Aircraft cabin door lifting assist mechanism

Abstract

The present invention provides an aircraft cabin door lifting assist mechanism, which belongs to the field of civil aircraft cabin door mechanisms, and specifically is a cabin door lifting assist mechanism applied to civil aircraft cabin doors, which can provide staged precise assist at a certain stage during the cabin door lifting process. A power assist roller is fixedly connected to the cabin door structure, a rocker arm is hingedly connected to the cabin door structure, a transmission roller is fixedly connected to the rocker arm, a fork is hingedly connected to the fuselage door frame structure, a slide groove and a power assist arm are designed on the fork, and a spring assembly is connected below. After the rocker arm rotates, it drives the transmission roller to enter the slide groove and drives the fork to rotate. After the fork rotates a certain angle, the power assist arm contacts the power assist roller, and the spring force of the spring assembly provides assist for the cabin door lifting. The present invention has the advantages of segmented precise assist, small space occupation, high assist efficiency, etc., and can achieve smooth control of the handle force during the cabin door lifting process.

Description

Technical Field

[0001] The present invention belongs to the field of civil aircraft cabin door mechanisms, and relates to an aircraft cabin door lifting assist mechanism, and in particular to a mechanism applied to a civil aircraft cabin door and capable of providing assist during the cabin door lifting stage. Background Art

[0002] Semi-blocked doors have high reliability and safety, and are the most commonly used door type on current civil aircraft. The opening process of a semi-blocked door is divided into two steps: lifting upward and opening outward. The lifting process of the door requires overcoming the gravity of the door, and the lifting movement is achieved by operating the door handle. In order to ensure operability, the handle operating force during the door lifting process should be controlled within a certain range, and the handle force during the entire lifting process should be as stable as possible without major mutations. In order to reduce the handle operating force during the door lifting process, it is necessary to design a door lifting assist mechanism. The lifting assist mechanism is mostly in the form of a spring. The spring is installed in the door assembly and is directly connected to the door mechanism. It moves throughout the entire process of the door mechanism movement. The assist efficiency is low, and it is impossible to provide separate assist for a certain high handle force range. Therefore, it is difficult to control the door handle force to meet design expectations. Summary of the Invention

[0003] The present invention provides an aircraft cabin door lifting assist mechanism, which can provide phased and precise assist at a certain stage in the cabin door lifting process without affecting the handle force at other movement stages, thereby reducing the range of sudden changes in the handle force during the cabin door lifting process and achieving smooth control of the handle force during the cabin door lifting process.

[0004] In order to solve the above problems, the specific technical solutions adopted by the present invention are as follows:

[0005] An aircraft door lifting assist mechanism includes a rocker arm 1, a transmission roller 2, a fork 3, a crank 4, a compression spring assembly 5, a front stop pin 8, a rear stop pin 9, a support 10 and an assist roller 13.

[0006] One end of the rocker arm 1 is hingedly connected to the side of the door structure 7 facing the fuselage door frame structure 6, and the other end of the rocker arm 1 is fixedly connected to the transmission roller 2; the power-assisting roller 13 is fixedly connected to the same side of the door structure 7, and is located below the rocker arm 1.

[0007] The fork-shaped member 3 is hingedly connected to the side of the fuselage door frame structure 6 facing the cabin door structure 7. The fork-shaped member 3 is located next to the power-assisting roller 13. A U-shaped slide groove 11 is provided at the upper end of the fork-shaped member 3, and a power-assisting arm 12 is provided on the side of the lower end close to the power-assisting roller 13. After the rocker arm 1 rotates to a certain angle, the transmission roller 2 at its end enters the slide groove 11 and drives the fork-shaped member 3 to rotate; the crank 4 is located between the fork-shaped member 3 and the fuselage door frame structure 6, and its upper end is fixedly connected to the middle of the fork-shaped member 3, and its lower end is hingedly connected to the upper end of the compression spring assembly 5. The compression spring The lower end of the component 5 is hingedly connected to the support 10, and the support 10 is fixedly connected to the fuselage door frame structure 6. The hinge position of the compression spring component 5 and the support 10 is located below between the fork 3 and the power-assisting roller 13; after the rocker arm 1 drives the fork 3 to rotate a certain angle, the power-assisting arm 12 contacts the lower end of the power-assisting roller 13. Under the spring force of the compression spring component 5, the power-assisting arm 12 pushes the power-assisting roller 13 to assist in lifting the cabin door. By changing the relative position of the power-assisting arm 12 and the power-assisting roller 13, the contact timing between the two is set, thereby limiting the position where the power assist starts.

