Main landing gear bay ventilation and aircraft

Abstract

The application discloses a main landing gear cabin ventilation device and an aircraft, relates to the technical field of aircraft environmental control oxygen, and aims to solve the problem that the existing ventilation device cannot adjust the ram air flow in the main air supply pipeline according to the temperature of a wheel assembly and has low economy. The main landing gear cabin ventilation device comprises a main air supply pipeline, a ventilation disc and a flow adjusting structure. The ventilation disc has an air inlet end face provided with an air inlet hole. The flow adjusting structure comprises a baffle arranged on the leeward side of the air inlet end face of the ventilation disc and connected with a transmission part. A heat transfer part is connected with a wind collector cover and an air bag of the wheel assembly to heat or cool the air in the air bag to make the air bag expand or shrink. One end of the transmission part is connected with the air bag, the other end is connected with the baffle, and the transmission part is driven to move through the expansion or shrink of the air bag, so that the baffle rotates relative to the air inlet end face to adjust the flow area of the air inlet hole, and the flow adjustment of the main air supply pipeline is realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft environmental control oxygen, and particularly relates to a main landing gear cabin ventilation device and an aircraft. BACKGROUND

[0002] The aircraft takes off from the ground, the wheels are braked after leaving the ground, and the wheels are stopped in a very short time. After the wheels stop rotating, they are retracted into the main landing gear cabin, and the cabin door is closed. From the wheels leaving the ground to the landing gear being retracted into the cabin and the cabin door being closed, the entire process is completed in a short time. Because the wheels change from a high-speed rotating state to a stopped rotating state in a very short time, a large amount of brake energy needs to be applied to the wheels. A large amount of heat generated by friction cannot be quickly discharged outside the cabin, which can cause the temperature in the cabin to rise rapidly after the landing gear is retracted into the cabin, and can cause the structure of the aircraft to overheat, affecting the structural strength.

[0003] At the same time, because the main landing gear cabin door is closed, the entire cabin is in a closed state, which causes the temperature of the brake carbon disc to decrease in the air at a slow rate. For short-range flights, the brake carbon disc may still be at a high temperature when the aircraft is about to land. The aircraft lands and brakes, which can further increase the temperature of the brake carbon disc, and the high temperature of the brake carbon disc can cause the wheels to fail, the tires to burst, the fusible plug to melt, and other accidents, affecting the safety of the aircraft; at the same time, it can also increase the time of passing through the station, affect the dispatch of the aircraft, and reduce the economy.

[0004] However, the existing aircraft is provided with a ventilation system in the main landing gear cabin, that is, during flight, cooling air is provided into the cabin through a ram air inlet to achieve rapid cooling of the brake carbon disc and temperature reduction of the cabin environment. The disadvantage is that the flow of cooling air entering the cabin through the ram air inlet is uncontrollable, and it is completely affected by the flight state of the aircraft. Generally, the speed of the aircraft is relatively low during the climbing stage, and the speed reaches a large flight speed during the cruising stage, that is, the flow of ram air entering the cabin gradually increases to a stable state during the cruising stage. At the same time, as the flight height increases, the outside environment temperature gradually decreases. Therefore, from takeoff to cruising, the cooling capacity of the ram air inlet into the main landing gear cabin 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 temperature of the cabin environment first increases and then decreases, and the high-temperature state is in a period after the cabin door is closed. That is, the cooling capacity of the ram air inlet into the cabin does not match the cooling demand of the cabin. Especially during the cruising stage, when the temperature of the brake carbon disc has decreased to the target temperature, the ram air is still supplied in a large amount, which provides unnecessary cooling capacity to 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

[0005] The application provides a main landing gear cabin 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 pipeline according to the temperature of the wheel assembly, and the economy is low.

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

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

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

[0009] A flow adjusting structure, comprising a baffle, a heat transfer member, an air bag 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 with the transmission component, the heat transfer member connects the air collector cover of the wheel assembly and the air bag, so as to heat or cool the air in the air bag to make the air bag expand or shrink, one end of the transmission component is connected with the air bag, the other end is connected with the baffle, and the transmission component is driven to move by the expansion or shrink of the air bag, so as to realize 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 adjustment of the main air supply pipeline.

