Unit emergency parachuting cabin door and mechanism thereof
By designing a unit emergency parachuting hatch and its mechanism including actuating cylinder, hinge support, triangular shaft, door structure and locking mechanism, the problem of large aircraft crews having difficulty getting off the plane quickly in emergency situations is solved, and the problem of large aircraft crew members is difficult to quickly leave the plane in an emergency situation is realized. The safe evacuation of personnel and automatic control of hatch doors at high speeds.
Patent Information
- Application Number
- CN202411705839.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-26
- Publication Date
- 2025-02-18
AI Technical Summary
In an emergency, large aircraft have difficulty reaching the cargo hold in a short time and using the emergency exit provided therein, and it is difficult to exit the cabin at high speeds.
A unit emergency parachuting hatch door and its mechanism are designed, including actuating cylinder, hinge support, triangular shaft, door body structure and locking mechanism. The automatic opening and locking of the hatch door is realized through mechanical and electro-hydraulic automatic control, and the opening is carried out. Then form a windshield.
Emergency evacuation of personnel at high speeds has been achieved, effectively occupying the internal space of the fuselage, light weight, and windproof function, improving the safety of crew members.
Smart Images
Figure CN119460058A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to aircraft door structure design technology, and in particular to an emergency parachute door for crew members and its mechanism. Background Art
[0002] Transport aircraft are generally required to set up emergency exit measures in the air to ensure the safety of crew members due to the complexity of their operating environment and flight missions. Civil transport aircraft such as passenger aircraft are often modified during test flights to enable crew members to have the ability to leave the aircraft in the air in an emergency. When setting up emergency evacuation exits in the air, it is required that personnel are easy to reach, so there are different setting requirements for different aircraft models. For small and medium-sized aircraft, it is easy for crew members to reach the cabin, and the cockpit is too small to set up emergency exits, so the emergency exits are designed in the cabin. However, for large aircraft, the cockpit is often located above the cargo hold, and generally stairs are required to reach the cargo hold. In an emergency, it is difficult for crew members to reach the cargo hold in a short time and use the emergency exit set up in it to leave the aircraft, so this type of aircraft often sets up a separate emergency escape channel for crew members. Relevant research currently shows that it is recommended to set up wind shielding measures when the aircraft speed is greater than 250Km / h, otherwise the airflow will increase the difficulty of personnel leaving the cabin.
[0003] When the aircraft is in distress in the air and the test pilots need to escape, they first blast and cut the rear fuselage skin to relieve the cabin pressure, then blast and cut the connection between the service door and the surrounding structure to separate the service door from the door frame, and finally throw the charge to move the service door into the cabin to form an escape passage in the service door area. The lack of a windshield has a significant impact on the personnel leaving the cabin. Because the transport aircraft is used in a complex environment, it is not convenient to use pyrotechnic products that are sensitive to the electromagnetic environment. It is a more reasonable choice to use electromechanical operation to open the cabin door for emergency evacuation.
[0004] The emergency parachute door structure of a certain aircraft crew is made of magnesium alloy castings. The structure is heavy, and the mechanism needs to be manually adjusted when the door is closed and locked, so the degree of automation is low.
[0005] A certain type of aircraft is designed with an air emergency evacuation door at the rear of the fuselage. The door is opened by the power of a gas cylinder and then kept in the open position by the airflow, thus acting as a wind shield. Due to the location difference, this configuration cannot be adopted. Summary of the invention
[0006] In order to solve the above problems, the present application provides an emergency parachute door for crew members and its mechanism, including:
[0007] Actuator, hinge support, triangular shaft, door structure and locking mechanism;
[0008] Two hinge supports are fixed on the machine body, and the door structure is hinged between the hinge supports through a triangular shaft. The triangular shaft has a rocker arm hinged to the movable end of the actuator. The actuator retracts and drives the triangular shaft to rotate and then drives the door structure to open and close.