[0008] The front stop pin 8 and rear stop pin 9 are each fixedly connected to the fuselage door frame structure 6, located on either side of the crank 4, with the front stop pin 8 positioned near the power-assist roller 13. The two stop pins cooperate with the crank 4 to limit the rotational range of the crank 4 and fork 3, with the front stop pin 8 not interfering with the power-assist arm 12. When the door is closed, the compression spring assembly 5 uses spring force to press the crank 4 against the rear stop pin 9. When the door is lifted, the compression spring assembly 5 uses spring force to press the crank 4 against the front stop pin 8. By varying the relative positions of the front stop pin 8 and crank 4, the timing of their contact is set, thereby defining the position at which power assistance ends.

[0009] The working process of the power assist mechanism is as follows: the lifting process of the semi-blocked door includes multiple stages such as unlatching, unlocking, and up and down movement; the door is in the closed position, and the compression spring assembly 5 presses the crank 4 onto the rear stop pin 9 through the spring force; in the initial stage of the lifting process, the door handle rotates to drive the internal mechanism of the door to move, completing internal operations such as unlatching and unlocking, but the position of the door relative to the fuselage door frame remains unchanged, that is, the position of the door structure 7 relative to the fuselage door frame structure 6 remains unchanged, at this time, the position of the fork 3 remains unchanged; the operating handle starts the door lifting process, and the door handle directly Or indirectly drive the rocker arm 1 to rotate in the direction away from the power-assisting roller 13, the rocker arm 1 drives the transmission roller 2 to enter the inside of the slide groove 11, and rotates until it contacts the inner surface of the slide groove 11; drive the rocker arm 1 to rotate further, the transmission roller 2 drives the fork 3 to rotate, and the fork 3 drives the crank 4 fixedly connected to it to rotate, so that the crank 4 is away from the rear stop pin 9, and the spring of the compression spring assembly 5 is further compressed under the rotation of the crank 4; further rotate the rocker arm 1, and the angle between the compression spring assembly 5 and the crank 4 gradually increases to 180°. After exceeding 180°, the power-assisting mechanism passes the center , the spring force of the compressed spring assembly 5 changes the rotation direction of the driving crank 4; driven by the spring force, the inner surface of the groove 11 is pressed against the driving roller 2, and the rocker arm 1 continues to rotate until the power-assisting arm 12 contacts the power-assisting roller 13, and the rocker arm 1 continues to rotate, so that the driving roller 2 moves away from the groove 11, and the spring force of the spring assembly 5 is directly transmitted to the power-assisting roller 13 through the power-assisting arm 12 of the fork-shaped member 3. Because the power-assisting roller 13 is fixedly connected to the door structure 7, the spring force at this time acts as an external force, directly giving the door an upward assist. By changing the power-assisting arm 12 The relative position of the power-assist roller 13 is adjusted to set the contact timing between the two, thereby limiting the position where the power-assist starts. During this process, the power-assist arm 12 is always close to the power-assist roller 13 under the action of the spring force, helping the hatch door to lift and move until the crank 4 contacts the front stop pin 8, so that the crank 4 and the fork 3 no longer rotate further. The spring force presses the crank 4 against the front stop pin 8, and the power-assist arm 12 moves away from the power-assist roller 13, and no longer provides power-assist for the hatch structure 7. By adjusting the relative position of the front stop pin 8 and the crank 4, the contact timing between the two is set, thereby limiting the position where the power-assist ends.

