Aircraft ground air conditioning system and control method thereof

Abstract

The present invention discloses an aircraft ground air conditioning system and a control method thereof, relating to the field of air conditioning regulation and used to increase the air outlet modes of the aircraft ground air conditioning system. The aircraft ground air conditioning system comprises: a first air duct, a second air duct, a third air duct, a fourth air duct, a fifth air duct, a first air outlet duct, and a second air outlet duct. The first air duct is configured to introduce air. The second air duct is located downstream of the first air duct and is fluidically connected; the second air duct is configured to adjust the temperature of the air. The third air duct is located downstream of the second air duct and is fluidically connected; the third air duct is configured to adjust the pressure of the air. The fourth air duct is located downstream of the third air duct and is fluidically connected; the fourth air duct is configured to evenly distribute the air. The fifth air duct is located downstream of the fourth air duct and is fluidically connected. The first air outlet duct is located downstream of the fifth air duct and is fluidically connected. The second air outlet duct is arranged in parallel with the first air outlet duct and is independent of each other. The above scheme can achieve multiple air supply modes.

Description

Technical Field

[0001] The present invention relates to the field of air conditioning regulation, and in particular to an aircraft ground air conditioning system and a control method thereof. Background Art

[0002] Aircraft ground air conditioning systems are used to provide cooling or heating air to aircraft on the ground. Civilian aircraft come in a variety of sizes, with varying sizes and passenger capacities, and therefore varying airflow requirements. Existing aircraft ground air conditioning systems are only suitable for specific aircraft models and cannot accommodate a wide range of aircraft types. When different aircraft types are parked on the ground, the corresponding ground air conditioning systems must be replaced, significantly increasing airport construction costs. Summary of the Invention

[0003] The present invention provides an aircraft ground air conditioning system and a control method thereof, which are used to increase the air outlet modes of the aircraft ground air conditioning system.

[0004] An embodiment of the present invention provides an aircraft ground air conditioning system, comprising:

[0005] a first air duct configured to introduce air;

[0006] a second air duct, located downstream of the first air duct and in fluid communication with the first air duct; the second air duct is configured to adjust the temperature of the air;

[0007] a third air duct located downstream of the second air duct and in fluid communication with the second air duct; the third air duct being configured to adjust the pressure of the air;

[0008] a fourth air duct, located downstream of the third air duct and in fluid communication with the third air duct; the fourth air duct is configured to evenly distribute the air;

[0009] a fifth air duct, located downstream of the fourth air duct and in fluid communication with the fourth air duct; and

[0010] a first air outlet channel, located downstream of the fifth air channel and in fluid communication with the fifth air channel;

[0011] The second air outlet duct is arranged in parallel with the first air outlet duct; the second air outlet duct is located downstream of the fifth air duct and is fluidically connected to the fifth air duct; wherein the first air outlet duct and the second air outlet duct are independent and each is independent.

[0012] In some embodiments, the aircraft ground air conditioning system further comprises:

[0013] A first-stage evaporator is installed inside the second air duct; and / or

[0014] The second-stage evaporator is installed inside the second air duct; the second-stage evaporator is located downstream of the first-stage evaporator.

[0015] In some embodiments, the aircraft ground air conditioning system further comprises:

[0016] The heater is installed inside the second air duct.

[0017] In some embodiments, the aircraft ground air conditioning system further comprises:

[0018] a first fan in fluid communication with the third air duct, the first fan being configured to introduce air into the third air duct via the first air duct and the second air duct; and

[0019] The second fan is arranged separately from the first fan; the second fan is also in fluid communication with the third air duct, and the second fan is configured to introduce air into the third air duct via the first air duct and the second air duct.

[0020] In some embodiments, the first fan and the second fan are symmetrically arranged relative to a central axis of the aircraft ground air conditioning system.

[0021] In some embodiments, the first fan and the second fan are independently controlled.

[0022] In some embodiments, the aircraft ground air conditioning system further comprises:

[0023] A flow balancing plate is installed inside the fourth air duct; the flow balancing plate is provided with a first flow balancing hole and a second flow balancing hole; the arrangement density of the first flow balancing hole is greater than the arrangement density of the second flow balancing hole.

[0024] In some embodiments, an opening size of the first flow balancing hole is smaller than an opening size of the second flow balancing hole.

