Main landing gear cabin ventilation device and aircraft

Abstract

The invention discloses a main landing gear cabin ventilation device and an aircraft, relates to the technical field related to aircraft environment control oxygen, and aims to solve the problems that an existing ventilation device cannot adjust the ram air flow in a main air supply pipeline according to the temperature of an aircraft wheel assembly, and the economical efficiency is low. The main landing gear cabin ventilation device comprises a main air supply pipeline, a ventilation disc and a flow adjusting structure, the ventilation disc is provided with an air inlet end face, and air inlet holes are formed in the air inlet end face; the flow adjusting structure comprises a baffle, the baffle is arranged on the leeward side of the air inlet end face of the ventilation disc and connected with the transmission part, the heat transfer part is connected with an air collecting cover of the airplane wheel assembly and the air bag so as to heat or cool air in the air bag to enable the air bag to expand or contract, one end of the transmission part is connected with the air bag, and the other end of the transmission part is connected with the baffle. The transmission part is driven to move through expansion or contraction of the air bag, so that the baffle rotates relative to the air inlet end face, the circulation area of the air inlet hole is adjusted, and flow adjustment of the main air supply pipeline is achieved.

Description

Technical Field

[0001] The present application relates to the technical field related to aircraft environmental control oxygen, and in particular to a main landing gear compartment ventilation device and an aircraft. Background Art

[0002] The aircraft taxis from the ground and takes off. After the wheels leave the ground, the brakes are applied and the wheels are stopped in a very short time. After the wheels stop rotating, they are retracted into the main landing gear bay and the hatch door is closed. The entire process, from the wheels leaving the ground, the landing gear retracted to the hatch door closing, is completed in a relatively short time. Since the time required for the wheels to change from a high-speed rotating state to a stopped rotating state is extremely short, huge braking energy needs to be applied to the wheels. The large amount of heat generated by friction cannot be quickly discharged from the cabin, which will cause the temperature inside the cabin to rise sharply after the landing gear is retracted into the cabin, which may cause the fuselage structure to overheat and affect its structural strength.

[0003] At the same time, since the main landing gear door is closed, the entire cabin is in a closed state, resulting in a slow cooling rate of the brake carbon disc in the air. For short-distance flights, the brake carbon disc may still be at a relatively high temperature when the aircraft is about to land. The taxiing brake after landing will further increase the temperature of the brake carbon disc. Excessive temperature may cause accidents such as wheel failure, tire explosion, and melting of fusible plugs, affecting aircraft safety; it will also increase the turnaround time, affect aircraft dispatch, and reduce economic efficiency.

[0004] However, the existing aircraft is equipped with a ventilation system in the main landing gear compartment, that is, during flight, cooling air is provided to the cabin through the ram air inlet to achieve rapid cooling of the brake carbon disc and cooling of the cabin environment. Its disadvantage is that the cooling air flow entering the cabin through the ram air inlet is uncontrollable and is completely affected by the flight state of the aircraft. Usually, the speed of the aircraft is relatively low during the climbing stage, until it reaches a higher flight speed during the cruising stage, that is, the ram air flow entering the cabin gradually increases until it reaches stability during the cruising stage. At the same time, as the flight altitude increases, the external ambient temperature gradually decreases. Therefore, from the aircraft takeoff to cruising, the amount of cold entering the main landing gear compartment through the ram air inlet gradually increases. After the landing gear is retracted into the cabin during the climbing stage, the temperature of the brake carbon disc gradually decreases, and the cabin environment temperature first increases and then decreases, and its high temperature state is in a period after the cabin door is closed. That is, the amount of cold supplied to the cabin by the ram air inlet does not match the cabin cooling demand. Especially in the cruise phase, when the temperature of the brake carbon disc has dropped to the target temperature, a large amount of ram air is still supplied, providing unnecessary cooling for the cabin. At this time, the increased aerodynamic resistance of the ram air inlet is invalid resistance, which increases the fuel compensation loss and seriously affects the economy of the aircraft. Summary of the invention

[0005] The present application provides a main landing gear compartment ventilation device and an aircraft, which can solve the problem that the existing ventilation device cannot adjust the ram air flow in the main air supply duct according to the temperature of the wheel assembly and has low economy.

