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CN-122009494-A - Airborne cooling system, aircraft and control method

CN122009494ACN 122009494 ACN122009494 ACN 122009494ACN-122009494-A

Abstract

The invention relates to the technical field of aircrafts, in particular to an airborne cooling system, an aircraft and a control method. The system comprises a power assembly, a pipeline assembly and a refrigerating assembly, wherein the power assembly comprises a gas compressor, a motor module, a first refrigerating turbine and a transmission shaft, the pipeline assembly comprises a gas inlet pipeline, a gas transmission pipeline and a gas supply pipeline, the gas inlet pipeline is connected with a gas inlet of the gas compressor, the gas transmission pipeline is connected between a gas outlet of the gas compressor and a gas inlet of the first refrigerating turbine, the gas supply pipeline comprises a gas supply branch and a gas supply valve, one end of the gas supply branch is connected with a gas outlet of the first refrigerating turbine, the other end of the gas supply branch is used for supplying cold gas for an aircraft, the gas supply valve is connected with the gas supply branch, the refrigerating assembly is used for refrigerating gas in the gas supply branch, and the refrigerating assembly and the transmission shaft work independently, so that the problems that the environmental control assembly cannot simultaneously complete pressure regulation and temperature regulation decoupling control and high engine bleed air loss are solved.

Inventors

  • ZHOU YUNAN
  • ZHOU YANZHANG
  • Xue Dingxi
  • Kuang Pan
  • YAO YEMING

Assignees

  • 中国航空工业集团公司金城南京机电液压工程研究中心

Dates

Publication Date
20260512
Application Date
20260414

Claims (19)