[0025] In some embodiments, the flow equalizing plate is divided into a first area, a second area and a third area; the first area and the second area are both provided with the first flow equalizing hole, and the third area is provided with the second flow equalizing hole; the first area faces the air outlet of the first fan, and the second area faces the air outlet of the second fan.

[0026] In some embodiments, an opening size of one end of the third air duct communicating with the second air duct is larger than an opening size of the other end of the third air duct communicating with the fourth air duct.

[0027] In some embodiments, the aircraft ground air conditioning system further comprises:

[0028] a first flexible joint, the third air duct being in fluid communication with the fourth air duct via the first flexible joint; and / or

[0029] A second flexible joint, the third air duct is fluidically connected to the fourth air duct through the second flexible joint.

[0030] In some embodiments, the aircraft ground air conditioning system further comprises:

[0031] a first air valve installed inside the fourth air duct, wherein the first air valve is configured to control the opening of the fourth air duct; and / or

[0032] The second air valve is installed inside the fifth air duct, and the second air valve is configured to control the opening of the fourth air duct.

[0033] In some embodiments, an opening size of one end of the fourth air duct in fluid communication with the third air duct is smaller than an opening size of the other end of the fourth air duct in fluid communication with the fifth air duct.

[0034] In some embodiments, the aircraft ground air conditioning system further comprises:

[0035] a third-stage evaporator, sandwiched between the fourth air duct and the fifth air duct; the third-stage evaporator is located downstream of the fourth air duct; and

[0036] The fourth-stage evaporator is sandwiched between the third-stage evaporator and the fifth air duct; the fourth-stage evaporator is located downstream of the third-stage evaporator.

[0037] An embodiment of the present invention further provides a method for controlling an aircraft ground air conditioning system, comprising the following steps:

[0038] Determine whether the required air volume is greater than the set value;

[0039] If the required air volume is greater than the set value, the first air outlet duct and the second air outlet duct of the aircraft ground air conditioning system are both opened.

[0040] In some embodiments, the aircraft ground air conditioning system control method further includes the following steps:

[0041] If the required air volume is less than or equal to the set value, the first air outlet duct and / or the second air outlet duct of the aircraft ground air conditioning system is opened.

[0042] In some embodiments, if the required air volume is greater than a set value, both the first fan and the second fan of the aircraft ground air conditioning system are operated.

[0043] In some embodiments, if the required air volume is less than or equal to a set value, one of the first fan and the second fan of the aircraft ground air conditioning system is selectively operated.

[0044] The aircraft ground air conditioning system provided by the above technical solution includes a first air duct, a second air duct, a third air duct, a fourth air duct, a fifth air duct, a first outlet air flow duct, and a second outlet air flow duct. Either the first outlet air flow duct or the second outlet air flow duct can be in an operative state, or both can be in an operative state. The aircraft ground air conditioning system has multiple air supply modes to meet the air flow requirements of aircraft with different air flow rates. This system is highly adaptable and offers a wide range of air flow adjustment, allowing it to meet the air flow requirements of different aircraft models. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0046] Figure 1 A schematic diagram of the three-dimensional structure of an aircraft ground air conditioning system provided by an embodiment of the present invention.

[0047] Figure 2 A schematic diagram of the three-dimensional structure of the third air duct of the aircraft ground air conditioning system provided by an embodiment of the present invention.

[0048] Figure 3 A schematic diagram of the three-dimensional structure of the fourth air duct of the aircraft ground air conditioning system provided by an embodiment of the present invention.

[0049] Figure 4 This is a schematic diagram of the main structure of the fourth air duct of the aircraft ground air conditioning system provided by an embodiment of the present invention.

[0050] Figure 5 A schematic diagram of the three-dimensional structure of a flow equalizing plate of an aircraft ground air conditioning system provided by an embodiment of the present invention.

[0051] Figure 6 This is a flow chart of a method for controlling an aircraft ground air conditioning system according to an embodiment of the present invention.