[0009] The lock mechanism is fixed on the machine body to lock the door structure in the closed state; the lock mechanism includes: a lock actuator with a fixed end fixed on the machine body, two lock box assemblies fixed on the machine body, a rocker arm assembly hinged between the lock box assemblies, and a compression spring assembly;
[0010] The lock box assembly is provided with a four-link hook lock mechanism, which is connected to both ends of the rocker arm assembly. The rotation of the rocker arm assembly drives the lock hook of the four-link hook lock mechanism to engage or disengage with the lock ring assembly on the door structure to achieve locking and unlocking; one end of the compression spring assembly is connected to the fuselage and the other end is connected to the rocker arm assembly to provide a locking preload for the rocker arm assembly; the movable end of the lock actuator is hinged to the rocker arm assembly to rotate, and when the lock actuator is actuated, it overcomes the preload of the compression spring assembly to drive the rocker arm assembly to unlock.
[0011] Preferably, the fixed end of the actuator is fixed to the machine body via a support, and a supporting connecting rod is connected between each hinge support and the support. The actuator and the supporting connecting rod (13) form a triangular structure for self-balancing the thrust of the actuator (11).
[0012] Preferably, the hinge support is a double-ear structure, the two ends of the triangular shaft are external spline shafts between the double-ear structures, the door body structure has two hinges with single-ear structures, and the keyway holes of the hinges cooperate with the external spline shafts to transmit torque.
[0013] Preferably, an electric switch mechanism is respectively provided at the locking position, unlocking position, door structure opening position and door structure closing position of the lock mechanism, and the electric switch mechanism is used to indicate whether the lock or unlocking is in place and whether the door structure is opened or closed.
[0014] Preferably, the switch mechanism comprises a switch support, a tension spring, a rocker arm, an adjustable screw, a roller, and a switch;
[0015] The electric switch support is hinged in the middle of the rocker arm, one end is connected to the tension spring, and the other end is provided with a roller. The electric switch is installed on the electric switch support and the adjustable screw is installed on the rocker arm. During the movement of other mechanisms, the roller is contacted to overcome the tension of the tension spring to drive the rocker arm to move, and the adjustable screw is pressed and connected with the electric switch; after the contact with the roller is released during the movement of other mechanisms, the tension spring drives the rocker arm to rotate to disconnect the adjustable screw from the electric switch.
[0016] Preferably, the door structure in the open state forms a wind shield to protect personnel from leaving the machine smoothly.
[0017] Preferably, a snap ring lock is provided in the lock actuator cylinder, which locks the travel of the lock actuator cylinder in the unlocked state, keeps the lock mechanism in the unlocked position, and avoids scratching personnel when evacuating.
[0018] Preferably, the rocker arm of the triangular rotating shaft has a Y-shaped structure.
[0019] Preferably, the four-link hook lock mechanism contains a dead point deflection, and when unlocking, the hatch is first pulled toward the closing direction, and the hatch can be opened only after the mechanism passes the dead point.
[0020] Preferably, a deflection inspection hole is provided on the lock box to confirm whether the dead point deflection of the four-bar hook lock mechanism meets the requirements.
[0021] Preferably, the door structure comprises: a main door structure, a docking corner box, a hinge, a docking plate, a corner piece, and a lock ring assembly; the door structure is integrally machined from an aluminum alloy, and its inner surface has longitudinal ribs and transverse ribs; the hinge is made of alloy steel material,
[0022] The hinge is connected to the longitudinal ribs through the butt corner boxes and to the transverse ribs through the butt plates.
[0023] Preferably, the hinge and locking ring assembly are installed on two opposite sides of the main structure of the door body.
[0024] The advantages of the present application include: the present invention can effectively occupy the space inside the fuselage, is light in weight, can realize automatic electromechanical and hydraulic control, has a windproof function after the cabin door is opened, and realizes the emergency evacuation of personnel at high speed. BRIEF DESCRIPTION OF THE DRAWINGS
[0025] Figure 1 This is a schematic diagram of an emergency parachute door for an aircraft crew and its mechanism scheme according to the present invention;
[0026] Figure 2 It is a schematic diagram of the door structure in the present invention;
[0027] Figure 3 This is a schematic diagram of the connection between the hinge and the door structure in the present invention;
[0028] Figure 4 It is a schematic diagram of the lock ring assembly in the present invention;
[0029] Figure 5 It is a schematic diagram of the retractable mechanism in the present invention;
[0030] Figure 6 This is a schematic diagram of the installation of the external spline shaft in the present invention;
[0031] Figure 7 It is a schematic diagram of the locking mechanism in the present invention;
[0032] Figure 8 Schematic diagram of a typical electric switch mechanism in the present invention. DETAILED DESCRIPTION
[0033] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.
