Flat opening type cabin door mechanism capable of mechanically and emergently releasing

Abstract

The invention provides a side-hung type cabin door mechanism capable of being mechanically released in emergency, and belongs to the technical field of airplane cabin doors. The emergency rope is connected to the operating handle, and the other end of the emergency rope is connected to the first gear set; two gears of the first gear set are respectively arranged on the fuselage structure and the small cabin door, and two gears of the second gear set are respectively arranged on the actuating cylinder rocker arm and the cabin door rocker arm; the cabin door actuating cylinder is used for driving the cabin door to be normally opened and connected with an actuating cylinder rocker arm which is connected with the large cabin door, and the large cabin door is hinged to the small cabin door; when the cabin door is normally opened, the cabin door actuating cylinder drives the actuating cylinder rocker arm, then the cabin door rocker arm is driven to move through the second gear set, and finally the large cabin door and the small cabin door are driven to rotate to the completely-opened position. When the cabin door is released emergently, the operation handle is pulled, the first gear set is pulled to rotate through the emergency rope, and the small cabin door and the large cabin door are driven to rotate to the completely-opened position.

Description

Technical Field

[0001] The present application belongs to the field of aircraft cabin doors, and in particular relates to a flat-opening cabin door mechanism capable of mechanical emergency release. Background Art

[0002] At present, the landing gear doors of domestic aircraft mainly use a single rocker arm flip door mechanism, and the door opening angle is small, generally not more than 120 degrees. However, with the special requirements of some aircraft, for example, when the aircraft landing gear squats, the landing gear door structure cannot touch the ground, which requires the door to open at a larger angle (at least more than 150 degrees). If it is designed as a flip door, the driving mechanism will have a small force arm, the door mechanism will have poor rigidity, and the mechanism will be difficult to arrange. In this case, the flat door mechanism uses a double rocker arm to push the door to the side of the fuselage. The door will also have a large rotation angle, resulting in a small force arm and difficult arrangement of the driving mechanism.

[0003] In the prior art, aircraft generally use hydraulic motors (or electric motors), torque transmission mechanisms and reducers as driving devices for large-angle door mechanisms. The advantage of this set of devices is that the structure is compact and the door mechanism can rotate to any large angle. The disadvantage is that the reliability requirements for the hydraulic motor (or electric motor), torque transmission mechanism and reducer are particularly high. If any joint is stuck, the whole set of mechanisms will be stuck and the door cannot be opened. In addition, this set of mechanisms cannot be arranged with a mechanical emergency door release function, which will also cause the landing gear to be unable to be lowered, seriously affecting the safety of the aircraft. Summary of the invention

[0004] The purpose of the present application is to provide a flat-opening hatch door mechanism capable of mechanical emergency release, so as to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: a flat-opening hatch door mechanism capable of mechanical emergency release, comprising:

[0006] Operating handle;

[0007] An emergency rope connected to the operating handle, the other end of the emergency rope being connected to the first gear set;

[0008] A first gear set and a second gear set each consisting of two gears, wherein the two gears of the first gear set are respectively arranged on the fuselage structure and the small door, and the two gears of the second gear set are respectively arranged on the actuator rocker arm and the door rocker arm;

[0009] A door actuator for driving the door to open normally, wherein the door actuator is connected to the actuator rocker arm, and the door rocker arm is connected to the large door, and the large door is hinged to the small door;

[0010] When the cabin door is opened normally, the cabin door actuator drives the actuator rocker arm, and the actuator rocker arm drives the cabin door rocker arm to move through the second gear set, thereby driving the large cabin door and the small cabin door to rotate to the fully open position;

[0011] When the cabin door is released in an emergency, the operating handle is pulled to drive the first gear set to rotate through the emergency rope, thereby driving the small cabin door and the large cabin door to rotate to the fully open position.

[0012] In an optional implementation manner of the present application, the emergency rope is a steel cable.

[0013] In an optional embodiment of the present application, the first gear group also includes an emergency rocker arm and a follower rocker arm, the follower rocker arm is integrally connected to the gear on the fuselage structure in the first gear group, the emergency rocker arm is installed on the gear shaft on the fuselage structure, and the other end of the emergency rocker arm is connected to the emergency rope.