[0052] Reference numerals:

[0053] 1. First air duct; 2. Second air duct; 3. Third air duct; 4. Fourth air duct; 5. Fifth air duct; 6. First air outlet duct; 7. Second air outlet duct; 8. First-stage evaporator; 9. Second-stage evaporator; 10. Heater; 11. First fan; 12. Second fan; 13. Flow equalizer; 14. First flexible joint; 15. Second flexible joint; 16. First air valve; 17. Second air valve; 18. Third-stage evaporator; 19. Fourth-stage evaporator;

[0054] 101. Steam-water separator; 102. Air filter;

[0055] 131, first flow balancing hole; 132, second flow balancing hole; 133, first area; 134, second area; 135, third area;

[0056] 301, air outlet; 302, side panel; 303, access panel; 304, reinforcement beam; 305, flange plate; 306, first lifting lug; 307, access port;

[0057] 401. First sealing plate; 402. Second sealing plate; 403. End plate; 404. Air inlet; 405. Reinforcement rib; 406. Second flange plate; 407. Second lifting ear; 41. Diffusion zone; 42. Flow equalization zone; 43. Rectification zone. DETAILED DESCRIPTION

[0058] The following combination Figures 1 to 6 The technical solution provided by the present invention is described in more detail.

[0059] An embodiment of the present invention provides an aircraft ground air conditioning system for providing temperature-controlled, pressure-controlled, and purified air for various types of civil aircraft, such as the A319, A320, B737-300, B777-500, B767-700, A330-200, A330-300, B787, and A380.

[0060] The aircraft ground air conditioning system includes a first air duct 1, a second air duct 2, a third air duct 3, a fourth air duct 4, a fifth air duct 5, a first air outlet duct 6, and a second air outlet duct 7. The first air duct 1 is configured to introduce air. The second air duct 2 is located downstream of the first air duct 1 and is in fluid communication with the first air duct 1; the second air duct 2 is configured to adjust the temperature of the air. The third air duct 3 is located downstream of the second air duct 2 and is in fluid communication with the second air duct 2; the third air duct 3 is configured to adjust the pressure of the air. The fourth air duct 4 is located downstream of the third air duct 3 and is in fluid communication with the third air duct 3; the fourth air duct 4 is configured to evenly distribute the air. The fifth air duct 5 is located downstream of the fourth air duct 4 and is in fluid communication with the fourth air duct 4. The first air outlet duct 6 is located downstream of the fifth air duct 5 and is in fluid communication with the fifth air duct 5. The second air outlet duct 7 is arranged in parallel with the first air outlet duct 6; the second air outlet duct 7 is located downstream of the fifth air duct 5 and is fluidically connected to the fifth air duct 5; wherein, the first air outlet duct 6 and the second air outlet duct 7 are independent and each is independent.

[0061] The first air duct 1, the second air duct 2, the third air duct 3, the fourth air duct 4, and the fifth air duct 5 adjust the temperature and pressure of the introduced air.

[0062] To filter impurities from the air entering the first air duct 1, a water separator 101 and an air filter 102 are installed upstream of the first air duct 1. The water separator 101 separates rainwater from air; the air filter 102 filters dust and impurities from the air. After passing through the water separator 101 and air filter 102, the air enters the first air duct 1. The first air duct 1 has a rectangular parallelepiped structure.

[0063] In some embodiments, the aircraft ground air conditioning system further includes a first-stage evaporator 8 and a second-stage evaporator 9. The first-stage evaporator 8 is installed inside the second air duct 2. The second-stage evaporator 9 is installed inside the second air duct 2; the second-stage evaporator 9 is located downstream of the first-stage evaporator 8.

[0064] The first stage evaporator 8 and the second stage evaporator 9 are used for dehumidification and cooling. By using the first stage evaporator 8 and the second stage evaporator 9 as two-stage evaporators, the dehumidification and cooling effects are better.

[0065] In some embodiments, the aircraft ground air conditioning system further includes a heater 10. The heater 10 is installed inside the second air duct 2. The heater 10 is specifically an electric heater 10, which is used to heat the airflow when the ambient temperature is low.

[0066] In some embodiments, the aircraft ground air conditioning system further includes a first fan 11 and a second fan 12. The first fan 11 is in fluid communication with the third air duct 3 and is configured to introduce air into the third air duct 3 via the first air duct 1 and the second air duct 2. The second fan 12 is arranged separately from the first fan 11 and is also in fluid communication with the third air duct 3 and is configured to introduce air into the third air duct 3 via the first air duct 1 and the second air duct 2. At least one of the first fan 11 and the second fan 12 is a high-pressure variable-frequency centrifugal fan, which is the power source for driving the airflow and has a built-in anti-reverse function.

