Aircraft air conditioning device, aircraft with aircraft air conditioning device and control method of aircraft air conditioning device

Abstract

An aircraft air conditioning device includes a ram air inlet duct for introducing low temperature ram air. The aircraft air conditioning device further comprises a cold air supply pipe, and the cold air supply pipe is connected to the ram air inlet pipe so that low-temperature ram air can flow into the cold air supply pipe; the radiation heat exchanger is arranged in at least one of a cabin and a cargo compartment or an equipment compartment of the aircraft, one end of the radiation heat exchanger is communicated with the cold air supply pipe, and the other end of the radiation heat exchanger is led to the outside of the aircraft. According to the aircraft air conditioning device, heat exchange is carried out mainly in a radiation heat exchange mode, noise and air blowing feeling caused by air blowing can be reduced or even eliminated, and comfort of the interior of a cockpit and the like is improved. The invention further provides an aircraft comprising the aircraft air conditioning device and a control method of the aircraft air conditioning device.

Description

Technical Field

[0001] The present application relates to the field of aircraft design, and in particular to an aircraft air conditioning device for adjusting the temperature of an interior space of an aircraft. Background Art

[0002] Aircraft are usually equipped with air conditioning devices to adjust the temperature in the interior space of the aircraft to improve the comfort of the aircraft crew and provide a suitable temperature environment for the equipment on the aircraft to ensure the normal operation of the aircraft equipment.

[0003] At present, the commonly used air conditioning method in aircraft is to use a turbo refrigeration system to adjust the temperature of the aircraft's interior space. The working principle of the turbo refrigeration system is that the turbo refrigeration system draws air from the aircraft's air source system, and the bleed air flows through the air conditioning components in the system, so that the high-temperature and high-pressure bleed air is adjusted to air conditioning supply air with appropriate flow, temperature and pressure, and then the regulated gas is transported to the cockpit, cabin and other aircraft cabins through a low-pressure duct to adjust the air temperature in the aircraft cabin.

[0004] The existing turbo refrigeration system has some problems in the application process. For example, in the cockpit, in order to balance the heat generated by the personnel and equipment, a large amount of air needs to be supplied to the cockpit. This causes a lot of noise in the cockpit due to the blowing of air, and the pilot will have a noticeable feeling of blowing air, which will reduce the pilot's comfort during the flight, affect the pilot's normal work and even affect his health, thus burying hidden dangers for the efficient and safe operation of the aircraft.

[0005] In addition, the air in the cockpit and other internal spaces of the aircraft has a high humidity content. When it comes into contact with the aircraft skin and equipment with lower temperatures, condensation will occur. The condensed water condensed on the skin and equipment will increase the flight weight of the aircraft on the one hand, and on the other hand, it will be corrosive to the equipment, resulting in a shortened service life of the equipment. In addition, the condensed water will also soak the thermal insulation and sound insulation cotton on the aircraft, causing the aircraft's thermal insulation and sound insulation performance to decrease, which will lead to an increase in the aircraft's internal heat and heat loads and noise. Condensed water can also cause mold in the skin and thermal insulation layers. In addition, there is often water dripping from the air outlet in the aircraft cabin, and a large part of the reason is also caused by the large air supply of the air conditioning system.

[0006] Therefore, there is a need to improve the structure of the aircraft's air conditioning device, which can effectively reduce the amount of air blown and improve the economy of aircraft operation. Summary of the invention

[0007] The present invention is made to solve the problems existing in the prior art mentioned above. The purpose of the present invention is to provide an aircraft air conditioning device with an improved structure, which can effectively reduce the amount of bleed air and the amount of blowing air, and improve the comfort of aircraft passengers.

[0008] The present application proposes an aircraft air conditioning device, which includes a ram air inlet pipe, which is used to introduce low-temperature ram air. In addition, the aircraft air conditioning device also includes: a cold air supply pipe, which is connected to the ram air inlet pipe so that the low-temperature ram air can flow into the cold air supply pipe; at least one radiation heat exchanger, which is arranged in at least one of the cabin, cargo hold or equipment compartment of the aircraft, one end of the radiation heat exchanger is connected to the cold air supply pipe, and the other end of the radiation heat exchanger leads to the outside of the aircraft.

[0009] Through such a structure, especially through the arrangement of the radiation heat exchanger, heat is exchanged with the interior space of the aircraft, such as the cockpit, cargo hold or equipment compartment, mainly through radiation heat exchange. In this way, it is not necessary to blow air into the interior space of the aircraft for heat exchange, thereby reducing or even eliminating the noise and blowing feeling caused by blowing, and in particular, improving the comfort inside the cockpit.