[0034] In actual applications, an emergency parachute door and its mechanism for the crew need to be installed in the lower part of the nose cockpit, where the space is compact and the curvature of the shape is large. Because it is in a non-airtight area, the fuselage structure rigidity is limited, the design requirements are high and the difficulty is great. This is the first time in China that a door of this configuration has been designed.
[0035] The present application provides an emergency parachute door and its mechanism for a crew, including: an emergency parachute door and its mechanism for a crew, the door and mechanism comprising a retractable mechanism 1, a door structure 2, a locking mechanism 3, and an electric switch mechanism 4, wherein:
[0036] The door structure 2 includes: a door main structure 5, a docking corner box 6, a hinge 7, a docking plate 8, a corner piece 9, and a lock ring assembly 10. The door structure 5 is integrally machined from aluminum alloy, and the hinge 7 is made of alloy steel. The two are connected through the docking corner box 6 and the docking plate 8, which can comprehensively utilize the mechanical properties of each material and effectively reduce the weight of the structure; the hatch is provided with an adjustable lock ring assembly 10, which can play a role in adjusting the hatch step difference by matching the different positions of the lock hook in the lock mechanism through the meshing of the tooth plate at different positions.
[0037] Preferably, the main door structure 5 and the hinge 7 are made of different materials and are combined into a whole.
[0038] Preferably, an adjustable locking ring assembly 10 is provided on the hatch door, which can be used to adjust the step difference of the hatch door.
[0039] Preferably, the main door structure 5 is integrally machined from aluminum alloy, and drainage holes are provided at the lowest point of each rib to prevent accumulation of condensed water.
[0040] Preferably, the hinge 7 is provided with an internal spline for transmitting the torque during the door opening and closing process.
[0041] Preferably, the door structure 5 forms a wind shield after opening to protect personnel from leaving the machine smoothly.
[0042] The retractable mechanism 1 comprises: an actuator 11, a support 12, a supporting link 13, a double-ear reinforcement 14, a triangular rotating shaft 15, a hinge support 16, an external spline shaft 17, and a process plug cover 18. The retractable mechanism 1 adopts a unique triangular structure and has self-stabilizing performance. It can convert the thrust of the actuator 11 into the internal force of the supporting link 13, reduce the load transmitted to the fuselage structure from the support 12 and the hinge support 16, and play a role in reducing the weight of the structure.
[0043] Preferably, the actuator 11 and the supporting connecting rod 13 form a triangular structure for self-balancing the thrust of the actuator 11 .
[0044] Preferably, the supporting connecting rod 13 is composed of two connecting rods arranged at a certain angle.
[0045] Preferably, both ends of the supporting link 13 are fixedly connected to the support 12 and the hinge support 16 respectively.
[0046] Preferably, the hatch structure 2 is connected to the retractable mechanism 1 via an external spline shaft 17, and a process plug cover 18 is installed on the external spline shaft 17, which together serve as a hatch support shaft.
[0047] Preferably, the triangular rotating shaft adopts a “Y”-shaped structure, with one end connected to the actuator 11 and the other end connected to the external spline shaft 17 .