[0067] In some embodiments, the first fan 11 and the second fan 12 are independently controlled. The first fan 11 and the second fan 12 each operate independently. When only the first fan 11 or only the second fan 12 is operating, this is referred to as a single-fan operating state. This single-fan operating state prevents air supply short-circuits and energy loss. When the first fan 11 and the second fan 12 operate simultaneously, this is referred to as a dual-fan system. The first fan 11 and the second fan 12 can rotate and serve as backup for each other, greatly improving system reliability.

[0068] In some embodiments, the first and second fans 11, 12 are arranged symmetrically with respect to the central axis of the aircraft ground air conditioning system. The main bodies of the first and second fans 11, 12 are both located outside the third air duct 3. This arrangement ensures that the structures of the first and second fans 11, 12 match those of the third air duct 3, allowing for a more rational arrangement of the various components.

[0069] See also Figure 1 In some embodiments, the opening of the third air duct 3 at one end connecting to the second air duct 2 is larger than the opening of the other end connecting to the fourth air duct 4. The third air duct 3 is generally T-shaped. Specifically, the third air duct 3 comprises two integral sections, assembled from multiple panels to form the desired shape. The first section of the third air duct 3 is generally trapezoidal in top view, while the second section is rectangular. An access cover is provided on the inclined surface of the first section. The access cover is closable and openable.

[0070] The first fan 11 and the second fan 12 are both installed on both sides of the second section of the third air duct 3. Due to the special shape of the third air duct 3, there is enough space outside both sides of the second section of the third air duct 3 to install the first fan 11 and the second fan 12.

[0071] Air outlets 301 are provided on both sides of the second section of the third air duct 3, one of which is connected to the fourth air duct 4 via a first flexible joint 14. The third air duct 3 is fluidically connected to the fourth air duct 4 via the first flexible joint 14. The first flexible joint 14 is used to connect the first fan 11 to the fourth air duct 4, eliminating manufacturing and assembly errors, transferring airflow, and reducing vibration transmission. The other air outlet 301 is fluidically connected to the fourth air duct 4 via a second flexible joint 15. The second flexible joint 15 is used to connect the second fan 12 to the fourth air duct 4, eliminating manufacturing and assembly errors, transferring airflow, and reducing vibration transmission.

[0072] The third air duct 3 performs sealing, transmission, converging, and diverting functions. It is welded together from multiple side panels 302, multiple access panels 303, several reinforcing beams 304, a first flange 305, and a first lifting lug 306. The side panels 302 and access panels 303 together form the housing of the third air duct 3. The first flange 305 increases strength and rigidity, facilitating installation and removal of the access cover; the reinforcing beams 304 increase the strength and rigidity of each surface of the air duct; and the first lifting lug 306 facilitates the handling and lifting of the third air duct 3. Two access ports 307 are provided on the third air duct 3 to facilitate maintenance of the electric heater 10.

[0073] The inlet of the third air duct 3 is fluidly connected to the second air duct 2, and the outlet of the third air duct 3 is connected to the first fan 11 and the second fan 12. The inlet is rectangular and the outlet is circular, for a total of two outlets, where the airflow changes from converging to diverging. The bottom of the inlet is lower than the bottom of the outlet, with a height difference of H. This is to promptly drain condensate to prevent it from entering the first fan 11 and the second fan 12.

[0074] See also Figures 3 to 5 In some embodiments, the opening size of one end of the fourth air duct 4 in fluid communication with the third air duct 3 is smaller than the opening size of the other end of the fourth air duct 4 in fluid communication with the fifth air duct 5 .

[0075] The fourth air duct 4 has a roughly trapezoidal, bell-shaped structure. Specifically, the fourth air duct 4 comprises a plurality of first sealing panels 401, which form a closed rectangular shape. The fourth air duct 4 also comprises a plurality of second sealing panels 402, which are assembled to form a bell-shaped structure. An end plate 403 is disposed at a portion of the second sealing panels 402, distal from the first sealing panels 401. The end plate 403 is provided with two air inlets 404, one of which is fluidically connected to the first flexible joint 14, and the other of which is fluidically connected to the second flexible joint 15.