[0010] Preferably, at least one drainage hole is provided on the radiation heat exchanger. The air flow in the radiation heat exchanger will generate negative pressure in the radiation heat exchanger. Under the action of the negative pressure, when the radiation air conditioner is cooling, the surface temperature is lower than the outside air temperature. The condensed water accumulated on the surface of the radiation heat exchanger can be sucked into the radiation heat exchanger through these drainage holes and discharged to the outside of the aircraft along with the air flow. The drainage hole is preferably arranged at the bottom of the radiation heat exchanger. The condensed water will flow to the bottom of the radiation heat exchanger due to gravity, so the drainage hole arranged at the bottom helps to discharge the condensed water out of the aircraft more thoroughly.

[0011] In a specific structure, a radiation heat exchanger is provided in the cabin and the cargo hold or equipment compartment, wherein the cold air supply pipe includes a first branch pipe and a second branch pipe, the first branch pipe is connected to the radiation heat exchanger in the cabin, and the second branch pipe is connected to the radiation heat exchanger in the cargo hold or equipment compartment.

[0012] More specifically, the aircraft air conditioning device includes at least one of a first regulating valve and a second regulating valve, wherein the first regulating valve is arranged on a first branch pipe, the second regulating valve is arranged on a second branch pipe, and the second branch pipe is connected to the inlet side of the first regulating valve. By opening and closing the first and second regulating valves, the ram airflow flowing into the cabin and the cargo hold or the equipment compartment can be opened and cut off. Further, the opening degrees of the first regulating valve and the second regulating valve are adjustable, thereby allowing the air flow flowing into the radiant heat exchanger of the cabin and the radiant heat exchanger of the cargo hold or the equipment compartment to be adjusted.

[0013] Preferably, the aircraft air conditioning device further comprises at least one of a first temperature sensor, a second temperature sensor and a third temperature sensor, wherein the first temperature sensor is connected to the ram air inlet pipe for detecting the temperature of the low-temperature ram air in the ram air inlet pipe, the second temperature sensor is connected to the cabin for detecting the temperature in the cabin, and the third temperature sensor is connected to the cargo hold or the equipment hold for detecting the temperature in the cargo hold or the equipment hold.

[0014] More preferably, the aircraft air conditioning system further comprises a controller, which communicates with the first regulating valve, the second regulating valve, the first temperature sensor, the second temperature sensor and the third temperature sensor in a wired or wireless manner. By means of the controller, the first regulating valve and the second regulating valve can be controlled based on the detected temperature, thereby enabling more accurate and flexible control of the operation of the aircraft air conditioning system.

[0015] Of course, the above-mentioned controller and temperature sensor are preferred structures, and the operation of the aircraft air conditioning device can also be controlled manually, which is also within the scope of the present application.

[0016] In another specific structure, the aircraft air conditioning device further includes: an air conditioning heat exchanger, which is connected to the ram air inlet pipe, and the low-temperature ram air sucked into the ram air inlet pipe can flow into the air conditioning heat exchanger and be heated. This is because the hot side is the high-temperature bleed air from the engine, and the temperature can reach 200° C., for example, so the ram air can reach 60° C. or more after being heated; a hot air pipe, which is connected to the downstream of the air conditioning heat exchanger, and the heated hot air can flow into the hot air pipe; and a hot air supply pipe, which is connected to the radiation heat exchanger in the cabin. Such a structure realizes the heating operation of the cabin.

[0017] In the structure of the above aircraft air conditioning device, a third regulating valve is preferably provided on the hot air supply pipe. The third regulating valve can be adjusted in cooperation with the first regulating valve to control the temperature of the air entering the radiation heat exchanger in the cabin. For example, when flying at high altitude, the outside temperature is -50°C, and by adjusting the opening of the first regulating valve and the third regulating valve, the outside air can be mixed with the air from the hot air pipe to adjust the temperature of the air entering the radiation heat exchanger to the required temperature, such as 0°C, to achieve the cooling function. Similarly, in a similar manner, the temperature of the air entering the radiation heat exchanger can also be adjusted to 40°C to achieve the heating function.

[0018] Further preferably, the aircraft air conditioning device further comprises at least one of a fourth temperature sensor and a fifth temperature sensor, wherein the fourth temperature sensor is disposed on the hot air supply pipe and is used to detect the temperature of the hot air in the hot air supply pipe, and the fifth temperature sensor is disposed on the hot air pipe and is used to detect the temperature of the hot air in the hot air pipe, wherein the controller communicates with the third regulating valve, the fourth temperature sensor and the fifth temperature sensor in a wireless or wired manner.

[0019] The present application also relates to an aircraft comprising an aircraft air conditioning device as described above.

