CN104002976B - Air supply system of aircraft cabin - Google Patents

Abstract

An air supply system for an aircraft cockpit, comprising: an air source; a main air supply channel defined between the skin of the cockpit and an interior panel and in fluid communication with the air source; a first air supply port defined at the seat The interior panel above and below the luggage rack communicates with the main air supply channel and is used to supply air to the upper body of the passenger; the second air supply port is defined on the interior panel under the seat of the cockpit and communicates with the main air supply channel. The channel is connected to supply air to the lower body of the passenger; the flow regulating device is arranged in the main air supply channel and is used to adjust the flow ratio of the air-conditioning air from the first air supply port and the second air supply port. The invention can meet the temperature comfort requirements of passengers with different clothing characteristics under different ambient temperature conditions and passengers with different sensitivities to the surrounding temperature and environmental conditions of the cabin. Improve the cockpit temperature environment where the head is cool and the feet are hot in summer, and the head is hot and the feet are cool in winter, so as to avoid the temperature stratification of the cockpit.

Description

Air supply system for aircraft cockpit

technical field

The invention relates to an air supply system for an aircraft cockpit.

Background technique

Due to the wide range of commercial aircraft operations and the special operating environment, they will encounter various extreme weather, and different passengers have different requirements for the comfort of the cockpit.

In summer, in some areas, the temperature is higher and the humidity is also higher. When the aircraft is on the ground, the skin temperature sometimes reaches above 50°C, and the air temperature in the cockpit of the aircraft will also reach above 40°C without the air conditioner turned on. However, when the aircraft is in the cruising state, the temperature of the outside atmosphere will gradually drop below -10°C.

In winter, in some cold regions, the climate is cold, with low temperature and low humidity. When the aircraft is on the ground and in extremely cold weather, when the air conditioner is not turned on, the temperature of the skin and cabin will reach below -40°C. Under flight conditions, the temperature of the outside atmosphere will reach below -70°C.

Due to the large changes in the altitude of the aircraft operation, and the large geographical span of the operation, the climate and weather conditions in different regions are different, resulting in great changes in the thermal load in the cabin in a short period of time. The temperature conditions inside and outside the cockpit, and thermal comfort conditions have also undergone great changes. The human body temperature is basically maintained at about 37°C. Under different environmental conditions, due to differences in physical conditions, sensitivity, clothing, etc., different crew members and passengers have different requirements for temperature comfort in the cockpit. The temperature comfort range of the human body is mostly in the range of 20°C-30°C. Therefore, the temperature design target value of the cockpit air conditioning system of commercial aircraft is mostly between 24°C and 27°C in order to meet the temperature comfort requirements of most crew members and passengers.

As the temperature of the external environment changes, the sensitive parts of the human body to temperature are very different. For example, in summer, the upper body of the human body, especially the head and face, is more sensitive to temperature. When the head and face feel cool, it will feel more comfortable; in winter, the lower body of the human body, especially the legs And feet are more sensitive to temperature. When people's feet and legs feel warm, people will feel more comfortable.

During the design process of the aircraft air conditioning system, due to the requirements of system installation space and weight, most of the current civil aircraft air conditioning systems adopt the method of air supply from the top of the cabin and exhaust from the bottom. As shown in the cabin 10 shown in FIG. 1 , the temperature of the conditioned air in the cabin 10 will gradually change during the process of being exhausted from the air outlet 12 through the cabin interior space 14 to the air exhaust outlet 16 . Therefore, when the thermal load of the aircraft is large, the air temperature around the passengers is relatively high, and the air temperature of the air conditioner is relatively low, the heads of the crew and passengers will feel more comfortable. However, when the thermal load of the aircraft is small or negative, the temperature of the air around the passengers is relatively low, and the temperature of the air-conditioning air supply is relatively high. It feels that the air temperature is high and the air is relatively dry. When the air-conditioning air flows to the feet and legs of the human body, the temperature has dropped. Therefore, the passenger feels that the head is hot and the feet are cool. The temperature comfort requirement of the environment, this is the temperature stratification phenomenon in the cockpit.

