CN-116409462-B - Aircraft with a plurality of aircraft body

CN116409462BCN 116409462 BCN116409462 BCN 116409462BCN-116409462-B

Abstract

The invention discloses an aircraft, wherein the aircraft comprises an aircraft main body, an onboard air conditioner and an electric propulsion system, the aircraft main body is provided with a cabin body, the onboard air conditioner is provided with an air outlet communicated with the cabin body, the onboard air conditioner comprises an evaporator and a condenser which are connected through a throttling device, the condenser is arranged corresponding to the air outlet, the electric propulsion system is arranged on the aircraft main body, and the evaporator is at least partially arranged in the electric propulsion system. The technical scheme of the invention aims to reduce the temperature of the electric propulsion system and improve the power density of the electric propulsion system.

Inventors

XUE SONGBAI
LI QING
YI LIJIE

Assignees

成都沃飞天驭科技有限公司
浙江吉利控股集团有限公司

Dates

Publication Date: 20260508
Application Date: 20230419

Claims (10)

1. An air-craft having the function of a vehicle, characterized by comprising the following steps: The aircraft body is provided with a cabin; The air conditioner comprises an air conditioner, an air conditioner and a control device, wherein the air conditioner is provided with an air outlet communicated with the cabin body, the air conditioner comprises an evaporator and a condenser which are connected through a throttling device, the condenser is arranged corresponding to the air outlet, and The electric propulsion system is arranged in the aircraft main body, and the evaporator is at least partially arranged in the electric propulsion system; The electric propulsion system is provided with a cooling channel for cooling liquid to flow, and the evaporator comprises an evaporation pipe section arranged in the cooling channel; the electric propulsion system comprises a motor provided with the cooling channel; the electric propulsion system comprises a propeller mechanism and a controller electrically connected with the motor; The motor comprises a motor shell, a stator arranged on the motor shell and a rotor matched with the stator, and the cooling channel passes through the stator, the rotor and the motor shell; The motor casing comprises a casing body with a containing cavity which is arranged in a penetrating way, a first end cover which covers one port of the containing cavity, and a second end cover which covers the other port of the containing cavity, the stator is arranged in the containing cavity, the rotor rotatably penetrates through the first end cover, the containing cavity and the second end cover, and the cooling channel comprises a pumping cavity arranged in the first end cover; the rotor comprises a rotating shaft which is rotatably arranged on the first end cover, the accommodating cavity and the second end cover in a penetrating manner, the rotating shaft is in driving connection with the propeller mechanism, the cooling channel further comprises a first cooling flow passage arranged on the rotating shaft and a second cooling flow passage arranged on the second end cover, and the first cooling flow passage is respectively communicated with the pumping cavity and the second cooling flow passage; The rotor further comprises a rotor core connected with the rotating shaft, the rotor core is accommodated in the accommodating cavity, the rotor core is matched with the stator, the cooling flow channels further comprise a plurality of fourth cooling flow channels arranged on the rotor core, the fourth cooling flow channels are provided with second liquid inlets opposite to the second end cover, the second cooling flow channels further comprise third flow channels communicated with the first cooling flow channels and third liquid passing ring grooves communicated with the third flow channels, the third liquid passing ring grooves encircle the rotating shaft, the third liquid passing ring grooves are opposite to the second liquid inlets, and the fourth cooling flow channels are arranged along the circumferential intervals of the third liquid passing ring grooves.
2. The aircraft of claim 1, wherein the rotor is drivingly connected to the propeller mechanism and the stator is electrically connected to the controller.
3. The vehicle of claim 2, wherein the motor further comprises a first pumping gear and a second pumping gear each disposed in the pumping chamber, the first pumping gear and the second pumping gear being in meshing engagement, the rotor being in driving connection with the first pumping gear.
4. The aircraft of claim 3, wherein the second end cap is provided with a through hole, the rotating shaft comprises a rotating fit section matched with the through hole, the first cooling flow passage comprises a first flow passage and a first liquid passing ring groove arranged on the outer circumferential surface of the rotating fit section, the first flow passage is communicated with the first liquid passing ring groove and the pumping cavity, the second cooling flow passage comprises a second flow passage, the second flow passage is provided with a first liquid inlet arranged on the inner wall surface of the through hole, and the first liquid inlet is communicated with the first liquid passing ring groove.
5. The aircraft of claim 4, wherein the cooling channel further comprises a third cooling flow channel provided to the housing, the third cooling flow channel in communication with the second cooling flow channel.
6. The aircraft of claim 5, wherein the second cooling flow passage comprises a second flow passage communicated with the first cooling flow passage and a second liquid passing ring groove communicated with the second flow passage, the second liquid passing ring groove is arranged around the rotating shaft, a plurality of third cooling flow passages are arranged at intervals along the circumferential direction of the second liquid passing ring groove, and the third cooling flow passages are communicated with the second liquid passing ring groove.
7. The aircraft of claim 5, wherein the first end cap is disposed below the housing, the cooling channel further comprises a sump disposed on an upper side of the first end cap, the sump is in communication with the third cooling flow passage and the pumping chamber, respectively, and the evaporator tube section is disposed in the sump.
8. The aircraft of claim 4, wherein the second end cap is spaced from the rotor core in an axial direction of the shaft by a fluid gap in communication with the third fluid ring slot, the stator includes a stator core having a plurality of winding channels, the fluid gap in communication with the winding channels, and the cooling channel further includes the fluid gap and the winding channels.
9. The aircraft of claim 4, wherein the cooling channel further comprises a fifth cooling flow path provided on a side of the first end cap adjacent the controller, the fifth cooling flow path communicating with the pumping chamber, the controller capping the fifth cooling flow path; and/or, the outer circumferential surface of the first pumping gear is meshed with the inner circumferential surface of the second pumping gear.
10. The aircraft of claim 2, wherein the outer peripheral surface of the motor housing is provided with cooling fins.