[0020] The present application also proposes a control method for some preferred structures of the aircraft air conditioning device of the present application. For example, the control method may include detecting the temperature in the cabin by a second temperature sensor and detecting the temperature in the cargo hold or equipment compartment by a third temperature sensor. When the detected temperature in the cabin indicates that the cabin needs to be cooled, the first regulating valve is opened to allow low-temperature ram air to flow into the radiation heat exchanger in the cabin to cool the air in the cabin. When the detected temperature in the cargo hold or equipment compartment indicates that the cargo hold or equipment compartment needs to be cooled, the second regulating valve is opened to allow low-temperature ram air to flow into the radiation heat exchanger in the cargo hold or equipment compartment to cool the air in the cargo hold or equipment compartment.

[0021] For another example, the control method may include detecting the temperature in the cabin by a second temperature sensor and detecting the temperature in the cargo hold by a third temperature sensor. When the detected temperature in the cabin indicates that the cabin needs to be cooled, the first regulating valve is opened. At this time, the first regulating valve and the third regulating valve are adjusted to control the air temperature entering the radiation heat exchanger in the cabin, and the air temperature is monitored by the fourth temperature sensor. In this way, low-temperature ram air flows into the radiation heat exchanger in the cabin to cool the air in the cabin. When the detected temperature in the cabin indicates that the cabin needs to be heated, the third regulating valve is opened to allow hot air heated by the air conditioning heat exchanger to flow into the radiation heat exchanger in the cabin to heat the air in the cabin. And, when the detected temperature in the cargo hold or the equipment compartment indicates that the cargo hold or the equipment compartment needs to be cooled, the second regulating valve is opened to allow low-temperature ram air to flow into the radiation heat exchanger in the cargo hold or the equipment compartment to cool the air in the cargo hold or the equipment compartment.

[0022] In the above-mentioned step of cooling or heating the cabin, the openings of the first regulating valve and the third regulating valve can be adjusted based on the measurement value of the second temperature sensor, so that a certain amount of low-temperature ram air from the ram air inlet pipe is mixed with a certain amount of hot air from the hot air pipe to obtain mixed air with a predetermined temperature and flow rate, and the mixed air is made to flow into the radiation heat exchanger in the cabin. In this way, the temperature of the hot air entering the radiation heat exchanger in the cabin for heating operation can be more flexibly controlled. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings show non-limiting preferred implementation structures of the present invention, and the features and advantages of the present invention can be more clearly seen in conjunction with the accompanying drawings.

[0024] Figure 1 A schematic structural diagram of an aircraft air conditioning system according to a first embodiment of the present invention is shown.

[0025] Figure 2 A schematic structural diagram of an aircraft air conditioning system according to a second embodiment of the present invention is shown.

[0026] (Explanation of symbols)

[0027] 1 Cockpit

[0028] 2 cargo hold or equipment hold

[0029] 10 Aircraft air conditioning unit

[0030] 11 Ram air inlet pipe

[0031] 12 Hot air pipe

[0032] 13 Air conditioning heat exchanger

[0033] 14 Cold air supply pipe

[0034] 15 Hot air supply pipe

[0035] 16 First branch pipe

[0036] 17 Second branch pipe

[0037] 21Radiation heat exchanger

[0038] 22 Drain holes

[0039] 31 First temperature sensor

[0040] 32 Second temperature sensor

[0041] 33 Third temperature sensor

[0042] 34 Fourth temperature sensor

[0043] 35 Fifth temperature sensor

[0044] 40 Controllers

[0045] 51 First regulating valve

[0046] 52 Second regulating valve

[0047] 53 The third regulating valve DETAILED DESCRIPTION

[0048] The specific implementation of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be understood that the drawings only show preferred embodiments of the present invention, which do not constitute a limitation on the scope of the present invention. Those skilled in the art can make various obvious modifications, variations, and equivalent substitutions to the present invention based on the embodiments shown in the drawings, and the technical features of the different embodiments described below can be arbitrarily combined with each other without contradiction, which all fall within the scope of protection of the present invention.

[0049] <First Embodiment>

[0050] Figure 1 A schematic structural block diagram of a first embodiment of an aircraft air conditioning device 10 of the present application is shown. Figure 1 The structure of the aircraft air conditioning unit 10 of this first embodiment will be described in detail.

[0051] The aircraft air conditioning device 10 of the first embodiment comprises a ram air inlet duct 11 communicating with the outside of the aircraft, and air with a lower temperature outside the aircraft can be introduced into the aircraft air conditioning device 10 via the ram air inlet duct 11 .

[0052] The ram air inlet pipe 11 is connected to a cold air supply pipe 14, and the introduced ram air can flow into the cold air supply pipe 14. In a preferred structure, a first regulating valve 51 is provided on the cold air supply pipe 14, and the ram air flowing into the cold air supply pipe 14 can be connected or cut off by opening and closing the first regulating valve 51. Further, the opening degree of the first regulating valve 51 is preferably adjustable, so that the ram air flowing into the cold air supply pipe 14 can be adjusted.

