An air conditioner structure for a low-altitude aircraft

Abstract

This utility model discloses an air conditioner structure for a low-altitude aircraft, relating to the field of low-altitude aircraft technology. It aims to solve the problems of space constraints, energy limitations, and rapid temperature regulation faced by air conditioners in existing low-altitude aircraft. The technical solution involves separating the air conditioner housing from the passenger cabin of the low-altitude aircraft via a firewall. The air conditioner housing is equipped with an air outlet and an air inlet, and also includes a first adjustment unit and a second adjustment unit for controlling the opening and closing of the air outlet and inlet. A brushless centrifugal fan is also installed inside the air conditioner housing, with an air conditioning filter, an evaporator core, and a PTC heater sequentially arranged between the brushless centrifugal fan and the air outlet. An integrated series structure design is adopted, with the entire unit installed at the front of the fuselage, isolated from the passenger cabin by the firewall, thus not occupying internal passenger cabin space and significantly improving cabin space utilization.

Description

Technical Field

[0001] This utility model relates to the field of low-altitude aircraft technology, specifically to an air conditioner structure for a low-altitude aircraft. Background Technology

[0002] Low-altitude aircraft, as an emerging mode of air transportation, are gradually being promoted and applied. With the rapid development of technologies such as drones and flying taxis, the air conditioning system of low-altitude aircraft has become a key component in ensuring passenger comfort and normal equipment operation. These aircraft typically have limited cabin space, highly integrated designs, and limited energy resources, requiring rapid cooling / heating over short distances.

[0003] Traditional low-altitude aircraft air conditioners are mostly located under the instrument panel or partially occupy the passenger cabin space, resulting in low cabin space utilization; the components are complex and heavy, which does not meet the requirements of lightweight aircraft design; the operating noise is high, affecting passenger comfort; and they cannot adapt to the complex aerodynamic environment and rapid temperature adjustment scenarios of low-altitude aircraft. Utility Model Content

[0004] The technical problem to be solved by this utility model is to overcome the existing defects and provide an air conditioner structure for low-altitude aircraft, which can effectively solve the problems in the background art.

[0005] To achieve the above objectives, this utility model discloses an air conditioner structure for a low-altitude aircraft. The technical solution adopted includes a front fuselage nose, an expansion valve, and an air conditioner housing. The air conditioner housing is installed on the front fuselage nose, and the air conditioner housing is connected to the air conditioning system pipeline through the expansion valve. The air conditioner housing is separated from the crew cabin of the low-altitude aircraft by a firewall. The air conditioner housing is provided with an air outlet and an air inlet respectively. The air conditioner housing is also equipped with a first adjustment unit and a second adjustment unit for controlling the opening and closing of the air outlet and the air inlet. The air conditioner housing is also equipped with a brushless centrifugal fan, and an air conditioning filter, an evaporator core and a PTC heater are arranged sequentially between the brushless centrifugal fan and the air outlet. The air inlet includes an internal return air duct and an external air intake duct. The air conditioner housing is connected to the passenger compartment and the outside world through the internal return air duct and the external air intake duct, respectively. It adopts an integrated series structure design and is installed as a whole at the front of the fuselage. It is isolated from the passenger compartment by a firewall, does not occupy the internal space of the passenger compartment, and significantly improves the utilization rate of cabin space.

[0006] As a preferred technical solution of this utility model, the air outlet includes a face air outlet and a defrost air outlet, and the air outlet is connected to the interior of the passenger compartment. The internal return air duct is located below the air outlet, which optimizes the air circulation in the cabin and improves comfort.

[0007] As a preferred technical solution of this utility model, the inner return air duct is located below the air outlet; the outer air intake duct adopts an arc-shaped air duct, and the opening direction of the outer air intake duct is not in the same direction as the low-altitude aircraft's travel direction. The arc-shaped outer air intake duct design reduces wind interference and ensures stable air intake.

[0008] As a preferred embodiment of this utility model, the first adjustment unit includes a defrost / blowing damper and a first damper shaft. The defrost / blowing damper is rotatably connected to the air conditioner housing via the first damper shaft, and the first damper shaft is connected to the output end of a first servo motor. The air conditioner housing is also provided with a first housing limiting rib and a second housing limiting rib corresponding to the position of the defrost / blowing damper. This simplifies the component design, and all adjustment functions can be achieved by driving two dampers with two sets of servo motors, reducing the number of parts and mold investment, and lowering weight and cost.

