CN211223889U - Ground air conditioning unit for electric drive airplane - Google Patents
Ground air conditioning unit for electric drive airplane Download PDFInfo
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- CN211223889U CN211223889U CN201921680166.7U CN201921680166U CN211223889U CN 211223889 U CN211223889 U CN 211223889U CN 201921680166 U CN201921680166 U CN 201921680166U CN 211223889 U CN211223889 U CN 211223889U
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The utility model discloses a be used for electric drive aircraft ground air conditioning unit, including one-level condenser, one-level evaporimeter, centrifugal fan air inlet cover, second grade evaporation air inlet cover, second grade evaporimeter, electric heater, second grade evaporimeter play fan housing, blast valve, one-level compressor, condensation fan, second grade condenser, centrifugal fan, second grade compressor. The outlet end of the first-stage evaporator is connected with the air inlet cover of the centrifugal fan, the outlet end of the air inlet cover of the centrifugal fan is connected with the centrifugal fan, the outlet end of the centrifugal fan is connected with the inlet end of the air inlet cover of the second-stage evaporator, the outlet end of the air inlet cover of the second-stage evaporator is connected with the inlet end of the second-stage evaporator, the outlet end of the second-stage evaporator is connected with the air supply valve, and the air supply valve is communicated with the engine room through an air. According to the technical scheme, the ground air conditioning unit is high in unit energy efficiency, and each fan can be adjusted and controlled according to the environmental temperature in the specific working process, so that the temperature and humidity of the aircraft cabin can be adjusted all the year round.
Description
Technical Field
The utility model relates to an aircraft ground air conditioning unit technical field, concretely relates to be used for electric drive aircraft ground air conditioning unit to satisfy the ground air conditioning unit that cabin inside refrigerate fast or the heating requires during the aircraft transiently stops the airport.
Background
With the rapid development of economy, the number of aircrafts is continuously increased, and during the stay period of the aircrafts on the ground of an airport, the aircrafts generally need to provide power and air conditioners to meet the requirements of comfort of passengers, ventilation and ventilation in the aircraft and the like, but the aircrafts are generally supplied by aviation kerosene at present, so that the pollution is caused to the atmosphere, the oil consumption is increased, the cost is increased, and based on the increase of environmental awareness, the ground of the airport adopts a special air conditioner set to supply energy to the aircrafts, and the ground air conditioner can adopt corridor bridge power facilities to provide power to meet the air conditioner requirements in an aircraft cabin, and the conventional ground air conditioner set has high energy consumption, high noise and frequent replacement.
In view of the above-mentioned drawbacks, a ground air conditioning unit for an electrically driven aircraft is provided.
SUMMERY OF THE UTILITY MODEL
The utility model provides a be used for electric drive aircraft ground air conditioning unit adopts two and above condensing fan devices to send for the unit and air exhaust on aircraft ground air conditioner to solved current ground air conditioning unit energy consumption height, noise big, change frequent technical problem.
The utility model discloses a following technical scheme realizes:
a ground air conditioning unit for an electrically driven airplane comprises a primary condenser, a primary evaporator, a centrifugal fan air inlet cover, a secondary evaporator air outlet cover, an air supply valve, a primary compressor, a condensing fan, a secondary condenser, a centrifugal fan and a secondary compressor;
the outlet end of the first-stage evaporator is connected with the air inlet cover of the centrifugal fan, the outlet end of the air inlet cover of the centrifugal fan is connected with the centrifugal fan, the outlet end of the centrifugal fan is connected with the inlet end of the air inlet cover of the second-stage evaporator, the outlet end of the air inlet cover of the second-stage evaporator is connected with the inlet end of the second-stage evaporator, and the outlet end of the second-stage evaporator is communicated with the cabin;
the outlet end of the refrigeration pipeline of the first-stage evaporator is connected with the inlet end of the first-stage compressor, and the outlet end of the first-stage compressor is connected with the inlet end of the refrigeration pipeline of the first-stage condenser; the outlet end of the refrigeration pipeline of the second-stage evaporator is connected with the inlet end of the second-stage compressor, the outlet end of the second-stage compressor is connected with the inlet end of the refrigeration pipeline of the second-stage condenser, the outlet ends of the refrigeration pipelines of the first-stage condenser and the second-stage condenser are connected with the inlet end of the throttling element, and the outlet ends of the throttling element are respectively connected with the inlet end of the refrigeration pipeline of the first-stage evaporator and the inlet end of the refrigeration pipeline of the second.
