阅读说明：本技术 一种飞机舱盖的开闭机构、飞机舱机构及其开闭方法 (Opening and closing mechanism of aircraft cabin cover, aircraft cabin mechanism and opening and closing method of aircraft cabin cover ) 是由 牟钋 任杰 张健 程素华 杜晓文 冯熙 于 2021-08-25 设计创作，主要内容包括：本发明涉及了一种飞机舱盖的开闭机构、飞机舱机构及其开闭方法,所述飞机舱盖开闭机构,包括插销系统、推杆系统和收紧装置；所述插销系统包括弹性元件和插销,所述弹性元件套穿在所述插销上,所述插销包括第一端和第二端,所述弹性元件的一端与所述第一端固定连接；所述收紧装置包括收紧绳；所述推杆系统一端与所第一端连接,所述推杆系统的另一端与所述收紧绳连接；所述推杆系统用于所述收紧绳拉紧时给所述插销推力。将传统的收紧绳拉紧直接锁紧的方式改为了利用刚性的插销来实现舱盖的锁紧,插销的力臂可以减小收紧绳承受的拉力,拉紧的收紧绳发生长度变化时,插销不会受到影响,即使出现轻微转动,也不会造成舱盖与机体间出现阶差间隙,可实现良好的封闭效果。(The invention relates to an opening and closing mechanism of an aircraft cabin cover, an aircraft cabin mechanism and an opening and closing method thereof, wherein the opening and closing mechanism of the aircraft cabin cover comprises a bolt system, a push rod system and a tightening device; the bolt system comprises an elastic element and a bolt, the elastic element is sleeved on the bolt, the bolt comprises a first end and a second end, and one end of the elastic element is fixedly connected with the first end; the tightening device comprises a tightening rope; one end of the push rod system is connected with the first end, and the other end of the push rod system is connected with the tightening rope; the push rod system is used for pushing the bolt when the tightening rope is tightened. The mode of the traditional tightening rope for directly locking is changed into the mode of utilizing a rigid bolt to realize the locking of the hatch cover, the force arm of the bolt can reduce the tension born by the tightening rope, and when the length of the tightening rope changes, the bolt cannot be influenced, and even if slight rotation occurs, the step gap between the hatch cover and the machine body cannot be caused, so that a good sealing effect can be realized.)

1. The opening and closing mechanism of the aircraft hatch cover is characterized by comprising a bolt system (1), a push rod system (2) and a tightening device;

the bolt system (1) comprises an elastic element (11) and a bolt (12), wherein the elastic element (11) is sleeved on the bolt (12), the bolt (12) comprises a first end (121) and a second end (122), one end of the elastic element (11) is fixedly connected with the first end (121), the other end of the elastic element (11) is abutted to the aircraft cabin body (5), and the second end (122) is used for fastening the aircraft cabin cover (4);

the tightening device comprises a tightening rope (3);

one end of the push rod system (2) is connected with the first end (121), and the other end of the push rod system (2) is connected with the tightening rope (3);

when the tightening rope (3) is tightened, the push rod system (2) can push the second end (122) of the bolt (12) to fasten the aircraft hatch.

2. The opening and closing mechanism of an aircraft hatch according to claim 1, characterised in that the push rod system (2) comprises a push rod (21) and a connecting rod (22), one end of the push rod (21) being connected to the first end (121) in a pivot pin, the other end of the push rod (21) being provided with a tether hole (211), the tether hole (211) being intended for connection to the cinching cord (3); one end of the connecting rod (22) is connected with a middle rotating pin shaft of the pressure lever (21).

3. The opening and closing mechanism of an aircraft hatch according to claim 1 or 2, characterised in that a first shore (1211) and a second shore (1212) are fixedly connected to the first end (121) on each side.

4. Aircraft cabin structure comprising a cabin cover (4) and a cabin body (5), characterized in that it further comprises an opening and closing mechanism for an aircraft cabin cover according to any one of claims 1 to 3,

one end of the cabin cover (4) is connected with the cabin body (5) through an inserting lug (41), a first inserting pin hole (42) is formed in the other end of the cabin cover (4), a second inserting pin hole is formed in the cabin body (5), and the first inserting pin hole (42) is communicated with the second inserting pin hole;

wherein one end of the elastic element (11) close to the second end (122) is fixedly connected with the cabin body (5);

when the tightening rope (3) is tightened, downward tension is provided for the push rod system (2) so that the push rod system (2) is displaced to push the first end (121) and further compress the elastic element (11), and the bolt (12) is inserted into the second bolt hole and the first bolt hole (42) in sequence; when the tightening rope (3) releases the pulling force of the push rod system (2), the bolt (12) is sequentially withdrawn from the first bolt hole (42) and the second bolt hole (42).