[0010] In the technical scheme, the heat transfer member connects the air collector cover of the wheel assembly and the air bag, so as to realize the heat conduction connection between the air bag and the air collector cover, so that the temperature of the air collector cover can heat or cool the air in the air bag, to realize the expansion or shrink of the air bag. At the same time, one end of the transmission component is connected with the air bag, and the other end is connected with the baffle, so that when the air bag expands or shrinks, the transmission component can be driven to move in a fixed direction, and then the baffle is driven to rotate relative to the air inlet end face, to adjust the area of the air inlet hole covered or exposed by the baffle, so that the flow area of the air inlet hole is adjusted, and the flow adjustment of the main air supply pipeline is further realized. In short, the flow of the ram air in the main air supply pipeline can be adaptively adjusted according to the temperature of the air collector cover in the wheel assembly, the wheel assembly is cooled on demand, and the economy of the whole system is improved.

[0011] In some embodiments of the application, the side of the baffle opposite to the air inlet end face of the ventilation disc is provided with a groove, and one end of the transmission component opposite to the air bag is slidingly fitted in the groove, wherein the air bag can drive the transmission component to move in a first direction, and the groove is inclined relative to the first direction;

[0012] The transmission component includes a transmission rod and a pin, one end of the transmission rod is connected to the air bag, the other end is connected to the pin, and the pin is slidingly fitted in the channel.

[0013] In some embodiments of the present application, the air inlet end face is circular, and a plurality of air inlet hole groups are arranged thereon, each air inlet hole group includes a plurality of air inlet holes arranged at intervals along the radial direction of the air inlet end face, and the flow area of the plurality of air inlet holes in each air inlet hole group gradually increases from the center of the air inlet end face to the edge of the air inlet end face.

[0014] The baffle includes an intermediate connecting portion and a plurality of vanes, and the radially inner side of each vane is connected to the intermediate connecting portion.

[0015] When all the air inlet holes are in the exposed state, the orthogonal projection of the vane on the air inlet end face and each air inlet hole group are arranged alternately along the circumferential direction of the air inlet end face.

[0016] When all the air inlet holes are in the shielding state, each air inlet hole group is located within the orthogonal projection of the corresponding vane on the air inlet end face.

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

[0018] In some embodiments of the present application, the air bag can drive the transmission component to move in a first direction, and the main landing gear cabin ventilation device further includes:

[0019] A protective cover is arranged in the installation space and is arranged around the outer periphery of the air bag and the transmission component, one side of the protective cover close to the air inlet end face is provided with a through slot, the through slot extends in the first direction, and one end of the transmission component away from the air bag extends out of the through slot and is connected to the baffle.

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

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

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

[0023] A 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 rotationally connected to the air inlet end face, the baffle is arranged in parallel with the air inlet end face, and the center lines of the baffle and the air inlet end face coincide.

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

[0026] In another aspect, the present application also provides an aircraft comprising the main landing gear cabin ventilation device according to any one of the above technical solutions.

[0027] Since the aircraft provided by the present application comprises the main landing gear cabin ventilation device according to any one of the above technical solutions, both can solve the same technical problems and achieve the same technical effects. In other words, since the aircraft has the main landing gear cabin ventilation device according to any one of the above technical solutions, the flow rate of the main air supply pipeline in the main landing gear cabin ventilation device can be adaptively adjusted according to the temperature of the fan cover in the wheel assembly of the aircraft, realizing on-demand cooling of the wheel assembly, thereby improving the economy of the entire system. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

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

[0030] Figure 2 is a sectional view of the flow rate adjusting structure in the main landing gear cabin ventilation device in the embodiments of the present application, to clearly show the specific structure of the flow rate adjusting structure;

[0031] Figure 3 is a structural schematic diagram of the baffle completely exposing the air inlet hole in the flow rate adjusting structure in the embodiments of the present application;

[0032] Figure 4 is a structural schematic diagram of the baffle completely covering the air inlet hole in the flow rate adjusting structure in the embodiments of the present application;

[0033] Figure 5 is a structural schematic diagram of the baffle partially covering the air inlet hole in the flow rate adjusting structure in the embodiments of the present application;

[0034] Figure 6 is a structural schematic diagram of another arrangement position of the channel in the embodiments of the present application.