Further, the air conditioning unit further comprises an environment temperature and humidity sensor for detecting the environment temperature in the engine room, a first-stage temperature and humidity sensor for detecting the air supply temperature and a second-stage temperature and humidity sensor, wherein the first-stage temperature and humidity sensor is arranged in a cavity of an air inlet cover of the second-stage evaporator, and the second-stage temperature and humidity sensor is arranged in a cavity of the second-stage evaporator.
Furthermore, the environment temperature and humidity sensor, the first-stage temperature and humidity sensor and the second-stage temperature and humidity sensor are respectively connected with an electrical control device, and the electrical control device is respectively connected with the first-stage compressor and the second-stage compressor.
Furthermore, the air conditioning unit further comprises an air filter and an electric heater, wherein outside air enters the air filter, the outlet end of the air filter is connected with the inlet end of the first-stage evaporator, the outlet end of the first-stage evaporator is connected with the inlet end of the centrifugal fan air inlet cover, the outlet end of the centrifugal fan air inlet cover is connected with the inlet end of the centrifugal fan, low-temperature air is compressed by the centrifugal fan to become low-temperature high-pressure air, the low-temperature high-pressure air enters the second-stage evaporator air inlet cover, the second-stage evaporator air inlet cover is connected with the second-stage evaporator, the outlet end of the second-stage evaporator is sequentially connected with an external air receiving pipe through the electric heater, the second-stage evaporator air.
Furthermore, the blast valve is arranged on an external wind receiving pipe communicated with the air outlet cover of the secondary evaporator and the aircraft cabin.
Further, the primary temperature and humidity sensor and the secondary temperature and humidity sensor are identical in structure.
Furthermore, the aircraft ground air conditioning unit also comprises a condensing fan, wherein the inlet end of the primary condenser and the inlet end of the secondary condenser are both connected with the condensing fan, and the refrigerant in the primary condenser and the refrigerant in the secondary condenser are cooled by the air sucked in the condensing fan.
The working principle is as follows:
the air conditioning unit can realize temperature and humidity adjustment on the aircraft cabin, namely, the temperature of the aircraft cabin is reduced in summer, the aircraft cabin is ventilated in transitional seasons, and the heat supply function of the aircraft cabin is realized in winter.
Refrigerating operation of the unit in summer: the outside high-temperature and high-humidity air is subjected to dust removal and impurity removal treatment by an air filter and is changed into low-temperature and low-humidity fresh air through cooling and dehumidifying treatment by a primary evaporator. The low-temperature air is sucked by the centrifugal fan through the air inlet cover of the centrifugal fan, the low-temperature air is compressed by the centrifugal fan to become low-temperature high-pressure air, the low-temperature high-pressure air is output to the air inlet cover of the secondary evaporator, and then the low-temperature high-pressure air is further cooled and dehumidified through the secondary evaporator, so that the temperature and the humidity of the air are processed to be low-temperature dry fresh air meeting the setting requirements of the.
The low-temperature dry air is sent into the airplane cabin through the electric heater, the secondary evaporator air outlet cover, the air supply air valve and the external connecting air pipe. The liquid refrigerants in the first-stage evaporator and the second-stage evaporator respectively absorb the heat of the air to become gas, the gas is respectively sucked by the first-stage compressor and the second-stage compressor and is compressed into refrigerant gas with high temperature, and the refrigerant gas is respectively discharged into the first-stage condenser and the second-stage condenser. The high-temperature and high-pressure refrigerant in the first-stage condenser and the second-stage condenser is cooled into a medium-temperature and high-pressure liquid refrigerant by air sucked by the condensing fan, and the medium-temperature and high-pressure liquid refrigerant is reduced in pressure by the throttling element and then is changed into a low-temperature and low-pressure liquid refrigerant to enter the first-stage evaporator 3 and the second-stage evaporator respectively. The liquid refrigerants in the first-stage evaporator and the second-stage evaporator respectively absorb the heat of the air to become gas, and the gas is respectively sucked by the first-stage compressor and the second-stage compressor. The temperature and the humidity in the aircraft cabin are controlled within a set range through the repeated circulation.
