Aircraft water dropping hatch

Abstract

The application provides a water-throwing hatch of a fire-extinguishing airplane, and belongs to the field of airplane design. The hatch is a two-leaf opposing hatch structure, the two sides are hinged to the fuselage structure through piano hinge, the hatch edge is provided with a sealing structure, two sets of opening mechanisms are symmetrically arranged above the two side hatches, the opening mechanism comprises a transmission shaft hinged to the fuselage structure, a crank and a connecting rod connected between the hatch and the transmission shaft, the two transmission shaft ends are hinged to the same actuator, the opening and closing of the hatch are realized through the extension and retraction of the actuator, two sets of latch mechanisms are symmetrically arranged above the two side hatches, the latch mechanism comprises a lock shaft hinged to the fuselage structure, a lock hook is arranged in the middle of the lock shaft, and the lock shaft is locked in the closed position in cooperation with the lock column fixed on the hatch, and the other actuator cooperates with the two lock shafts to control the locking and unlocking of the latch mechanism through the extension and retraction movement. The application adopts a single actuator to drive the opening of the double-leaf door, and the mechanism has high synchronism; through the transmission angle design of the opening mechanism, smaller load is realized, and the safety of the mechanism is improved.

Description

Technical Field

[0001] This invention belongs to the field of aircraft design and relates to a water droplet door for firefighting aircraft. Specifically, it relates to a door that can be opened in the air to provide a passage for the delivery of firefighting materials on firefighting aircraft. Background Technology

[0002] In the event of accidental fires or other disasters, firefighting aircraft can perform firefighting missions by dropping extinguishing materials from the air. The water drop door is a crucial component of firefighting aircraft. Before a firefighting mission, the aircraft's water tanks contain extinguishing materials, and the water drop door is closed while bearing the weight of the materials inside. During the airdrop of extinguishing materials, the water drop door can automatically open and remain open. After the mission is completed, the water drop door automatically closes. The water drop door has high requirements for load-bearing capacity, safety, and reliability, making it one of the design challenges of firefighting aircraft. Summary of the Invention

[0003] The purpose of this invention is to provide a water-dropping hatch for firefighting aircraft, which can achieve functions such as hatch locking in the closed position, automatic opening, and automatic closing. This invention has advantages such as simple structure, good watertightness, high mechanism synchronization, and good load-bearing capacity.

[0004] To achieve the above objectives, the specific technical solution adopted by the present invention is as follows:

[0005] A water-dropping hatch for a fire-fighting aircraft, the water-dropping hatch comprising a hatch structure 1, a key hinge 2, a crank I 3, a connecting rod I 4, a crank II 5, a connecting rod II 6, a locking pin 7, a drive shaft 8, an actuator I 9, an actuator II 10, a locking shaft 11, a cam 12, a sealing bracket 13, a sealing strip 14, a sealing clamping element 15, a locking hook 16, and a roller 17.

[0006] The water-dropping hatch is a two-leaf opening structure, comprising two identical hatch structures 1. Each hatch structure 1 is an integrally machined structure, including a skin and transverse and longitudinal support structures arranged on its inner side. The sealing clamping element 15 is located on the outer periphery of the inner side of the hatch structure 1, and is used to cooperate with the sealing strip 14 to ensure the watertight performance of the water-dropping hatch. The sealing bracket 13 is an L-shaped structure with a slot, which is fixedly connected to the inner side of the fuselage structure. The sealing strip 14 is clamped in the slot of the sealing bracket 13. The sealing clamping element 15, the sealing bracket 13, and the sealing strip 14 constitute a sealing structure.

[0007] Piano key hinges 2 are fixedly connected to the outer edges of the two door structures 1, and are hinged to the fuselage structure through the piano key hinges 2.