[0035] The main reference signs in the drawings of the present application are explained as follows:

[0036] 1-main air supply pipeline;

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

[0038] 3-flow regulating structure; 31-shutter; 311-groove; 312-intermediate connecting part; 313-fan blade; 32-heat transfer member; 33-air bag; 34-transmission mechanism; 341-transmission rod; 342-pin;

[0039] 4-protection cover;

[0040] 5-bypass pipeline;

[0041] 6-resistance module;

[0042] 100-stamped air inlet;

[0043] 200-wheel assembly; 201-collector cover;

[0044] 300-skin exhaust port. DETAILED DESCRIPTION

[0045] The technical solutions in the embodiments of the present application will be described clearly and completely below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall 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", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0047] The terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, the meaning of "multiple" is two or more.

[0048] In the description of the present application, it should be noted that unless specifically defined and limited otherwise, the terms "mounting", "connected", "connection" should be interpreted broadly, for example, can be fixed connection, can also be detachable connection, or integrally connected; can be mechanical connection, can be directly connected, can also be indirectly connected through intermediate medium, can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0049] The present application provides a main landing gear cabin ventilation device and an aircraft, which are described in detail below. It should be noted that the description order of the following embodiments is not limited as the preferred order of the embodiments of the present application. Moreover, in the following embodiments, the description of each embodiment has its own emphasis, and the parts not described in detail in a certain embodiment can be referred to the related description of other embodiments.

[0050] Reference Figures 1-3 The main landing gear cabin ventilation device provided by the present application comprises a main air supply pipeline 1, a ventilation disc 2 and a flow regulating structure 3. The first port of the main air supply pipeline 1 is used to communicate with the ram air inlet 100, and the second port of the main air supply pipeline 1 is arranged opposite to the wheel assembly 200 in the main landing gear cabin, so as to deliver ram air to the wheel assembly 200, for delivering cooling air to the specified position of the cooled component. The ventilation disc 2 is arranged in the main air supply pipeline 1, and the ventilation disc 2 has an air inlet end face 21, which is provided with an air inlet hole 211 for the ram air to pass through. The flow regulating structure 3 comprises a baffle plate 31, a heat transfer piece 32, an air bag 33 and a transmission component 34. The baffle plate 31 is arranged at the leeward side of the air inlet end face 21 of the ventilation disc 2 and is connected with the transmission component 34. The heat transfer piece 32 connects the air collector 201 of the wheel assembly 200 and the air bag 33, so as to heat or cool the air in the air bag 33 to make the air bag 33 expand or shrink. One end of the transmission component 34 is connected with the air bag 33, and the other end is connected with the baffle plate 31. The transmission component 34 is driven to move by the expansion or shrink of the air bag 33, and then the baffle plate 31 rotates relative to the air inlet end face 21 to adjust the flow area of the air inlet hole 211, so as to realize the flow regulation of the main air supply pipeline 1.

[0051] In the technical solution, the heat transfer member 32 connects the wind collector 201 of the wheel assembly 200 and the air bag 33 to realize the heat conduction connection between the air bag 33 and the wind collector 201, so that the temperature of the wind collector 201 can heat or cool the air in the air bag 33 to realize the expansion or contraction of the air bag 33. At the same time, since one end of the transmission member 34 is connected with the air bag 33 and the other end is connected with the baffle 31, when the air bag 33 expands or contracts, the transmission member 34 can be driven to move in a fixed direction, and in turn drive the baffle 31 to rotate relative to the air inlet end surface 21 to adjust the area of the air inlet hole 211 covered or exposed by the baffle 31, so that the flow area of the air inlet hole 211 is adjusted, and further the flow regulation of the main air supply pipeline 1 is realized. In short, the flow of ram air in the main air supply pipeline 1 can be adaptively adjusted according to the temperature of the wind collector 201 in the wheel assembly 200, and the wheel assembly 200 is supplied with cooling as needed, so as to improve the economy of the whole system.