And (3) operating the unit in transitional seasons: when the ambient temperature is higher, the unit can be according to the humiture that sets for in the cabin and the ambient temperature that ambient temperature and humidity sensor detected carry out the comparison, then according to the air supply temperature that one-level humiture sensor and second grade humiture sensor detected, to the compressor of every level through adding the deloading operation, the increase and decrease operation of number is opened to the condensing fan, makes the humiture in the cabin maintain throughout and sets for the within range. When the environment temperature is lower, only the centrifugal fan is started, the low-temperature air outside is subjected to dust removal and impurity removal treatment through the filter, is sucked by the centrifugal fan through the centrifugal fan air inlet cover of the primary evaporator, is compressed into low-temperature high-pressure air through the centrifugal fan, is output to the secondary evaporator air inlet cover, and is sent into an airplane cabin through the electric heater, the secondary evaporator air outlet cover, the air supply valve and the external connecting air pipe.
Heating operation in winter: the machine set only starts the centrifugal fan and the electric heater. The fresh low-temperature air outside is subjected to dust removal and impurity removal treatment through a filter, is sucked by a centrifugal fan through a centrifugal fan air inlet cover through a primary evaporator 3, is compressed into low-temperature high-pressure air through the centrifugal fan and is output to a secondary evaporator air inlet cover, the low-temperature air is heated through an electric heater and is changed into high-temperature air, and the high-temperature air is sent into an airplane cabin through a secondary evaporator air outlet cover, an air supply air valve and an external connecting air pipe.
Compared with the prior art, the utility model, following advantage and beneficial effect have:
(1) according to the technical scheme, the aircraft ground air conditioning unit is high in unit energy efficiency, and each fan can be adjusted and controlled according to the ambient temperature in the specific working process.
(2) The aircraft ground air conditioning unit can solve the problem of movement of the aircraft ground air conditioning unit for supplying cold and heat to the cabin due to fixed installation of the unit.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of embodiment 1;
wherein: 1-a first-stage condenser, 2-an air filter, 3-a first-stage evaporator, 4-a centrifugal fan air inlet cover, 5-a second-stage evaporator air inlet cover, 6-a second-stage evaporator, 7-an electric heater, 8-a second-stage evaporator air outlet cover, 9-an air supply valve, 10-a first-stage compressor, 11-a condensing fan, 12-a second-stage condenser, 13-a centrifugal fan, 14-a second-stage compressor, 15-an electric control device, 16-a second-stage temperature and humidity sensor, 17-a first-stage temperature and humidity sensor and 18-an environment temperature and humidity sensor.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in detail with reference to the following embodiments, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not intended as limitations of the present invention.
Example 1:
as shown in fig. 1 and 2, a ground air conditioning unit for an electrically driven aircraft includes a primary condenser 1, a primary evaporator 3, a centrifugal fan air inlet cover 4, a secondary evaporator air inlet cover 5, a secondary evaporator 6, a secondary evaporator air outlet cover 8, a blast valve 9, a primary compressor 10, a condensing fan 11, a secondary condenser 12, a centrifugal fan 13, and a secondary compressor 14;
the outlet end of the first-stage evaporator 3 is connected with the air inlet cover 4 of the centrifugal fan, the outlet end of the air inlet cover 4 of the centrifugal fan is connected with the centrifugal fan 13, the outlet end of the centrifugal fan 13 is connected with the inlet end of the air inlet cover 5 of the second-stage evaporator, the outlet end of the air inlet cover 5 of the second-stage evaporator is connected with the inlet end of the second-stage evaporator 6, and the outlet end of the second-stage evaporator 6 is communicated with the cabin;
the outlet end of the refrigeration pipeline of the first-stage evaporator 3 is connected with the inlet end of a first-stage compressor 10, and the outlet end of the first-stage compressor 10 is connected with the inlet end of the refrigeration pipeline of the first-stage condenser 1; the outlet end of the refrigeration pipeline of the second-stage evaporator 6 is connected with the inlet end of a second-stage compressor 14, the outlet end of the second-stage compressor 14 is connected with the inlet end of the refrigeration pipeline of a second-stage condenser 12, the outlet ends of the refrigeration pipelines of the first-stage condenser 1 and the second-stage condenser 12 are both connected with the inlet ends of throttling elements, and the outlet ends of the throttling elements are respectively connected with the inlet end of the refrigeration pipeline of the first-stage evaporator 3 and the inlet end of the refrigeration pipeline of the second-.
