CN215922561U

CN215922561U - Aircraft and air conditioning system thereof

Info

Publication number: CN215922561U
Application number: CN202122381300.7U
Authority: CN
Inventors: 胡华智; 陈肯镇; 陈南山; 陈佳龙
Original assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Current assignee: Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date: 2021-09-29
Filing date: 2021-09-29
Publication date: 2022-03-01
Anticipated expiration: 2031-09-29

Abstract

The application discloses airborne vehicle and air conditioning system thereof belongs to airborne vehicle technical field. The aircraft air conditioning system comprises a box body, an integrated condensing module, an integrated evaporating module and an electric compressor, wherein the integrated condensing module, the integrated evaporating module and the electric compressor are arranged in the box body; the integrated condensation module comprises a condenser and an axial flow fan, and the integrated evaporation module comprises an evaporator and a blower; the electric control device is used for communicating with the ground control end and/or the control panel of the aircraft and controlling and adjusting the air conditioning system according to the control instruction of the user. The embodiment of the utility model simplifies the complexity of installation, effectively saves space and lightens weight by integrating and modularizing all split type components.

Description

Aircraft and air conditioning system thereof

Technical Field

The present application relates to the field of aircraft technology, and more particularly, it relates to aircraft and air conditioning systems therefor.

Background

At present, an air conditioning system of an intelligent manned aircraft or a helicopter is generally a split-type installation structure, namely, all split-type components are assembled together one by one, and an engine is used as a power source to maintain the circulating flow of a refrigerant in a pipeline, so that the heat dissipation and the temperature reduction are performed on a cabin. The split air-conditioning system has more components, the structure is complex, the rapid installation is not facilitated, and the connector is easy to oxidize for a long time and loosen by vibration. And the air conditioning system is huge, so that the space utilization rate of the aircraft is reduced, and the overall weight of the aircraft is increased.

SUMMERY OF THE UTILITY MODEL

In view of the above, the present application provides an aircraft and an air conditioning system thereof, so as to simplify the installation complexity of the air conditioning system of the aircraft and reduce the volume and weight of the air conditioning system.

According to one aspect of the utility model, there is provided an aircraft air conditioning system comprising a cabinet, the air conditioning system comprising: the integrated condensation module, the integrated evaporation module and the electric compressor are arranged in the box body;

the integrated condensation module comprises a condenser and an axial flow fan, wherein the condenser is used for changing gaseous refrigerants into liquid refrigerants, and the axial flow fan is used for supplying air and reducing temperature;

the integrated evaporation module comprises an evaporator and a blower, wherein the evaporator is used for changing liquid refrigerant into gaseous refrigerant and generating cold air, and the blower is used for introducing air into the box body and introducing the cold air into a cabin of the aircraft;

the electric compressor is connected with both the condenser and the evaporator and is used for converting the gaseous refrigerant generated by the evaporator into the gaseous refrigerant and sending the gaseous refrigerant into the condenser;

and the electric control device is used for communicating with the ground control end and/or a control panel of the aircraft and controlling and adjusting the air conditioning system according to the control instruction of the user.

Preferably, the box is assembled with dismantled and assembled the mode by bottom plate and polylith curb plate, and the polylith curb plate has all been seted up a plurality of and is used for the heat dissipation and subtract heavy through-hole.

Preferably, a first air inlet is formed in the position, corresponding to the condenser, of the box body, and a first dust cover is installed outside the first air inlet; and/or more than one second air inlet is formed in the position, corresponding to the evaporator, on the box body, and a second dust cover is installed outside the second air inlet.

Preferably, a cold air pipe is arranged on the box body corresponding to the blower, the blower generates suction force to suck air from the second air inlet, the air is cooled by heat absorption of the evaporator to become cold air, and the cold air pipe supplies the cold air to a cabin of the manned aircraft.

Preferably, the air conditioning system further includes a filtering device installed in a connection pipe between the condenser and the motor-driven compressor, and in a connection pipe between the evaporator and the motor-driven compressor.

Preferably, the electric compressor is arranged at the inner bottom of the box body, and a rubber ring is arranged between the electric compressor and the box body.

Preferably, a water receiving tray and a water outlet pipe are arranged below the evaporator in the box body.

Preferably, the axial fan is self-contained with a dust cover, and/or the blower is a dual-shaft blower.

Preferably, the electric compressor comprises a fixed frequency compressor or an inverter compressor.

According to another aspect of the present invention, there is provided an aircraft comprising a fuselage, a cockpit, a trunk, a propeller system, an air conditioning system as described above, and a control panel, the air conditioning system being mounted in the trunk, cooling air, and sending the cooled air to the cockpit.