[0008] The crank I 3, connecting rod I 4, drive shaft 8, crank II 5, and connecting rod II 6 constitute an opening mechanism, including two sets of identical opening mechanisms symmetrically arranged above the two hatch structures 1. The two drive shafts 8 are respectively arranged along the length of the two hatch structures 1, and their two ends are hinged to the fuselage structure. Several cranks I 3 are provided, symmetrically arranged on the two drive shafts 8. One end of each crank I 3 is fixedly connected to the drive shaft 8, and the other end of each crank I 3 is hinged to one end of each connecting rod I 4. The other end of each connecting rod I 4 is hinged to the hatch structure 1 on the same side. The number of connecting rods I 4 is the same as the number of cranks I 3. One end of each of the two cranks II 5 is fixedly connected to the same end of each of the two drive shafts 8, and one end of each of the two connecting rods II 6 is connected to the other end of each of the two cranks II 5.

[0009] The actuator I 9 is a retractable drive structure that is fixedly connected to the fuselage structure. Its lower end is also hinged to the other end of the connecting rods II 6 on both sides. The extension and retraction of the actuator I 9 drives the opening mechanism to open and close the water tank door. Specifically, when the water tank door is in the closed position, the actuator I 9 is in the retracted state, and when the water tank door is in the open position, the actuator I 9 is in the extended state.

[0010] The locking shaft 11, locking hook 16, locking pin 7, and cam 12 constitute a latching mechanism. The latching mechanism has two sets of identical structures, symmetrically arranged above the two hatch structures 1 and below the drive shaft 8, with one set of latching mechanisms corresponding to each hatch structure 1. The two locking shafts 11 are arranged along the length of the hatch structure 1, and both ends of each locking shaft 11 are hinged to the fuselage structure. Multiple locking hooks 16 are fixedly connected to the middle of each of the two locking shafts 11. The locking hooks 16 cooperate with the locking pins 7 fixedly connected to the hatch structure 1 on the same side to lock the water-dropping hatch in the closed position, and the number of locking pins 7 is the same as the number of locking hooks 16. One end of each of the two cams 12 is fixedly connected to the end of the two locking shafts 11 away from the actuator I 9, and the other end of the cam 12 is provided with a track groove for cooperating with the roller 17.

[0011] The actuator II 10 is a retractable drive structure, which is fixedly connected to the fuselage structure. A roller 17 is fixedly connected to its lower side. The roller 17 also cooperates with the track grooves of two cams 12. Through the extension and retraction of the actuator II 10, the latch mechanism is driven to control the locking and unlocking of the latch mechanism. When the water tank door is in the closed position, the actuator II 10 is in the extended state. When the water tank door is in the open position, the actuator II 10 is in the retracted state.

[0012] Furthermore, when the floodgate is in the closed position, the angle between the two connecting rods II 6 is between 175° and 185°.

[0013] Furthermore, the number of cranks I 3 is greater than 4.

[0014] Furthermore, the number of the locking hooks 16 is greater than four.

[0015] In use: When the water tank door is in the closed position, the locking hook 16 engages with the locking pin 7 to lock the water tank door; the drive actuator II 10 is shortened, and the roller 17, which is fixedly connected to the actuator II 10, slides in the track groove of the two cams 12 and drives the cams 12 to rotate around the axis of the locking shaft 11. The locking shaft 11 drives the locking hook 16 to rotate and move away from the locking pin 7 to release the lock. This process is the unlocking process of the door.

[0016] Crank II 5, connecting rod II 6, actuator I 9, and fuselage structure together constitute a crank-slider mechanism. The included angle between the two connecting rods II 6 is set between 175° and 185°, controlling the transmission angle of the crank-slider mechanism. When the floodgate is subjected to a load in the opening direction, the two connecting rods II 6 cancel out most of the opening load, with only a small portion of the load transmitted to actuator I 9, reducing the risk of accidental opening of the floodgate. After unlocking, actuator I 9 extends, and drive shaft 8 rotates under the drive of the crank-slider mechanism, causing crank I 3 to rotate axially around drive shaft 8. Crank I 3, connecting rod I 4, fuselage structure, and door structure 1 constitute a four-bar linkage. The rotation of crank I 3 causes door structure 1 to rotate around the axis of key hinge 2, thus opening the floodgate.

