Semi-embedded bulge type heat dissipation cabin structure of airplane and small airplane

Abstract

The invention discloses a semi-embedded bulge type heat dissipation cabin structure of an aircraft and a small aircraft, and relates to the field of aviation heat management and intake and exhaust design. The semi-embedded bulge type heat dissipation cabin structure of the airplane specifically comprises a bulge structure, a heat dissipation cabin, a cooling module, an air inlet and an air outlet, the bulge structure is arranged on a straight section of an airplane body, the heat dissipation cabin is located in the bulge structure, the cooling module is obliquely arranged in the heat dissipation cabin, and the air inlet is located in the air outlet. The air inlet is formed in the windward side of the bulge structure, and the air outlet is formed in the bottom of the bulge structure. By optimizing the arrangement mode and the air inlet structure of the cooling module, the cooling ventilation quantity is guaranteed, the flight resistance is reduced, and the small aircraft cooling system is suitable for space-limited small aircraft cooling systems.

Description

Technical Field

[0001] This invention relates to the fields of aviation thermal management and air intake / exhaust design, and particularly to a semi-recessed bulge-type heat dissipation chamber structure for aircraft and small aircraft. Background Technology

[0002] In small aircraft, the cooling duct is typically located between the fuselage skin and the cockpit wall. Due to the limited space, the condenser, radiator, and fan components of the air conditioning system (collectively referred to as cooling modules) are usually quite large. Furthermore, these cooling modules need to be arranged as perpendicular to the airflow direction as possible to ensure even airflow across the cooling surface for better heat dissipation. If the cooling modules are installed flush with the fuselage skin (i.e., the fan surface is parallel to the incoming airflow), the insufficient gap between the cooling modules and the structural wall will obstruct airflow into the structure, drastically reducing the airflow through the cooling modules and significantly diminishing the cooling effect, failing to meet the operating requirements of the air conditioning system. If the cooling modules are installed completely perpendicular to the incoming airflow, the components will protrude from the fuselage skin, requiring large bulges for airflow rectification, which will create significant drag during level flight. Therefore, achieving efficient heat dissipation while also considering drag reduction within a limited space is a pressing technical challenge. Summary of the Invention

[0003] In view of this, the present invention provides a semi-recessed bulge-type heat dissipation chamber structure for aircraft and a small aircraft. By optimizing the arrangement of the cooling modules and the air intake structure, it ensures both heat dissipation and ventilation volume and reduces flight drag, making it suitable for heat dissipation systems of small aircraft with limited space.

[0004] The present invention provides a semi-recessed bulge-type heat dissipation compartment structure for aircraft, including a bulge structure, a heat dissipation compartment, a cooling module, an air inlet, and an air outlet. The bulge structure is arranged on a straight section of the fuselage, the heat dissipation compartment is located inside the bulge structure, the cooling module is arranged obliquely inside the heat dissipation compartment, the air inlet is opened on the windward side of the bulge structure, and the air outlet is opened at the bottom of the bulge structure.

[0005] Furthermore, the cooling module is arranged inside the heat dissipation chamber at an upward angle from the nose to the tail.

[0006] Furthermore, the cooling module includes a condenser, a radiator, and a fan, which are arranged sequentially from top to bottom inside the heat dissipation chamber.

[0007] Furthermore, the condenser is tilted upwards at a 20°-40° angle from the front to the rear of the unit, and there is a certain distance between the top surface of the condenser and the top of the heat dissipation chamber.

[0008] Furthermore, the air outlet is located on the bulge structure and at the bottom of the cooling module.

[0009] Furthermore, the air inlet extends upward from the front to the rear of the engine and tilts upward to form an air intake channel, the tilt angle of which is 8°-12°.

[0010] Furthermore, the upper edge of the air intake channel extends 20mm-40mm beyond the lower surface of the fuselage, and the lower edge of the air intake channel is lower than the lower edges of the condenser and the radiator.