[0006] To achieve the above-mentioned purpose, the main landing gear compartment ventilation device provided by the present application includes:

[0007] a main air supply pipeline, wherein a first port of the main air supply pipeline is communicated with a ram air inlet, and a second port of the main air supply pipeline is arranged opposite to a wheel assembly in the main landing gear compartment so as to deliver ram air to the wheel assembly;

[0008] A ventilation disk is arranged in the main air supply pipeline, the ventilation disk has an air inlet end surface, and the air inlet end surface is provided with an air inlet hole;

[0009] A flow regulating structure includes a baffle, a heat transfer element, an airbag and a transmission component. The baffle is arranged on the leeward side of the air inlet end face of the ventilation disc and is connected to the transmission component. The heat transfer element is connected to the air collecting hood of the wheel assembly and the airbag to heat or cool the air in the airbag to expand or contract the airbag. One end of the transmission component is connected to the airbag and the other end is connected to the baffle. The expansion or contraction of the airbag drives the transmission component to move, thereby realizing the rotation of the baffle relative to the air inlet end face to adjust the flow area of ​​the air inlet hole and realize the flow regulation of the main air supply duct.

[0010] In this technical solution, the heat transfer component connects the air hood and the airbag of the wheel assembly to achieve a heat-conducting connection between the airbag and the air hood, so that the temperature of the air hood can heat or cool the air in the airbag to achieve the expansion or contraction of the airbag. At the same time, since one end of the transmission component is connected to the airbag and the other end is connected to the baffle, when the airbag expands or contracts, it can drive the transmission component to move in a fixed direction, and then drive the baffle to rotate relative to the air inlet end face to adjust the area of ​​the baffle blocking or exposing the air inlet hole, so that the flow area of ​​the air inlet hole is adjusted, and the flow regulation of the main air supply duct is further achieved. In short, the flow rate of the ram air in the above-mentioned main air supply duct can be adaptively adjusted according to the temperature of the air hood in the wheel assembly, so as to realize on-demand cooling of the wheel assembly, thereby improving the economy of the entire system.

[0011] In some embodiments of the present application, a groove is provided on a side of the baffle facing away from the air inlet end surface of the ventilating disc, and an end of the transmission component facing away from the airbag is slidably fitted in the groove, wherein the airbag can drive the transmission component to move along a first direction, and the groove is arranged obliquely relative to the first direction;

[0012] The transmission component comprises a transmission rod and a pin, one end of the transmission rod is connected to the airbag, and the other end is connected to the pin, and the pin is slidably fitted in the groove.

[0013] In some embodiments of the present application, the air inlet end surface is circular and is provided with a plurality of air inlet hole groups, each of which includes a plurality of air inlet holes arranged at intervals along the radial direction of the air inlet end surface, and the flow area of ​​the plurality of air inlet holes in each of which gradually increases from the center of the air inlet end surface to the edge of the air inlet end surface;

[0014] Wherein, the baffle comprises a middle connecting portion and a plurality of blades, and the radial inner sides of the plurality of blades are connected to the middle connecting portion;

[0015] When all the air inlet holes are in an exposed state, the orthographic projections of the fan blades on the air inlet end surface and each group of the air inlet holes are alternately arranged in sequence along the circumference of the air inlet end surface;

[0016] When all the air inlet holes are in a blocked state, each group of the air inlet holes is located within the orthographic projection of the corresponding fan blade on the air inlet end surface.

[0017] In some embodiments of the present application, the ventilation disc also includes an exhaust end face, which is arranged at the second port and is spaced apart from the air inlet end face to enclose an installation space, the airbag and the transmission component are arranged in the installation space, and the bottom of the airbag is connected to the exhaust end face.

[0018] In some embodiments of the present application, the airbag can drive the transmission component to move along the first direction, and the main landing gear compartment ventilation device further includes:

[0019] A protective cover is arranged in the installation space and arranged on the periphery of the airbag and the transmission component. A through groove is provided on the side of the protective cover close to the air inlet end surface, and the through groove extends along a first direction. An end of the transmission component facing away from the airbag extends out of the through groove and is connected to the baffle.

[0020] In some embodiments of the present application, the main landing gear compartment ventilation device further includes:

[0021] A bypass pipeline, wherein the air inlet of the bypass pipeline is used to communicate with the ram air inlet, and the exhaust port of the bypass pipeline is used to communicate with the skin exhaust port.

[0022] In some embodiments of the present application, the main landing gear compartment ventilation device further includes:

[0023] The resistance module is arranged in the bypass pipeline and can adjust the flow resistance of the bypass pipeline.

[0024] In some embodiments of the present application, the baffle is rotatably connected to the air inlet end face, the baffle is arranged parallel to the air inlet end face, and the center lines of the two coincide.

[0025] In some embodiments of the present application, the heat transfer element is a heat pipe.

[0026] On the other hand, the present application also provides an aircraft, comprising a main landing gear compartment ventilation device as described in any of the above technical solutions.