The current air-conditioning air supply system of commercial aircraft is difficult to meet the human body's requirements for temperature, temperature and comfort at the same time.

Contents of the invention

The object of the present invention is to provide an air-conditioning air supply system used on a commercial aircraft that meets the temperature comfort requirements of different crew members and passengers under different conditions.

In order to achieve the above object, the present invention provides an air supply system for an aircraft cockpit, which includes: an air source, which is used to provide air-conditioning air to the interior of the cockpit; between them and communicate with the air source; the first air supply port is defined on the trim panel above the seat and below the luggage rack of the cockpit and communicates with the main air supply channel, and is used to supply air to the Air is supplied to the upper body of the passenger on the seat; the second air supply port is defined on the interior trim panel under the seat of the cockpit and communicates with the main air supply passage for blowing air to the seat when sitting on the seat. air supply to the lower body of the passenger; a flow regulating device, which is arranged in the main air supply channel and is used to adjust the flow ratio of the air-conditioning air from the first air supply port and the second air supply port.

Further, the air supply system further includes a connecting channel, which is fluidly connected between the first air supply port and the second air supply port, so as to cooperate with the flow regulating device to adjust the first air supply port and the second air supply port. The flow rate of the air-conditioning air between the second air supply ports.

According to a preferred implementation manner, the flow regulating device is arranged adjacent to the first air supply port.

According to one embodiment, the flow regulating device includes a pivot disposed in a cavity defined by the connecting passage, and a baffle capable of rotating around the pivot between a first state and a second state, In the first state, the baffle closes the first air supply port and opens the second air supply port; in the second state, the baffle closes the second air supply port and opens the second air supply port Describe the first air supply port.

According to one embodiment, the baffle is roughly V-shaped, with an opening facing downward, and an angle of the opening is greater than 90 degrees and less than 180 degrees.

According to one embodiment, the flow adjustment device further includes a handle fixedly connected to the baffle and extending from the main air supply channel, which is used for manual adjustment. When the passengers on the seats in the cockpit feel that the surrounding environment is relatively hot, the passengers can adjust the baffle under the luggage rack above the seat through the handle to increase the air-conditioning air supply volume of the first air supply outlet arranged under the luggage rack And the air supply volume of the air-conditioning air of the second air supply port is reduced, and the air supply direction can also be adjusted at the same time, so that the air-conditioning air with a lower temperature is blown to the passenger's head, thereby achieving the purpose of rapid cooling.

When the ambient temperature is low, or the passenger's lower body feels cold due to clothing, etc., the passenger can adjust the baffle under the luggage rack through the handle to adjust the air-conditioning air supply of the second air supply outlet under the seat according to personal needs. The air volume can be increased while reducing the air supply volume of the air-conditioning air from the first air supply port, thereby improving the temperature of the environment around the lower part of the body and improving comfort.

According to one embodiment, the connecting channel is a pipe provided between the skin of the cabin and the interior trim panel, or a groove formed on the inner wall of the interior trim panel. Those skilled in the art can construct the connecting channel connecting the first air supply port and the second air supply port according to actual needs. The cabin air supply system of the present invention can meet the temperature comfort requirements of passengers with different clothing characteristics under different ambient temperature conditions and passengers with different sensitivities to ambient temperature conditions around the cabin. Improve the cockpit temperature environment where the head is cool and the feet are hot in summer, and the head is hot and the feet are cool in winter, so as to avoid the temperature stratification of the cockpit.

Description of drawings

Fig. 1 schematically shows the air supply system of the aircraft cockpit of the prior art;

Fig. 2 schematically shows the air supply system of the aircraft cabin of the present invention;

Fig. 3 schematically shows the flow regulating device of the air supply system in Fig. 2. When adjusting from the solid line position to the dotted line position, the flow rate of the first air supply port becomes larger, while the flow rate of the second air supply port becomes smaller;

Fig. 4 schematically shows the handle of the flow regulating device of the air supply system of Fig. 2;

Fig. 5 schematically shows the air supply state in which the flow regulating device of the air supply system of Fig. 2 completely closes the first air supply port;

Fig. 6 schematically shows the air supply state in which the flow regulating device of the air supply system of Fig. 2 completely closes the second air supply port; and