[0076] In order to increase the structural strength of the fourth air duct 4, the fourth air duct 4 further includes a reinforcing rib 405. The reinforcing rib 405 is mounted on the first closing plate 401 and / or the second closing plate 402. The reinforcing rib 405 is fixed to the first closing plate 401 and the second closing plate 402 by welding.

[0077] In some embodiments, the aircraft ground air conditioning system further includes a flow equalizer plate 13 installed within the fourth air duct 4. The flow equalizer plate 13 is provided with first flow equalizer holes 131 and second flow equalizer holes 132. The arrangement density of the first flow equalizer holes 131 is greater than the arrangement density of the second flow equalizer holes 132. The first flow equalizer holes 131 can distribute the airflow more evenly.

[0078] In some embodiments, the opening size of the first flow balancing hole 131 is smaller than the opening size of the second flow balancing hole 132 .

[0079] In some embodiments, the flow equalizing plate 13 is divided into a first area 133, a second area 134 and a third area 135; the first area 133 and the second area 134 are both provided with a first flow equalizing hole 131, and the third area 135 is provided with a second flow equalizing hole 132; the first area 133 faces the air outlet of the first fan 11, and the second area 134 faces the air outlet of the second fan 12.

[0080] like Figure 4As shown, the flow equalizing plate 13 is a porous plate with folded edges on all sides, divided into three areas: a first area 133, a second area 134 and a third area 135. The first area 133 faces the projection area of the first fan 11, and the second area 134 faces the projection area of the second fan 12. The third area 135 is the non-fan outlet projection area. The fan outlet projection area (i.e., the first area 133 and the second area 134) is determined according to the range of the positive projection of the injection angle of the fan outlet on this flow equalizing plate 13. The first area 133 and the second area 134 are symmetrically distributed on the left and right sides of the center line. The porosity and pore size of the first flow equalizing holes 131 in the first area 133 and the second area 134 are the same, but different from the second flow equalizing holes 132 in the non-fan outlet projection area. The first flow equalizing holes 131 in the first area 133 and the second area 134 have a small pore size and a low porosity. The second flow equalizing holes 132 in the third area 135 have a large pore size and a large porosity. The equalizing plate 13 adopts the above structure, which can effectively adjust the flow rate, realize equal flow, give full play to the heat exchange capacity of the heat exchanger, improve heat exchange efficiency and achieve energy saving. Under the blocking effect of the equalizing plate 13, the wind speed is reduced, the dynamic pressure is reduced and the static pressure is increased.

[0081] The fourth air duct 4 has two air inlets and one air outlet. The distance between the air inlet and outlet of the fourth air duct 4 is set to L, and the size of L depends on the high-pressure centrifugal fan's airflow injection angle α and the fan's total pressure. If L is too large, the unit's overall dimensions will increase and the evaporator's headwind velocity will be too low; if L is too small, the headwind velocity will be too high and unevenly distributed. In short, L being too large or too small is not conducive to the evaporator's heat exchange capacity. For aircraft ground air conditioning systems, L = 900-1500mm, specifically 900mm, 1000mm, 1100mm, 1200mm, 1300mm, 1400mm, and 1500mm.

[0082] The fourth air duct 4 performs sealing, deceleration, dynamic pressure reduction, static pressure increase, flow diversion, flow balancing, flow rectification, and flow transmission. The components are positioned with the end plate upstream and the closing plates downstream, forming the duct housing. The upstream portion is funnel-shaped, while the rear portion is brick-like. U-shaped reinforcement ribs are welded to the outside of the housing to enhance the strength and rigidity of the third air duct 3, increase its pressure-bearing capacity, and prevent airflow pulsation noise.