[0014] In an optional embodiment of the present application, during emergency release, the emergency rocker arm rotates under the traction of the emergency rope. When the emergency rocker arm is in contact with the emergency rope, the emergency rocker arm rotates together with the emergency rope, thereby driving the gear on the small cabin door to rotate.

[0015] In an optional embodiment of the present application, the size of the gears on the fuselage structure is larger than the size of the gears on the small cabin door.

[0016] In an optional implementation manner of the present application, the ratio of the gear size on the fuselage structure to the gear size on the small cabin door is 1.5-3.

[0017] In an optional embodiment of the present application, the gear on the actuator rocker arm is larger than the gear on the door rocker arm.

[0018] In an optional embodiment of the present application, the ratio of the gear size on the actuator rocker arm to the gear size on the door rocker arm is 1.5-3.

[0019] The mechanical emergency-releaseable flat-opening door mechanism of the present application realizes the function of using a traditional hydraulic actuator to drive a large-angle rotating door mechanism, solves the problem of low reliability of the applied motor, torque transmission mechanism and reducer, and possible mechanism jamming failure, which leads to the door being unable to open and the landing gear being unable to be lowered. Simple traditional structural parts replace the complex torque transmission mechanism, greatly reducing the development risk and improving the safety and reliability of the door mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0021] Figure 1This is a schematic diagram of the closed state of the single-sided flat-opening hatch in this application.

[0022] Figure 2 This is a schematic diagram of the open state of the single-sided flat-opening hatch in this application.

[0023] Figure 3 This is a schematic diagram of the first gear set in this application. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0025] In order to solve the problem that the reliability of hydraulic motors (or electric motors), torque transmission mechanisms and reducers in aviation applications is low, and the entire mechanism is very likely to fail, resulting in the failure of the cabin door to be opened and the landing gear to be lowered, an application is made to provide a mechanical emergency flat cabin door structure.

[0026] like Figures 1 to 3 As shown, the mechanical emergency foldable hatch structure of the present application includes: an operating handle 1, an emergency rope 2, a first gear set 31, a second gear set 32, a small hatch 4, a large hatch 5, a hatch actuator 6, an actuator rocker arm 7 and a hatch rocker arm 8.

[0027] The operating handle 1 is arranged in the cockpit or the fuselage cabin, and the lower end of the operating handle 1 is connected to the emergency rope 2 , and the other end of the emergency rope 2 is connected to the first gear set 31 .

[0028] The first gear set 31 is a gear transmission structure composed of two gears, one of which is mounted on the small cabin door 4, and the other is mounted on the fuselage structure. The first gear set 31 also includes an emergency rocker arm 312 and a follower rocker arm 311, the follower rocker arm 311 is integrally connected to the fuselage structure gear, the emergency rocker arm 312 is connected to the rotating shaft of the fuselage structure gear, and the emergency rope 2 is connected to the end of the emergency rocker arm 312.

[0029] In some embodiments of the present application, the emergency rope 2 is a steel rope to improve its durability.

[0030] Furthermore, in the first gear set 31, the gear on the fuselage structure is larger than the gear on the small cabin door 4. In the preferred embodiment of the present application, the ratio of the former gear size to the latter gear size is about 1.5-3, for example, its typical value may be 2.

[0031] Similar to the first gear set 31, the second gear set 32 ​​is also a gear transmission structure composed of two gears, one of which is arranged on the door rocker arm 8, and the other is arranged on the actuator rocker arm 7. One end of the door actuator 6 is hinged to the fuselage structure, and the other end is hinged to the actuator rocker arm 7. The door rocker arm 8 is hinged to the large door 5, and the large door 5 and the small door 4 are also hinged.

[0032] In the present application, the gear on the door rocker arm 8 is smaller than the gear on the cylinder rocker arm 7, so that the large-angle rotation of the door rocker arm 8 can be converted into a small-angle rotation of the cylinder rocker arm 7, so that the door cylinder 6 has a sufficient force arm to drive the large door 5 and the small door 4, which is convenient for driving the door cylinder 6. Furthermore, the gear ratio of the cylinder rocker arm 7 to the door rocker arm 8 is about 1.5 to 3, and its typical value can be 2, for example.