The aircraft air conditioning unit further comprises an environment temperature and humidity sensor 18 for detecting the environment temperature in the cabin, a first-stage temperature and humidity sensor 17 for detecting the air supply temperature and a second-stage temperature and humidity sensor 16, wherein the first-stage temperature and humidity sensor 17 is arranged in a cavity of the second-stage evaporator air inlet cover 5, and the second-stage temperature and humidity sensor 16 is arranged in a cavity of the second-stage evaporator air outlet cover 8.
The environment temperature and humidity sensor 18, the first-stage temperature and humidity sensor 17 and the second-stage temperature and humidity sensor 16 are all connected with the electric control device 15, and the electric control device 15 is respectively connected with the first-stage compressor 10 and the second-stage compressor 14.
The aircraft ground air conditioning unit further comprises an air filter 2 and an electric heater 7, wherein outside air enters the air filter 2, the outlet end of the air filter 2 is connected with the inlet end of the first-stage evaporator 3, the outlet end of the first-stage evaporator 3 is connected with the inlet end of the centrifugal fan air inlet cover 4, the outlet end of the centrifugal fan air inlet cover 4 is connected with the inlet end of the centrifugal fan 13, low-temperature air is compressed by the centrifugal fan 13 to become low-temperature high-pressure air which enters the second-stage evaporator air inlet cover 5, the outlet end of the second-stage evaporator air inlet cover 5 is connected with the inlet end of the electric heater 7, the outlet end of the electric heater 7 is sequentially connected with an external air receiving pipe through the second-stage evaporator air outlet cover 8 and the air supply valve 9.
The air supply valve 9 is arranged on an external air receiving pipe communicated with the air outlet cover 8 of the secondary evaporator and the aircraft cabin.
The primary temperature and humidity sensor 17 and the secondary temperature and humidity sensor 16 are identical in structure.
The aircraft ground air conditioning unit further comprises a condensing fan 11, the inlet end of the first-stage condenser 1 and the inlet end of the second-stage condenser 12 are both connected with the condensing fan 11, and the refrigerant in the first-stage condenser 1 and the refrigerant in the second-stage condenser 12 are cooled by the air sucked in the condensing fan 11.
The specific operation process of the ground air conditioning unit for electric drive described in this embodiment is as follows:
1) refrigerating operation of the unit in summer: the outside high-temperature and high-humidity air is subjected to dust removal and impurity removal treatment by the air filter 2 and is changed into low-temperature and low-humidity fresh air through the temperature reduction and dehumidification treatment of the primary evaporator 3. The low-temperature air is sucked by the centrifugal fan 13 through the centrifugal fan air inlet cover 4, the low-temperature air is compressed into low-temperature high-pressure air through the centrifugal fan 13, the low-temperature high-pressure air is output to the secondary evaporator air inlet cover 5, the temperature and the humidity of the air are further reduced and dehumidified through the secondary evaporator 6, and the low-temperature dry fresh air meeting the cabin setting requirements is processed through the temperature and the humidity of the air.
The low-temperature dry air is sent into the airplane cabin through the electric heater 7, the secondary evaporator air outlet cover 8, the air supply air valve 9 and the external connecting air pipe. The liquid refrigerant in the first-stage evaporator 3 and the second-stage evaporator 6 absorbs heat of air to become gas, and the gas is sucked by the first-stage compressor 10 and the second-stage compressor 14, respectively, and is compressed into refrigerant gas with high temperature, and is discharged into the first-stage condenser 1 and the second-stage condenser 12, respectively. The high-temperature and high-pressure refrigerant in the primary condenser 1 and the secondary condenser 12 is cooled into a medium-temperature and high-pressure liquid refrigerant by air sucked by a condensing fan, and the medium-temperature and high-pressure liquid refrigerant is reduced in pressure by a throttling element and then becomes a low-temperature and low-pressure liquid refrigerant to enter the primary evaporator 3 and the secondary evaporator 6 respectively. The liquid refrigerant in the first-stage evaporator 3 and the second-stage evaporator 6 absorbs heat of air and turns into gas, which is sucked by the first-stage compressor 10 and the second-stage compressor 14, respectively. The temperature and the humidity in the aircraft cabin are controlled within a set range through the repeated circulation.
