CN109367801B - Distributed airplane thermal management system and method based on airplane hydraulic system and micro evaporative refrigeration cycle - Google Patents
Distributed airplane thermal management system and method based on airplane hydraulic system and micro evaporative refrigeration cycle Download PDFInfo
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- CN109367801B CN109367801B CN201811175029.8A CN201811175029A CN109367801B CN 109367801 B CN109367801 B CN 109367801B CN 201811175029 A CN201811175029 A CN 201811175029A CN 109367801 B CN109367801 B CN 109367801B
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- 238000005057 refrigeration Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title description 6
- 239000010720 hydraulic oil Substances 0.000 claims abstract description 62
- 239000007788 liquid Substances 0.000 claims abstract description 60
- 238000001816 cooling Methods 0.000 claims abstract description 42
- 230000004087 circulation Effects 0.000 claims abstract description 24
- 239000000295 fuel oil Substances 0.000 claims abstract description 13
- 238000001704 evaporation Methods 0.000 claims description 25
- 230000008020 evaporation Effects 0.000 claims description 25
- 210000001015 abdomen Anatomy 0.000 claims description 9
- 239000000126 substance Substances 0.000 claims description 2
- 238000007726 management method Methods 0.000 claims 8
- 239000000446 fuel Substances 0.000 abstract description 10
- 230000017525 heat dissipation Effects 0.000 abstract description 5
- 230000015572 biosynthetic process Effects 0.000 abstract description 4
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 3
- 239000003507 refrigerant Substances 0.000 description 3
- 239000002699 waste material Substances 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 229910021529 ammonia Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 239000011555 saturated liquid Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B21/00—Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
- F15B21/04—Special measures taken in connection with the properties of the fluid
- F15B21/042—Controlling the temperature of the fluid
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0607—Environmental Control Systems providing hot air or liquid for deicing aircraft parts, e.g. aerodynamic surfaces or windows
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
A distributed aircraft heat management system based on an aircraft hydraulic system and a micro evaporative refrigeration cycle comprises a hydraulic oil tank, a hydraulic pump, a throttle valve, a hydraulic system actuating element, a hydraulic oil-air heat exchanger, an evaporative liquid cooling circulation system, a fuel oil-hydraulic oil heat exchanger, a fuel oil system and an aircraft skin heat exchanger, wherein heat generated by the hydraulic actuating element such as an undercarriage is directly transferred to an inner panel and an outer panel of the aircraft skin for dissipation by using a Loop Heat Pipe (LHP) of a double condenser, so that effective heat dissipation is increased, and excessive temperature rise of hydraulic oil is avoided; utilize hydraulic circulation low pressure hydraulic oil of low reaches, after ram air cooling, as heat sink to airborne equipment cooling, prevented the formation of fuel high temperature, reduced the fuel pressure drop, reduced part quantity and reduced aircraft performance compensation loss, make full use of the advantage that hydraulic system distribution range is wide, heat collection power is strong, make airborne equipment cooling system overall arrangement more nimble convenient.
Description
Technical Field
The invention relates to a distributed airplane heat management system and method based on an airplane hydraulic system and a micro evaporative refrigeration cycle, belongs to the field of airplane airborne equipment, and particularly relates to improvement of an airborne equipment cooling system on an airplane.
Background
As aircraft performance increases, the on-board electromechanical systems will generate more heat, presenting new opportunities and challenges to thermal management techniques for aircraft. The defects of the prior art are mainly shown in that:
1) on one hand, the traditional aircraft hydraulic system has larger temperature rise after passing through a hydraulic system actuating element, and the hydraulic oil is usually replaced after the traditional aircraft hydraulic system is used, so that the method has long working period and wastes more hydraulic oil;
2) on the other hand, the main heat sinks of the aircraft are fuel and ram air at present, but their heat dissipation capacity is nearly saturated. With the increase of the heat load of the onboard electromechanical system, the cooling load of the fuel system is increased seriously, and the fuel is used as a cold source to cool a hydraulic system or an onboard device of an aircraft, so that the high temperature of the fuel can be formed, and the problem of thermal stability is caused finally. Moreover, the fuel cooling is mostly in the form of concentrated cooling, and the heat collecting capacity is limited.