[0027] Since the aircraft provided by the present application includes the main landing gear compartment ventilation device as described in any of the above technical solutions, the two can solve the same technical problem and achieve the same technical effect. In other words, since the aircraft has the main landing gear compartment ventilation device as described in any of the above technical solutions, the flow rate of the main air supply pipeline in the main landing gear compartment ventilation device can be adaptively adjusted according to the temperature of the air collecting hood in the wheel assembly of the aircraft, so as to realize the cooling of the wheel assembly on demand, thereby improving the economy of the entire system. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0029] Figure 1 is a schematic structural diagram of a main landing gear compartment ventilation device in an embodiment of the present application;

[0030] Figure 2 is a cross-sectional view of a flow regulating structure in a main landing gear compartment ventilation device in an embodiment of the present application, so as to clearly illustrate the specific structure of the flow regulating structure;

[0031] Figure 3 This is a schematic diagram of the structure in which the baffle completely exposes the air inlet hole in the flow regulating structure in the embodiment of the present application;

[0032] Figure 4 This is a schematic diagram of a structure in which a baffle completely blocks an air inlet in a flow regulating structure in an embodiment of the present application;

[0033] Figure 5 It is a schematic diagram of a structure in which a baffle partially blocks an air inlet hole in a flow regulating structure in an embodiment of the present application;

[0034] Figure 6 It is a structural schematic diagram of another setting position of the groove in the embodiment of the present application.

[0035] The main reference numerals in the drawings of this application specification are described as follows:

[0036] 1-Main air supply duct;

[0037] 2-ventilation plate; 21-air inlet end face; 211-air inlet hole; 22-air exhaust end face;

[0038] 3-flow regulating structure; 31-baffle; 311-channel; 312-middle connecting part; 313-fan blade; 32-heat transfer element; 33-air bag; 34-transmission mechanism; 341-transmission rod; 342-pin;

[0039] 4- Protective cover;

[0040] 5-Bypass pipeline;

[0041] 6- Resistance module;

[0042] 100 - ram air inlet;

[0043] 200-wheel assembly; 201-wind collecting cover;

[0044] 300-Skin exhaust port. DETAILED DESCRIPTION

[0045] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0046] In the description of the present application, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0047] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0048] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0049] The present application provides a main landing gear compartment ventilation device and an aircraft, which are described in detail below. It should be noted that the description order of the following embodiments does not limit the preferred order of the embodiments of the present application. In the following embodiments, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, please refer to the relevant description of other embodiments.

[0050] Reference Figure 1 to Figure 3 The main landing gear compartment ventilation device provided in the present application includes a main air supply duct 1, a ventilation disc 2 and a flow regulating structure 3. The first port of the main air supply duct 1 is used to communicate with the ram air inlet 100, and the second port of the main air supply duct 1 is arranged opposite to the wheel assembly 200 in the main landing gear compartment to deliver ram air to the wheel assembly 200, so as to deliver cooling air to the designated position of the cooled component. The ventilation disc 2 is arranged in the main air supply duct 1, and the ventilation disc 2 has an air inlet end face 21, and the air inlet end face 21 is provided with an air inlet hole 211 for the ram air to pass through. The flow regulating structure 3 includes a baffle 31, a heat transfer element 32, an airbag 33 and a transmission component 34. The baffle 31 is arranged on the leeward side of the air inlet end face 21 of the ventilation disk 2 and is connected to the transmission component 34. The heat transfer element 32 is connected to the air collecting hood 201 of the wheel assembly 200 and the airbag 33 to heat or cool the air in the airbag 33 to expand or contract the airbag 33. One end of the transmission component 34 is connected to the airbag 33 and the other end is connected to the baffle 31. The expansion or contraction of the airbag 33 drives the transmission component 34 to move, thereby realizing the rotation of the baffle 31 relative to the air inlet end face 21 to adjust the flow area of ​​the air inlet hole 211 and realize the flow regulation of the main air supply pipeline 1.

[0051] In this technical solution, the heat transfer member 32 connects the air collecting hood 201 and the air bag 33 of the wheel assembly 200 to achieve a heat-conducting connection between the air bag 33 and the air collecting hood 201, so that the temperature of the air collecting hood 201 can heat or cool the air in the air bag 33 to achieve the expansion or contraction of the air bag 33. At the same time, since one end of the transmission component 34 is connected to the air bag 33 and the other end is connected to the baffle 31, when the air bag 33 expands or contracts, it can drive the transmission component 34 to move in a fixed direction, and then drive the baffle 31 to rotate relative to the air inlet end face 21 to adjust the area of ​​the baffle 31 covering or exposing the air inlet hole 211, so that the flow area of ​​the air inlet hole 211 is adjusted, and the flow regulation of the main air supply pipeline 1 is further achieved. In short, the flow rate of the ram air in the above-mentioned main air supply pipeline 1 can be adaptively adjusted according to the temperature of the air collecting hood 201 in the wheel assembly 200, so as to realize the cooling of the wheel assembly 200 on demand, thereby improving the economy of the entire system.