[0053] The aircraft air conditioning device 10 is firstly configured to be able to adjust the indoor temperature in a cabin 1 such as a cockpit, a passenger cabin or the like on an aircraft. Figure 1 As shown in FIG. 1 , at least one, preferably a plurality of radiation heat exchangers 21 are provided in the cabin 1. The radiation heat exchanger 21 is, for example, a tubular structure, that is, formed as a radiation heat exchange tube, and is connected to the cold air supply pipe 14, so that the ram air entering the cold air supply pipe 14 can flow into the radiation heat exchanger 21.

[0054] The radiation heat exchanger 21 is also in communication with the outside of the aircraft. After exchanging heat with the air in the cabin 1 , the ram air that has undergone heat exchange can be discharged to the outside of the aircraft.

[0055] The radiation heat exchanger 21 is preferably made of a material with good thermal conductivity and high emissivity, such as stainless steel, copper, etc. The relatively low temperature ram air flowing into the radiation heat exchanger 21 reduces the temperature of the radiation heat exchanger 21, specifically, the temperature of the radiation heat exchanger 21 resists the indoor temperature in the cabin 1, and the radiation heat exchanger 21 can mainly adjust the indoor temperature in the cabin 1 by means of radiation heat exchange. Of course, those skilled in the art will know that since the radiation heat exchanger 21 is in contact with the air in the cabin 1, although it is not the main heat exchange method, there is still conduction heat exchange and convection heat exchange between the radiation heat exchanger 21 and the indoor air of the cabin 1.

[0056] The figure shows that the multiple radiation heat exchangers 21 in the cabin 1 are arranged in parallel, but those skilled in the art will appreciate that the multiple radiation heat exchangers 21 may also be arranged in series, or in both parallel and series. For example, the multiple radiation heat exchangers 21 are divided into multiple groups, each group of radiation heat exchangers 21 is arranged in series, and the groups of radiation heat exchangers 21 are arranged in parallel.

[0057] Preferably, in order to reduce the heat exchange occurring on the way from the ram air inlet pipe 11 to the radiation heat exchanger 21 , the cold air supply pipe 14 is preferably coated with a heat insulating material, such as a foam material, while the radiation heat exchanger 21 is exposed in the space of the cabin 1 .

[0058] Preferably, at least one, preferably a plurality of drainage holes 22 are provided on the radiation heat exchanger 21. The drainage holes 22 may be arranged along the longitudinal direction of the radiation heat exchanger 21.

[0059] In a high temperature and high humidity weather environment, the cabin 1 needs to be cooled down. At this time, low temperature ram air enters the radiation heat exchanger 21 in the cabin 1 to reduce the temperature in the cabin 1. At this time, since the temperature of the radiation heat exchanger 21 is lower than the air temperature in the cabin 1, the moisture contained in the air in the cabin 1 will condense on the surface of the radiation heat exchanger 21 to form condensed water. When the aircraft is flying at high altitude, the ambient air pressure outside the aircraft is lower than the air pressure inside the aircraft, such as in the cabin 1, thereby forming a negative pressure in the radiation heat exchanger 21, that is, the pressure in the radiation heat exchanger 21 is lower than the pressure inside the cabin 1. In this case, the condensed water on the surface of the radiation heat exchanger 21 will flow into the radiation heat exchanger 21 through the drain hole 22 under the action of the negative pressure, or it can also be understood that the condensed water is discharged into the radiation pipe through the pressure difference between the cabin pressure and the ram air, and then discharged to the outside of the aircraft together with the ram air in the radiation heat exchanger 21. In this way, the aircraft air conditioning device 10 of the present application can also play a role in drying the air and reducing the amount of condensed water.

[0060] Further, under the action of gravity, condensed water will accumulate at the bottom of the radiation heat exchanger 21, so correspondingly, the drain hole 22 is preferably located at the bottom of the radiation heat exchanger 21. In this way, the condensed water can be more thoroughly sucked into the radiation heat exchanger 21 and discharged to the outside of the aircraft.

[0061] Alternatively or additionally, the aircraft air conditioning system 10 may also be provided for regulating the temperature in the cargo hold or equipment compartment 2. Figure 1 As can be seen in FIG. 1 , at least one, preferably a plurality of radiation heat exchangers 21 are also provided in the cargo hold or equipment compartment 2. Furthermore, in the case where the aircraft air conditioning device 10 is configured to control both the cabin 1 and the cargo hold or equipment compartment 2, the cold air supply pipe 14 may be configured to include two branch pipes, namely a first branch pipe 16 and a second branch pipe 17, wherein one end of the first branch pipe 16 is connected to the cold air supply pipe 14 and is connected to the outlet side of the first regulating valve 51, and the other end is connected to the radiation heat exchanger 21 in the cabin 1. In addition, one end of the second branch pipe 17 is connected to the inlet side of the first regulating valve 51 of the cold air supply pipe 14, and the other end is connected to the radiation heat exchanger 21 in the cargo hold or equipment compartment 2.