According to the aircraft air conditioning system disclosed by the embodiment of the utility model, all split components of the air conditioning system are integrated and modularized, so that the complexity of installation is simplified, and the air conditioning system can be quickly and conveniently installed; and the electric compressor is adopted to provide a power source, so that the space is effectively saved, and the overall weight of the aircraft is reduced.

Drawings

Fig. 1 is a schematic structural diagram of an air conditioning system of an aircraft according to an embodiment.

Fig. 2 is a schematic structural diagram of an integrated condensing module, an integrated evaporating module and an electric compressor of an air conditioning system of an aircraft according to an embodiment.

Fig. 3 is a partially exploded view of a housing of an air conditioning system of an aircraft according to an embodiment of the utility model.

In the figure: 1. a box body; 11. a base plate; 12. a side plate; 121. a through hole; 13. a first air inlet; 14. a second air inlet; 15. a water pan; 16. a water outlet pipe; 2. an integrated condensing module; 21. a condenser; 22. an axial flow fan; 3. an integrated evaporation module; 31. an evaporator; 32. a blower; 4. an electric compressor; 5. an electric control device; 6. a first dust cover; 7. a cold air pipe; 8. a second dust cover; 9. a filtration device; 100. a rubber ring.

Detailed Description

In order to make the technical problems, technical solutions and advantageous effects to be solved by the present application clearer and clearer, the present application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.

Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

Example one

The present embodiment provides an aircraft air conditioning system that is installed in a trunk, cools air, and sends the cooled air into a cabin. As shown in fig. 1 and 2, the air conditioning system includes a cabinet 1, and an integrated condensing module 2, an integrated evaporating module 3, an electric compressor 4, and an electric control device 5 placed in the cabinet. The integrated condensing module 2 includes a condenser 21 and an axial fan 22, the condenser 21 is used for changing the gaseous refrigerant into the liquid refrigerant, and the axial fan 22 is used for supplying air and cooling.

The integrated evaporator module 3 comprises an evaporator 31 and a blower 32, the evaporator 32 being intended to convert liquid refrigerant into gaseous refrigerant and to generate cold air, the blower 32 being intended to introduce air into the interior of the box and to introduce cold air into the cabin of the aircraft.

The electric compressor 4 is connected with both the integrated condensation module 2 and the integrated evaporation module 3, and is used for changing the gaseous refrigerant generated by the integrated evaporation module 3 into the gaseous refrigerant and sending the gaseous refrigerant into the integrated condenser 2.

And the electric control device 5 is used for communicating with the ground control end and/or a control panel of the aircraft and controlling and adjusting the air conditioning system according to a control command of a user.

In other embodiments, the enclosure 1 may not be part of the air conditioning system, but may be part of the equipment in which the air conditioning system is installed, such as a passenger aircraft. Relevant parts of the integrated condensation module 2 adopt a modularized integrated design and are assembled together in advance, the integrated condensation module 2 comprises a condenser 21 and an axial flow fan 22, the condenser 21 is used for changing gaseous refrigerants into liquid refrigerants, and the axial flow fan 22 is used for air supply and temperature reduction. The relevant components of the integrated evaporation module 3 are assembled in advance, using a modular integrated design, the integrated evaporation module 3 comprising an evaporator 31 for changing a liquid refrigerant into a gaseous refrigerant and generating cold air, and a blower 32 for introducing air into the box and for introducing cold air into the passenger aircraft cabin. In the assembly process, both the condenser 21 and the evaporator 31 are connected to the electric compressor 4, and the electric compressor 4 is used for consuming power to change the low-temperature and low-pressure gaseous refrigerant generated in the evaporator 31 into a high-temperature and high-pressure gaseous refrigerant and sending the gaseous refrigerant into the condenser 21. The electric compressor 4 can adopt a fixed-frequency compressor (namely a fixed-speed compressor), and the temperature is adjusted by controlling the start, stop and frequency of the compressor; an inverter compressor may also be used, the temperature being regulated by controlling the frequency of the compressor. Compared with other power sources, the electric compressor 4 has smaller volume and lighter weight, and under the condition of ensuring the performance, the electric compressor 4 is adopted to save space relatively and reduce the whole weight effectively.