[0017] The closing process of the water-dropping chamber door is the reverse of the opening process.

[0018] The beneficial effects of this invention are as follows:

[0019] 1. The present invention adopts a double-door design, which has a large opening area when the door is opened, resulting in high fire extinguishing efficiency.

[0020] 2. This invention uses a single actuator to drive the double doors to open, resulting in high synchronization of the mechanism.

[0021] 3. By designing the transmission angle of the opening mechanism, this invention achieves a smaller load on the actuator when the door is closed, thus improving the safety of the mechanism.

[0022] 4. This invention adopts an integral machined structure, which is simple in form and lightweight. The sealing and clamping parts, skin, and transverse and longitudinal support structures of this invention are integrally machined, which has certain advantages in terms of weight, space, and assembly efficiency. Attached Figure Description

[0023] Figure 1 For the closed position isometric of the present invention Figure 1 .

[0024] Figure 2 For the closed position isometric of the present invention Figure 2 .

[0025] Figure 3 Open the positional isometric view for this invention.

[0026] Figure 4 Schematic diagram of the latch mechanism of the present invention Figure 1 .

[0027] Figure 5 Schematic diagram of the latch mechanism of the present invention Figure 2 .

[0028] Figure 6 Schematic diagram of the latch mechanism of the present invention Figure 3 .

[0029] Figure 7 This is a schematic diagram of the opening mechanism of the present invention.

[0030] Figure 8 The following is a partial sectional view of the sealing structure of the present invention, wherein (a) is an overall view of the hatch structure and (b) is a partial sectional view.

[0031] Figure 9 This is a schematic diagram of the overall machined hatch structure of the present invention.

[0032] In the diagram: 1. Door structure; 2. Key hinge; 3. Crank I; 4. Connecting rod I; 5. Crank II; 6. Connecting rod II; 7. Locking pin; 8. Drive shaft; 9. Actuator I; 10. Actuator II; 11. Locking shaft; 12. Cam; 13. Sealing bracket; 14. Sealing strip; 15. Sealing clamp; 16. Locking hook; 17. Roller. Detailed Implementation

[0033] The technical solution of the present invention will now be clearly and completely described. Obviously, the described embodiments are merely some embodiments of the present invention, and not all embodiments. All other embodiments derived by those skilled in the art based on the embodiments of the present invention through modifications or adjustments are within the protection scope of the present invention.

[0034] A water-dropping hatch for a fire-fighting aircraft, comprising a hatch structure 1, a key-type hinge 2, a crank I 3, a connecting rod I 4, a crank II 5, a connecting rod II 6, a locking pin 7, a drive shaft 8, an actuator I 9, an actuator II 10, a locking shaft 11, a cam 12, a sealing bracket 13, a sealing strip 14, a sealing clamping element 15, a locking hook 16, and a roller 17, as shown. Figure 1 and Figure 2 As shown.

[0035] The water-dropping hatch is a two-leaf, double-opening structure, comprising two identical hatch structures 1, each hatch structure 1 being an integrally machined structure (e.g., Figure 9 As shown), it includes a skin and its inner side arranged with horizontal and vertical support structures; the sealing clamping member 15 is set on the outer peripheral edge of the inner side of the hatch structure 1, and is used to cooperate with the sealing strip 14 to ensure the watertight performance of the flooding hatch; the sealing bracket 13 is an L-shaped structure with a slot, which is fixedly connected to the inner side of the fuselage structure; the sealing strip 14 is clamped in the slot of the sealing bracket 13; the sealing clamping member 15, the sealing bracket 13 and the sealing strip 14 form a sealing structure, as shown. Figure 8 As shown.

[0036] Piano key hinges 2 are fixedly connected to the outer edges of the two door structures 1, and are hinged to the fuselage structure through the piano key hinges 2.