Disclosure of Invention
According to one aspect of the invention, a distributed aircraft thermal management system based on an aircraft hydraulic system and a micro evaporative refrigeration cycle is provided, which is characterized by comprising:
a hydraulic oil tank, a hydraulic pump, a throttle valve, a hydraulic element, a hydraulic oil-air heat exchanger, at least one condenser, a fuel-hydraulic oil heat exchanger, a skin heat exchanger, a fuel oil tank, a fuel oil pump and an electrical system,
wherein:
the hydraulic element comprises at least one of a main landing gear system hydraulic element, a wheel braking system hydraulic element, an aileron steering engine hydraulic element, a horizontal tail steering engine hydraulic element, a vertical tail steering engine hydraulic element and a cabin door system hydraulic element,
the skin heat exchanger comprises at least one of a first aircraft belly surface skin heat exchanger, a wing surface skin heat exchanger, a tail wing surface skin heat exchanger and a second aircraft belly surface skin heat exchanger,
the hydraulic pump is connected with the hydraulic oil tank,
the hydraulic component is connected downstream of the hydraulic pump,
the hydraulic oil-air heat exchanger is installed downstream of the hydraulic components,
the condenser is installed downstream of the hydraulic oil-air heat exchanger,
the fuel-hydraulic oil heat exchanger is arranged between the third condenser and the hydraulic oil tank,
at least one local evaporation liquid cooling circulation loop which respectively corresponds to at least one condenser, each local evaporation liquid cooling circulation loop comprises an airborne equipment heat exchanger, a circulating working medium pump, a local evaporation liquid cooling evaporator, a gas compressor and a throttle valve, wherein the gas inlet end of the condenser is connected with the gas compressor, the outlet end of the condenser is connected with the throttle valve, the downstream end of the throttle valve is connected with the inlet of the local evaporation liquid cooling evaporator, the outlet of the local evaporation liquid cooling evaporator is connected with the gas compressor to form an evaporation refrigeration cycle,
the hydraulic element is connected with at least one of the first aircraft abdomen surface skin heat exchanger, the wing surface skin heat exchanger, the empennage surface skin heat exchanger and the second aircraft abdomen surface skin heat exchanger through the loop heat pipe of the double condensers,
wherein the content of the first and second substances,
the loop heat pipe evaporator is installed on the hydraulic element,
the liquid storage device is arranged at the front end of the liquid inlet of the loop heat pipe evaporator,
the steam outlet of the loop heat pipe evaporator is connected with one end of a first steam pipe,
the other end of the first steam pipe is connected with a condenser and a second steam pipe of the inner panel of the first aircraft surface skin,
the second steam pipe is connected with a condenser of the second aircraft surface skin outer panel,
the condenser of the second aircraft skin outer panel is connected to one end of a second liquid return line,
the other end of the second liquid return pipe is connected with a condenser of the first aircraft surface skin inner panel and the first liquid return pipe,
the outlet end of the first liquid return pipe is connected with the liquid storage device.
Drawings
Fig. 1 is a schematic diagram of a distributed aircraft thermal management system based on an aircraft hydraulic system and a micro evaporative refrigeration cycle according to one embodiment of the invention.
Fig. 2 is a configuration diagram of a localized evaporative liquid-cooled circulation system according to one embodiment of the present invention.
Fig. 3 is a layout view of the manner in which the hydraulic system components are connected to the aircraft skin heat exchanger, according to one embodiment of the present invention.
Detailed Description
According to the scheme of the invention, the double-condenser loop heat pipe is directly used for transferring the heat generated by the hydraulic actuating element to the aircraft wing skin for dissipation, so that the hydraulic oil is fully radiated under the condition of saving energy as much as possible, the performance of a hydraulic system is improved, and the energy waste is reduced. The invention utilizes the low-pressure hydraulic oil at the downstream of the hydraulic circulation as a heat sink to cool the airborne equipment after being cooled by ram air, thereby preventing the formation of high temperature of fuel oil, reducing the pressure drop of the fuel oil, reducing the number of parts and the performance compensation loss of the airplane, and controlling the quality and the cost of the airplane; the device adopts three local evaporative liquid cooling circulations which take hydraulic oil as heat sinks to cool the local airborne equipment, fully utilizes the advantages of wide distribution range and strong heat collecting capacity of a hydraulic system, and leads the layout of the cooling system of the airborne equipment to be more flexible and convenient.