[0048] The lock mechanism 3 includes: an upper lock box 19, a compression spring assembly 20, a rocker assembly 21, a lower lock box 22, a switch contact 23, a lock shaft 24, an actuator support 25, a lock actuator 26, a support angle piece 27, a lock shaft joint 28, and a four-link hook lock mechanism 29. The lock mechanism 3 is connected to the fuselage structure through the lock box assembly 19, 22 and the support angle piece 27 to play a supporting role. The lock shaft 24 and the lock shaft joint 28 are connected together by bolts, wherein the lock shaft joint 28 passes through the lock box 19, 22, so that the outer spline on the lock shaft joint 28 cooperates with the inner spline in the four-link hook lock mechanism 29 for transmission. The notch on the lock hook in the four-link hook lock mechanism 29 engages with the lock ring assembly 10 on the door structure to achieve the locking of the cabin door. The rocker assembly 21 and the lock position switch contact 23 are installed on the lock shaft 24. The rocker arm support 21 is used to connect the lock actuator 26, the compression spring assembly 20 and the lock open position switch contact pressure screw. The lock closed position switch contact 23 is used to press the switch in the lock position to give an electrical signal. The other end of the lock actuator 26 is connected to the support on the frame. When unlocking, the lock actuator 26 retracts, driving the lock shaft 24 to rotate in the lock box 19, 22, driving the four-link hook lock mechanism 29 to disengage the lock hook from the lock ring assembly 10. A snap ring lock is provided in the lock actuator 26. After the actuator retracts a certain distance, the snap ring lock is locked to keep the lock hook in the open position to avoid hindering the emergency evacuation of the crew. The lock mechanism 3 is provided with a four-link hook lock 29 (including the "dead point" deflection) and a compression spring assembly 20 to ensure the locking safety of the lock mechanism.
[0049] Preferably, the lock shaft 24 is connected to the lock shaft joint 28 by bolts, and a spline structure is provided on the lock shaft joint 28, and the spline structure is engaged with the spline in the four-bar hook lock mechanism 29 to realize transmission.
[0050] Preferably, a compression spring assembly 20 is provided in the lock mechanism to provide resistance during the front stage of unlocking, so as to keep the door in the closed and locked position.
[0051] Preferably, a snap ring lock is provided in the lock actuator 26 to keep the lock mechanism in the unlocked position after unlocking, so as to avoid scratching people when evacuating.
[0052] Preferably, the four-link hook lock mechanism 29 contains a "dead point" deflection. When unlocking, the lock mechanism needs to first pull the door toward the closing direction, and the door can be opened only after the mechanism passes the "dead point".
[0053] Preferably, the end of the locking shaft joint 28 is provided with a hexagonal structure, and the locking shaft joint 28 can be screwed with a universal tool to adjust the position of the mechanism.
[0054] Preferably, the lock boxes 19 and 22 are provided with deflection inspection holes for confirming whether the “dead point” deflection of the four-bar hook lock mechanism 29 meets the requirements.
[0055] The electric switch mechanism 4 includes: an electric switch support 30, a tension spring 31, a rocker arm 32, an adjustable screw 33, a roller 34, and an electric switch 35. The electric switch 35 is installed on the electric switch support 30, and the rocker arm 32, the tension spring 31, the adjustable screw 33, the roller 34, etc. are arranged on the electric switch support 30. During the movement of other mechanisms, the roller 34 is contacted to drive the rocker arm 32 to move until the adjustable screw 33 is pressed and connected with the electric switch 35; after the contact with the roller 34 is released, the tension spring 31 drives the rocker arm 32 to rotate to disconnect the adjustable screw 33 from the electric switch 35. The electric switch mechanism 4 is arranged in 4 places, which are respectively used to indicate 4 states of the hatch door being fully opened, fully closed, and the lock mechanism being locked and unlocked.
[0056] The advantages of the present invention are: the present invention can effectively occupy the space inside the fuselage, is light in weight, can realize automatic electromechanical and hydraulic control, has a windproof function after the cabin door is opened, and realizes the emergency evacuation of personnel at a high speed.
[0057] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application 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.