[0052] Wherein, the ram air inlet 100 is located on the skin ram side, used to introduce the cold air of the external environment into the main landing gear cabin, and provide cold energy for ventilation in the cabin. Specifically, when the wheel assembly 200 is in a high temperature state, the air bag 33 expands, the transmission member 34 drives the baffle 31 to rotate, and the shielding area of the baffle 31 to the air inlet hole 211 gradually decreases, at this time the flow area of the air inlet hole 211 gradually increases to the maximum, as shown in Figure 3 On the contrary, when the wheel assembly 200 does not need to be cooled, the air bag 33 contracts, the transmission member 34 drives the baffle 31 to rotate in the opposite direction, and the shielding area of the baffle 31 to the air inlet hole 211 gradually increases until completely covers the air inlet hole 211, as shown in Figure 4 At this time, the flow area of the air inlet hole 211 is the smallest. That is, the main landing gear cabin ventilation device can automatically adjust the flow of ram air in the main air supply pipeline 1 according to the temperature state of the wheel assembly 200, and the main landing gear cabin is cooled as needed.

[0053] It should be noted that the baffle 31 rotates relative to the air inlet end surface 21 to shield 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 the air shielding position of completely shielding the air inlet hole 221 and the ventilation position of completely exposing the air inlet hole 221, and the baffle 31 can stop at the air shielding position (i.e. Figure 4 The ventilation position (i.e. Figure 3 As shown in the state), and any position between the air shielding position and the ventilation position, as shown in Figure 5 Wherein, when the baffle 31 is in the air shielding position, the second port of the main air supply pipeline 1 does not deliver ram air to the wheel assembly 200, and when the baffle 31 is in the ventilation position, the flow 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 air bag 33 to heat or cool the air in the air bag 33 to make the air bag 33 expand or contract. The heat pipe has a high heat transfer efficiency, thereby ensuring that the volume of the air bag 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, its heat is transferred to the airbag 33 by using 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 of the air inlet 211 gradually decreases until the air inlet 211 is completely exposed. At this time, the flow area of ​​the air inlet 211 reaches its maximum.

[0056] Conversely, 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, driving the transmission component 34 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, gradually increasing its obstruction of the air inlet 211 until it completely covers the air inlet 211. At this point, the flow area of ​​the air inlet 211 reaches its minimum. This application utilizes a combined structure of heat pipe-airbag 33-transmission component 34-baffle 31 to achieve automatic flow regulation of the main air supply pipeline. This combined structure is simple and easy to implement.

[0057] In some embodiments of the present application, a groove 311 is provided on the side of the baffle 31 facing away from the air inlet end surface 21 of the ventilating disc 2. The end of the transmission component 34 facing away from the airbag 33 slides within the groove 311. The airbag 33 can drive the transmission component 34 to move in a first direction Z. The groove 311 is tilted relative to the first direction Z. Furthermore, 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. The pin 342 slides within the groove 311. As a result, when the transmission rod 341 moves up and down in the first direction Z, the pin 342 connected to the end of the transmission rod 341 moves synchronously with the transmission rod 341 and applies upward or downward pressure to the walls of the groove 311, thereby driving the baffle 31 to rotate. For example, the transmission rod 341 is L-shaped and rigid, ensuring reliable power transmission between the airbag 33 and the baffle 31.