The invention relates to a cooling system and a cooling method for airborne equipment applied to an airplane, in particular to a cooling system and a cooling method for local airborne equipment, which fully utilize an airplane surface skin heat exchanger and ram air to reduce the temperature of hydraulic circulating downstream hydraulic oil, utilize the hydraulic oil with low temperature and low pressure in the hydraulic circulating downstream as a heat sink, and adopt three local evaporative liquid cooling circulations taking the hydraulic oil as the heat sink to cool the local airborne equipment.
The invention aims to solve the problems of insufficient heat sink, concentrated heat exchange and complex layout of the current airplane, and the Loop Heat Pipe (LHP) of the double condensers is used for directly transferring heat generated by a hydraulic actuating element such as an undercarriage to the skin of the airplane for dissipation, so that an effective heat dissipation mode is increased, and the excessive temperature rise of hydraulic oil is avoided. And the downstream low-pressure hydraulic oil of the hydraulic circulation is cooled by ram air, and then the airborne equipment is cooled by adopting the coupling of three local vapor compression refrigeration cycles and local liquid cooling cycles, so that the hydraulic system is fully utilized, and has the advantages of wide distribution range and strong heat collecting capacity, the formation of high temperature of fuel oil can be prevented, the pressure drop of the fuel oil is reduced, the number of parts is reduced, the performance compensation loss of the airplane is reduced, and the quality and the cost of the airplane are controlled.
According to one aspect of the invention, a distributed aircraft thermal management system based on an aircraft hydraulic system and a micro evaporative refrigeration cycle is provided, which is characterized in that:
as shown in figure 1, in the working state of the aircraft hydraulic system, hydraulic oil is pumped out from a hydraulic oil tank (101) through a hydraulic pump (102), the temperature of an outlet of the pump is about 50-60 ℃, heat is released through actuating elements (104, 105, 106, 107, 108, 109 and 110), and generated heat is transmitted to an aircraft skin heat exchanger (116, 117, 118 and 119) through two loop heat pipes for heat dissipation. After passing through the hydraulic actuating elements (104, 105, 106, 107, 108, 109, 110), the temperature of the hydraulic oil is basically kept unchanged, and then the hydraulic oil is cooled by ram air through a hydraulic oil-air heat exchanger (111), so that the temperature of an outlet can reach 35 ℃ or even lower. The reduced-pressure and cooled hydraulic oil is heated by a condenser A, B, C (112, 113 and 114) to take away heat of a circulation A, B, C, then exchanges heat with fuel oil by a fuel oil-hydraulic oil heat exchanger (115), and returns to a hydraulic oil tank (101) to complete circulation.
According to a further aspect of the present invention, there is provided a local micro-evaporative refrigeration cycle using hydraulic oil as a heat sink, comprising:
a plurality of on-board plant heat exchangers (306, 307, 308); an evaporator (303); a compressor (304); a plurality of condensers (112, 113, 114); a throttle valve (305);
as shown in fig. 2, the circulating working medium PAO is pumped out by a pump (302), heat exchange is performed in onboard equipment heat exchangers (306, 307, 308), the heat of the onboard equipment is absorbed by the working medium, and heat exchange is performed in an evaporator (303) with a coolant (liquid ammonia) in an evaporation refrigeration cycle, so that the refrigerant is heated and evaporated, and then compressed by a compressor (304) to become superheated steam, and the superheated steam is transmitted to a condenser A, B, C (112, 113, 114) to perform heat exchange with hydraulic oil. The refrigerant vapor is condensed into saturated liquid at constant temperature and constant pressure through a condenser A, B, C (112, 113, 114), and flows to an evaporator (303) after being decompressed and cooled through a throttle valve (305) to complete the refrigerant circulation. The hydraulic oil is warmed by the condenser A, B, C (112, 113, 114) to remove heat from the evaporative liquid cooling loop A, B, C. The heat of the heat exchanger of the airborne equipment is taken away by the heat sink hydraulic oil through the local liquid cooling circulation and the evaporation refrigeration circulation.
According to a further aspect of the present invention, there is provided a method of connecting a hydraulic component to an aircraft skin radiator, comprising:
a reservoir (201); an evaporator (202); two condensers (204, 206); two steam pipes (203, 205); two liquid return pipes (207, 208);
as shown in figure 3, the liquid reservoir (201) in the connection mode is filled with working medium (pure ammonia), when the heat generated by the actuating element of the hydraulic system is applied to the evaporator (202), the working medium is evaporated, the steam flows from the first steam pipe (203) and the second steam pipe (205) to the first condenser (204) on the inner panel of the skin and the second condenser (206) on the outer panel of the skin of the airplane surface, the heat is released therefrom and condensed into liquid, the released heat is absorbed by the inner panel and the outer panel of the skin, the condensed liquid working medium flows back to the evaporator (202) through the second liquid return pipe (207) and the first liquid return pipe (208) under the action of capillary force in the evaporator, the heat absorption and the evaporation are continued, and the circulation is carried out, and the heat transmission is completed.