[0011] Furthermore, the bulge structure is arranged in the belly position of the fuselage, and the bottom surface of the bulge structure protrudes from the lower surface of the fuselage.

[0012] Furthermore, the heat dissipation compartment includes a top surface and a side surface, the top surface being connected to the cabin floor, and the side surface being connected to the cabin longitudinal beam ribs.

[0013] The present invention also provides a small aircraft, including the semi-recessed bulge-shaped heat dissipation compartment structure described above.

[0014] Compared with existing technologies, the present invention has the following beneficial technical effects: This invention provides a semi-recessed bulge-type heat dissipation chamber structure for aircraft and a small aircraft. By optimizing the arrangement of the cooling modules and the structure of the air inlet, it ensures both heat dissipation and ventilation while reducing flight drag. Specifically, by arranging the cooling modules at an angle to maintain a distance from the inner wall of the heat dissipation chamber, airflow efficiency is improved. The upper edge of the air inlet extends beyond the fuselage surface, which can isolate low-energy flow in the boundary layer, increase incoming flow pressure, and increase ventilation. The lower edge of the air inlet is lower than the lower edge of the condenser, ensuring that the airflow blows directly onto the condenser core. The overall structure is compact and suitable for the limited space of small aircraft, balancing heat dissipation efficiency and drag reduction design. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of a semi-recessed bulge-shaped heat dissipation compartment structure for aircraft provided by the present invention.

[0016] Figure 2 This is a schematic diagram showing the distribution structure of the bulge structure, heat dissipation chamber, cooling module, air inlet, and air outlet in this invention.

[0017] Wherein: 10-bulge structure; 20-heat dissipation chamber; 21-top surface; 22-side surface; 30-cooling module; 31-condenser; 32-heat dissipation radiator; 33-fan; 40-air inlet; 50-air outlet; 60-fuselage; 61-head; 62-tail; 70-air inlet duct. Detailed Implementation

[0018] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0019] In the description of this invention, it should be noted that the orientations or positional relationships indicated in this description are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the purpose of facilitating the description of this invention and simplifying the description, and are not intended to indicate or imply that the parts or elements referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the invention.

[0020] Please see Figure 1-2 This invention provides a semi-recessed, bulge-type heat dissipation duct structure for aircraft, comprising a bulge structure 10, a heat dissipation duct 20, a cooling module 30, an air inlet 40, and an air outlet 50. The bulge structure 10 is arranged on a straight section of the fuselage 60, the heat dissipation duct 20 is located inside the bulge structure 10, the cooling module 30 is arranged obliquely inside the heat dissipation duct 20, the air inlet 40 is located on the windward side of the bulge structure 10, and the air outlet 50 is located at the bottom of the bulge structure 10. This invention, by optimizing the arrangement of the cooling module 30 and the structural design of the air inlet 40, ensures both heat dissipation and ventilation while reducing flight drag.

[0021] Specifically, the heat dissipation compartment 20 includes a top surface 21 and side surfaces 22. The top surface 21 is generally connected to the cabin floor, and there are four side surfaces 22, which are generally connected to the longitudinal beam ribs. The bulge structure 10 is located on the belly of the fuselage 60, and the bottom surface of the bulge structure 10 protrudes from the lower surface of the fuselage 60, which facilitates the placement of the air intake 40 on the windward side of the bulge structure 10, allowing external airflow to easily enter the heat dissipation compartment 20 from the air intake 40. The air outlet 50 is located on the bulge structure 10 and at the bottom of the cooling module 30, facilitating the exhaust of hot air.