[0052] The ram air inlet 100 is located on the ram side of the skin and is used to introduce cold air from the outside environment into the main landing gear compartment to provide cooling for ventilation in the compartment. Specifically, when the wheel assembly 200 is in a high temperature state, the airbag 33 expands, the transmission component 34 drives the baffle 31 to rotate, and the baffle 31 gradually reduces the shielding area of ​​the air inlet 211. At this time, the flow area of ​​the air inlet 211 gradually increases to the maximum, such as Figure 3 On the contrary, when the wheel assembly 200 does not need to be cooled, the airbag 33 shrinks, the transmission component 34 drives the baffle 31 to rotate in the opposite direction, and the baffle 31 gradually increases the shielding area of ​​the air inlet 211 until the air inlet 211 is completely covered, as shown in FIG. Figure 4 As shown, at this time, the flow area of ​​the air inlet 211 is the smallest. That is, the main landing gear bay ventilation device can automatically adjust the ram air flow in the main air supply duct 1 according to the temperature state of the wheel assembly 200, and the main landing gear bay is cooled on demand.

[0053] It should be noted that the baffle 31 rotates relative to the air inlet end surface 21 to block the air inlet hole 211 or expose the air inlet hole 211. In other words, the baffle 31 can rotate relative to the air inlet end surface 21 between a wind-blocking position that completely blocks the air inlet hole 221 and a ventilation position that completely exposes the air inlet hole 221, and the baffle 31 can stop at the wind-blocking position (i.e. Figure 4 status shown), ventilation position (i.e. Figure 3 As shown in the state) and any position between the wind shielding position and the ventilation position, such as Figure 5 When the baffle 31 is in the wind-blocking position, the second port of the main air supply pipeline 1 will not deliver ram air to the wheel assembly 200, and when the baffle 31 is in the ventilation position, the flow rate of ram air delivered by the second port of the main air supply pipeline 1 to the wheel assembly 200 is the largest.

[0054] Based on the above embodiment, the heat transfer element 32 is a heat pipe, one end of the heat pipe is directly connected to the air collecting hood 201, and the other end is inserted into the airbag 33 to heat or cool the air in the airbag 33 to expand or contract the airbag 33. The heat pipe has a high heat transfer efficiency, thereby ensuring that the volume of the airbag 33 and the temperature of the air collecting hood 201 are more matched, thereby ensuring that the flow rate of the ram air in the main air supply duct 1 is more matched with the temperature of the air collecting hood 201.

[0055] Specifically, when the wheel assembly 200 is in a high temperature state, the heat is transferred to the airbag 33 by means of a heat pipe. The air in the airbag 33 is heated and its top structure expands upward, pushing the transmission component 34 connected to its top to move upward. The transmission component 34 converts the linear motion generated by the expansion of the airbag 33 into rotational motion, driving the baffle 31 to rotate so that its obstruction to the air inlet 211 is gradually reduced until the air inlet 211 is completely exposed, at which time the flow area of ​​the air inlet 211 reaches a maximum.

[0056] On the contrary, when the wheel assembly 200 does not need to be cooled, the temperature transmitted to the airbag 33 through the heat pipe is relatively low, and the top structure of the airbag 33 contracts downward to drive the transmission component 34 to move downward. The transmission component 34 converts the linear motion generated by the contraction of the airbag 33 into rotational motion, driving the baffle 31 to rotate in the opposite direction to gradually increase the shielding of the air inlet 211 until the air inlet 211 is completely covered. At this time, the flow area of ​​the air inlet 211 reaches the minimum. The present application utilizes the combined structure of the heat pipe-airbag 33-transmission component 34-baffle 31 to realize automatic adjustment of the flow of the main air supply pipeline. The combined structure is simple in structure and easy to implement.