[0010] The beneficial effects of the present invention are:

[0011] 1. It can achieve segmented and precise power assistance. The power-assisting roller and the power-assisting arm only come into contact during a certain stage of movement. This design can achieve segmented and precise power assistance during the door lifting process, effectively solving the problem of sudden changes in handle force during a certain stage of the door lifting process and improving the stability of the handle force.

[0012] 2. It does not occupy the interior space of the door. The main mechanism of the present invention is installed on the fuselage door frame structure, which does not occupy the interior space of the door. For small doors with limited space and compact layout, the present invention has a significant space advantage.

[0013] 3. Provides direct assistance and high efficiency. Traditional door assist mechanisms are mounted on the door and provide assistance through internal force, resulting in low efficiency. The spring structure of the present invention is mounted on the fuselage door frame structure and provides assistance by applying a direct external force to the door, resulting in high efficiency and a more pronounced effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is an axonometric view of the power assist mechanism of the present invention.

[0015] Figure 2 It is a front view of the power assist mechanism of the present invention.

[0016] Figure 3 This is a schematic diagram of the power assisting process of the power assisting mechanism of the present invention.

[0017] Figure 4 This is a schematic diagram of the movement position of the power assist mechanism of the present invention after the door lifting movement is completed.

[0018] In the figure: 1 rocker arm; 2 transmission roller; 3 fork; 4 crank; 5 compression spring assembly; 6 fuselage door frame structure; 7 cabin door structure; 8 front stop pin; 9 rear stop pin; 10 support; 11 slide; 12 power arm; 13 power roller. DETAILED DESCRIPTION

[0019] The following is a clear and complete description of the technical solution of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments improved or adjusted by ordinary technicians in this field fall within the scope of protection of the present invention.

[0020] like Figures 1 to 4 As shown, an aircraft door lifting assist mechanism includes a rocker arm 1, a transmission roller 2, a fork 3, a crank 4, a compression spring assembly 5, a front stop pin 8, a rear stop pin 9, a support 10 and an assist roller 13.

[0021] One end of the rocker arm 1 is hingedly connected to the side of the door structure 7 facing the fuselage door frame structure 6, and the other end of the rocker arm 1 is fixedly connected to the transmission roller 2; the power-assisting roller 13 is fixedly connected to the same side of the door structure 7, and is located below the rocker arm 1.

[0022] The fork-shaped member 3 is hingedly connected to the side of the fuselage door frame structure 6 facing the cabin door structure 7. The fork-shaped member 3 is located next to the power-assisting roller 13. A U-shaped slide groove 11 is provided at the upper end of the fork-shaped member 3, and a power-assisting arm 12 is provided on the side of the lower end close to the power-assisting roller 13. After the rocker arm 1 rotates to a certain angle, the transmission roller 2 at its end enters the slide groove 11 and drives the fork-shaped member 3 to rotate; the crank 4 is located between the fork-shaped member 3 and the fuselage door frame structure 6, and its upper end is fixedly connected to the middle of the fork-shaped member 3, and its lower end is hingedly connected to the upper end of the compression spring assembly 5. The compression spring The lower end of the component 5 is hingedly connected to the support 10, and the support 10 is fixedly connected to the fuselage door frame structure 6. The hinge position of the compression spring component 5 and the support 10 is located below between the fork 3 and the power-assisting roller 13; after the rocker arm 1 drives the fork 3 to rotate a certain angle, the power-assisting arm 12 contacts the lower end of the power-assisting roller 13. Under the spring force of the compression spring component 5, the power-assisting arm 12 pushes the power-assisting roller 13 to assist in lifting the cabin door. By changing the relative position of the power-assisting arm 12 and the power-assisting roller 13, the contact timing between the two is set, thereby limiting the position where the power assist starts.