The beneficial effects of the invention include:
1. the heat generated by the hydraulic actuating element is directly transferred to the aircraft wing skin by the loop heat pipe for dissipation, so that an effective heat dissipation mode is increased, the hydraulic oil is fully dissipated under the condition of saving energy as much as possible, the performance of a hydraulic system is improved, and the energy waste is reduced.
2. The low-pressure hydraulic oil at the downstream of the hydraulic circulation is used as a heat sink to cool the airborne equipment after being cooled by ram air, compared with fuel oil, the high-temperature aviation hydraulic oil has good antirust effect, good high-temperature stability and low-temperature fluidity, prevents the formation of high temperature of the fuel oil, reduces the pressure drop of the fuel oil, reduces the number of parts and the performance compensation loss of the airplane, ensures the quality of the airplane and controls the cost;
3. the three local evaporative liquid cooling circulations using the hydraulic oil as the heat sink are adopted to cool the local airborne equipment, and the hydraulic system fully utilized has the advantages of wide distribution range and strong heat collecting capacity, so that the layout of the cooling system of the airborne equipment is more flexible and convenient.
The technical scheme of the distributed aircraft thermal management system based on the aircraft hydraulic system and the micro evaporative refrigeration cycle is described in detail below with reference to the accompanying drawings.
As shown in figure 1, a hydraulic pump (102) is connected with a hydraulic oil tank (101), a main landing gear system (104), a wheel brake system (105), an aileron steering engine (106), a horizontal tail steering engine (107), a vertical tail steering engine (108), a cabin door system (109) and other hydraulic elements (110) are connected in parallel at the downstream of the hydraulic pump (102), a loop with a throttle valve (103) is arranged in front of the hydraulic elements and connected to the oil tank, a hydraulic oil-air heat exchanger (111) is arranged at the downstream of a summary position of actuating elements of the hydraulic system, a condenser A (112), a condenser B (113) and a condenser C (114) are connected in series at the downstream of the hydraulic oil-air heat exchanger (111), and a fuel oil-hydraulic oil heat exchanger (115) is arranged between the condenser C (114).
Referring to fig. 2, the condenser A, B, C (112, 113, 114) of the present invention has an inlet connected to the compressor (304), an outlet connected to the throttle valve (305), an inlet connected to the evaporator (303) downstream of the throttle valve (305), and an outlet connected to the compressor (304) to form a vapor compression cycle. In a local liquid cooling cycle, the outlet end of the evaporator (303) is connected to the pump (302), and the on-board equipment heat exchanger (306, 307, 308) is installed downstream of the pump (302) and connected to the inlet end of the evaporator (303).
Referring to fig. 1 and 3, the connection mode of the hydraulic system component and the aircraft skin surface heat exchanger of the invention comprises a Loop Heat Pipe (LHP), taking the connection mode of a main landing gear system, a wheel braking system and an aircraft belly skin surface heat exchanger 1 as an example. A Loop Heat Pipe (LHP) evaporator (202) is mounted on a main landing gear system (104) and a wheel braking system (105), a liquid storage device (201) is mounted at the front end of a liquid inlet of the evaporator (202), a steam outlet of the evaporator (202) is connected with one end of a first steam pipe (203), the other end of the first steam pipe (203) is connected with a first condenser (204) and a second steam pipe (205) in an inner panel of an aircraft surface skin, the second steam pipe (205) is connected with a second condenser (206) in an outer panel of the aircraft surface skin, the second condenser (206) in the outer panel of the aircraft surface skin is connected with one end of a second liquid return pipe (207), the other end of the second liquid return pipe (207) is connected with the first condenser (204) in the inner panel of the aircraft surface skin and an inlet end of the first liquid return pipe (208), and an outlet end of the first liquid return pipe (208) is connected with the liquid storage device (201).