[0057] In some embodiments of the present application, a groove 311 is provided on one side of the baffle 31 facing away from the air inlet end surface 21 of the ventilating disc 2, and one end of the transmission component 34 facing away from the airbag 33 is slidably fitted in the groove 311, wherein the airbag 33 can drive the transmission component 34 to move along the first direction z, and the groove 311 is arranged obliquely relative to the first direction z. In addition, the transmission component 34 includes a transmission rod 341 and a pin 342, one end of the transmission rod 341 is connected to the airbag 33, and the other end is connected to the pin 342, and the pin 342 is slidably fitted in the groove 311. Therefore, when the transmission rod 341 moves up and down along the first direction Z, the pin 342 connected to the end of the transmission rod 341 will move synchronously with the transmission rod 341, and it can apply upward or downward pressure to the groove wall of the groove 311 to push the baffle 31 to rotate. For example, the transmission rod 341 is L-shaped, and it is a rigid structure, which ensures that the power transmission between the airbag 33 and the baffle 31 is more reliable.

[0058] Alternatively, in some other embodiments, the transmission component 34 includes a meshing gear and a rack, wherein the rack is fixed to the top of the airbag 33 and can move up and down along the first direction z following the expansion or contraction of the airbag 33, and the gear is coaxially fixedly connected to the baffle 31. Thus, when the gear rotates under the action of the rack, the baffle 31 can be driven to rotate.

[0059] It can be understood that the transmission component 34 can convert the linear motion of the airbag 33 along the first direction z when it expands or contracts into the rotational motion of the baffle 31, so as to drive the baffle 31 to rotate. For example, the transmission component 34 can also be a crank slider mechanism.

[0060] In some embodiments of the present application, the air inlet end face 21 is circular and is provided with a plurality of air inlet hole groups, each of which includes a plurality of air inlet holes 211 arranged at intervals along the radial direction of the air inlet end face 21, and the flow area of ​​the plurality of air inlet holes 311 in each air inlet hole group gradually increases from the center of the air inlet end face 21 to the edge of the air inlet end face 21. Among them, the baffle 31 includes an intermediate connecting portion 312 and a plurality of fan blades 313, and the radial inner sides of the plurality of fan blades 313 are connected to the intermediate connecting portion 312. Specifically, when all the air inlet holes 211 are in an exposed state, the orthographic projections of the fan blades 313 on the air inlet end face 21 are arranged alternately with each air inlet hole group, such as Figure 3 When all the air inlet holes 211 are in the blocked state, each group of air inlet holes is located within the orthographic projection of the corresponding fan blade 313 on the air inlet end surface 21, as shown in FIG. Figure 4 The above technical solution of the present application can achieve synchronous adjustment of the flow areas of all air inlet holes 211 .

[0061] In some embodiments of the present application, the ventilated disc 2 also includes an exhaust end face 22, which is arranged at the second port and is spaced apart from the air inlet end face 21 to enclose and form an installation space, and the airbag 33 and the transmission component 34 are arranged in the installation space, and the bottom of the airbag 33 is connected to the exhaust end face 22. This ensures that the flow regulating structure 3 does not need to occupy additional space, that is, all the components therein are installed in the installation space defined by the air inlet end face 21 and the exhaust end face 22. In addition, it can be ensured that the cooling air enters the wheel assembly 200 with the shortest path and maximum momentum, providing sufficient cooling capacity for cooling the brake carbon disc.

[0062] For example, there are eight groups of air inlet hole groups, which are distributed at equal angles around the center of the air inlet end surface 21, and the air inlet holes 211 in each of the air inlet hole groups are circular, and the diameters of the multiple air inlet holes 211 in each group of air inlet hole groups increase successively from the center of the air inlet end surface 21 to the edge of the air inlet end surface 21.

[0063] It can be understood that the exhaust end surface 22 is provided with an exhaust hole for the ram air to pass through, and the exhaust hole is arranged opposite to the vent on the wind collecting cover 201. The bottom of the airbag 33 is fixed and flush with the exhaust end surface 22. The top of the airbag 33 is a freely expandable surface, which is rigidly connected to the transmission component 34. When the airbag 33 expands, the top structure expands upward, driving the transmission component 34 to move upward; conversely, when the airbag 33 contracts, the top structure of the airbag 33 drives the transmission component 34 to move downward.

[0064] In some embodiments of the present application, the above-mentioned groove 311 is arranged on the side of the middle connecting portion 312 facing away from the air inlet end face 21. When all the air inlet holes 211 are in an exposed state, the orthographic projection of the fan blades 313 on the air inlet end face 21 is arranged alternately with each group of air inlet holes, and the transmission rod 341 moves to the top of the groove 311. At this time, the airbag 33 expands to a maximum volume. When all the air inlet holes 211 are in a blocked state, each group of air inlet holes is located within the orthographic projection of the corresponding fan blade 313 on the air inlet end face 21, and the transmission rod 341 moves to the bottom of the groove 311. At this time, the airbag 33 shrinks to a minimum volume. Of course, the above-mentioned groove 311 can also be arranged on the side of the fan blade 313 facing away from the air inlet end face 21, such as Figure 6 shown.