Claims
1. A crew emergency parachute door and its mechanism, characterized in that: include: An actuator (11), a hinge support (16), a triangular rotating shaft (15), a door structure (2) and a locking mechanism (3); Two hinge supports (16) are fixed on the machine body, and the door structure (2) is hinged between the hinge supports (16) via a triangular rotating shaft (15). The triangular rotating shaft (15) has a rocker arm hinged to the movable end of the actuator cylinder (11). The actuator cylinder (11) is telescopically driven to rotate the triangular rotating shaft (15) and thereby drive the door structure (2) to open and close. The lock mechanism (3) is fixed on the machine body and locks the door structure (2) in a closed state; the lock mechanism (3) comprises: a lock actuator (26) whose fixed end is fixed on the machine body, two lock box assemblies (19, 22) fixed on the machine body, a rocker arm assembly (21) hinged between the lock box assemblies (19, 22), and a compression spring assembly (20); A four-link hook lock mechanism (29) is provided in the lock box assembly (19, 22), and the four-link hook lock mechanism (29) is connected to both ends of the rocker arm assembly (21). The rotation of the rocker arm assembly (21) drives the lock hook of the four-link hook lock mechanism (29) to engage or disengage with the lock ring assembly (10) on the door body structure (2) to achieve locking and unlocking; one end of the compression spring assembly (20) is connected to the fuselage and the other end is connected to the rocker arm assembly (21), providing a locking preload for the rocker arm assembly (21); the movable end of the lock actuator (26) is hinged to the rocker arm assembly (21) to rotate, and when the lock actuator (26) is actuated, it overcomes the preload of the compression spring assembly (20) and drives the rocker arm assembly (21) to unlock.
2. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: The fixed end of the actuator (11) is fixed to the fuselage through a support (12), and a supporting connecting rod (13) is connected between each hinge support (16) and the support (12). The actuator (11) and the supporting connecting rod (13) form a triangular structure for self-balancing the thrust of the actuator (11).
3. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: The hinge support (16) is a double-ear structure, and the two ends of the triangular rotating shaft (15) are external spline shafts (17) between the double-ear structures. The door body structure (2) has two hinges (7) with single-ear structures, and the keyway holes of the hinges (7) cooperate with the external spline shafts (17) to transmit torque.
4. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: An electric switch mechanism (4) is respectively arranged at the locking position, unlocking position, door body structure (2) opening position and door body structure (2) closing position of the lock mechanism (3), and the electric switch mechanism (4) is used to indicate whether the locking or unlocking is in place, and whether the door body structure (2) is opened or closed.
5. The crew emergency parachute door and its mechanism as claimed in claim 4, characterized in that: The switch mechanism (4) comprises a switch support (30), a tension spring (31), a rocker arm (32), an adjustable screw (33), a roller (34), and a switch (35); The middle of the rocker arm (32) is hinged to the switch support (30), one end of which is connected to the tension spring (31), and the other end of which is provided with a roller (34). The switch (35) is mounted on the switch support (30), and the adjustable screw (33) is mounted on the rocker arm (32). During the movement of other mechanisms, the roller (34) is contacted to overcome the tension of the tension spring (31) to drive the rocker arm (32) to move, and the adjustable screw (33) is pressed and connected with the switch (35); after the contact with the roller (34) is released during the movement of other mechanisms, the tension spring (31) drives the rocker arm (32) to rotate to disconnect the adjustable screw (33) from the switch (35).
6. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: The door structure (2) in the open state forms a wind shield to protect personnel from leaving the machine smoothly.
7. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: A snap ring lock is arranged in the lock actuator (26), and the travel of the lock actuator (26) is locked in the unlocked state, so that the lock mechanism (3) is kept in the unlocked position, thereby preventing people from being scratched when evacuating.
8. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: The rocker arm of the triangular rotating shaft (15) is in a Y-shaped structure.
9. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: The four-link hook lock mechanism (29) contains a dead point deflection. When unlocking, the door is first pulled closer to the closing direction, and the door can be opened only after the mechanism passes the dead point.
10. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: The lock boxes (19, 22) are provided with deflection inspection holes for confirming whether the dead point deflection of the four-link hook lock mechanism (29) meets the requirements.
11. The crew emergency parachute door and its mechanism as claimed in claim 1, characterized in that: The door structure (2) comprises: a main door structure (5), a docking corner box (6), a hinge (7), a docking plate (8), a corner piece (9), and a lock ring assembly (10); the door structure (5) is integrally machined from an aluminum alloy, and its inner surface has longitudinal ribs and transverse ribs; the hinge (7) is made of alloy steel material, The hinge (7) is connected to the longitudinal rib via a butt corner box (6) and is connected to the transverse rib via a butt plate (8).
12. The crew emergency parachute door and its mechanism as claimed in claim 11, characterized in that: The hinge (7) and the lock ring assembly (10) are installed on two opposite sides of the door body main structure (5).