[0037] The crank I 3, connecting rod I 4, drive shaft 8, crank II 5, and connecting rod II 6 constitute an opening mechanism, including two sets of identical opening mechanisms symmetrically arranged above the two hatch structures 1. The two drive shafts 8 are arranged along the length of the two hatch structures 1, with both ends hinged to the fuselage structure. Six cranks I 3 are symmetrically arranged on the two drive shafts 8, one end of which is fixedly connected to the drive shaft 8, and the other end is hinged to one end of connecting rod I 4. There are also six connecting rods I 4, corresponding one-to-one with cranks I 3. The other end of connecting rod I 4 is hinged to the hatch structure 1 on the same side. One end of each of the two cranks II 5 is fixedly connected to the same end of the two drive shafts 8. One end of each of the two connecting rods II 6 is connected to the other end of each of the two cranks II 5. Figure 2 and Figure 7 As shown.

[0038] The actuator I 9 is a retractable drive structure, fixedly connected to the fuselage structure, and its lower end is simultaneously hinged to the other ends of the connecting rods II 6 on both sides. When the water tank door is in the closed position, the actuator I 9 is in the retracted state, and the included angle between the connecting rods II 6 on both sides is between 175° and 185°. Figure 2 As shown, when the water chamber door is in the open position, actuator I 9 is in the extended state, as... Figure 3 As shown.

[0039] The locking shaft 11, locking hook 16, locking pin 7, and cam 12 constitute a latching mechanism. Two sets of latching mechanisms with identical structures are symmetrically arranged above the two hatch structures 1 and below the drive shaft 8, with one set of latching mechanisms corresponding to each hatch structure 1. The two locking shafts 11 are arranged along the length of the hatch structure 1, with both ends of each locking shaft 11 hinged to the fuselage structure. Four locking hooks 16 are fixedly connected to the middle of each of the two locking shafts 11. The locking hooks 16 cooperate with the locking pins 7 fixedly connected to the hatch structure 1 on the same side to lock the water-dropping hatch in the closed position. The number of locking pins 7 is the same as the number of locking hooks 16 and they correspond one-to-one. Figure 5As shown; one end of each of the two cams 12 is fixedly connected to the ends of the two locking shafts 11 away from the actuator I 9, and the other end of the cam 12 is provided with a track groove for cooperating with the roller 17, as shown. Figure 6 As shown.

[0040] The actuator II 10 is a retractable drive structure that is fixedly connected to the fuselage structure. A roller 17 is fixedly connected to its lower side. The roller 17 also cooperates with the track grooves of the two cams 12 to control the locking and unlocking of the latch mechanism. When the water tank door is in the closed position, the actuator II 10 is in the extended state. When the water tank door is in the open position, the actuator II 10 is in the retracted state.

[0041] In practical use: With the hatch fully closed, the actuator II10 is shortened by a hydraulic or electric power source. The roller 17, which is fixedly connected to the actuator II10, slides in the track groove and drives the cam 12 to rotate around the axis of the locking shaft 11. The locking hook 16 on the locking shaft 11 rotates and moves away from the locking pin 7. This process is the unlocking process of the hatch.

[0042] Crank II5, connecting rod II6, actuator I9, and fuselage structure together constitute a "crank-slider" mechanism. After unlocking, actuator I9 is ​​extended by a hydraulic or electric power source, and transmission shaft 8 rotates under the drive of the aforementioned "crank-slider" mechanism, causing crank I3 to rotate axially around transmission shaft 8. Crank I3, connecting rod I4, fuselage structure, and hatch structure 1 constitute a four-bar linkage. The rotation of crank I3 will cause the hatch to rotate around the axis of piano key hinge 2, thereby opening the hatch.

[0043] The closing process of the hatch is the reverse of the opening process.

[0044] The above-described embodiments are merely illustrative of the implementation methods of the present invention, but should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the protection scope of the present invention.