[0062] Preferably, a second regulating valve 52 is provided on the second branch pipe 17, through which the ram air flowing into the radiation heat exchanger 21 in the cargo hold or equipment compartment 2 can be opened and closed, that is, the air conditioning of the cargo hold or equipment compartment 2 can be opened and closed. Further preferably, the opening degree of the second regulating valve 52 is adjustable, thereby allowing the amount of ram air flowing into the radiation heat exchanger 21 in the cargo hold or equipment compartment 2 to be adjusted, thereby adjusting the cooling capacity of the air in the cargo hold or equipment compartment 2.

[0063] Similar to the radiation heat exchanger 21 in the cabin 1 , the radiation heat exchanger 21 in the cargo hold or equipment compartment 2 is also provided with at least one, preferably a plurality of drainage holes 22 to drain the water condensed on the radiation heat exchanger 21 .

[0064] In order to control the operation of the aircraft air conditioning system 10, the aircraft air conditioning system 10 further includes a controller 40, which can communicate with the first regulating valve 51 and the second regulating valve 52 in a wired or wireless manner to control the opening and closing of the first regulating valve 51 and the second regulating valve 52 and their opening degrees.

[0065] Preferably, the aircraft air conditioning device 10 further comprises a plurality of temperature sensors for detecting the temperature of various parts of the aircraft air conditioning device 10 , and the controller 40 may control the operation of the aircraft air conditioning device 10 according to the temperatures detected by the temperature sensors.

[0066] exist Figure 1In the first embodiment shown in FIG. 1 , the aircraft air conditioning device 10 includes a first temperature sensor 31, a second temperature sensor 32, and a third temperature sensor 33. The first temperature sensor 31 is connected to the ram air inlet pipe 11 for detecting the temperature of the ram air entering the ram air inlet pipe 11, the second temperature sensor 32 is connected to the cabin 1 for detecting the temperature in the cabin 1, and the third temperature sensor 33 is connected to the cargo hold or the equipment compartment 2 for detecting the temperature in the cargo hold or the equipment compartment 2.

[0067] When the second temperature sensor 32 detects that the temperature in the cabin 1 is high and the cabin 1 needs to be cooled, the controller 40 controls the first regulating valve 51 to open, so that the ram air in the ram air inlet pipe 11 can enter the cold air supply pipe 14 and flow into the radiation heat exchanger 21 in the cabin 1. The ram air in the radiation heat exchanger 21 reduces the temperature of the radiation heat exchanger 21, and then reduces the temperature in the cabin 1 through heat exchange (mainly radiation heat exchange) between the radiation heat exchanger 21 and the air in the cabin 1.

[0068] Further, based on the temperature of the ram air in the ram air inlet pipe 11 detected by the first temperature sensor 31, the controller 40 can determine the flow rate of the ram air that needs to flow into the radiation heat exchanger 21 of the cabin 1, and the controller 40 controls the ram air flow rate by adjusting the opening of the first regulating valve 51 to achieve the desired cooling effect.

[0069] Similarly, when the third temperature sensor 33 detects that the temperature in the cargo hold or equipment compartment 2 is high, the controller 40 may open the second regulating valve 52 according to the detected temperature in the cargo hold or equipment compartment 2 to refrigerate the air in the cargo hold or equipment compartment 2. In addition, the controller 40 may also adjust the opening of the second regulating valve 52 to control the ram air flow rate flowing into the radiation heat exchanger 21 in the cargo hold or equipment compartment 2.

[0070] <Second Embodiment>

[0071] Figure 2 A schematic structural block diagram of a second embodiment of an aircraft air conditioning device 10 of the present application is shown.

[0072] In the absence of contrary description or conflict, the specific structure described above with respect to the first embodiment is also applicable to the second embodiment. The features in the second embodiment that are the same or similar to those in the first embodiment are represented by the same reference numerals. In the following disclosure of the second embodiment, the features that are the same or similar to those in the first embodiment will be briefly mentioned without further description, and the structures that are different from the first embodiment will be specifically described.