  1. 1. An on-board cooling system, the on-board cooling system comprising: the power assembly comprises a compressor, a motor module, a first refrigeration turbine and a transmission shaft, wherein the compressor, the motor module and the first refrigeration turbine are coaxially transmitted through the transmission shaft; The air supply system comprises a pipeline assembly, an air supply pipeline and an air supply pipeline, wherein the pipeline assembly comprises an air inlet pipeline, an air transmission pipeline and an air supply pipeline, the air inlet pipeline is connected with an air inlet of the air compressor, the air transmission pipeline is connected between an air outlet of the air compressor and an air inlet of the first refrigeration turbine, the air supply pipeline comprises an air supply branch and an air supply valve, one end of the air supply branch is connected with the air outlet of the first refrigeration turbine, the other end of the air supply branch is used for supplying cool air for an aircraft, the air supply valve is connected with the air supply branch, and the air supply valve is used for adjusting the flow of outlet air of the air supply branch; the refrigerating assembly is connected with the gas supply branch and used for refrigerating gas in the gas supply branch, and the refrigerating assembly and the transmission shaft work independently.
  2. 2. The airborne cooling system of claim 1 wherein the air intake circuit includes a natural air intake branch, an air intake valve, an engine bleed branch and a bleed valve, wherein one end of the natural air intake branch is connected to an air intake of the compressor and the other end is connected to the outside atmosphere, one end of the engine bleed branch is connected to an air intake of the compressor and the other end is connected to an engine system, the air intake valve is connected to the natural air intake branch, and the bleed valve is connected to the engine bleed branch.
  3. 3. The on-board cooling system of claim 1, wherein the refrigeration assembly comprises a compressor, a first condenser, an expansion valve, an evaporator, and an evaporation circulation line, wherein the compressor, the first condenser, the expansion valve, and the evaporator are in sequential circulation communication via the evaporation circulation line, and wherein the air supply line passes through the evaporator.
  4. 4. An on-board cooling system according to claim 1, further comprising a device radiator; the power assembly further comprises a second refrigeration turbine, wherein the second refrigeration turbine and the transmission shaft are coaxially driven; The pipeline assembly further comprises a refrigeration pipeline, the refrigeration pipeline comprises a first refrigeration branch, a first regulating valve and a second refrigeration branch, the first refrigeration branch is connected between an exhaust port of the first refrigeration turbine and an air inlet of the second refrigeration turbine, the first regulating valve is connected with the first refrigeration branch, the second refrigeration branch is connected with an exhaust port of the second refrigeration turbine, and the equipment radiator is connected with the second refrigeration branch for heat exchange.
  5. 5. The airborne cooling system of claim 4 wherein the refrigeration circuit further includes a second regulating valve, wherein an end of the second refrigeration branch remote from the second refrigeration turbine is in communication with an external atmosphere; The pipeline assembly further comprises a return pipeline, wherein the return pipeline comprises a first return branch and a first return valve, one end of the first return branch is connected with the second refrigeration branch, the other end of the first return branch is connected with an air inlet of the air compressor, the first return valve is connected with the first return branch, and the communication position of the first return branch and the second refrigeration branch is positioned between the equipment radiator and the second regulating valve; the first reflux valve is electrically connected with the motor module, and the motor module is in a motor working mode when the first reflux valve is in an opening state.
  6. 6. The on-board cooling system of claim 4, further comprising an auxiliary assembly, wherein the auxiliary assembly comprises a second condenser and a water separator, wherein the gas line is connected to a hot side passage of the second condenser; the refrigerating pipeline further comprises a third refrigerating branch and a third regulating valve, the third refrigerating branch is connected with an exhaust port of the second refrigerating turbine, the third refrigerating branch is connected with a cold side channel of the second condenser, the cold side channel is isolated from the hot side channel, the third regulating valve is connected with the third refrigerating branch, and the third regulating valve is located between the second condenser and the second refrigerating turbine.
  7. 7. An on-board cooling system according to claim 6, wherein the third refrigeration branch is connected to the motor module.
  8. 8. The airborne cooling system of claim 6, wherein the refrigeration circuit further comprises a fourth regulating valve, wherein an end of the third refrigeration branch remote from the second refrigeration turbine is connected to the outside atmosphere; The pipeline assembly further comprises a return pipeline, wherein the return pipeline comprises a second return branch and a second return valve, the third refrigeration branch is communicated with the second return branch, the second return branch is connected with an air inlet of the air compressor, the second return valve is connected with the second return branch, and the communication position of the second return branch and the third refrigeration branch is positioned between the fourth regulating valve and an air outlet of the second refrigeration turbine; the second reflux valve is electrically connected with the motor module, and when the second reflux valve is in an opening state, the motor module is switched into a motor working mode.
  9. 9. The airborne cooling system of claim 1 wherein the circuit assembly further comprises an exhaust circuit, the exhaust circuit comprising an exhaust branch and an exhaust valve, one end of the exhaust branch being connected to an exhaust port of the compressor and the other end being open to the outside atmosphere, the exhaust valve being connected to the exhaust branch, the location of communication of the exhaust branch to the air supply branch being located between the air supply valve and the exhaust port of the compressor.
