D27/16) - B64U 10/20: Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) - B64U 50/12: using turbine engines, e.g. turbojets or turbofans - B64U 50/13: using external fans or propellers - B60L 2200/10: Air crafts - B64D 27/026: {comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33)} - B64U 30/10: Wings - B64U 50/19: using electrically powered motors - B64U 2201/00: UAVs characterised by their flight controls - Y02T 10/70: Energy storage systems for electromobility, e.g. batteries - Y02T 10/7072: Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR - B60L: PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES (arrangements or mounting of electrical propulsion units or of plural diverse prime-movers for mutual or common propulsion in vehicles B60K1/00, B60K6/20; arrangements or mounting of electrical gearing in vehicles B60K17/12, B60K17/14; preventing wheel slip by reducing power in rail vehicles B61C15/08; dynamo-electric machines H02K; control or regulation of electric motors H02P); SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES (electric coupling devices combined with mechanical couplings of vehicles B60D1/64; electric heating for vehicles B60H1/00); ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL (control or regulation of electric motors H02P); MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A power assembly, a power system including the power assembly and an unmanned aerial vehicle (UAV) including the power system are disclosed. The power assembly may include an engine, a transmission mechanism, an electrical generator, and a battery. The transmission mechanism may include a first drive shaft and a second drive shaft, both of which may be transmittingly connected to an output shaft of the engine. The first drive shaft may be used to drive a propulsion propeller of the UAV to rotate, and the second drive shaft may be used to drive the electrical generator to generate electricity. The electrical generator may be electrically connected to the battery to charge the battery. The battery may be used to drive rotors of the UAV to rotate. ## Claims ### Claim 1 A power assembly for driving an unmanned aerial vehicle (UAV), comprising: an engine; a transmission mechanism; an electrical generator; and a battery electrically connected to the electrical generator, wherein the transmission mechanism comprises a first drive shaft and a second drive shaft, both of which are transmittingly connected to an output shaft of the engine; the first drive shaft is configured to drive rotation of a propulsion propeller of the UAV; the second drive shaft is configured to drive the electrical generator to generate electricity; the electrical generator is configured to charge the battery; and the battery is configured to supply power to a rotor power mechanism of the UAV that drives rotation of rotors of the UAV. ### Claim 2 (depends on 1) The power assembly of claim 1, wherein the first drive shaft and the second drive shaft start or stop at the same time. ### Claim 3 (depends on 2) The power assembly of claim 2, wherein an operating time range of the second drive shaft is within an operating time range of the first drive shaft. ### Claim 4 (depends on 3) The power assembly of claim 3, further comprising a clutch for controlling a transmission connection state between the output shaft of the engine and the second drive shaft. ### Claim 5 (depends on 1) The power assembly of claim 1, further comprising a first transmission gear train and a second transmission gear train, wherein the first transmission gear train is configured to transmittingly connect the output shaft of the engine to the first drive shaft, and the second transmission gear train is configured to transmittingly connect the output shaft of the engine to the second drive shaft. ### Claim 6 (depends on 5) The power assembly of claim 5, wherein an amount of power output from the engine to the propulsion propeller is greater than an amount of power output from the engine to the electrical generator. ### Claim 7 (depends on 1) The power assembly of claim 1, wherein the first drive shaft extends in a first direction to be transmittingly connected to the propulsion propeller; and the second drive shaft extends in a second direction to be transmittingly connected to the electrical generator. ### Claim 8 (depends on 7) The power assembly of claim 7, wherein the first direction is perpendicular to the second direction, or an angle between the first direction and the second direction is 180°. ### Claim 9 (depends on 1) The power assembly of claim 1, further comprising a power module, wherein the electrical generator is electrically connected to the battery through the power module. ### Claim 10 (depends on 9) The power assembly of claim 9, wherein the power module is also configured to drive the rotation of the rotors. ### Claim 11 (depends on 1) The power assembly of claim 1, wherein the engine is a turboshaft engine. ### Claim 12 (depends on 9) A power system, comprising: the power assembly of claim 9, wherein the rotor power mechanism of the UAV comprises a plurality of motors, each of the rotors is respectively fixed on an output shaft of one of the plurality of motors, and the plurality of the motors is electrically connected to the battery and the power module. ### Claim 13 (depends on 12) An unmanned aerial vehicle (UAV), comprising: a flight control system and the power system of claim 12. ### Claim 14 (depends on 13) The UAV of claim 13, wherein the battery is configured to drive the rotation of the rotors during a time when the UAV is in a hovering state. ### Claim 15 (depends on 13) The UAV of claim 13, wherein during a time when the UAV is in a horizontal flight state, a portion of an output power of the engine is configured to drive the electrical generator, and another portion of the output power of the engine is configured to drive the propulsion propeller. ### Claim 16 (depends on 13) The UAV of claim 13, wherein during a time when the UAV is in a horizontal flight state, all the output power of the engine is configured to drive the propulsion propeller. ### Claim 17 (depends on 15) The UAV of claim 15, wherein the flight control system is configured to control a charging time of the battery by the power module based on current energy of the battery and a power of the electrical generator. ### Claim 18 (depends on 15) The UAV of claim 15, wherein the flight control system is configured to adjust a ratio of the portion of the power output from the engine to the propulsion propeller to the portion of the power output from the engine to the electrical generator based on a state of the UAV during a time when the UAV is in the horizontal flight state. ### Claim 19 (depends on 18) The UAV of claim 18, wherein the state of the UAV during the horizontal flight state comprises a power required to maintain the UAV in horizontal flight and a power required to charge the battery. ### Claim 20 (depends on 13) The UAV of claim 13, further comprising a fuselage, wings and a tail, wherein the wings are arranged on sides of the fuselage, the tail is arranged at a rear end of the fuselage in a forward direction, and the rotors are arranged radially and symmetrically around the fuselage.