Apparatus for controlling temperature and pressure of aircraft

An apparatus comprising:

• a shaft installed in an aircraft, the shaft being rotatable by having a motor coupled thereto;
• a compressor, rotatable by being connected to the shaft, configured to form a flow of heated compressed air by compressing a first portion of external air introduced into the aircraft;
• a heat exchanger configured to heat-exchange the heated compressed air with a second portion of external air introduced into the aircraft;
• a turbine, rotatable by being connected to the shaft, configured to form a flow of cooling air by expanding the heat-exchanged compressed air;
• a cooling heat exchanger configured to exchange heat between a refrigerant, in the cooling heat exchanger, and the cooling air, wherein the cooling air cools the refrigerant in the cooling heat exchanger, and the refrigerant circulates through a fuel cell power train to cool the fuel cell power train in the aircraft;
• and
• a cooling line connected to an outlet of the turbine, through which cooling air flowing from the outlet of the turbine flows,
• wherein the cooling heat exchanger is disposed between the cooling line and a refrigerant circulation line for circulating the refrigerant,
• wherein a heated refrigerant flowing through the refrigerant circulation line is selectively cooled by the cooling air in the cooling heat exchanger,
• wherein a first cooling line is connected between an air circulation line and the cooling line,
• wherein the air circulation line is configured to circulate air in an interior of the aircraft, and
• wherein the cooling air flowing from the outlet of the turbine is selectively directly supplied to the air circulation line through the first cooling line to perform cooling in the interior.

An apparatus comprising:

• a shaft installed in an aircraft, the shaft being rotatable by having a motor coupled thereto;
• a compressor, rotatable by being connected to the shaft, configured to form a flow of heated compressed air by compressing a first portion of external air introduced into the aircraft;
• a heat exchanger configured to heat-exchange the heated compressed air with a second portion of the external air introduced into the aircraft;
• a turbine, rotatable by being connected to the shaft, configured to form a flow of cooling air by expanding the heat-exchanged compressed air;
• a heating line configured to supply the heated compressed air flowing from an outlet of the compressor to a refrigerant circulation line for circulating a refrigerant cooling a fuel cell power train;
• an air circulation line configured to circulate air in an interior of the aircraft;
• a refrigerant-air heat exchanger disposed between the refrigerant circulation line and the air circulation line and configured to heat-exchange the refrigerant with air;
• and
• a cooling line connected to an outlet of the turbine, through which cooling air flowing from the outlet of the turbine flows,
• wherein a cooling heat exchanger is disposed between the cooling line and the refrigerant circulation line, and a heated refrigerant flowing through the refrigerant circulation line is selectively cooled by the cooling air in the cooling heat exchanger.