[0065] In some embodiments of the present application, the main landing gear compartment ventilation device further includes a protective cover 4. The protective cover 4 is arranged in the installation space and arranged on the periphery of the airbag 33 and the transmission component 34. A through slot is provided on the side of the protective cover 4 close to the air inlet end face 21. The through slot extends along the first direction z. The end of the transmission component 34 facing away from the airbag 33 extends out of the through slot and is connected to the baffle 31. Therefore, the technical solution can protect the airbag 33 and the transmission component 34 by providing the protective cover 4, and prevent them from being damaged by the ram airflow flowing through the air inlet end face 21. In addition, the through slot provided on the protective cover 4 can also guide the partial structure of the transmission component 34 located in the through slot, so as to ensure that the transmission component 34 can only move along the first direction z.

[0066] It should be noted that, for the embodiment in which the transmission component 34 includes a transmission rod 341 and a pin 342, the transmission rod 341 is disposed in the protective cover 4, and the end thereof facing away from the airbag 33 is connected with the pin 342, and the pin 342 is slidably fitted in the groove 311, and the pin 342 is conducive to achieving the sliding fit between the transmission rod 341 and the groove 311, wherein the pin 342 and the transmission rod 341 can be rigidly connected together by welding, threaded connection or clamping connection. Of course, in some embodiments, the transmission component 34 only includes the transmission rod, and the end of the transmission rod facing away from the airbag 33 is directly slidably fitted in the groove 311.

[0067] For example, one end of the protective cover 4 facing the baffle 31 is directly connected to the groove 311, and a through groove is provided on the side of the protective cover 4 close to the air inlet end face 21. The size of the through groove in the first direction Z is the same as the size of the groove 311 in the first direction Z, so as to ensure that when the pin 342 moves to any position in the groove 311, the movement of the transmission rod 341 connected thereto in the protective cover 4 is not restricted.

[0068] Specifically, if Figure 3 As shown, when the pin 342 moves to the top of the channel 311, the transmission rod 341 moves to the top of the through slot accordingly. Similarly, when the pin 342 moves to the bottom of the channel 311, the transmission rod 341 moves to the bottom of the through slot accordingly.

[0069] In some embodiments of the present application, the baffle 31 includes an intermediate connection portion 312 and a plurality of blades 313, the radial inner sides of the plurality of blades 313 are connected to the intermediate connection portion 312, and the groove 311 is provided in the intermediate connection portion 312. In the embodiment, the intermediate connection portion 312 is not provided with an air inlet hole 211 within the positive projection range of the air inlet end face 21, and the baffle 31 is prevented from moving in the X / Y / Z direction by rotating the intermediate connection portion 312 and the air inlet end face 21, so that it can only move around the central axis of the air inlet end face 21 (for example Figure 2 For example, the baffle 31 includes an intermediate connection portion 312 and a plurality of blades 313, the radial inner sides of the plurality of blades 313 are connected to the intermediate connection portion 312, and the groove 311 is provided on the side of the blade 313 facing away from the air inlet end face 21, by rotating the intermediate connection portion 312 and the air inlet end face 21, the baffle 31 is prevented from moving in the X / Y / Z directions, so that it can only move around the central axis of the air inlet end face 21 (for example Figure 2 The protective cover 4 is provided with a plurality of air intake holes 211 disposed on the air intake end face 21. The protective cover 4 is provided with a plurality of air intake holes 212 disposed on the air intake end face 21. The protective cover 4 is provided with a plurality of air intake holes 211 disposed on the air intake end face 21. The protective cover 4 is provided with a plurality of air intake holes 211 disposed on the air intake end face 21. The protective cover 4 is provided with a plurality of air intake holes 211 disposed on the air intake end face 21. The protective cover 4 is provided with a plurality of air intake holes 211 disposed on the air intake end face 21. The protective cover 4 is provided with a plurality of air intake holes 211 disposed on the air exhaust end face 2 ...

[0070] The flow direction of the ram air in the main air supply pipeline 1 is from the first port of the main air supply pipeline 1 to the second port of the main air supply pipeline 1. Therefore, the windward side of the air inlet end face 21 and the air outlet end face 22 refers to the side facing or close to the first port, and the leeward side of the air inlet end face 21 and the air outlet end face 22 refers to the side facing away from or away from the first port.