[0073] The aircraft air conditioning device 10 of the second embodiment includes a ram air inlet pipe 11, to which a cold air supply pipe 14 is connected, and the cold air supply pipe 14 can be communicated with the radiant heat exchangers 21 in the cabin 1 and the cargo hold or the equipment compartment 2, so as to realize the refrigeration operation of the cabin 1 and the cargo hold or the equipment compartment 2. Each radiant heat exchanger 21 is provided with at least one, preferably a plurality of drainage holes 22, so that the condensed water condensed on the surface of the radiant heat exchanger 21 is sucked into the radiant heat exchanger 21 by the negative pressure in the radiant heat exchanger 21, and discharged to the outside of the aircraft along with the ram air.

[0074] A first regulating valve 51 and a second regulating valve 52 may be provided on the first branch pipe 16 leading to the cabin 1 and the second branch pipe 17 leading to the cargo hold or equipment compartment 2, respectively. In addition, the aircraft air conditioning device 10 of the second embodiment also includes a first temperature sensor 31, a second temperature sensor 32, and a third temperature sensor 33. The controller 40 may control the refrigeration operation of the cabin 1 and the cargo hold or equipment compartment 2 based on the temperature parameters detected by the first temperature sensor 31, the second temperature sensor 32, and the third temperature sensor 33.

[0075] Unlike the first embodiment, the aircraft air conditioning device 10 of the second embodiment is also capable of heating the cabin 1. To this end, in the second embodiment, an air conditioning heat exchanger 13 is provided in the ram air inlet pipe 11, and a hot air pipe 12 is connected downstream of the air conditioning heat exchanger 13. The relatively low-temperature ram air sucked into the ram air inlet pipe 11 is heated in the process of flowing through the air conditioning heat exchanger 13, and the heated hot air flows into the hot air pipe 12. The hot side of the air conditioning heat exchanger 13 is the high-temperature bleed air from the engine. Figure 2 The ram air with a lower temperature in the ram air inlet pipe 11 ( Figure 2 The gas (schematically indicated by arrow G1) exchanges heat with the high-temperature bleed air G1 and is heated to a predetermined temperature.

[0076] A hot air supply pipe 15 is connected to the hot air pipe 12, and the hot air supply pipe 15 is connected to the radiation heat exchanger 21 in the cabin 1. In this way, the heated hot air can flow into the radiation heat exchanger 21 to heat the cabin 1. In addition, the hot air supply pipe 15 is also connected to the first branch pipe 16 at a position before entering the radiation heat exchanger 21. In this way, the cold air from the first branch pipe 16 and the hot air in the hot air supply pipe 15 can be mixed, thereby allowing the temperature of the air entering the radiation heat exchanger 21 in the cabin 1 to be adjusted to a predetermined temperature. In the heating mode, the predetermined temperature may be higher than the adjustment target temperature in the cabin 1, and in the cooling mode, the predetermined temperature may be lower than the adjustment target temperature in the cabin 1.

[0077] Preferably, a third regulating valve 53 is provided on the hot air supply pipe 15. By opening and closing the third regulating valve 53, the hot air flowing from the hot air pipe 12 to the radiation heat exchanger 21 can be opened and cut off. The third regulating valve 53 can also preferably adjust the opening degree to control the temperature of the radiation heat exchanger 21 of the cabin 1, thereby adjusting the temperature of the gas entering the radiation heat exchanger 21 in the cabin 1.

[0078] Furthermore, the openings of the first regulating valve 51 and the third regulating valve 53 may be adjusted so that the hot air from the hot air pipe 12 and the cold air from the ram air inlet pipe 11 are mixed to control the air entering the radiation heat exchanger 21 of the cabin 1 to a desired temperature.

[0079] A fourth temperature sensor 34 is provided on the hot air supply pipe 15 for detecting the temperature of the hot air in the hot air pipe 12. A fifth temperature sensor 35 is provided on the hot air pipe 12 for detecting the temperature of the hot air in the radiation heat exchanger 21 flowing into the cabin 1. The controller 40 can adjust the opening of the third regulating valve 53 based on the temperature in the cabin 1 detected by the second temperature sensor 32, the hot air temperature in the hot air supply pipe 15 detected by the fourth temperature sensor 34, and the hot air temperature in the hot air pipe 12 detected by the fifth temperature sensor 35, thereby adjusting the temperature of the cabin 1.

[0080] The operating method of the aircraft air conditioning system 10 according to the second embodiment will be described below:

[0081] When it is detected that the temperature in the cabin 1 is high and the air in the cabin 1 needs to be cooled, the first regulating valve 51 can be opened, for example, by the controller 40. By adjusting the opening of the first regulating valve 51 and the third regulating valve 53, the temperature of the gas entering the radiation heat exchanger 21 can be controlled. As a result, low-temperature ram air flows into the radiation heat exchanger 21 in the cabin 1 to cool the cabin 1. Of course, during the cooling process, only the first regulating valve 51 can be opened and the third regulating valve 53 can be closed, which is also within the scope of the present application.