  10. 10. The on-board cooling system of claim 9, wherein the exhaust line has an exit temperature of 20 ℃ to 50 ℃ and the exit of the exhaust line is configured to be disposed toward a wing of the aircraft.
  11. 11. An aircraft, characterized in that it comprises an on-board cooling system according to any one of claims 1-10.
  12. 12. A control method of an on-board cooling system applied to the on-board cooling system according to any one of claims 1 to 10, characterized by comprising: responding to an air supply instruction of an aircraft, and acquiring the working state of the aircraft; when the aircraft is in a normal flight state, acquiring target air supply flow and target air supply temperature of the aircraft, and starting a power assembly, a pipeline assembly and a refrigerating assembly; Adjusting the opening of the air supply pipeline according to the target air supply flow; And adjusting the refrigeration power of the refrigeration assembly according to the target air supply temperature.
  13. 13. The method of claim 12, wherein the conduit assembly further comprises an exhaust conduit; The control method further includes: And adjusting the opening of the exhaust pipeline according to the target air supply flow.
  14. 14. The method of claim 12, wherein when the aircraft is in a normal flight state, acquiring a target air supply flow and a target air supply temperature of the aircraft, and starting the power assembly, the pipeline assembly and the refrigeration assembly, comprising: When the aircraft is in the normal flight state, acquiring target air supply flow, target air supply temperature and flight height of the aircraft, and starting the power assembly and the refrigeration assembly; when the flying height is lower than the preset height, a natural air inlet branch is opened, an engine air inlet branch is closed, an air transmission pipeline and an air supply pipeline are opened, a refrigeration pipeline is opened, an air exhaust pipeline is opened, and the motor module is controlled to be in a motor working mode; When the flying height is higher than the preset height, the engine air-entraining branch is started, the air conveying pipeline and the air supply pipeline are started, the first refrigerating branch and the second refrigerating branch are started, the air exhaust pipeline is started, the natural air inlet branch is closed, the third refrigerating branch is closed, and the motor module is controlled to be in a generator working mode.
  15. 15. The method of claim 14, wherein when the aircraft is in a normal flight state, acquiring a target air supply flow and a target air supply temperature of the aircraft, and starting the power assembly, the pipeline assembly and the refrigeration assembly, further comprising: When the target supply flow is higher than a preset flow, the gas exhausted by the second refrigeration branch is returned to the gas inlet of the gas compressor, the gas exhausted by the third refrigeration branch is returned to the gas inlet of the gas compressor, and the motor module is controlled to be in the motor working mode; And when the target air supply flow is lower than the preset flow, discharging the air discharged by the second refrigeration branch to the external atmosphere, and discharging the air discharged by the third refrigeration branch to the external atmosphere.
  16. 16. A method of controlling an on-board cooling system according to claim 12, the control method is characterized by further comprising the following steps: When the aircraft is in a mechanical failure flight state, acquiring a first emergency target air quantity and a first emergency target air temperature of the aircraft, opening an engine air-entraining branch, an air-conveying pipeline and an air-supplying pipeline, closing a natural air-intake branch, closing a refrigerating pipeline and closing an air-exhausting pipeline; adjusting the opening degree of the engine bleed air branch according to the first emergency target gas quantity; And adjusting the refrigeration power of the refrigeration assembly according to the first emergency target air temperature.
  17. 17. A method of controlling an on-board cooling system according to claim 12, the control method is characterized by further comprising the following steps: When the aircraft is in a bleed air fault flight state, acquiring a second emergency target air quantity and a second emergency target air temperature of the aircraft, opening a natural air inlet branch, an air transmission pipeline and an air supply pipeline, closing an engine bleed air branch, closing a refrigerating pipeline, closing an exhaust pipeline, and controlling a motor module to be in a motor working mode; adjusting the rotating speed of the motor module according to the second emergency target air quantity; and adjusting the refrigeration power of the refrigeration assembly according to the second emergency target air temperature.
  18. 18. A method of controlling an on-board cooling system according to claim 12, the control method is characterized by further comprising the following steps: When the aircraft is in an emergency power supply flight state, acquiring a third emergency target air quantity and a third emergency target air temperature of the aircraft, opening an engine air-entraining branch, an air transmission pipeline and an air supply pipeline, closing a natural air-in branch, closing a refrigeration pipeline, closing an air exhaust pipeline, and controlling a motor module to be in a generator working mode; adjusting the opening of the engine bleed air branch according to the third emergency target air quantity; and adjusting the refrigeration power of the refrigeration assembly according to the third emergency target air temperature.
  19. 19. A method of controlling an on-board cooling system according to claim 12, the control method is characterized by further comprising the following steps: When the aircraft is in a ground maintenance state, acquiring a ground target air temperature of the aircraft, opening the power assembly, the air inlet pipeline, the air transmission pipeline and the air supply pipeline, closing the air exhaust pipeline, closing the refrigeration assembly, and controlling the motor module to be in a motor working mode; and adjusting the opening of the air supply pipeline according to the ground target air temperature.