[0033] When the door is retracted or extended normally, the door actuator 6 drives the gear on the actuator rocker arm 7 to rotate, which drives the door rocker arm 8 to rotate, and then drives the small door 4 and the large door 5 to rotate to the fully open position. The follower rocker arm 311 in the first gear set 31 rotates accordingly, and the emergency rocker arm 312 does not rotate.

[0034] When the cabin door is released in an emergency, the operating handle 1 is lifted, and the emergency rope 2 is pulled to drive the emergency rocker arm 312 to rotate. When the emergency rocker arm 312 and the follower rocker arm 311 are in contact, the two together drive the first gear set to rotate, and then drive the small cabin door 4, the large cabin door 5, and the cabin door rocker arm 8 to the open position, completing the emergency release operation of the cabin door.

[0035] In view of the fact that the rocker arm in the existing flat-opening door mechanism has a relatively large rotation angle (exceeding 150°) and the driving force arm is too small, which is not conducive to the layout of the door driving mechanism, the present application applies the radius and angle conversion function of the gear set to the door mechanism, converts the large-angle rotation (greater than 150°) of the flat-pushing folding door into a small-angle rotation (less than 90°), and at the same time increases the rotation force arm, realizing the function of driving the large-angle rotation door mechanism with the traditional hydraulic actuator, solving the problem that the reliability of the motor, torque transmission mechanism and reducer is not high, and the mechanism may be stuck, resulting in the door not being able to open and the landing gear not being able to be lowered. The complex torque transmission mechanism is replaced by a simple traditional structural part, which greatly reduces the development risk and improves the safety and reliability of the door mechanism. At the same time, by adding a set of manual mechanical emergency release mechanisms, the safety of the door mechanism opening under energy failure conditions is guaranteed.

[0036] 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 flat-opening hatch door mechanism capable of mechanical emergency release, characterized in that: include: Operating handle; An emergency rope connected to the operating handle, the other end of the emergency rope being connected to the first gear set; A first gear set and a second gear set each consisting of two gears, wherein the two gears of the first gear set are respectively arranged on the fuselage structure and the small door, and the two gears of the second gear set are respectively arranged on the actuator rocker arm and the door rocker arm; A door actuator for driving the door to open normally, wherein the door actuator is connected to the actuator rocker arm, and the door rocker arm is connected to the large door, and the large door is hinged to the small door; When the cabin door is opened normally, the cabin door actuator drives the actuator rocker arm, and the actuator rocker arm drives the cabin door rocker arm to move through the second gear set, thereby driving the large cabin door and the small cabin door to rotate to the fully open position; When the cabin door is released in an emergency, the operating handle is pulled to drive the first gear set to rotate through the emergency rope, thereby driving the small cabin door and the large cabin door to rotate to the fully open position.

2. The mechanical emergency release flat-opening hatch mechanism according to claim 1, characterized in that: The emergency rope is a steel cable.

3. The mechanical emergency release flat-opening hatch mechanism according to claim 1, characterized in that: The first gear group also includes an emergency rocker arm and a follower rocker arm. The follower rocker arm is integrally connected to the gear on the fuselage structure in the first gear group. The emergency rocker arm is installed on the gear shaft on the fuselage structure, and the other end of the emergency rocker arm is connected to the emergency rope.

4. The mechanical emergency release flat-opening hatch mechanism according to claim 3, characterized in that: During emergency release, the emergency rocker arm rotates under the traction of the emergency rope. When the emergency rocker arm is in contact with the emergency rope, the emergency rocker arm rotates together with the emergency rope, thereby driving the gear on the small cabin door to rotate.

5. The mechanical emergency release flat-opening hatch mechanism according to claim 4, characterized in that: The size of the gear on the fuselage structure is larger than the size of the gear on the small cabin door.

6. The mechanical emergency release flat-opening hatch mechanism according to claim 5, characterized in that: The ratio of the gear size on the fuselage structure to the gear size on the small cabin door is 1.5-3.

7. The mechanical emergency release flat-opening hatch mechanism according to claim 1, characterized in that: The gear on the actuator rocker arm is larger than the gear on the door rocker arm.

8. The mechanical emergency release flat-opening hatch mechanism according to claim 7, characterized in that: The ratio of the gear size on the actuator rocker arm to the gear size on the door rocker arm is 1.5 to 3.

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