[0082] If it is detected that the temperature in the cabin 1 is low and the air in the cabin 1 needs to be heated, for example, when the aircraft is cruising at a high altitude, the controller 40 opens the third regulating valve 53 to allow the heated hot air to flow into the radiation heat exchanger 21 of the cabin 1, thereby achieving the heating operation of the cabin 1. When heating the cabin 1, in addition to opening the third regulating valve 53, the first regulating valve 51 may also be opened, and by adjusting the openings of the third regulating valve 53 and the first regulating valve 51, a certain amount of hot air is mixed with a certain amount of low-temperature ram air to obtain mixed air of a desired temperature, and the mixed air is provided to the radiation heat exchanger 21 of the cabin 1.

[0083] Similarly, during the heating process, only the third regulating valve 53 may be opened, which is also within the scope of the present application. During the cooling or heating process of the interior environment of the cabin 1, the openings of the first regulating valve 51 and the third regulating valve 53 may be adjusted to control the air in the radiation heat exchanger 21 entering the cabin 1 at a predetermined temperature. Taking the cooling process as an example, when the temperature in the cabin 1 needs to be controlled at 25°C, the temperature of the mixed air in the radiation heat exchanger 21 entering the cabin 1 may be controlled at, for example, 10°C, etc., by adjusting the openings of the first regulating valve 51 and the third regulating valve 53.

[0084] The temperature of the mixed air entering the radiation heat exchanger 21 of the cabin 1 is monitored by the fourth temperature sensor 34. If the temperature monitored by the fourth temperature sensor 34 does not reach the predetermined temperature, the operator or the controller on the aircraft will continue to adjust the opening of the first regulating valve 51 and the second regulating valve 53 until the temperature detected at the fourth temperature sensor 34 reaches the predetermined temperature.

[0085] Similarly, when it is detected that the temperature in the cargo hold or equipment compartment 2 is high and the cargo hold or equipment compartment 2 needs to be refrigerated, the controller 40 controls the second regulating valve 52 to open to allow low-temperature ram air to flow into the radiation heat exchanger 21 in the cargo hold or equipment compartment 2, thereby enabling the cargo hold or equipment compartment 2 to be refrigerated.

[0086] Although not shown in the figure, those skilled in the art will appreciate that a pipeline may be led out from the hot air pipe 12 and connected to the second branch pipe 17, and connected downstream of the second regulating valve 52. In addition, an additional temperature sensor may be provided downstream of the connection point of the pipeline to monitor the mixed air temperature in the radiation heat exchanger 21 entering the cargo hold or equipment compartment 2. In this way, the cargo hold or equipment compartment 2 may be heated, or the temperature of the air in the radiation heat exchanger 21 entering the cargo hold or equipment compartment 2 may be adjusted. The principle is the same as that described above with respect to the cabin 1, and will not be described again here.

Claims

1. An aircraft air conditioning device, comprising a ram air inlet pipe, wherein the ram air inlet pipe is used to introduce low-temperature ram air, characterized in that: The aircraft air conditioning unit further comprises: a cold air supply pipe, the cold air supply pipe being connected to the ram air inlet pipe so that the low-temperature ram air can flow into the cold air supply pipe; At least one radiant heat exchanger is disposed in at least one of a cockpit, a cargo hold, or an equipment hold of the aircraft, one end of the radiant heat exchanger is connected to the cold air supply pipe, and the other end of the radiant heat exchanger leads to the outside of the aircraft.

2. The aircraft air conditioning device according to claim 1, characterized in that At least one drainage hole is provided on the radiation heat exchanger.

3. The aircraft air conditioning system according to claim 1 or 2, characterized in that The radiation heat exchanger is arranged in the cockpit and the cargo hold or the equipment hold, Wherein, the cold air supply pipe includes a first branch pipe and a second branch pipe, the first branch pipe is connected to the radiation heat exchanger in the cabin, and the second branch pipe is connected to the radiation heat exchanger in the cargo hold or the equipment compartment.

4. The aircraft air conditioning device according to claim 3, characterized in that The aircraft air conditioning device includes at least one of a first regulating valve and a second regulating valve, wherein the first regulating valve is arranged on the first branch pipe, the second regulating valve is arranged on the second branch pipe, and the second branch pipe is connected to the inlet side of the first regulating valve.

5. The aircraft air conditioning device according to claim 4, characterized in that The aircraft air conditioning device further comprises at least one of a first temperature sensor, a second temperature sensor and a third temperature sensor, wherein the first temperature sensor is connected to the ram air inlet pipe for detecting the temperature of low-temperature ram air in the ram air inlet pipe, the second temperature sensor is connected to the cabin for detecting the temperature in the cabin, and the third temperature sensor is connected to the cargo hold or the equipment bay for detecting the temperature in the cargo hold or the equipment bay.