[0071] Continue to refer to Figure 1 The main landing gear bay ventilation device further includes a bypass duct 5. Specifically, the air inlet of the bypass duct 5 is used to communicate with the ram air inlet 100, and the air outlet of the bypass duct 5 is used to communicate with the skin air outlet 300. The bypass duct 5 is used to transport the excess cold air entering the main landing gear bay from the ram air inlet 100 to the skin air outlet 300. The skin air outlet 300 is located on the back pressure side of the skin, that is, the end of the bypass duct 5, and is used to discharge the excess cold air entering the main landing gear bay from the ram air inlet 100 to the outside of the aircraft, so as to provide forward power for the aircraft, so as to realize thrust recovery and improve the economy of the system.

[0072] Based on the above embodiment, the main landing gear compartment ventilation device further includes a resistance module 6, which is arranged in the bypass duct 5 and can adjust the flow resistance of the bypass duct 5 to prevent airflow short circuit. The resistance value of the resistance module 6 can be adjusted as needed, and the flow resistance of the bypass duct 5 is matched with the flow resistance of the main air supply duct 1, so that the ventilation flow supplied to the main landing gear compartment can be changed according to the flow area change of the air inlet hole 211 of the air inlet end surface 21. For example, the resistance module 6 can be a porous plate structure, a grille or a flow regulating valve.

[0073] For example, when the flow area of ​​the air inlet hole 211 of the air inlet end surface 21 is equal to the first preset area, the baffle 31 completely exposes the air inlet hole 211, which indicates that the ram air flow rate in the main air supply duct 1 is the largest. The air resistance of the bypass duct 5 can be increased by controlling the resistance module 6, so that most of the ram air entering through the ram air inlet 100 flows through the main air supply duct 1.

[0074] Similarly, when the flow area of ​​the air inlet holes 211 of the air inlet end surface 21 is equal to 0, the baffle 31 completely blocks all the air inlet holes 211. At this time, it indicates that the wheel assembly 200 in the main landing gear compartment does not need to be cooled, and the ram air flow in the main air supply duct 1 is minimal. The air resistance of the bypass duct 5 can be reduced by controlling the resistance module 6, so that the ram air entering through the ram air port 100 is discharged outside the aircraft through the bypass duct 5.

[0075] In some embodiments of the present application, the baffle 31 is rotatably connected to the air inlet end face 21, the baffle 31 and the air inlet end face 21 are arranged in parallel, and the center lines of the two coincide, thereby ensuring that the gap between the baffle 31 and the air inlet end face 21 is equal everywhere, the baffle 31 can simultaneously block or expose the air inlet hole 211, and no jamming problem will occur during the rotation of the baffle 31 relative to the air inlet end face 21.

[0076] In summary, the working process of the main landing gear compartment ventilation device of the present application is as follows:

[0077] 1. When the landing gear is retracted to the main landing gear compartment and the door is closed, the wheel assembly 200 is at a relatively high temperature. The heat of the air collecting cover 201 is transferred to the air bag 33 through the heat pipe. The air bag 33 expands due to the heat, pushing the transmission component 34 to move upward. The transmission component 34 drives the pin 342 to move upward in the groove 311, driving the fan-shaped baffle 31 to rotate. The fan-shaped baffle 31 gradually reduces the shielding of the air inlet 211 until it moves between two adjacent groups of air inlet holes. The flow area of ​​the air inlet 211 reaches the maximum, the flow resistance in the main air supply pipeline 1 is the minimum, and all the ram air is supplied to the cabin.

[0078] 2. When the temperature of the brake carbon disc drops, the heat transferred to the airbag 33 through the heat pipe decreases, the airbag 33 shrinks, and the top structure of the airbag 33 drives the transmission component 34 to move downward. The transmission component 34 drives the pin 342 to move downward in the groove 311, driving the fan-shaped baffle 31 to rotate in the opposite direction. The fan-shaped baffle 31 gradually blocks the air inlet 211, the flow resistance in the main air supply pipeline 1 increases, the flow rate decreases, and the flow rate of the bypass pipeline 5 increases, and is discharged from the skin exhaust port 300 to the outside of the machine, realizing partial thrust recovery.

[0079] 3. When the temperature of the brake carbon disc drops to the target temperature, the airbag 33 shrinks to the minimum state, the transmission component 34 drives the pin 342 to move to the bottom of the groove 311, and the fan-shaped baffle 31 completely blocks the air inlet hole 211. At this time, the flow area of ​​the air inlet hole 211 reaches the minimum, and the flow of the bypass line 5 reaches the maximum, achieving maximum thrust energy recovery.

[0080] In some embodiments of the present application, the present application also provides an aircraft, comprising a main landing gear compartment ventilation device recorded in any of the above technical solutions.