[0023] The front stop pin 8 and rear stop pin 9 are each fixedly connected to the fuselage door frame structure 6, located on either side of the crank 4, with the front stop pin 8 positioned near the power-assist roller 13. The two stop pins cooperate with the crank 4 to limit the rotational range of the crank 4 and fork 3, with the front stop pin 8 not interfering with the power-assist arm 12. When the door is closed, the compression spring assembly 5 uses spring force to press the crank 4 against the rear stop pin 9. When the door is lifted, the compression spring assembly 5 uses spring force to press the crank 4 against the front stop pin 8. By varying the relative positions of the front stop pin 8 and crank 4, the timing of their contact is set, thereby defining the position at which power assistance ends.

[0024] The working process of the power assist mechanism is as follows: the lifting process of the semi-blocked door includes multiple stages such as unlatching, unlocking, and up and down movement; the door is in the closed position, and the compression spring assembly 5 presses the crank 4 onto the rear stop pin 9 through the spring force; in the initial stage of the lifting process, the door handle rotates to drive the internal mechanism of the door to move, completing internal operations such as unlatching and unlocking, but the position of the door relative to the fuselage door frame remains unchanged, that is, the position of the door structure 7 relative to the fuselage door frame structure 6 remains unchanged, at this time, the position of the fork 3 remains unchanged; the operating handle starts the door lifting process, and the door handle directly Or indirectly drive the rocker arm 1 to rotate in the direction away from the power-assisting roller 13, the rocker arm 1 drives the transmission roller 2 to enter the inside of the slide groove 11, and rotates until it contacts the inner surface of the slide groove 11; drive the rocker arm 1 to rotate further, the transmission roller 2 drives the fork 3 to rotate, and the fork 3 drives the crank 4 fixedly connected to it to rotate, so that the crank 4 is away from the rear stop pin 9, and the spring of the compression spring assembly 5 is further compressed under the rotation of the crank 4; further rotate the rocker arm 1, and the angle between the compression spring assembly 5 and the crank 4 gradually increases to 180°. After exceeding 180°, the power-assisting mechanism passes the center , the spring force of the compressed spring assembly 5 changes the rotation direction of the driving crank 4; driven by the spring force, the inner surface of the groove 11 is pressed against the driving roller 2, and the rocker arm 1 continues to rotate until the power-assisting arm 12 contacts the power-assisting roller 13, and the rocker arm 1 continues to rotate, so that the driving roller 2 moves away from the groove 11, and the spring force of the spring assembly 5 is directly transmitted to the power-assisting roller 13 through the power-assisting arm 12 of the fork-shaped member 3. Because the power-assisting roller 13 is fixedly connected to the door structure 7, the spring force at this time acts as an external force, directly giving the door an upward assist. By changing the power-assisting arm 12 The relative position of the power-assist roller 13 is adjusted to set the contact timing between the two, thereby limiting the position where the power-assist starts. During this process, the power-assist arm 12 is always close to the power-assist roller 13 under the action of the spring force, helping the hatch door to lift and move until the crank 4 contacts the front stop pin 8, so that the crank 4 and the fork 3 no longer rotate further. The spring force presses the crank 4 against the front stop pin 8, and the power-assist arm 12 moves away from the power-assist roller 13, and no longer provides power-assist for the hatch structure 7. By adjusting the relative position of the front stop pin 8 and the crank 4, the contact timing between the two is set, thereby limiting the position where the power-assist ends.

[0025] The above-described embodiments merely express the implementation methods of the present invention, but should not be understood as limiting the scope of the patent of the present invention. It should be pointed out that for those skilled in the art, several variations and improvements can be made without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention.