In the present embodiment, the integrated condensing module 2, the integrated evaporating module 3 and the motor-driven compressor 4 are all installed in the case 1. The electric control device 5 is used for being connected with a control system of the manned aircraft, the electric control device 5 can be installed outside the box body 1, the electric control device 5 can be maintained independently without disassembling and assembling the box body 1, and the internal space of the box body 1 can be better utilized to properly reduce the internal volume of the box body 1. Of course, the electronic control device 5 may be installed in the cabinet 1. The electric control device 5 comprises a communication module, the communication module is preferably a wireless communication module, specifically, wireless communication modes such as WIFI, 4G and/or 5G are adopted, communication connection is established between the electric control device 5 and the temperature and humidity sensor, the ground control end and/or the aircraft control panel, so that a user control instruction is obtained, the air conditioning system is controlled and adjusted according to the user control instruction, and the comfort level of a user taking the manned aircraft is improved.

In this embodiment, the ground control terminal includes, but is not limited to, a ground dispatch system, a user terminal (such as a tablet computer or a mobile phone for controlling flight), and/or a client.

According to the air conditioning system in the aircraft, the split components of the air conditioning system are integrated and modularized, so that the complexity of installation is simplified, and the air conditioning system can be quickly and conveniently installed; the air conditioning system is adjusted and controlled in a wireless communication mode, and compared with a control link adopting a wired connection of plug connectors, the air conditioning system is more reliable. And the electric compressor is adopted to provide a power source, so that the space is effectively saved, and the overall weight of the aircraft is reduced.

In this embodiment, as shown in fig. 3, the box body 1 is formed by assembling the bottom plate 11 and the plurality of side plates 12 in a detachable manner, the shapes of the plurality of side plates 12 may be different from each other, and specifically, the plurality of side plates 12 and the floor plate 11 may be assembled and fixed by screws. When the air conditioning system is actually assembled, generally, the side plate 12 is installed on the bottom plate 11, the side plate 12 with one or two reserved side surfaces is not installed, then the electric compressor 4, the integrated condensation module 2, the integrated evaporation module 3 and the electric control device 5 are installed on the box body 1, then the pipeline is vacuumized, then condensing agents are added, and finally the side plate 12 with the reserved surface is installed and fixed. When maintenance is necessary, the side plate 12 can be removed and maintenance can be performed on the internal components. In this embodiment, a plurality of through holes 121 for heat dissipation and weight reduction are formed in each of the side plates 12, and the through holes 121 can play a role in heat dissipation and weight reduction, so that the weight of the box body 1 and the whole air conditioning system can be effectively reduced, the weight of the whole equipment such as a manned aircraft equipped with the air conditioning system can be effectively reduced, the energy consumption can be reduced in the flight process, and the flight distance can be prolonged.

In this embodiment, as shown in fig. 3, a first air inlet 13 is formed in a position of the box 1 corresponding to the condenser 21, and a first dust cover 6 is installed outside the first air inlet 13. In the present embodiment, the axial flow fan 22 is provided with a dust cover. Air enters from the first air inlet 13, the axial flow fan 22 discharges the air, and the axial flow fan 22 can not only draw air and supply air and accelerate heat exchange between the condenser 21 and the air, but also cool the condenser 21 and the electric compressor 4.

In the present embodiment, as shown in fig. 3, a cold air duct 7 is provided in the cabinet 1 at a position corresponding to the blower 32, and cold air is supplied to the passenger compartment of the passenger aircraft through the cold air duct 7 when the blower 32 is discharging air. In this embodiment, the box 1 is provided with a second air inlet 14 at a position corresponding to the evaporator 31, and a second dust cover 8 is installed outside the second air inlet 14. The blower 32 generates suction force to suck air from the second air inlet 14, absorbs heat by the evaporator 31 to reduce the temperature of the air to form cold air, and then supplies the cold air to the cabin of the passenger aircraft through the cold air pipe 7. The air circulation at the evaporator 31 is preferably an internal circulation, i.e. air is drawn from the cabin of the manned aircraft, cooled and then returned to the cabin, which can effectively improve the cooling efficiency. In this embodiment, two second air inlets 14 with different positions are disposed on the box body 1, and a second dust cover 8 is mounted outside each of the two second air inlets 14. In addition, the blower 32 may be a twin-shaft blower. In other embodiments, three or more second air inlets 14 with different positions may be provided on the box 1 corresponding to the position of the evaporator 31, and a corresponding second dust cover 8 is installed at each second air inlet 14. In this embodiment, a water receiving tray 15 and a water outlet pipe 16 are installed in the cabinet 1 below the evaporator 31.

In the present embodiment, as shown in fig. 2 and 3, the electric compressor 4 is mounted and fixed on the bottom plate 11, which is the inner bottom of the casing 1, and a rubber ring 100 is provided between the electric compressor 4 and the bottom plate 11 of the casing 1, and the rubber ring 100 plays a role of buffering and vibration isolation. In the present embodiment, the integrated condensing module 2 is located directly above the electric compressor 4, and the integrated evaporating module 3 is located beside the electric compressor 4. In this embodiment, the air conditioning system further includes a filtering device 9, the filtering device 9 may be installed in both a connection pipe between the condenser 21 and the electric compressor 4 and a connection pipe between the evaporator 31 and the electric compressor 4, and the filtering device 9 is used to filter the connection pipe, filter impurities inside the pipe, and avoid blocking of the pipe.