[0058] Alternatively, in some other embodiments, the transmission component 34 comprises a gear and a rack engaged with each other, wherein the rack is fixed to the top of the air bag 33 and can move up and down along the first direction z following the expansion or contraction of the air bag 33, and the gear is coaxially fixed 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 air bag 33 along the first direction z into the rotational motion of the baffle 31 when the air bag 33 expands or contracts, 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 a plurality of groups of air inlet holes are arranged on the air inlet end face 21. Each group of air inlet holes comprises a plurality of air inlet holes 211 arranged at intervals along the radial direction of the air inlet end face 21. The flow area of the plurality of air inlet holes 311 in each group of air inlet holes gradually increases from the center of the air inlet end face 21 to the edge of the air inlet end face 21. The baffle 31 comprises a middle connecting portion 312 and a plurality of fan blades 313, and the radially inner side of each of the plurality of fan blades 313 is connected to the middle connecting portion 312. Specifically, when all the air inlet holes 211 are in the exposed state, the orthogonal projection of the plurality of fan blades 313 on the air inlet end face 21 is arranged alternately with each group of air inlet holes in turn, as shown in FIG. 4A. When all the air inlet holes 211 are in the shielding state, each group of air inlet holes is located within the orthogonal projection of the corresponding fan blade 313 on the air inlet end face 21, as shown in FIG. 4B. The above technical solution of the present application can realize the synchronous adjustment of the flow area of all the air inlet holes 211. Figure 3 Figure 4

[0061] In some embodiments of the present application, the ventilation disc 2 further comprises an air outlet end face 22, which is arranged at the second port and is spaced apart from the air inlet end face 21 to form an installation space. The air bag 33 and the transmission component 34 are arranged in the installation space, and the bottom of the air bag 33 is connected to the air outlet end face 22. Thus, the flow adjusting structure 3 does not need to occupy additional space, and all the components thereof are arranged in the installation space defined by the air inlet end face 21 and the air outlet end face 22. In addition, the cooling air can enter the inside of the wheel set assembly 200 in the shortest path and with the maximum momentum, so as to provide sufficient cooling capacity for the brake carbon disc.

[0062] For example, the above-mentioned eight groups of air inlet holes are distributed at equal angles around the center of the air inlet end face 21, and the air inlet holes 211 in each of the above-mentioned groups of air inlet holes are circular. The diameters of the plurality of air inlet holes 211 in each group of air inlet holes gradually increase from the center of the air inlet end face 21 to the edge of the air inlet end face 21.

[0063] ​​It can be understood that the exhaust end face 22 is provided with an exhaust hole for the ram air to pass through, the exhaust hole is arranged opposite to the air vent on the air collector 201, the bottom of the air bag 33 is fixed and is flush with the exhaust end face 22, the top of the air bag 33 is a freely inflatable surface, and the air bag 33 is hard connected with the transmission component 34. When the air bag 33 is inflated, the top structure is inflated upwards, and the transmission component 34 is driven to move upwards; conversely, when the air bag 33 is deflated, the top structure of the air bag 33 drives the transmission component 34 to move downwards.

[0064] In some embodiments of the present application, the above-mentioned channel 311 is arranged on the side of the intermediate connecting portion 312 away from the air inlet end face 21, when all the air inlet holes 211 are in the exposed state, the orthographic projection of the fan blade 313 on the air inlet end face 21 is arranged alternately with each group of air inlet hole groups in turn, and the transmission rod 341 moves to the top end of the channel 311, at this time the air bag 33 is inflated to the maximum volume. When all the air inlet holes 211 are in the shielding state, each group of air inlet hole groups is located in 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 end of the channel 311, at this time the air bag 33 is deflated to the minimum volume. Of course, the above-mentioned channel 311 can also be arranged on the side of the fan blade 313 away from the air inlet end face 21, as shown in FIG. 6. Figure 6