Claims

1. An aircraft door lifting assist mechanism, characterized in that: The power-assisting mechanism comprises a rocker arm (1), a transmission roller (2), a fork (3), a crank (4), a compression spring assembly (5), a front stop pin (8), a rear stop pin (9), a support (10) and a power-assisting roller (13); One end of the rocker arm (1) is hingedly connected to the side of the door structure (7) facing the fuselage door frame structure (6), and the other end of the rocker arm (1) is fixedly connected to the transmission roller (2); the power-assisting roller (13) is fixedly connected to the same side of the door structure (7) and is located below the rocker arm (1); The fork-shaped member (3) is hingedly connected to the side of the fuselage door frame structure (6) facing the cabin door structure (7). The fork-shaped member (3) is located next to the power-assisting roller (13). The upper end of the fork-shaped member (3) is provided with a U-shaped slide groove (11), and the side of the lower end close to the power-assisting roller (13) is provided with a power-assisting arm (12). After the rocker arm (1) rotates to a certain angle, the transmission roller (2) at its end enters the slide groove (11) and drives the fork-shaped member (3) to rotate; the upper end of the crank (4) is fixedly connected to the middle of the fork-shaped member (3), and the lower end is connected to the compression spring assembly. (5) The upper end is hingedly connected, the lower end of the compression spring assembly (5) is hingedly connected to the support (10), the support (10) is fixedly connected to the fuselage door frame structure (6), and the hinge position of the compression spring assembly (5) and the support (10) is located below between the fork-shaped member (3) and the power-assisting roller (13); after the rocker arm (1) drives the fork-shaped member (3) to rotate a certain angle, the power-assisting arm (12) contacts the lower end of the power-assisting roller (13), and under the spring force of the compression spring assembly (5), the power-assisting arm (12) pushes the power-assisting roller (13) to assist the cabin door to be lifted; The front stop pin (8) and the rear stop pin (9) are respectively fixedly connected to the fuselage door frame structure (6). The two are respectively located on both sides of the crank (4), and the front stop pin (8) is located on the side close to the power-assisting roller (13). The two stop pins are respectively matched with the crank (4) to limit the rotation range of the crank (4) and the fork-shaped member (3), wherein the front stop pin (8) does not interfere with the power-assisting arm (12).

2. The aircraft door lifting assist mechanism according to claim 1, characterized in that: By changing the relative position of the power-assisting arm (12) and the power-assisting roller (13), the position where the power-assisting starts is defined.

3. The aircraft door lifting assist mechanism according to claim 1, characterized in that: The position where the power assist ends is defined by changing the relative position of the front stop pin (8) and the crank (4).

4. The aircraft door lifting assist mechanism according to claim 1, characterized in that: The crank (4) is located between the fork (3) and the fuselage door frame structure (6).

5. The aircraft door lifting assist mechanism according to claim 1, characterized in that: The working process of the power assist mechanism is as follows: the door is in the closed position, and the compression spring assembly (5) presses the crank (4) against the rear stop pin (9) by the spring force; in the initial stage of the lifting process, the door handle is rotated to complete the unlocking operation, and the position of the fork (3) remains unchanged; the door lifting process begins, and the door handle drives the rocker arm (1) to rotate in a direction away from the power assist roller (13), and the rocker arm (1) drives the transmission roller (2) to enter the inside of the slide groove (11) and rotate until it contacts the inner surface of the slide groove (11); the rocker arm (1) is driven to rotate further, and the transmission roller (2) drives the fork (3) to rotate, and the fork (3) drives the crank (4) to rotate, so that the crank (4) is away from the rear stop pin (9), and the compression spring assembly (5) is further compressed; the rocker arm (1) is further rotated, the power assist mechanism passes the center, and the compression spring assembly (5) The spring force changes the rotation direction of the driving crank (4); driven by the spring force, the inner surface of the groove of the slide groove (11) is pressed against the driving roller (2), and the rocker arm (1) continues to rotate until the power-assisting arm (12) contacts the power-assisting roller (13). The rocker arm (1) continues to rotate, causing the driving roller (2) to move away from the slide groove (11). The spring force of the spring assembly 5 is directly transmitted to the power-assisting roller (13) through the power-assisting arm (12) of the fork-shaped member (3), giving the cabin door an upward power assist. During this process, the power-assisting arm (12) is always in close contact with the power-assisting roller (13) until the crank (4) contacts the front stop pin (8), so that the crank (4) and the fork-shaped member (3) no longer rotate further. The spring force presses the crank (4) against the front stop pin (8), and the power-assisting arm (12) moves away from the power-assisting roller (13), and no longer provides power assist for the cabin door structure (7).

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