2) And (3) operating the unit in transitional seasons: when the ambient temperature is higher, the unit can compare with the ambient temperature that ambient temperature and humidity sensor 18 detected according to the humiture that sets for in the cabin, then according to the air supply temperature that first order humiture sensor 17 and second grade humiture sensor 16 detected, to the compressor of each level through the increase and decrease operation of loading, the increase and decrease operation of the number is opened to the condensing fan, makes the humiture in the cabin maintain the within range of setting for all the time. When the ambient temperature is low, only the centrifugal fan 13 is turned on.
The low-temperature air outside is subjected to dust removal and impurity removal treatment through the filter 2, is sucked by the centrifugal fan 13 through the centrifugal fan air inlet cover 4 through the primary evaporator 3, is compressed into low-temperature high-pressure air through the centrifugal fan 13, is output to the secondary evaporator air inlet cover 5, and is sent to an airplane cabin through the electric heater 7, the secondary evaporator air outlet cover 8, the air supply valve 9 and an external connecting air pipe.
3) Heating operation in winter: the unit only starts the centrifugal fan 13 and the electric heater 7. Fresh low-temperature air outside is subjected to dust removal and impurity removal treatment through a filter 2, is sucked into a centrifugal fan 13 through a centrifugal fan air inlet cover 4 through a primary evaporator 3, is compressed into low-temperature high-pressure air through the centrifugal fan 13 and is output to a secondary evaporator air inlet cover 5, the low-temperature air is heated through an electric heater 7 and is changed into high-temperature air, and the high-temperature air is sent into an airplane cabin through a secondary evaporator air outlet cover 8, an air supply valve 9 and an external connecting air pipe.
According to the embodiment, the temperature of the aircraft cabin is reduced in summer, the aircraft cabin is ventilated in transitional seasons, and the heat of the aircraft cabin is supplied in winter, so that the temperature and humidity of the aircraft cabin can be regulated all the year round.
The specific structures and operating principles of the first-stage condenser 1, the first-stage evaporator 3, the centrifugal fan air inlet cover 4, the second-stage evaporator air inlet cover 5, the second-stage evaporator 6, the electric heater 7, the second-stage evaporator air outlet cover 8, the air supply valve 9, the first-stage compressor 10, the condensing fan 11, the second-stage condenser 12, the centrifugal fan 13, the second-stage compressor 14, the electric control device 15, the second-stage temperature and humidity sensor 16, the first-stage temperature and humidity sensor 17, and the environmental temperature and humidity sensor 18 in this embodiment are well known to those skilled in the art, and will not be described in detail.
The above-mentioned embodiments further describe the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the scope of the present invention, which is within the spirit and principle of the present invention. Any modifications, equivalent substitutions, improvements and the like made by the method are all included in the protection scope of the invention.