Claims (8)
1. A distributed aircraft thermal management system based on an aircraft hydraulic system and a micro evaporative refrigeration cycle is characterized by comprising:
a hydraulic oil tank (101), a hydraulic pump (102), a hydraulic component, a hydraulic oil-air heat exchanger (111), at least one condenser (112, 113, 114), a fuel-hydraulic oil heat exchanger (115), a skin heat exchanger, a fuel oil tank (120), a fuel oil pump (121) and an electrical system (122),
wherein:
the hydraulic component comprises at least one of a main landing gear system hydraulic component (104), a wheel braking system hydraulic component (105), a aileron steering engine hydraulic component (106), a horizontal tail steering engine hydraulic component (107), a vertical tail steering engine hydraulic component (108) and a cabin door system hydraulic component (109),
the skin heat exchanger comprises at least one of a first aircraft belly surface skin heat exchanger (116), a wing surface skin heat exchanger (117), a tail surface skin heat exchanger (118), a second aircraft belly surface skin heat exchanger (119),
the hydraulic pump (102) is connected with the hydraulic oil tank (101),
the hydraulic component is connected downstream of the hydraulic pump (102),
a hydraulic oil-air heat exchanger (111) is installed downstream of the hydraulic components,
at least one condenser (112, 113, 114) is installed downstream of the hydraulic oil-air heat exchanger (111),
a fuel-hydraulic oil heat exchanger (115) is arranged between the last one of the at least one condenser and the hydraulic oil tank (101),
at least one local evaporation liquid cooling circulation loop which respectively corresponds to at least one condenser (112, 113 and 114), each local evaporation liquid cooling circulation loop comprises an airborne equipment heat exchanger, a circulating working medium pump (302), a local evaporation liquid cooling evaporator (303), a compressor (304) and a second throttle valve (305), wherein the airborne equipment heat exchanger, the circulating working medium pump (302) and the local evaporation liquid cooling evaporator (303) are connected into a working medium circulation loop, the air inlet ends of the condensers (112, 113 and 114) are connected with the compressor (304), the outlet ends of the condensers (112, 113 and 114) are connected with the second throttle valve (305), the downstream end of the second throttle valve (305) is connected with the inlet of the local evaporation liquid cooling evaporator (303), the outlet end of the local evaporation liquid cooling evaporator (303) is connected with the compressor (304) to form an evaporation refrigeration cycle,
the hydraulic element is connected with the skin heat exchanger through the loop heat pipe of the double condensers,
wherein the content of the first and second substances,
the loop heat pipe evaporator (202) is mounted on the hydraulic component,
the liquid accumulator (201) is arranged at the front end of a liquid inlet of the loop heat pipe evaporator (202),
the steam outlet of the loop heat pipe evaporator (202) is connected with one end of a first steam pipe (203),
the other end of the first steam pipe (203) is connected with a condenser (204) and a second steam pipe (205) of the inner panel of the first aircraft surface skin,
a second steam pipe (205) is connected to a condenser (206) of a second aircraft skin outer panel,
a condenser (206) of a second aircraft skin outer panel is connected to one end of a second liquid return conduit (207),
the other end of the second liquid return pipe (207) is connected with a condenser (204) of the first aircraft surface skin inner panel and a first liquid return pipe (208),
the outlet end of the first liquid return pipe (208) is connected with the liquid reservoir (201),
a branch with a first throttle valve (103) is arranged in front of the hydraulic component and connected to a hydraulic oil tank (101).
2. The distributed aircraft thermal management system of claim 1, wherein the hydraulic oil-to-air heat exchanger (111) is configured to exchange heat between ram air and hydraulic oil circulating in the hydraulic system, thereby cooling the hydraulic oil, and the cooled hydraulic oil is configured to cool airborne equipment.
3. The distributed aircraft thermal management system of claim 1, wherein:
at least one condenser (112, 113, 114) exchanges heat with the hydraulic oil by using an evaporative refrigeration cycle, cools the aircraft onboard equipment, and transmits the circulated heat to heat sink hydraulic oil to be taken away by the hydraulic oil.
4. The distributed aircraft thermal management system of claim 1, wherein:
the hydraulic oil tank (101) is an immersed hydraulic oil tank.