6. The aircraft air conditioning device according to claim 5, characterized in that The aircraft air conditioning device further includes a controller, which communicates with the first regulating valve, the second regulating valve, the first temperature sensor, the second temperature sensor, and the third temperature sensor in a wired or wireless manner.

7. The aircraft air conditioning device according to claim 1, characterized in that The aircraft air conditioning unit further comprises: an air conditioning heat exchanger, the air conditioning heat exchanger being connected to the ram air inlet pipe, and the low-temperature ram air sucked into the ram air inlet pipe can flow into the air conditioning heat exchanger and be heated; a hot air pipe, the hot air pipe being connected downstream of the air conditioner heat exchanger, into which the heated hot air can flow; and A hot air supply pipe is connected to the radiation heat exchanger in the cabin.

8. The aircraft air conditioning device according to claim 6, characterized in that The aircraft air conditioning unit further comprises: an air conditioning heat exchanger, the air conditioning heat exchanger being connected to the ram air inlet pipe, the hot side of the air conditioning heat exchanger being high temperature bleed air from the engine, the low temperature ram air sucked into the ram air inlet pipe being able to flow into the air conditioning heat exchanger and be heated; a hot air supply duct, the hot air supply duct being in communication with the radiant heat exchanger in the cabin; and a hot air pipe connected downstream of the air conditioning heat exchanger, into which heated hot air can flow, and wherein the first branch pipe intersects with the hot air supply pipe before entering the radiation heat exchanger of the cabin; A third regulating valve is arranged on the hot air supply pipe.

9. The aircraft air conditioning device according to claim 8, characterized in that The aircraft air conditioning device further comprises at least one of a fourth temperature sensor and a fifth temperature sensor, wherein the fourth temperature sensor is arranged downstream of the intersection of the hot air supply pipe and the first branch pipe, and is used to detect the temperature of air entering the radiation heat exchanger in the cabin, and the fifth temperature sensor is arranged on the hot air pipe, and is used to detect the temperature of the hot air in the hot air pipe. Wherein, the controller communicates with the third regulating valve, the fourth temperature sensor and the fifth temperature sensor in a wireless or wired manner.

10. An aircraft, characterized in that: The aircraft comprises an aircraft air conditioning device according to any one of claims 1 to 9.

11. A method for controlling an aircraft air conditioning system according to claim 6, characterized in that: The control method comprises: The second temperature sensor detects the temperature in the cabin, and the third temperature sensor detects the temperature in the cargo hold or equipment hold; When the detected temperature in the cabin indicates that the cabin needs to be cooled, opening the first regulating valve to allow the low-temperature ram air to flow into the radiation heat exchanger in the cabin to cool the air in the cabin; and When the detected temperature in the cargo hold or equipment compartment shows that the cargo hold or equipment compartment needs to be refrigerated, the second regulating valve is opened to allow the low-temperature ram air to flow into the radiation heat exchanger in the cargo hold or equipment compartment to perform refrigeration operations on the air in the cargo hold or equipment compartment.

12. A method for controlling an aircraft air conditioning system according to claim 9, characterized in that: The control method comprises: The second temperature sensor detects the temperature in the cabin, and the third temperature sensor detects the temperature in the cargo hold; When the detected temperature in the cabin indicates that the cabin needs to be cooled, the first regulating valve is opened to allow the low-temperature ram air to flow into the radiation heat exchanger in the cabin to cool the air in the cabin; When the detected temperature in the cabin indicates that the cabin needs to be heated, the third regulating valve is opened to allow the hot air heated by the air conditioning heat exchanger to flow into the radiation heat exchanger in the cabin to heat the air in the cabin; When the detected temperature in the cargo hold or equipment compartment shows that the cargo hold or equipment compartment needs to be refrigerated, the second regulating valve is opened to allow the low-temperature ram air to flow into the radiation heat exchanger in the cargo hold or equipment compartment to perform refrigeration operations on the air in the cargo hold or equipment compartment.

13. The control method according to claim 12, characterized in that: Based on the measurement value of the second temperature sensor, the first regulating valve and the third regulating valve are adjusted so that a certain amount of low-temperature ram air from the ram air inlet pipe is mixed with a certain amount of hot air from the hot air pipe to obtain mixed air with a predetermined temperature and flow rate, and the mixed air is made to flow into the radiation heat exchanger in the cabin.

14. The control method according to claim 13, characterized in that: The fourth temperature sensor detects the temperature of the mixed air formed by the low-temperature ram air from the first branch pipe and the hot air from the hot air pipe. If the temperature detected by the fourth temperature sensor does not reach the predetermined temperature, the first regulating valve and the third regulating valve continue to be adjusted until the temperature of the mixed air reaches the predetermined temperature.

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