Claims (7)
1. An air conditioning assembly for an electrically powered aircraft ground, characterized by: the system comprises a primary condenser (1), a primary evaporator (3), a centrifugal fan air inlet cover (4), a secondary evaporator air inlet cover (5), a secondary evaporator (6), a secondary evaporator air outlet cover (8), an air supply valve (9), a primary compressor (10), a secondary condenser (12), a centrifugal fan (13) and a secondary compressor (14);
the outlet end of the first-stage evaporator (3) is connected with the air inlet cover (4) of the centrifugal fan, the outlet end of the air inlet cover (4) of the centrifugal fan is connected with the centrifugal fan (13), the outlet end of the centrifugal fan (13) is connected with the inlet end of the air inlet cover (5) of the second-stage evaporator, the outlet end of the air inlet cover (5) of the second-stage evaporator is connected with the inlet end of the second-stage evaporator (6), and the outlet end of the second-stage evaporator (6) is communicated with the cabin;
the outlet end of a refrigeration pipeline of the first-stage evaporator (3) is connected with the inlet end of a first-stage compressor (10), and the outlet end of the first-stage compressor (10) is connected with the inlet end of the refrigeration pipeline of the first-stage condenser (1); the outlet end of a refrigeration pipeline of the secondary evaporator (6) is connected with the inlet end of the secondary compressor (14), the outlet end of the secondary compressor (14) is connected with the inlet end of the refrigeration pipeline of the secondary condenser (12), the outlet ends of the refrigeration pipelines of the primary condenser (1) and the secondary condenser (12) are both connected with the inlet ends of throttling elements, and the outlet ends of the throttling elements are respectively connected with the inlet end of the refrigeration pipeline of the primary evaporator (3) and the inlet end of the refrigeration pipeline of the secondary evaporator (6).
2. An electrically driven aircraft ground air conditioning unit as claimed in claim 1, wherein: the air conditioning unit further comprises an environment temperature and humidity sensor (18) used for detecting the environment temperature in the cabin, a first-stage temperature and humidity sensor (17) used for detecting the air supply temperature and a second-stage temperature and humidity sensor (16), wherein the first-stage temperature and humidity sensor (17) is arranged in a cavity of the second-stage evaporator air inlet cover (5), and the second-stage temperature and humidity sensor (16) is arranged in a cavity of the second-stage evaporator (6).
3. An electrically driven aircraft ground air conditioning unit as claimed in claim 2, wherein: the environment temperature and humidity sensor (18), the first-stage temperature and humidity sensor (17) and the second-stage temperature and humidity sensor (16) are respectively connected with the electric control device (15), and the electric control device (15) is respectively connected with the first-stage compressor (10) and the second-stage compressor (14).
4. An electrically driven aircraft ground air conditioning unit as claimed in claim 3, wherein: the air conditioning unit further comprises an air filter (2) and an electric heater (7), external air enters the air filter (2), the outlet end of the air filter (2) is connected with the inlet end of the first-stage evaporator (3), the outlet end of the first-stage evaporator (3) is connected with the inlet end of the centrifugal fan air inlet cover (4), the outlet end of the centrifugal fan air inlet cover (4) is connected with the inlet end of the centrifugal fan (13), low-temperature air is compressed into low-temperature high-pressure air through the centrifugal fan (13) and enters the second-stage evaporator air inlet cover (5), the second-stage evaporator air inlet cover (5) is connected with the second-stage evaporator (6), the outlet end of the second-stage evaporator (6) is sequentially connected with the electric heater (7), the second-stage evaporator air outlet cover (8), an air supply valve (9) is connected with an external air receiving pipe, and the external air.
5. An electrically driven aircraft ground air conditioning unit according to claim 4, characterised in that: and the air supply valve (9) is arranged on an external air receiving pipe communicated with the air outlet cover (8) of the secondary evaporator and the aircraft cabin.
6. An electrically driven aircraft ground air conditioning unit according to claim 4, characterised in that: the primary temperature and humidity sensor (17) and the secondary temperature and humidity sensor (16) are identical in structure.
7. An electrically driven aircraft ground air conditioning unit as claimed in claim 1, wherein: the aircraft ground air conditioning unit further comprises a condensing fan (11), the inlet end of the primary condenser (1) and the inlet end of the secondary condenser (12) are both connected with the condensing fan (11), and the refrigerant in the primary condenser (1) and the refrigerant in the secondary condenser (12) are cooled by the sucked air in the condensing fan (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921680166.7U CN211223889U (en) | 2019-10-09 | 2019-10-09 | Ground air conditioning unit for electric drive airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921680166.7U CN211223889U (en) | 2019-10-09 | 2019-10-09 | Ground air conditioning unit for electric drive airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211223889U true CN211223889U (en) | 2020-08-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921680166.7U Active CN211223889U (en) | 2019-10-09 | 2019-10-09 | Ground air conditioning unit for electric drive airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211223889U (en) |
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2019
- 2019-10-09 CN CN201921680166.7U patent/CN211223889U/en active Active
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