[0022] Specifically, the cooling module 30 includes a condenser 31, a radiator 32, and a fan 33. The condenser 31, the radiator 32, and the fan 33 are arranged in order from top to bottom inside the heat dissipation chamber 20. That is, the condenser 31 is arranged at the top, the radiator 32 is arranged in the middle, and the fan 33 is arranged at the bottom. The condenser 31 serves to dissipate heat absorbed by the refrigerant from the cabin, acting as the "hot end" of the main air conditioning cycle. Its operation involves the compressor pumping high-temperature, high-pressure gaseous refrigerant (such as Freon) that absorbs heat from the cabin into the condenser. As cooler outside air flows through the condenser's fins and pipes, it carries away the refrigerant's heat, cooling it and causing it to condense into a high-temperature, high-pressure liquid. The radiator 32 dissipates heat from other aircraft systems (such as engines and electronic equipment) or from liquids used to regulate air temperature. Its operation involves a separate liquid cooling cycle in addition to the air conditioning cycle. The coolant (such as a water-glycol mixture) in this cycle flows through equipment requiring heat dissipation, absorbing heat and becoming a high-temperature liquid. This high-temperature liquid is then pumped into the radiator. As outside air flows through the radiator, it carries away the coolant's heat, cooling it down, and then the coolant returns to absorb heat, continuing the cycle. The function of fan 33 is to provide forced airflow, ensuring sufficient airflow over the surfaces of condenser 31 and radiator 32 during ground operations, low-speed flight, or when the air is thin at high altitudes. In flight, fan 33 primarily relies on the natural flow of ram air over the cooling compartment. However, before takeoff, when the aircraft is parked on the ground, or during low-speed taxiing, insufficient ram air leads to a sharp decrease in cooling efficiency. At this time, fan 33 activates, actively drawing in outside air and forcing it through the fins of condenser 31 and radiator 32, then expelling the hot air from outlet 50. It acts as a "source of air." Condenser 31 handles refrigerant, belonging to the refrigeration cycle; while radiator 32 handles coolant, belonging to the liquid cycle. They are typically installed side-by-side, sharing the cooling resources of fan 33 and the airflow.

[0023] When the aircraft is in flight, the airflow enters the heat dissipation chamber 20 through the air inlet 40. The high-speed airflow blows onto the surface of the condenser 31 core and the top wall of the heat dissipation chamber 20. After the incoming flow slows down, the dynamic pressure is converted into local high static pressure with a small loss. With the suction action of the fan 33, a sufficient amount of air can pass through the condenser 31, the heat dissipation chamber 32 and the fan 33 in sequence. The hot air is then discharged from the heat dissipation chamber 20 through the air outlet 40, completing the heat dissipation process.

[0024] Since the cooling module 30 is arranged upwards from the nose 61 to the tail 62 inside the heat dissipation compartment 20, the condenser 31, radiator 32, and fan 33 are also arranged upwards from the nose 61 to the tail 62 inside the heat dissipation compartment 20. This arrangement ensures a certain distance between the top surface of the condenser 31 and the top of the heat dissipation compartment 20, resulting in better airflow efficiency. Specifically, the condenser 31 is inclined upwards from the nose 61 to the tail 62 at an angle of 20°-40°, for example, 20°, 30°, or 44°.

[0025] Specifically, the air inlet 40 extends upwards from the nose 61 towards the tail 62, forming an air intake duct 70 with an inclination angle of 8°-12°, for example, 8°, 9°, 10°, 11°, or 12°, to ensure that the airflow within the duct does not undergo severe separation. The upper edge of the air intake duct 70 extends 20mm-40mm beyond the lower surface of the fuselage 60, for example, 20mm, 30mm, or 40mm, to isolate the low-energy flow in the boundary layer during flight and increase the average dynamic pressure of the incoming flow to increase the ventilation volume of the cooling module 30. The lower edge of the air intake duct 70 is lower than the lower edges of the condenser 31 and the radiator 20, ensuring that the external airflow can directly reach the core surface of the condenser 31.

