A flat-opening hatch mechanism capable of mechanical emergency release

Abstract

The present application provides a casement door mechanism that can be mechanically released in an emergency, which belongs to the technical field of aircraft doors, the door mechanism comprising: an operating handle; an emergency rope connected to the operating handle, the other end of which is connected to a first gear set; a first gear set and a second gear set, the two gears of the first gear set being respectively arranged on the fuselage structure and the small door, and the two gears of the second gear set being respectively arranged on the actuator rocker arm and the door rocker arm; a door actuator for driving the door to open normally, which is connected to the actuator rocker arm, the door rocker arm is connected to the large door, and the large door and the small door are hinged; when the door is opened normally, the door actuator drives the actuator rocker arm, and then drives the door rocker arm to move through the second gear set, and finally drives the large door and the small door to rotate to a fully open position; when the door is released in an emergency, the operating handle is pulled, and the first gear set is pulled to rotate through the emergency rope, driving the small door and the large door to rotate to a fully open position.

Description

Technical Field

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

[0002] Currently, domestic aircraft landing gear doors primarily utilize a single-arm flip door mechanism, resulting in a relatively small door opening angle, typically no greater than 120°. However, with the special requirements of some aircraft—for example, when the aircraft's landing gear is lowered, the landing gear door structure must not touch the ground. This requires the door to open at a larger angle (at least greater than 150°). If designed as a flip door, the drive mechanism's lever arm would be too small, resulting in poor rigidity and difficult mechanism layout. In this case, a casement door mechanism, utilizing dual rockers to push the door to the side of the fuselage, would also suffer from a large door rotation angle, resulting in a small lever arm and difficult drive mechanism layout.

[0003] Prior art aircraft typically use a hydraulic motor (or electric motor), a torque transmission mechanism, and a speed reducer as the drive for wide-angle door mechanisms. This system has the advantage of a compact structure, allowing the door mechanism to rotate to any wide angle. However, it places extremely high demands on the reliability of the hydraulic motor (or electric motor), torque transmission mechanism, and speed reducer. A jam in any joint can cause the entire system to jam, preventing the door from opening. Furthermore, this system lacks the ability to mechanically lower the door in an emergency, preventing the landing gear from lowering, seriously impacting aircraft safety. Summary of the Invention

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

[0005] The technical solution of this application is: a casement door mechanism capable of mechanical emergency release, comprising:

[0006] operating handle;

[0007] an emergency rope connected to the operating handle, wherein the other end of the emergency rope is 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 provided on the fuselage structure and the small door, and the two gears of the second gear set are respectively provided 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 and the small door are hinged;

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

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

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

[0013] In an optional embodiment of the present application, the first gear group further 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 gear on the fuselage structure is larger than the size of the gear on the small cabin door.

[0016] In an optional embodiment 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 to 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 motor, torque transmission mechanism and reducer, and possible mechanism jamming failure, which leads to the door not being able to open and the landing gear not being able 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 solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this 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 casement door 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 not high, and the entire mechanism is very likely to fail, resulting in the door not being able to open and the landing gear not being able to be lowered, an application is made to provide a mechanical emergency flat 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 comprises a two-gear gear transmission structure, one of which is mounted on the small door 4 and the other 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 shaft of the fuselage structure gear. 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 a preferred embodiment of the present application, the ratio of the gear size of the former to the gear size of the latter is about 1.5 to 3, for example, a typical value may be 2.

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

[0032] In the present application, the gear on door rocker arm 8 is smaller than the gear on actuator rocker arm 7. This allows large-angle rotation of door rocker arm 8 to be converted into small-angle rotation of actuator rocker arm 7. This provides door actuator 6 with sufficient lever arm to drive both large door 5 and small door 4, facilitating actuation of door actuator 6. Furthermore, the gear ratio between the gear on actuator rocker arm 7 and the gear on door rocker arm 8 is approximately 1.5 to 3, with a typical value of 2 being possible, for example.

[0033] When the hatch door is normally retracted or extended, the hatch actuator 6 drives the gear on the actuator rocker arm 7 to rotate, which drives the hatch rocker arm 8 to rotate, and then drives the small hatch door 4 and the large hatch 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 hatch 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 hatch 4, the large hatch 5, and the hatch rocker arm 8 to the open position, completing the hatch emergency release operation.

[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 drive mechanism, this application applies the radius and angle conversion function of the gear set to the door mechanism, converting the large-angle rotation (greater than 150°) of the flat-pushing folding door into a small-angle rotation (less than 90°). At the same time, a rotation force arm is added, realizing the function of using a traditional hydraulic actuator to drive the large-angle rotation door mechanism. This solves the problem of low reliability of the motor, torque transmission mechanism and reducer, which may cause the mechanism to jam and fail, resulting in the door not opening and the landing gear not being able 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. 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 description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A casement door mechanism capable of mechanical emergency release, characterized in that: include: operating handle; an emergency rope connected to the operating handle, wherein the other end of the emergency rope is 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 provided on the fuselage structure and the small door, and the two gears of the second gear set are respectively provided 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 and the small door are hinged; When the hatch door is opened normally, the hatch door actuator drives the actuator rocker arm, and the actuator rocker arm drives the hatch door rocker arm to move through the second gear set, thereby driving the large hatch door and the small hatch door to rotate to the fully open position; When the hatch is released in an emergency, the operating handle is pulled, and the first gear set is rotated through the emergency rope, thereby driving the small hatch and the large hatch to rotate to the fully open position.

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

3. The mechanical emergency release flat-opening hatch mechanism according to claim 1, wherein: 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, wherein: 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 hatch to rotate.

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

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

7. The mechanical emergency release casement door mechanism according to claim 1, wherein: The gear on the actuator rocker arm is larger than the gear on the door rocker arm.

8. The mechanical emergency release casement door 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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