Description

Airborne cooling system, aircraft and control method Technical Field The invention relates to the technical field of aircrafts, in particular to an airborne cooling system, an aircraft and a control method. Background The aircraft refrigerating system mainly comprises two main core functional units of a refrigerating assembly and an environmental control assembly, and has two core functions of cooling airborne equipment and regulating and controlling cabin environment. The refrigeration component is used as a temperature control core unit of the airborne equipment, can output a stable cold source through refrigeration circulation, provides a controllable heat sink, and can pertinently take away redundant heat generated in the core load operation process of the airborne avionics equipment, the electromechanical system and the like, so that the working temperature of the equipment is restricted in a rated safety range, and the stable and reliable operation of various airborne equipment in a full flight envelope is ensured. The environment control assembly takes the air entraining of the aircraft engine as a working medium, realizes air source temperature regulation and control through the expansion refrigeration process of the air entraining, provides an air source meeting the requirement of pressurization for the aircraft cabin, and can output a cooling or heating air source with corresponding parameters according to the flight working condition and the cabin use requirement to complete comprehensive regulation and control of the pressure and the temperature in the cabin. However, the environmental control assembly is required to complete pressure regulation and temperature regulation treatment simultaneously through the same engine bleed air source and then is supplied to the cabin, and under the working condition of dynamic change of the flight envelope, only the stable control of the air supply temperature can be realized, and the air supply flow cannot be accurately regulated. Thereby causing the situation that the instantaneous pressure is too large or too small in the cabin pressure regulating process, and causing the phenomenon of pressing ears of passengers. Meanwhile, a large amount of engine bleed air is consumed to meet the temperature regulation requirement, so that invalid loss of the engine bleed air is caused, the overall energy utilization efficiency of the system is low, and the excessive waste of airborne energy is caused. Disclosure of Invention The invention provides an airborne cooling system, an aircraft and a control method, which are used for solving the problems that an environmental control assembly cannot simultaneously complete voltage regulation and temperature regulation decoupling control and the engine bleed air loss is high. In a first aspect, the present application provides an on-board cooling system comprising: the power assembly comprises a compressor, a motor module, a first refrigeration turbine and a transmission shaft, wherein the compressor, the motor module and the first refrigeration turbine are coaxially transmitted through the transmission shaft; The air supply system comprises a pipeline assembly, an air supply pipeline and an air supply pipeline, wherein the pipeline assembly comprises an air inlet pipeline, an air transmission pipeline and an air supply pipeline, the air inlet pipeline is connected with an air inlet of the air compressor, the air transmission pipeline is connected between an air outlet of the air compressor and an air inlet of the first refrigeration turbine, the air supply pipeline comprises an air supply branch and an air supply valve, one end of the air supply branch is connected with the air outlet of the first refrigeration turbine, the other end of the air supply branch is used for supplying cool air for an aircraft, the air supply valve is connected with the air supply branch, and the air supply valve is used for adjusting the flow of outlet air of the air supply branch; the refrigerating assembly is connected with the gas supply branch and used for refrigerating gas in the gas supply branch, and the refrigerating assembly and the transmission shaft work independently. The air inlet pipeline comprises a natural air inlet branch, an air inlet valve, an engine air-entraining branch and an air-entraining valve, wherein one end of the natural air inlet branch is connected with an air inlet of the air compressor, the other end of the natural air inlet branch is connected with the outside atmosphere, one end of the engine air-entraining branch is connected with the air inlet of the air compressor, the other end of the engine air-entraining branch is used for being connected with an engine system, the air inlet valve is connected with the natural air inlet branch, and the air-entraining valve is connected with the engine air-entraining branch. Optionally, the refrigeration assembly comprises a compressor, a first condenser, an expansion valve,