When the air conditioning system is actually assembled, a certain side plate 12 is generally installed on a bottom plate 11, the side plate 12 with one or two reserved side surfaces is not installed, then the electric compressor 4, the integrated condensation module 2, the integrated evaporation module 3 and the electric control device 5 are installed on the box body 1, then the pipeline is vacuumized, then condensing agents are added, and finally the side plate 12 with the reserved surface is installed and fixed. The blower 32 generates suction force to suck air from the second air inlet 14, absorbs heat by the evaporator 31 to reduce the temperature of the air to form cold air, and then supplies the cold air to the cabin of the passenger aircraft through the cold air pipe 7.

Example two

The embodiment also provides the manned aircraft, which comprises a fuselage, a cabin, a trunk, a control system, an air conditioning system, a lighting system, a power supply system, a propeller system, a control panel and a temperature and humidity sensor arranged in the cabin. The air conditioning system is installed in the trunk, cools the air, and sends the cooled air into the cabin.

In this embodiment, the air conditioning system is the air conditioning system of the first embodiment, and the technical features of the first embodiment are correspondingly applied in this embodiment, which is not repeated here.

In the aircraft of this embodiment, through at trunk installation integration intelligent air conditioner, it is convenient to install, has effectively saved the space of aircraft, improves space utilization to alleviate the whole weight of aircraft, energy saving consumes, improves the time of endurance.

While the present embodiments have been described with reference to the accompanying drawings, it is to be understood that the utility model is not limited to the precise embodiments described above, which are meant to be illustrative and not restrictive, and that various changes may be made therein by those skilled in the art without departing from the spirit and scope of the utility model as defined by the appended claims.

Claims

1. An aircraft air conditioning system, includes the box, its characterized in that: the air conditioning system includes: the integrated condensation module, the integrated evaporation module and the electric compressor are arranged in the box body;

the electric compressor is connected with the integrated condensation module and the integrated evaporation module and is used for converting the gaseous refrigerant generated by the integrated evaporation module into the gaseous refrigerant and sending the gaseous refrigerant into the integrated condensation module;

and the electric control device is used for communicating with the ground control end and/or a control panel of the aircraft and controlling and adjusting the air conditioning system according to a control command of a user.

2. An aircraft air conditioning system according to claim 1, characterised in that: the box body is formed by assembling a bottom plate and a plurality of side plates in a detachable mode, and the side plates are provided with a plurality of through holes for heat dissipation and weight reduction.

3. An aircraft air conditioning system according to claim 1, characterised in that: a first air inlet is formed in the position, corresponding to the condenser, of the box body, and a first dust cover is installed outside the first air inlet; and/or more than one second air inlet is formed in the position, corresponding to the evaporator, of the box body, and a second dust cover is installed outside the second air inlet.

4. An aircraft air conditioning system according to claim 3, wherein: and a cold air pipe is arranged on the box body corresponding to the blower, the blower generates suction force to suck air from the second air inlet, the air is cooled into cold air after being absorbed by the evaporator, and the cold air pipe provides the cold air for a cabin of the manned aircraft.

5. Aircraft air conditioning system according to any of claims 1 to 4, characterized in that: the air conditioning system further includes a filtering device installed in a connection pipe between the condenser and the motor-driven compressor, and in a connection pipe between the evaporator and the motor-driven compressor.

6. Aircraft air conditioning system according to any of claims 1 to 4, characterized in that: the electric compressor is installed at the inner bottom of the box body, and a rubber ring is arranged between the electric compressor and the box body.

7. Aircraft air conditioning system according to any of claims 1 to 4, characterized in that: and a water receiving tray and a water outlet pipe are arranged below the evaporator in the box body.

8. Aircraft air conditioning system according to any of claims 1 to 4, characterized in that: the axial flow fan is provided with a dust cover, and/or the blower is a double-shaft blower.

9. The aircraft air conditioning system of any of claims 1 to 4, the electrically powered compressor comprising a fixed frequency compressor or an inverter compressor.

10. An aircraft comprising a fuselage, a cabin, a trunk, an air conditioning system and a control panel, wherein the air conditioning system is an aircraft air conditioning system as claimed in any one of claims 1 to 8, mounted in the trunk for cooling air and delivering the cooled air to the cabin.