[0026] This invention provides a semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft. During flight, airflow enters the heat dissipation chamber 20 through the air inlet 40. The high-speed airflow blows onto the surface of the condenser core 31 and the top wall of the heat dissipation chamber 20. After the incoming flow slows down, the dynamic pressure is converted into local high static pressure with minimal loss. Combined with the suction effect of the fan 33, sufficient air can pass sequentially through the condenser 31, radiator 32, and fan 33. The hot air is then discharged from the heat dissipation chamber 20 through the air outlet 40, completing the heat dissipation process. The structural space created by the medium-sized bulge shape allows for the inclined arrangement of the cooling module 30, separating it from the inner wall of the heat dissipation chamber 20 and deflecting it towards the direction of the incoming flow to achieve better airflow efficiency. An air inlet 40 is opened on the windward side of the bulge structure 10. External air enters the heat dissipation chamber 20 through the air inlet 40 and is deflected before flowing through the cooling module 30, satisfying the ventilation requirements of the cooling module 30 while also considering drag reduction design.

[0027] As described above, the semi-recessed bulge-type heat dissipation chamber structure for aircraft provided by this invention improves airflow efficiency by tilting the cooling module 30 to maintain a distance from the inner wall of the heat dissipation chamber 20; the upper edge of the air inlet 40 extends beyond the fuselage surface, which can isolate low-energy flow in the boundary layer, increase incoming flow pressure, and increase ventilation volume; the lower edge of the air inlet 40 is lower than the lower edge of the condenser, ensuring that the airflow blows directly onto the core of the condenser 31; the overall structure is compact, suitable for the limited space of small aircraft, and takes into account both heat dissipation efficiency and drag reduction design.

[0028] The present invention also provides a small aircraft, including the semi-recessed bulge-shaped heat dissipation nacelle structure described above. For other structures of the small aircraft, please refer to the prior art, which will not be repeated here.

[0029] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention in any way. Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present invention. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the scope of the present invention.

Claims

1. A semi-recessed, bulge-shaped heat dissipation compartment structure for aircraft, characterized in that: The device includes a bulge structure (10), a heat dissipation chamber (20), a cooling module (30), an air inlet (40), and an air outlet (50). The bulge structure (10) is arranged on the straight section of the fuselage (60). The heat dissipation chamber (20) is located inside the bulge structure (10). The cooling module (30) is arranged obliquely inside the heat dissipation chamber (20). The air inlet (40) is opened on the windward side of the bulge structure (10). The air outlet (50) is opened at the bottom of the bulge structure (10).

2. The semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft according to claim 1, characterized in that: The cooling module (30) is arranged inside the heat dissipation chamber (20) from the nose (61) to the tail (62) and tilted upward.

3. The semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft according to claim 2, characterized in that: The cooling module (30) includes a condenser (31), a radiator (32), and a fan (33), which are arranged in order from top to bottom inside the heat dissipation chamber (20).

4. The semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft according to claim 2, characterized in that: The condenser (31) is inclined upward at 20°-40° from the front (61) to the rear (62), and there is a certain distance between the top surface of the condenser (31) and the top of the heat dissipation chamber (20).

5. The semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft according to claim 1, characterized in that: The air outlet (50) is located on the bulge structure (10) and at the bottom of the cooling module (30).

6. The semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft according to claim 2, characterized in that: The air inlet (40) extends from the head (61) to the tail (62) and tilts upward to form an air intake channel (70), the tilt angle of which is 8°-12°.

7. The semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft according to claim 6, characterized in that: The upper edge of the air intake channel (70) extends 20mm-40mm beyond the lower surface of the fuselage (60), and the lower edge of the air intake channel (70) is lower than the lower edges of the condenser (31) and the radiator (20).

8. The semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft according to claim 1, characterized in that: The bulge structure (10) is located on the belly of the fuselage (60), and the bottom surface of the bulge structure (10) protrudes from the lower surface of the fuselage (60).

9. The semi-recessed, bulge-shaped heat dissipation chamber structure for aircraft according to claim 1, characterized in that: The heat dissipation compartment (20) includes a top surface (21) and a side surface (22). The top surface (21) is connected to the cabin floor, and the side surface (22) is connected to the cabin longitudinal beam ribs.

10. A small aircraft, characterized in that: Including the semi-recessed bulge-type heat dissipation chamber structure for aircraft as described in any one of claims 1-9.

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