Fig. 7 schematically shows the air supply state when the flow regulating device of the air supply system in Fig. 2 is in the middle position.

detailed description

As shown in FIGS. 2 to 7 , the present invention discloses an air supply system 200 for an aircraft cabin 100 . The air supply system 200 includes: an air source 202, which is used to provide air-conditioning air to the interior of the cabin 100; Fluid communication; the first air supply port 206, which is defined on the interior trim panel 104 above the seat 106 of the cockpit 100 and below the luggage rack 108 and communicates with the main air supply channel 204, is used to provide air to passengers sitting on the seat 106 The upper body air supply; the second air supply port 208, which is defined on the interior trim panel 104 below the seat 106 of the cockpit 100 and communicates with the main air supply channel 204, for blowing air to the lower body of the passenger sitting on the seat 106; wind; and a flow regulating device 210 , which is arranged in the main air supply channel 204 and used to adjust the flow ratio of the air-conditioning air from the first air supply port 206 and the second air supply port 208 .

As shown in FIGS. 5 to 7 , the connecting channel 212 communicates between the first air supply port 206 and the second air supply port 208 , and is used to cooperate with the flow regulating device 210 to adjust the flow between the first air supply port 206 and the second air supply port 208 . air-conditioning wind flow. The connecting passage 212 can be an extension of the main air supply passage 204, or a pipe arranged between the skin 102 of the cabin 100 and the interior trim panel 104, or a recess formed on the inner wall of the interior trim panel 104. groove.

Preferably, the flow regulating device 210 is disposed adjacent to the first air supply port 206 . As best shown in FIG. 3 , in one embodiment, the flow regulating device 210 may include a pivot 2104 disposed in a cavity defined by the connecting channel 212 , and can be positioned around the pivot 2104 in a first Rotate between the first state and the second state to respectively close the baffles 2102 of the first air outlet and the second air outlet. In the embodiment shown in the drawings, the baffle 2102 is roughly V-shaped, and its opening is advantageously directed downward, and the angle of the opening is greater than 90 degrees and less than 180 degrees. In detail, as shown in FIG. 3 and FIG. 4 , the baffle 2102 includes a substantially flat first plate-shaped portion 2102 a and a substantially flat second plate-shaped portion 2102 b, and the pivot 2104 passes through the first plate-shaped portion portion 2102a and the second plate-shaped portion 2102b in the transition portion, so that the first plate-shaped portion 2102a and the second plate-shaped portion 2102b can pivot thereabout. In the first state shown in Figure 5, the baffle 2102 is rotated so that the free edge of its first plate-shaped portion 2102a approaches or fits against the upper edge of the first air outlet 206, and at the same time, the second plate-shaped portion 2102a The extension direction of the portion 2102b is substantially downward so as not to hinder the downward flow of the airflow. At this time, the baffle plate 2102 can close the first air supply port 206 while opening the second air supply port 208 to the maximum. In the second state as shown in FIG. 6 , the baffle plate 2102 is rotated so that the free edges of its first plate-shaped portion 2102 a and the second plate-shaped portion 2102 b are respectively close to or attached to the lower part of the first air outlet 206 The edge and the wall of the connecting channel 212 , at this point, it can be understood that the length of the second plate-like portion 2102 b should be advantageously configured to be substantially equal to the distance from the pivot 2104 to the wall of the connecting channel 212 . In this way, the baffle plate 2102 basically closes the lower second air supply port 208 while opening the first air supply port 206 to the maximum. When in the intermediate position between the first state and the second state as shown in Figure 7, the baffle plate 2102 can simultaneously open the first air supply port 206 and the second air supply port 208, in this state, the baffle plate 2102 can still be rotated The baffle 2102 makes the flow ratio of the air-conditioning air from the first air supply port 206 and the second air supply port 208 meet the optimum requirement. In order to facilitate adjustment by passengers, the flow adjustment device 210 further includes a handle 2106 fixedly connected to the baffle plate 2102 and extending from the main air supply channel 204 for manual adjustment, as shown in FIG. 4 .