Claims

1. A water-dropping hatch for a fire-fighting aircraft, characterized in that, The water-dropping hatch includes a hatch structure (1), a key hinge (2), a crank I (3), a connecting rod I (4), a crank II (5), a connecting rod II (6), a locking pin (7), a drive shaft (8), an actuator I (9), an actuator II (10), a locking shaft (11), a cam (12), a sealing bracket (13), a sealing strip (14), a sealing clamping element (15), a locking hook (16), and a roller (17). The water-dropping hatch is a two-leaf opening structure, including two identical hatch structures (1); the sealing clamping component (15) is set on the outer periphery of the inner side of the hatch structure (1) and is used to cooperate with the sealing strip (14) to ensure watertight performance; the sealing bracket (13) is an L-shaped structure with a slot, which is fixedly connected to the inner side of the fuselage structure; the sealing strip (14) is clamped in the slot of the sealing bracket (13); Piano key hinges (2) are fixedly connected to the outer edges of the two door structures (1), and are hinged to the fuselage structure through the piano key hinges (2); The crank I (3), connecting rod I (4), drive shaft (8), crank II (5) and connecting rod II (6) form an opening mechanism. Two sets of opening mechanisms with the same structure are symmetrically arranged above the two hatch structures (1). The two drive shafts (8) are arranged along the length of the two hatch structures (1) respectively, and their two ends are hinged to the fuselage structure. Several cranks I (3) are arranged on the two drive shafts (8). One end of the crank I (3) is fixedly connected to the drive shaft (8), and the other end of the crank I (3) is hinged to one end of the connecting rod I (4). The other end of the connecting rod I (4) is hinged to the hatch structure (1) on the same side. One end of the two cranks II (5) is fixedly connected to the same end of the two drive shafts (8), and one end of the two connecting rods II (6) is connected to the other end of the two cranks II (5). The actuator I (9) is a retractable drive structure that is fixedly connected to the fuselage structure. Its lower end is simultaneously hinged to the other end of the connecting rods II (6) on both sides. Through the retractable movement of the actuator I (9), the opening mechanism is driven to realize the opening and closing of the water-dropping hatch. The locking shaft (11), locking hook (16), locking column (7), and cam (12) constitute a latching mechanism. The latching mechanism has two sets of identical structures, symmetrically arranged above the two hatch structures (1) and below the drive shaft (8). The two locking shafts (11) are arranged along the length of the hatch structure (1). The two ends of each locking shaft (11) are hinged to the fuselage structure. Multiple locking hooks (16) are fixedly connected to the middle of each of the two locking shafts (11). The locking hooks (16) cooperate with the locking column (7) fixedly connected to the hatch structure (1) on the same side to lock the water-dropping hatch in the closed position. One end of each of the two cams (12) is fixedly connected to the end of the two locking shafts (11) away from the actuator I (9). The other end of the cam (12) is provided with a track groove for cooperating with the roller (17). The actuator II (10) is a retractable drive structure that is fixedly connected to the fuselage structure. A roller (17) is fixedly connected to its lower side. The roller (17) also cooperates with the track grooves of two cams (12). Through the retractable movement of the actuator II (10), the latch mechanism is driven to control the locking and unlocking of the water-dropping chamber door.

2. The water-dropping hatch of a fire-fighting aircraft according to claim 1, characterized in that, When the floodgate is in the closed position, the angle between the two connecting rods II (6) is between 175° and 185°.

3. The water-dropping hatch of a fire-fighting aircraft according to claim 1, characterized in that, The aforementioned hatch structure (1) is an integral machined structure, including the skin and the transverse and longitudinal support structures arranged on its inner side.

4. The water-dropping hatch of a fire-fighting aircraft according to claim 1, characterized in that... The number of cranks I(3) is greater than 4.

5. The water-dropping hatch of a fire-fighting aircraft according to claim 1, characterized in that, The number of the locking hooks (16) is greater than 4.

6. The water-dropping hatch of a fire-fighting aircraft according to claim 1, characterized in that, When the water tank door is in the closed position, actuator I (9) is in the retracted state; when the water tank door is in the open position, actuator I (9) is in the extended state.

7. The water-dropping hatch of a fire-fighting aircraft according to claim 1, characterized in that, When the water tank door is in the closed position, actuator II (10) is in the extended state; when the water tank door is in the open position, actuator II (10) is in the retracted state.

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