[0065] In some embodiments of the present application, the main landing gear cabin ventilation device further comprises a protective cover 4. The protective cover 4 is arranged in the installation space and is arranged on the outer periphery of the air bag 33 and the transmission component 34, the side of the protective cover 4 close to the air inlet end face 21 is provided with a through slot, the through slot extends along the first direction z, and the end of the transmission component 34 away from the air bag 33 extends out of the through slot and is connected with the baffle 31. Thus, the technical scheme can protect the air bag 33 and the transmission component 34 by arranging the protective cover 4, so as to prevent the structure from being damaged by the ram air flowing through the air inlet end face 21. In addition, the through slot arranged on the protective cover 4 can also guide the part 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 comprises the transmission rod 341 and the pin 342, the transmission rod 341 is arranged in the protective cover 4, and the end of the transmission rod 341 away from the air bag 33 is connected with the pin 342, the pin 342 is slidingly fitted in the channel 311, and the pin 342 is beneficial to realize the sliding fit between the transmission rod 341 and the channel 311, wherein the pin 342 and the transmission rod 341 can be rigidly connected together by welding, threaded connection or clamping connection and the like. Of course, in some embodiments, the transmission component 34 only comprises a transmission rod, and the end of the transmission rod away from the air bag 33 is directly slidingly fitted in the channel 311.

[0067] ​For example, one end of the protective cover 4 facing the baffle 31 is connected to the channel 311, and the side of the protective cover 4 close to the air inlet end surface 21 is provided with a through slot, the size of the through slot in the first direction Z is the same as the size of the channel 311 in the first direction Z, so as to ensure that when the pin 342 moves to any position in the channel 311, the movement of the transmission rod 341 connected to the pin 342 in the protective cover 4 is not limited.

[0068] Specifically, as shown in the drawings, when the pin 342 moves to the top of the channel 311, correspondingly, at this time the transmission rod 341 moves to the top of the through slot. Similarly, when the pin 342 moves to the bottom of the channel 311, correspondingly, at this time the transmission rod 341 moves to the bottom of the through slot. Figure 3

[0069] In some embodiments of the present application, for the baffle 31 including the intermediate connecting portion 312 and a plurality of blades 313, the radially inner side of each of the plurality of blades 313 is connected to the intermediate connecting portion 312, and for the embodiment in which the channel 311 is arranged on the intermediate connecting portion 312, the intermediate connecting portion 312 is not provided with the air inlet hole 211 in the projection range of the air inlet end surface 21. By rotationally connecting the intermediate connecting portion 312 and the air inlet end surface 21, the movement of the baffle 31 in the X / Y / Z directions is prevented, so that the baffle 31 can only rotate around the central axis (for example, the X axis shown in the drawings) of the air inlet end surface 21. Figure 2 For the embodiment in which the baffle 31 includes the intermediate connecting portion 312 and a plurality of blades 313, the radially inner side of each of the plurality of blades 313 is connected to the intermediate connecting portion 312, and for the embodiment in which the channel 311 is arranged on the side of the blade 313 away from the air inlet end surface 21, by rotationally connecting the intermediate connecting portion 312 and the air inlet end surface 21, the movement of the baffle 31 in the X / Y / Z directions is prevented, so that the baffle 31 can only rotate around the central axis (for example, the X axis shown in the drawings) of the air inlet end surface 21. Figure 2 In other words, the air inlet hole 211 on the air inlet end surface 21 is located outside the projection range of the protective cover 4 on the air inlet end surface 21, and the air outlet hole on the air outlet end surface 22 is located outside the projection range of the protective cover 4 on the air outlet end surface 22. That is, no ram air flows through the protective cover 4, and the outside of the main air supply pipeline 1 and the protective cover 4 together define a ram air flow channel.

[0070] In the main air supply pipeline 1, the flow direction of the ram air 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 surface 21 and the air outlet end surface 22 refers to the side facing or close to the first port, and the leeward side of the air inlet end surface 21 and the air outlet end surface 22 refers to the side away from or away from the first port.​

[0071] With reference to the above Figure 1 The main landing gear cabin ventilation device further comprises a bypass pipeline 5, specifically, an air inlet of the bypass pipeline 5 is configured to communicate with the ram air inlet 100, and an air outlet of the bypass pipeline 5 is configured to communicate with the skin air outlet 300, and the bypass pipeline 5 is configured to transport the excess cold air entering the main landing gear cabin through the ram air inlet 100 to the skin air outlet 300. The skin air outlet 300 is located at the skin back pressure side, i.e., the end of the bypass pipeline 5, and is configured to discharge the excess cold air entering the main landing gear cabin through the ram air inlet 100 out of the aircraft, thereby providing forward power for the aircraft to achieve thrust recovery and improve the economy of the system.