[0083] The equalizing plate 13 is located inside the shell, dividing the fourth air duct 4 into two parts: the front part is the diffusion zone 41 and the equalizing zone 42, and the rear part is the rectifying zone 43. In the diffusion zone 41, the airflow from the first flexible joint 14 and the second flexible joint 15 first merges and converges, and then diffuses along the way, resulting in a speed reduction, a dynamic pressure reduction, and a static pressure increase; in the equalizing zone 42, a flow equalization effect occurs, and the airflow velocity distribution is adjusted through the different distributions of porosity and pore diameter. In the rectifying zone 43, after the airflow passes through the equalizing plate 13, there are many small vortices. Since there is no cross-sectional sudden change or gradual change in the turbulence, the vortices are gradually driven forward by the main airflow in the center of the equalizing hole, forming a laminar flow, and the flow reaches a uniform state on the windward side of the third-stage evaporator 18 described later. At this time, the flow velocity at each location is in the range of 1.8m / s to 2.0m / s, and the distribution is relatively uniform.

[0084] Two rectangular holes are provided on the end plate of the fourth air duct 4. The number of rectangular holes is equal to the number of the first fan 11 and the second fan 12, and the size is consistent with the flexible joint. Threaded through holes are designed around the rectangular holes, and nuts are welded at the through holes for connection with the first flexible joint 14 and the second flexible joint 15. The two rectangular holes on the end plate realize the transformation of airflow from diversion to confluence. A second flange plate 406 is welded inside the end plate 403 to increase strength and rigidity. Reinforcement ribs 405 are welded inside and outside the fourth air duct 4 to increase strength and rigidity and reduce airflow pulsation noise; and a second lifting ear 407 is welded for installation and lifting. The fourth air duct 4 is used to reduce speed, reduce dynamic pressure, increase static pressure, equalize flow, rectify, and transmit airflow.

[0085] See also Figure 1 In some embodiments, the aircraft ground air conditioning system further includes a third-stage evaporator 18 and a fourth-stage evaporator 19. The third-stage evaporator 18 is interposed between the fourth air duct 4 and the fifth air duct 5; the third-stage evaporator 18 is located downstream of the fourth air duct 4. The fourth-stage evaporator 19 is interposed between the third-stage evaporator 18 and the fifth air duct 5; the fourth-stage evaporator 19 is located downstream of the third-stage evaporator 18.

[0086] The third and fourth evaporators 18 and 19 are integrated to ensure that the capacity of each evaporator can be fully utilized regardless of whether the fan is running alone or in pairs, thereby improving energy efficiency. The third and fourth evaporators 18 and 19 are used for further dehumidification and cooling.

[0087] In some embodiments, the aircraft ground air conditioning system further includes a first damper 16. The first damper 16 is installed within the fourth air duct 4 and is configured to control the opening of the fourth air duct 4. The first damper 16 employs an existing structure and is used to control the opening and closing of the fourth air duct 4, as well as the size of the flow area.

[0088] See also Figure 1The aircraft ground air conditioning system also includes a second air valve 17. Second air valve 17 is installed within fifth air duct 5 and is configured to control the opening of fourth air duct 4. Second air valve 17 utilizes an existing structure to control the opening and closing of fifth air duct 5 and the size of its flow area.

[0089] The first air valve 16 and the second air valve 17 are controlled independently, and the change of the valve position of one valve does not affect the valve position of the other valve.

[0090] The airflow within an aircraft ground air conditioning system follows this pattern: air enters the system through the steam-water separator, where it is separated from rainwater. After passing through the filter, it enters the second duct 2, passes through the first-stage evaporator 8 and the second-stage evaporator 9 for dehumidification and cooling, then passes through the second duct 2 and the electric heater 10 before entering the third duct 3. It is then drawn into the first and second fans 11 and 12, transforming into high-pressure, low-temperature gas. The two airflows pass through their respective flexible joints and enter the fourth duct 4. After merging, they diffuse, decelerate, reduce dynamic pressure, increase static pressure, equalize flow, and undergo rectification. They then pass through the third-stage evaporator 18 and the fourth-stage evaporator 19 in a quasi-laminar flow state for further dehumidification and cooling, before entering the fifth duct 5. After passing through the fifth duct 5, the air is delivered through two sets of air ducts. Both sets of air ducts are equipped with dampers, which control the airflow path and volume by opening or closing them.

[0091] The airflow goes through a series channel before the first fan 11 and the second fan 12, and is then connected in parallel, then in series, and then in parallel again. This structure greatly simplifies the structural design and integrates each evaporator to ensure that the evaporator capacity can be fully utilized regardless of whether a single or double fan is running, thereby improving energy saving.