[0009] As a preferred technical solution of this utility model, the second adjustment unit includes an internal and external air regulating damper and a second damper shaft. The second damper shaft is rotatably connected to the air conditioner housing. One end of the second damper shaft is located inside the air conditioner housing and is equipped with the internal and external air regulating damper. The other end of the second damper shaft is connected to the output end of the second servo motor. The air conditioner housing is also provided with a third housing limiting rib and a fourth housing limiting rib corresponding to the position of the internal and external air regulating damper.

[0010] Compared with the prior art, the beneficial effects of this utility model are: This utility model adopts an integrated series structure design, is installed as a whole at the front of the fuselage nose, is isolated from the crew cabin by a firewall, does not occupy the internal space of the crew cabin, and significantly improves the utilization rate of cabin space.

[0011] The design of components is simplified, and all adjustment functions can be achieved by driving two dampers with two sets of servo motors, reducing the number of parts and mold investment, and reducing weight and cost.

[0012] The air conditioner unit is isolated from the passenger compartment, and the low-noise characteristics of the brushless centrifugal fan effectively reduce operating noise; the internal return air duct is located below the air outlet, optimizing air circulation in the cabin and improving comfort.

[0013] The arc-shaped external air intake duct design reduces wind interference and ensures stable air intake. Combined with the fast-switching defrost / temperature regulation mode and high-efficiency heat exchange components, it meets the needs of low-altitude aircraft for rapid temperature regulation and adaptation to complex environments. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the structure of this utility model; Figure 2 This is a schematic diagram of the internal structure of this utility model.

[0015] In the diagram: 1. Front unit head; 2. Expansion valve; 3. Air conditioner housing; 4. Brushless centrifugal fan; 5. Air conditioning filter; 6. Evaporator core; 7. PTC heater; 8. Firewall; 9. First housing limiting rib; 10. Defrost vent; 11. Defrost / face blowing damper; 12. Second housing limiting rib; 13. First damper shaft; 14. Face blowing vent; 15. Internal return air duct; 16. External air intake duct; 17. Third housing limiting rib; 18. Internal and external air regulating damper; 19. Second damper shaft; 20. Fourth housing limiting rib; 21. First servo motor; 22. Second servo motor. Detailed Implementation

[0016] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model. Example 1

[0017] like Figures 1 to 2 As shown, this utility model discloses an air conditioner structure for a low-altitude aircraft. The technical solution adopted includes a front fuselage nose 1, an expansion valve 2, and an air conditioner housing 3. The air conditioner housing 3 is installed on the front fuselage nose 1, and the air conditioner housing 3 is connected to the air conditioning system pipeline through the expansion valve 2; thereby realizing refrigerant flow control and throttling pressure reduction.

[0018] The air conditioner housing 3 is separated from the crew cabin of the low-altitude aircraft by a firewall 8; The air conditioner housing 3 is provided with an air outlet and an air inlet. The air outlet includes a face air outlet 14 and a defrost air outlet 10, and the air outlet is connected to the interior of the passenger compartment.

[0019] The air inlet includes an inner return air duct 15 and an outer air intake duct 16. The air conditioner housing 3 is connected to the passenger compartment and the outside through the inner return air duct 15 and the outer air intake duct 16, respectively.

[0020] The air conditioner housing 3 is isolated from the passenger compartment by a firewall 8, and is connected to the passenger compartment through an internal return air duct 15, a face air vent 14 and a defrost air vent 10, so as to avoid occupying the cabin space and reduce noise transmission.

[0021] The internal return air duct 15 is located below the air outlet; the external air intake duct 16 adopts an arc-shaped air duct, and the opening of the external air intake duct 16 is not in the same direction as the direction of travel of the low-altitude aircraft.

[0022] The air conditioner housing 3 is also equipped with a brushless centrifugal fan 4, and an air conditioning filter 5, an evaporator core 6 and a PTC heater 7 are arranged sequentially between the brushless centrifugal fan 4 and the air outlet. The brushless centrifugal fan 4 provides power. After the air is filtered by the air conditioning filter 5, it is cooled by the evaporator core 6 or heated by the PTC 7, and then sent into the passenger compartment through the corresponding air outlet.

[0023] The air conditioner housing 3 is also equipped with a first adjustment unit and a second adjustment unit for controlling the opening and closing of the air outlet and the air inlet. The first adjustment unit includes a defrost / blowing damper 11 and a first damper shaft 13. The defrost / blowing damper 11 is rotatably connected to the air conditioner housing 3 via the first damper shaft 13, and the first damper shaft 13 is connected to the output end of the first servo motor 21. The air conditioner housing 3 is also provided with a first housing limiting rib 9 and a second housing limiting rib 12 corresponding to the position of the defrost / blowing damper 11.