[0072] Based on the above embodiment, the main landing gear cabin ventilation device further comprises a resistance module 6 arranged in the bypass pipeline 5, which is configured to adjust the flow resistance of the bypass pipeline 5 to prevent air flow short circuiting. The resistance value of the resistance module 6 can be adjusted as needed, and the flow resistance of the bypass pipeline 5 is matched with that of the main air supply pipeline 1, so that the ventilation flow rate supplied into the main landing gear cabin can be changed according to the flow area of the air inlet hole 211 of the air inlet end face 21. For example, the resistance module 6 can be a multi-hole plate structure, a grid or a flow regulating valve.

[0073] For example, when the flow area of the air inlet hole 211 of the air inlet end face 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 pipeline 1 is maximum. The air resistance of the bypass pipeline 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 pipeline 1.

[0074] Similarly, when the flow area of the air inlet hole 211 of the air inlet end face 21 is equal to 0, the baffle 31 completely blocks all the air inlet holes 211, which indicates that the wheel assembly 200 in the main landing gear cabin does not need to be cooled, and the ram air flow rate in the main air supply pipeline 1 is minimum. The air resistance of the bypass pipeline 5 can be reduced by controlling the resistance module 6, so that the ram air entering through the ram air inlet 100 is discharged out of the aircraft through the bypass pipeline 5.

[0075] In some embodiments of the present application, the baffle 31 is rotationally 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 baffle 31 and the air inlet end face 21 coincide, thereby ensuring that the gap between the baffle 31 and the air inlet end face 21 is equal everywhere, and the baffle 31 can simultaneously block or expose the air inlet hole 211 without jamming during rotation relative to the air inlet end face 21.

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

[0077] 1. With the landing gear retracted into the main landing gear bay and the hatch closed, the wheel assembly 200 is at a relatively high temperature. Heat from the air collecting hood 201 is transferred to the airbag 33 via a heat pipe. The airbag 33 expands due to the heat, pushing the transmission component 34 upward. This in turn drives the pin 342 upward within the groove 311, rotating the fan-shaped baffle 31. The fan-shaped baffle 31 gradually reduces its coverage of the air inlet holes 211 until it moves between two adjacent groups of air inlet holes. This maximizes the flow area of ​​the air inlet holes 211, minimizes the flow resistance within the main air supply duct 1, and allows the entire ram air to enter 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, causing the airbag 33 to contract. The top structure of the airbag 33 drives the transmission component 34 downward, which in turn drives the pin 342 downward within the groove 311, causing the fan-shaped baffle 31 to rotate in the opposite direction. The fan-shaped baffle 31 gradually blocks the air inlet 211, increasing the flow resistance in the main air supply duct 1 and reducing the flow rate. The bypass duct 5 increases the flow rate and is discharged out of the aircraft through the skin exhaust port 300, achieving partial thrust recovery.

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

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

[0081] Because the aircraft provided in this application includes a main landing gear well ventilation device as described in any of the above technical solutions, both devices can solve the same technical problems and achieve the same technical effects. In other words, because the aircraft includes a main landing gear well ventilation device as described in any of the above technical solutions, the flow rate of the main air supply duct in the main landing gear well ventilation device can be adaptively adjusted based on the temperature of the air collecting hood in the aircraft's wheel assembly, achieving on-demand cooling of the wheel assembly, thereby improving the economic efficiency 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 merely describes specific embodiments of the present application, but the protection scope of the present application is not limited thereto, any person skilled in the art can easily think of changes or replacements within the technical scope disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims. In addition, the principles and embodiments of the present application are described by applying specific examples in the specification, and the above description of the embodiments is only used to help understand the method and core idea of the present application, and the content of the specification should not be understood as limiting the present application.