Description

Aircraft with a plurality of aircraft body Technical Field The invention relates to the technical field of aircrafts, in particular to an aircraft. Background In the prior art, an aircraft comprises an aircraft body and an electric propulsion system arranged on the aircraft body, the electric propulsion system provides flying power for the aircraft, the electric propulsion system is easy to heat to a higher temperature in the operation process of the electric propulsion system, so that the power density of the electric propulsion system is lower, the electric propulsion system is usually cooled by air cooling in the prior art, however, the cooling degree of the electric propulsion system is limited by air cooling, the temperature of the electric propulsion system is still higher, and the power density is lower. Disclosure of Invention The main object of the present invention is to provide an aircraft aimed at reducing the temperature of the electric propulsion system and increasing the power density of the electric propulsion system. To achieve the above object, the present invention provides an aircraft comprising: The aircraft body is provided with a cabin; The air conditioner comprises an air conditioner, an air conditioner and a control device, wherein the air conditioner is provided with an air outlet communicated with the cabin body, the air conditioner comprises an evaporator and a condenser which are connected through a throttling device, the condenser is arranged corresponding to the air outlet, and And the electric propulsion system is arranged in the aircraft main body, and the evaporator is at least partially arranged in the electric propulsion system. Optionally, the electric propulsion system is provided with a cooling channel for cooling liquid to flow, and the evaporator comprises an evaporation pipe section arranged in the cooling channel. Optionally, the electric propulsion system is provided with a propulsion system refrigerant channel, and the refrigerant channel of the evaporator comprises the propulsion system refrigerant channel. Optionally, the electric propulsion system comprises a propeller mechanism, a motor in driving connection with the propeller mechanism, and a controller in electrical connection with the motor, the motor being provided with the cooling channel. Optionally, the motor includes the motor casing, locates the motor casing the stator, with stator complex rotor, the rotor with screw mechanism drive connection, the stator with the controller electricity is connected, cooling channel passes through the stator the rotor, and the motor casing. Optionally, the motor casing includes having the casing that is the holding chamber that link up the setting, lid in hold first end cover of chamber port, lid in hold second end cover of chamber another port, the stator is located hold the chamber, the rotor rotationally wear to locate first end cover, hold the chamber, and the second end cover, the cooling channel is including locating the pumping chamber of first end cover, the motor still includes all locating first pumping gear and the second pumping gear of pumping chamber, first pumping gear with the meshing of second pumping gear, the rotor with first pumping gear drive connection. Optionally, the rotor includes rotationally wears to locate first end cover the chamber is acceptd, reaches the pivot of second end cover, the pivot with screw mechanism drive connection, the cooling channel still includes locates the first cooling runner of pivot, and locate the second cooling runner of second end cover, first cooling runner respectively with the pumping chamber, and the second cooling runner intercommunication. Optionally, the second end cover is provided with a via hole, the rotating shaft comprises a rotating fit section matched with the via hole, the first cooling runner comprises a first runner and a first liquid passing ring groove arranged on the outer peripheral surface of the rotating fit section, the first runner is communicated with the first liquid passing ring groove and the pumping cavity, the second cooling runner comprises a second runner, the second runner is provided with a first liquid inlet arranged on the inner wall surface of the via hole, and the first liquid inlet is communicated with the first liquid passing ring groove. Optionally, the cooling channel further includes a third cooling channel provided in the housing, and the third cooling channel is in communication with the second cooling channel. Optionally, the second cooling runner includes with the second runner of first cooling runner intercommunication and with the second of second runner intercommunication crosses the liquid ring groove, the second crosses the liquid ring groove and encircles the pivot setting, the third cooling runner is equipped with a plurality of, and is a plurality of the third cooling runner is followed the second crosses the circumference interval setting of liquid ring gr