[0081] Since the aircraft provided by the present application includes the main landing gear compartment ventilation device as described in any of the above technical solutions, the two can solve the same technical problem and achieve the same technical effect. In other words, since the aircraft has the main landing gear compartment ventilation device as described in any of the above technical solutions, the flow rate of the main air supply pipeline in the main landing gear compartment ventilation device can be adaptively adjusted according to the temperature of the air collecting hood in the wheel assembly of the aircraft, so as to realize the cooling of the wheel assembly on demand, thereby improving the economy of the entire system.

[0082] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0083] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims. In addition, the specification uses specific examples to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method and its core idea of ​​the present application. The content of this specification should not be understood as a limitation on the present application.

Claims

1. A main landing gear compartment ventilation device, characterized in that: include: a main air supply pipeline, wherein a first port of the main air supply pipeline is communicated with a ram air inlet, and a second port of the main air supply pipeline is arranged opposite to a wheel assembly in the main landing gear compartment so as to deliver ram air to the wheel assembly; A ventilation disk is arranged in the main air supply pipeline, the ventilation disk has an air inlet end surface, and the air inlet end surface is provided with an air inlet hole; A flow regulating structure includes a baffle, a heat transfer element, an airbag and a transmission component. The baffle is arranged on the leeward side of the air inlet end face of the ventilation disc and is connected to the transmission component. The heat transfer element is connected to the air collecting hood of the wheel assembly and the airbag to heat or cool the air in the airbag to expand or contract the airbag. One end of the transmission component is connected to the airbag and the other end is connected to the baffle. The expansion or contraction of the airbag drives the transmission component to move, thereby realizing the rotation of the baffle relative to the air inlet end face to adjust the flow area of ​​the air inlet hole and realize the flow regulation of the main air supply duct.

2. The main landing gear compartment ventilation device according to claim 1, characterized in that: A groove is provided on one side of the baffle plate facing away from the air inlet end surface of the ventilating disc, and an end of the transmission component facing away from the airbag is slidably fitted in the groove, wherein the airbag can drive the transmission component to move along a first direction, and the groove is arranged obliquely relative to the first direction; The transmission component comprises a transmission rod and a pin, one end of the transmission rod is connected to the airbag, and the other end is connected to the pin, and the pin is slidably fitted in the groove.

3. The main landing gear compartment ventilation device according to claim 1, characterized in that: The air inlet end surface is circular and is provided with a plurality of air inlet hole groups, each of which comprises a plurality of air inlet holes arranged at intervals along the radial direction of the air inlet end surface, and the flow areas of the plurality of air inlet holes in each of which gradually increase from the center of the air inlet end surface to the edge of the air inlet end surface; Wherein, the baffle comprises a middle connecting portion and a plurality of blades, and the radial inner sides of the plurality of blades are connected to the middle connecting portion; When all the air inlet holes are in an exposed state, the orthographic projections of the fan blades on the air inlet end surface and each group of the air inlet holes are arranged alternately in sequence along the circumference of the air inlet end surface; When all the air inlet holes are in a blocked state, each group of the air inlet holes is located within the orthographic projection of the corresponding fan blade on the air inlet end surface.

4. The main landing gear compartment ventilation device according to any one of claims 1 to 3, characterized in that: The ventilation disc also includes an exhaust end face, which is arranged at the second port and is spaced apart from the air inlet end face to enclose an installation space. The airbag and the transmission component are both arranged in the installation space, and the bottom of the airbag is connected to the exhaust end face.

5. The main landing gear compartment ventilation device according to claim 1, characterized in that: The main landing gear compartment ventilation device also includes: A protective cover is arranged in the installation space and arranged on the periphery of the airbag and the transmission component. A through groove is provided on the side of the protective cover close to the air inlet end surface, and the through groove extends along a first direction. An end of the transmission component facing away from the airbag extends out of the through groove and is connected to the baffle.

6. The main landing gear compartment ventilation device according to claim 1, characterized in that: Also includes: A bypass pipeline, wherein the air inlet of the bypass pipeline is used to communicate with the ram air inlet, and the exhaust port of the bypass pipeline is used to communicate with the skin exhaust port.

7. The main landing gear compartment ventilation device according to claim 6, characterized in that: Also includes: The resistance module is arranged in the bypass pipeline and can adjust the flow resistance of the bypass pipeline.

8. The main landing gear compartment ventilation device according to claim 1, characterized in that: The baffle is rotatably connected to the air inlet end surface, the baffle is arranged parallel to the air inlet end surface, and the center lines of the two coincide.

9. The main landing gear compartment ventilation device according to claim 1, characterized in that: The heat transfer element is a heat pipe.

10. An aircraft, comprising the main landing gear compartment ventilation device according to any one of claims 1 to 9.

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