[0092] See also Figure 6 An embodiment of the present invention provides a method for controlling an aircraft ground air conditioning system. The method is implemented using the aircraft ground air conditioning system described in any of the above embodiments. The method includes the following steps:

[0093] First, it is determined whether the required air volume is greater than a set value, which may be a standard air volume determined by the model of the civil aircraft.

[0094] Secondly, if the required air volume is greater than the set value, the first air outlet duct 6 and the second air outlet duct 7 of the aircraft ground air conditioning system are both connected.

[0095] The above technical solution inputs the civil aircraft model and selects the standard air volume. After comparing the standard air volume with the characteristic air volume, the first fan 11 and the second fan 12 are selected for operation. The fan operating frequency is controlled according to the outdoor ambient temperature, atmospheric pressure, cabin temperature, and humidity to achieve reasonable and appropriate air supply.

[0096] In some embodiments, the aircraft ground air conditioning system control method further includes the following steps: if the required air volume is less than or equal to a set value, the first air outlet duct 6 and / or the second air outlet duct 7 of the aircraft ground air conditioning system is opened.

[0097] In some embodiments, the aircraft ground air conditioning system control method further includes the following steps: if the required air volume is greater than a set value, both the first fan 11 and the second fan 12 of the aircraft ground air conditioning system are operated.

[0098] In some embodiments, the aircraft ground air conditioning system control method further includes the following steps: if the required air volume is less than or equal to a set value, the first fan 11 and the second fan 12 of the aircraft ground air conditioning system selectively operate.

[0099] Enter the current landing aircraft model in the aircraft ground air conditioning electric control box, and the electric control system automatically selects the standard air volume and compares the standard air volume with the characteristic air volume of 8000m 3 / h for comparison, and automatically selects one of the first fan 11 and the second fan 12 for single fan operation or dual fan operation. The air conditioning control system detects parameters such as outdoor ambient temperature, atmospheric pressure, cabin temperature, relative humidity, etc., and controls the fan frequency according to the detected values to control the output air volume, thereby delivering a certain flow rate of high static pressure fresh air with a comfortable temperature to the cabin.

[0100] This air supply system is designed based on the largest aircraft ground air conditioning system, the F-type aircraft ground air conditioning system. By selecting single and dual blower functions and using variable frequency control for high-pressure centrifugal fans, one aircraft ground air conditioning system can meet the needs of all major civil aviation aircraft types. Currently, major aircraft types at civil airports both domestically and internationally include the A319, A320, B737-300, B777-500, B767-700, A330-200, A330-300, B787, and A380. This allows a single aircraft ground air conditioning system to meet the cooling (or heating) needs of an entire civil aviation airport during parking, significantly simplifying the design, selection, and management of air conditioning equipment and eliminating the hassle of transporting equipment between different aircraft bays.

[0101] Simplifying aircraft ground air conditioning equipment selection and management, improving equipment utilization: Civil aviation airports previously required different types of aircraft, including C, D, E, and F aircraft ground air conditioning systems and corresponding air supply systems, to accommodate various civil aircraft types. By implementing the technical solutions of the present invention, a single aircraft ground air conditioning system can be configured to meet the requirements of all aircraft types.

[0102] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the protection content of the present invention.