When the passenger on the seat 106 in the cabin 100 feels that the surrounding environment is relatively hot, the passenger can adjust the baffle 2102 above the seat 106 and below the luggage rack 108 through the handle 2106, so that the first air outlet arranged below the luggage rack 2106 The air supply volume of the air-conditioning air at 206 is increased and the air supply volume of the air-conditioning air at the second air supply port 208 is reduced, and the air supply direction can also be adjusted at the same time, so that the air-conditioning air with a lower temperature is blown to the passenger's head, thereby playing a role The purpose of rapid cooling.

When the ambient temperature is low, or the passenger’s lower body feels cold due to clothing, etc., the passenger can adjust the baffle 2102 under the luggage rack 2106 through the handle 2106 according to individual needs, and adjust the second air outlet 208 under the seat 106 The air supply volume of the air-conditioning air can be increased to increase the air supply volume of the air-conditioning air of the first air supply port 206, thereby improving the temperature of the surrounding environment of the lower part of the body and improving the comfort.

The above-mentioned air-conditioning wind comes from the air-conditioning system of the aircraft, and the air-conditioning system can be any one of the prior art, which will not be repeated here.

Through the air supply system 200 of the aircraft cabin 100 of the present invention, the temperature comfort requirements of passengers in different clothes and passengers with different sensitivities to the temperature and environmental conditions around the cabin 100 can be met under different ambient temperature conditions. The invention can improve the cockpit temperature environment in which the head is cool and the feet are hot in summer, and the head is hot and the feet are cool in winter, so as to avoid the temperature stratification phenomenon of the cockpit.

The technical content and technical characteristics of the present invention have been disclosed above, but it can be understood that under the creative idea of the present invention, those skilled in the art can make various changes and improvements to the above structure, but all belong to the protection scope of the present invention. The description of the above embodiments is illustrative rather than restrictive, and the protection scope of the present invention is determined by the claims.

Claims (6)

1. A kind of air supply system of aircraft cockpit, it comprises: an air source (202), which is used to provide air-conditioning air to the interior of the cockpit (100); a main air supply channel (204) defined between the skin (102) and interior trim panel (104) of the cabin (100) and in fluid communication with said air source (202); The first air supply port (206), which is defined on the trim panel (104) above the seat (106) and below the luggage rack (108) of the cockpit (100) and communicates with the main air supply channel (204), For blowing air to the upper body of the passenger sitting on the seat (106); The second air supply port (208), which is defined on the trim panel (104) below the seat (106) of the cockpit (100) and communicates with the main air supply channel (204), is used to The lower body of the passenger on the seat (106) is air-supplied; a flow regulating device (210), which is arranged in the main air supply channel (204) and is used to adjust the flow ratio of air-conditioning air from the first air supply port (206) and the second air supply port (208), A connecting channel (212), which communicates between the first air supply port (206) and the second air supply port (208), to adjust the first air supply port ( 206) and the air conditioning air flow between the second air outlet (208). 2. The air supply system of an aircraft cockpit according to claim 1, characterized in that, the flow regulating device (210) is arranged adjacent to the first air supply port (206). 3. The air supply system of the aircraft cockpit according to claim 2, characterized in that, the flow regulating device (210) comprises a pivot (2104) arranged in the cavity defined by the connecting channel (212), and a baffle (2102) capable of rotating around the pivot (2104) between a first state and a second state, in the first state, the baffle (2102) closes the first air outlet (206) and open the second air supply port (208), in the second state, the baffle (2102) closes the second air supply port (208) and opens the first air supply port (206 ). 4. The air supply system of the aircraft cockpit according to claim 3, characterized in that, the baffle (2102) is roughly V-shaped, its opening faces downward, and the angle of the opening is greater than 90 degrees and less than 180 degrees. 5. The air supply system of the aircraft cockpit according to claim 3, characterized in that, the flow regulating device (210) also includes a fixed connection to the baffle (2102) and from the main air supply channel ( 204) Extended handle (2106) for manual adjustment. 6. The air supply system of the aircraft cabin according to claim 1, characterized in that, the connecting channel (212) is arranged between the skin (102) and the interior panel (104) of the cabin (100) pipes, or grooves formed on the inner wall of the trim panel (104).