[0024] The air outlet mode is controlled by the first adjustment unit: the first servo motor 21 drives the first damper shaft 13, which in turn drives the defrost / blow air damper 11 to rotate. When it contacts the second housing limit rib 12, the defrost air outlet 10 opens for front window defrosting; when it contacts the first housing limit rib 9, the blow air outlet 14 opens for cabin temperature adjustment.

[0025] The second adjustment unit includes an indoor / outdoor air regulating damper 18 and a second damper shaft 19. The second damper shaft 19 is rotatably connected to the air conditioner housing 3. One end of the second damper shaft 19 is located inside the air conditioner housing 3 and is equipped with the indoor / outdoor air regulating damper 18. The other end of the second damper shaft 19 is connected to the output end of the second servo motor 22. The air conditioner housing 3 is also provided with a third housing limiting rib 17 and a fourth housing limiting rib 20 corresponding to the position of the indoor / outdoor air regulating damper 18.

[0026] The air intake mode is controlled by the second adjustment unit: the second servo motor 22 drives the second damper shaft 19, which in turn drives the internal and external air regulating damper 18 to rotate. When the damper contacts the fourth housing limit rib 20, the internal return air duct 15 opens to achieve internal circulation; when it contacts the third housing limit rib 17, the external air intake duct 16 opens to achieve external circulation; the middle position is the mixed air mode.

[0027] The circuits and mechanical connections involved in this utility model are common practices used by those skilled in the art, and technical inspiration can be obtained through a limited number of experiments. They are common knowledge.

[0028] Components not described in detail in this article are existing technologies.

[0029] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An air conditioner structure for a low-altitude aircraft, comprising a front fuselage nose (1), an expansion valve (2), and an air conditioner housing (3), wherein the air conditioner housing (3) is mounted on the front fuselage nose (1), and the air conditioner housing (3) is connected to an air conditioning system pipeline through the expansion valve (2); Its features are: The air conditioner housing (3) is separated from the crew cabin of the low-altitude aircraft by a firewall (8); The air conditioner housing (3) is provided with an air outlet and an air inlet respectively. The air conditioner housing (3) is also equipped with a first adjustment unit and a second adjustment unit for controlling the opening and closing of the air outlet and the air inlet. The air conditioner housing (3) is also equipped with a brushless centrifugal fan (4), and an air conditioning filter (5), an evaporator core (6) and a PTC heater (7) are arranged in sequence between the brushless centrifugal fan (4) and the air outlet. The air inlet includes an inner return air duct (15) and an outer air intake duct (16). The air conditioner housing (3) is connected to the passenger compartment and the outside through the inner return air duct (15) and the outer air intake duct (16), respectively.

2. The air conditioner structure for a low-altitude aircraft according to claim 1, characterized in that: The air outlet includes a face air outlet (14) and a defrost air outlet (10), and the air outlet is connected to the interior of the crew cabin.

3. The air conditioner structure for a low-altitude aircraft according to claim 1 or 2, characterized in that: The inner return air duct (15) is located below the air outlet; the outer air intake duct (16) adopts an arc-shaped air duct, and the opening of the outer air intake duct (16) is not in the same direction as the direction of travel of the low-altitude aircraft.

4. The air conditioner structure for a low-altitude aircraft according to claim 1, characterized in that: The first adjustment unit includes a defrost / blowing damper (11) and a first damper shaft (13). The defrost / blowing damper (11) is rotatably connected to the air conditioner housing (3) through the first damper shaft (13), and the first damper shaft (13) is connected to the output end of the first servo motor (21). The air conditioner housing (3) is also provided with a first housing limiting rib (9) and a second housing limiting rib (12) corresponding to the position of the defrost / blowing damper (11).

5. The air conditioner structure for a low-altitude aircraft according to claim 1, characterized in that: The second adjustment unit includes an in-situ air regulating damper (18) and a second damper shaft (19). The second damper shaft (19) is rotatably connected to the air conditioner housing (3). One end of the second damper shaft (19) is located inside the air conditioner housing (3) and is equipped with the in-situ air regulating damper (18). The other end of the second damper shaft (19) is connected to the output end of the second servo motor (22). The air conditioner housing (3) is also provided with a third housing limiting rib (17) and a fourth housing limiting rib (20) corresponding to the position of the in-situ air regulating damper (18).

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