[0103] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. An aircraft ground air conditioning system, characterized in that: include: A first air duct (1) is configured to introduce air; a second air duct (2), located downstream of the first air duct (1) and in fluid communication with the first air duct (1); the second air duct (2) is configured to adjust the temperature of the air; a third air duct (3), located downstream of the second air duct (2) and in fluid communication with the second air duct (2); the third air duct (3) is configured to adjust the pressure of the air; a fourth air duct (4) located downstream of the third air duct (3) and in fluid communication with the third air duct (3); wherein the third air duct (3) is in fluid communication with the fourth air duct (4) through two air outlets (301); the fourth air duct (4) is configured to evenly distribute the air; an opening size of one end of the fourth air duct (4) in fluid communication with the third air duct (3) is smaller than an opening size of the other end of the fourth air duct (4) in fluid communication with the fifth air duct (5); The fifth air duct (5) is located downstream of the fourth air duct (4) and is in fluid communication with the fourth air duct (4); and a first air outlet duct (6), located downstream of the fifth air duct (5) and in fluid communication with the fifth air duct (5); a second air outlet duct (7) arranged in parallel with the first air outlet duct (6); the second air outlet duct (7) is located downstream of the fifth air duct (5) and is in fluid communication with the fifth air duct (5); wherein the first air outlet duct (6) and the second air outlet duct (7) are independent and each is independent; A first fan (11) is in fluid communication with the third air duct (3); a second fan (12) arranged separately from the first fan (11); and A flow balancing plate (13) is installed inside the fourth air duct (4); the flow balancing plate (13) is provided with a first flow balancing hole (131) and a second flow balancing hole (132); the arrangement density of the first flow balancing holes (131) is greater than the arrangement density of the second flow balancing holes (132); The opening size of the first flow balancing hole (131) is smaller than the opening size of the second flow balancing hole (132); The flow balancing plate (13) is divided into a first area (133), a second area (134) and a third area (135); the first area (133) and the second area (134) are both provided with the first flow balancing hole (131), and the third area (135) is provided with the second flow balancing hole (132); the first area (133) faces the air outlet of the first fan (11), and the second area (134) faces the air outlet of the second fan (12); The aircraft ground air conditioning system further comprises: a first-stage evaporator (8), installed inside the second air duct (2); and The second-stage evaporator (9) is installed inside the second air duct (2); the second-stage evaporator (9) is located downstream of the first-stage evaporator (8).

2. The aircraft ground air conditioning system according to claim 1, characterized in that: Also includes: The heater (10) is installed inside the second air duct (2).

3. The aircraft ground air conditioning system according to claim 1, wherein: The first fan (11) is configured to introduce air into the third air duct (3) via the first air duct (1) and the second air duct (2); and The second fan (12) is also in fluid communication with the third air duct (3), and the second fan (12) is configured to introduce air into the third air duct (3) via the first air duct (1) and the second air duct (2).

4. The aircraft ground air conditioning system according to claim 3, characterized in that: The first fan (11) and the second fan (12) are arranged symmetrically relative to the central axis of the aircraft ground air conditioning system.

5. The aircraft ground air conditioning system according to claim 3, characterized in that: The first fan (11) and the second fan (12) are independently controlled.

6. The aircraft ground air conditioning system according to claim 1, wherein: The opening size of one end of the third air duct (3) communicating with the second air duct (2) is larger than the opening size of the other end of the third air duct (3) communicating with the fourth air duct (4).

7. The aircraft ground air conditioning system according to claim 1, wherein: Also includes: a first flexible joint (14), wherein the third air duct (3) is in fluid communication with the fourth air duct (4) via the first flexible joint (14); and / or A second flexible joint (15), wherein the third air duct (3) is in fluid communication with the fourth air duct (4) via the second flexible joint (15).

8. The aircraft ground air conditioning system according to claim 1, wherein: Also includes: A third-stage evaporator (18) is sandwiched between the fourth air duct (4) and the fifth air duct (5); the third-stage evaporator (18) is located downstream of the fourth air duct (4); and The fourth-stage evaporator (19) is sandwiched between the third-stage evaporator (18) and the fifth air duct (5); the fourth-stage evaporator (19) is located downstream of the third-stage evaporator (18).

9. A method for controlling an aircraft ground air conditioning system, characterized in that: The method is implemented using the aircraft ground air conditioning system according to any one of claims 1 to 8, and comprises the following steps: Determine whether the required air volume is greater than the set value; If the required air volume is greater than the set value, the first air outlet duct (6) and the second air outlet duct (7) of the aircraft ground air conditioning system are both connected.

10. The aircraft ground air conditioning system control method according to claim 9, characterized in that: The following steps are also included: If the required air volume is less than or equal to the set value, the first air outlet duct (6) and / or the second air outlet duct (7) of the aircraft ground air conditioning system are opened.

11. The aircraft ground air conditioning system control method according to claim 9, characterized in that: If the required air volume is greater than the set value, both the first fan (11) and the second fan (12) of the aircraft ground air conditioning system are operated.

12. The aircraft ground air conditioning system control method according to claim 9, characterized in that: If the required air volume is less than or equal to the set value, one of the first fan (11) and the second fan (12) of the aircraft ground air conditioning system is selectively operated.

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