5. A distributed airplane heat management method based on an airplane hydraulic system and a micro evaporative refrigeration cycle is characterized by comprising the following steps:
the hydraulic pump (102) is connected with the hydraulic oil tank (101),
connecting hydraulic components to the downstream of the hydraulic pump (102), wherein the hydraulic components comprise at least one of a main landing gear system hydraulic component (104), a wheel brake system hydraulic component (105), a aileron steering engine hydraulic component (106), a horizontal tail steering engine hydraulic component (107), a vertical tail steering engine hydraulic component (108) and a cabin door system hydraulic component (109),
the hydraulic oil-air heat exchanger (111) is installed downstream of the hydraulic components,
at least one condenser (112, 113, 114) is arranged downstream of the hydraulic oil-air heat exchanger (111),
the fuel-hydraulic oil heat exchanger (115) is arranged between the last one of the at least one condenser and the hydraulic oil tank (101),
at least one local evaporation liquid cooling circulation loop is arranged and corresponds to at least one condenser (112, 113, 114) respectively, each local evaporation liquid cooling circulation loop comprises an airborne equipment heat exchanger, a circulating working medium pump (302), a local evaporation liquid cooling evaporator (303), a gas compressor (304) and a second throttle valve (305), and the local evaporation liquid cooling circulation loop comprises:
the heat exchanger of the airborne equipment, the circulating working medium pump (302) and the local evaporation liquid cooling evaporator (303) are connected into a working medium circulating loop,
the air inlet end of the condenser is connected with a compressor (304),
the outlet end of the condenser is connected to a second throttle valve (305),
connecting the downstream end of the second throttle valve (305) with the inlet of the local evaporation liquid cooling evaporator (303),
the outlet of the local evaporation liquid cooling evaporator (303) is connected with a compressor (304),
thereby forming an evaporation refrigeration cycle,
connecting a hydraulic element with a skin heat exchanger through a loop heat pipe of a double condenser, wherein the skin heat exchanger comprises at least one of a first aircraft belly surface skin heat exchanger (116), a wing surface skin heat exchanger (117), a tail surface skin heat exchanger (118) and a second aircraft belly surface skin heat exchanger (119),
the loop heat pipe evaporator (202) is mounted on the hydraulic component,
the liquid storage device (201) is arranged at the front end of the liquid inlet of the loop heat pipe evaporator (202), the steam outlet of the loop heat pipe evaporator (202) is connected with one end of a first steam pipe (203),
connecting the other end of the first steam pipe (203) with a condenser (204) and a second steam pipe (205) of the inner panel of the first aircraft surface skin,
connecting a second steam pipe (205) to a condenser (206) of a second aircraft skin outer panel,
connecting a condenser (206) of a second aircraft skin outer panel to one end of a second liquid return conduit (207),
connecting the other end of the second liquid return pipe (207) to a condenser (204) of the first aircraft skin inner panel and to the first liquid return pipe (208),
the outlet end of the first liquid return pipe (208) is connected with the liquid reservoir (201),
a branch provided with a first throttle valve (103) is arranged in front of the hydraulic component and connected to a hydraulic oil tank (101).
6. The distributed aircraft thermal management method of claim 5, comprising:
and (3) performing heat exchange between the ram air and the hydraulic oil in the circulation of the hydraulic system by using a hydraulic oil-air heat exchanger (111) so as to cool the hydraulic oil, wherein the cooled hydraulic oil is used for cooling airborne equipment.
7. The distributed aircraft thermal management method of claim 5, wherein:
the condenser (112, 113, 114) is used for exchanging heat with the hydraulic oil through an evaporation refrigeration cycle, cooling the aircraft-mounted equipment, and transmitting the heat of the cycle to heat sink hydraulic oil to be taken away by the hydraulic oil.
8. The distributed aircraft thermal management method of claim 5, wherein:
the hydraulic oil tank (101) is an immersed hydraulic oil tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201811175029.8A CN109367801B (en) | 2018-10-09 | 2018-10-09 | Distributed airplane thermal management system and method based on airplane hydraulic system and micro evaporative refrigeration cycle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811175029.8A CN109367801B (en) | 2018-10-09 | 2018-10-09 | Distributed airplane thermal management system and method based on airplane hydraulic system and micro evaporative refrigeration cycle |
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| CN109367801B true CN109367801B (en) | 2020-09-18 |
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| CN116280208A (en) * | 2021-09-06 | 2023-06-23 | 南京工业大学 | Aircraft environment control system for supplying hot water by utilizing air circulation |
| CN114435582A (en) * | 2022-01-10 | 2022-05-06 | 南京理工大学 | Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure |
| CN115013156B (en) * | 2022-06-27 | 2022-12-13 | 哈尔滨工业大学 | Near-field thermophotovoltaic power generation device for recovering waste heat of aviation turbojet engine |
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