Claims

1. A main landing gear bay ventilation device, characterized in that, The application relates to a main landing gear cabin ventilation device. The main landing gear cabin ventilation device comprises a main air supply pipeline, a ventilation disc, a flow regulating structure and a bypass pipeline. The first port of the main air supply pipeline is communicated with a ram air inlet, and the second port of the main air supply pipeline is arranged opposite a wheel assembly in the main landing gear cabin to supply ram air to the wheel assembly. The ventilation disc is arranged in the main air supply pipeline and has an air inlet end face provided with air inlet holes.

2. A main landing gear bay venting arrangement according to claim 1, characterised in that, The flow regulating structure comprises a baffle, a heat transfer member, an air bag and a transmission member. The baffle is arranged on the leeward side of the air inlet end face of the ventilation disc and is connected with the transmission member.

3. A main landing gear bay venting arrangement according to claim 1, characterised in that, The heat transfer member connects a wind collector of the wheel assembly and the air bag to heat or cool the air in the air bag to make the air bag expand or contract. One end of the transmission member is connected with the air bag, the other end is connected with the baffle, and the transmission member is driven to move by the expansion or contraction of the air bag, thereby realizing the rotation of the baffle relative to the air inlet end face to regulate the flow area of the air inlet holes and realize the flow regulation of the main air supply pipeline. The side of the baffle opposite to the air inlet end face of the ventilation disc is provided with a groove, and one end of the transmission member opposite to the air bag is slidingly fitted in the groove. The air bag can drive the transmission member to move in a first direction, and the groove is arranged obliquely relative to the first direction.

4. A main landing gear bay venting arrangement according to any one of claims 1 to 3, wherein, The transmission member comprises a transmission rod and a pin.

5. A main landing gear bay venting arrangement according to claim 4, wherein, One end of the transmission rod is connected with the air bag, the other end is connected with the pin, and the pin is slidingly fitted in the groove. The air inlet end face is circular and is provided with a plurality of air inlet hole groups.

6. The main landing gear bay vent of claim 1, wherein, Each air inlet hole group comprises a plurality of air inlet holes arranged at intervals along the radial direction of the air inlet end face. The flow area of the air inlet holes in each air inlet hole group gradually increases from the center of the air inlet end face to the edge of the air inlet end face.

7. A main landing gear bay venting arrangement according to claim 6, wherein, The baffle comprises an intermediate connecting portion and a plurality of blades. When all the air inlet holes are in an exposed state, the normal projection of the blades on the air inlet end face and each air inlet hole group are arranged alternately along the circumferential direction of the air inlet end face. When all the air inlet holes are in a shielding state, each air inlet hole group is located in the normal projection of the corresponding blade on the air inlet end face. The ventilation disc further comprises an air outlet end face. The air outlet end face is arranged at the second port and is arranged spaced apart from the air inlet end face to form an installation space. The air bag and the transmission member are arranged in the installation space, and the bottom of the air bag is connected with the air outlet end face. The main landing gear cabin ventilation device further comprises a protective cover arranged in the installation space and arranged outside the air bag and the transmission member. One side of the protective cover close to the air inlet end face is provided with a through groove extending in a first direction. One end of the transmission member opposite to the air bag extends out of the through groove and is connected with the baffle. The bypass pipeline has an air inlet communicated with the ram air inlet and an air outlet communicated with a skin air outlet. A resistance module is arranged in the bypass pipeline and capable of adjusting the flow resistance of the bypass pipeline.

8. The main landing gear bay vent of claim 1, wherein, The baffle is rotationally connected to the air inlet end face, and the baffle and the air inlet end face are arranged in parallel and have coinciding center lines.

9. The main landing gear bay vent of claim 1, wherein, The heat transfer member is a heat pipe.

10. An aircraft comprising a main landing gear bay ventilation device according to any one of claims 1 to 9.

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