5. The aircraft cabin mechanism of claim 4, wherein a first top pillar (1211) and a second top pillar (1212) are fixedly connected to both sides of the first end (121), respectively; a first guide support (52) and a second guide support (53) are respectively arranged on two sides of the elastic element (11), one end of the first guide support (52) is fixedly connected with the cabin body (5), a first sliding groove (521) is formed in the first guide support (52), and the first jacking column (1211) is arranged in the first sliding groove (521); simultaneously, the one end of second direction support (53) with cabin body (5) fixed connection, be provided with second spout (531) on second direction support (53), second fore-set (1212) is arranged in second spout (531).

6. The aircraft cabin mechanism according to claim 5, characterized in that the push rod system (2) comprises a press rod (21) and a connecting rod (22), one end of the press rod (21) is pin-jointed with the first end (121), the other end of the press rod (21) is provided with a rope tying hole (211), and the rope tying hole (211) is used for connecting with the tightening rope (3); one end of the connecting rod (22) is connected with the middle pin shaft of the pressure lever (21), and the other end of the connecting rod (22) is connected with the second guide support (53).

7. The aircraft cabin mechanism according to claim 4, further comprising a cutter (55) and a power source (56), the cinch cord (3) passing into the cutter (55), the power source (56) being for powering the cutter (55).

8. The aircraft cabin mechanism according to any one of claims 4 to 7, characterized in that, when the tightening rope (3) is tightened, the pin (12) is inserted into the second pin hole and the first pin hole (42) in sequence and exposed to the first pin hole (42).

9. A method of opening and closing an aircraft cabin mechanism according to any one of claims 4 to 8, comprising the steps of:

step 1, installing an opening and closing mechanism of an aircraft hatch;

step 2, when the hatch cover (4) in the initial state is in an open state, closing the hatch cover (4), tensioning the tightening rope (3), moving the pressure lever (21) and driving the bolt (12) to be sequentially inserted into the second bolt hole and the first bolt hole (42) to complete the closing of the hatch cover (4);

when the cabin cover (4) is in a closed state in an initial state, the acting force of the tightening rope (3) on the pressing rod (21) is relieved, and the pressing rod (21) drives the bolt (12) to sequentially withdraw from the first bolt hole (42) and the second bolt hole under the action of the elastic element (11), so that the cabin cover (4) is separated from the cabin body (5).

Technical Field

The invention relates to an opening and closing mechanism of an aircraft cabin cover, in particular to an opening and closing mechanism of an aircraft cabin cover, an aircraft cabin mechanism and an opening and closing method of the aircraft cabin cover.

Background

When some airplanes are used for throwing objects in the air or recovering umbrellas, the canopy, the air bag canopy and the like separated by aerodynamic force need to be sealed with the cabin body, the cabin cover of the airplane is directly tensioned by a traditional opening and closing mechanism by a one-time tightening rope, but the tightening rope has certain elongation rate under the influence of environment and load, so that step difference and gap are easily generated between the canopy and the airplane body, and the performances of the airplane, such as aerodynamics, stealth and the like, are influenced. Even under some extreme working conditions, the aircraft hatch cover can fall off under the action of pneumatic force, so that flight accidents are caused.

Disclosure of Invention

The invention aims to: aiming at the problem that in the prior art, when the aircraft cabin cover is directly tensioned by virtue of the tightening rope, the tightening rope has a certain elongation rate to cause step difference and gap between the cabin cover and the cabin body, the opening and closing mechanism of the aircraft cabin cover, the aircraft cabin mechanism and the opening and closing method thereof are provided.

In order to achieve the purpose, the invention adopts the technical scheme that:

an opening and closing mechanism of an aircraft hatch cover comprises a bolt system, a push rod system and a tightening device;

the bolt system comprises an elastic element and a bolt, the elastic element is sleeved on the bolt, the bolt comprises a first end and a second end, one end of the elastic element is fixedly connected with the first end, the other end of the elastic element is abutted to the cabin body of the airplane, and the second end is used for fastening the cabin cover of the airplane;

the tightening device comprises a tightening rope;

one end of the push rod system is connected with the first end, and the other end of the push rod system is connected with the tightening rope;

when the tightening rope is tightened, the push rod system can push the second end of the bolt to fasten the aircraft hatch cover.

The opening and closing mechanism of the aircraft hatch cover disclosed by the invention mainly comprises a bolt system, a push rod system and a tightening rope which are sequentially connected, and is simple in structure and strong in operability. When the cabin cover is used, the cabin body and the cabin cover are provided with bolt holes matched with the bolts, the tightening ropes are tightened, the push rod system pushes the bolts, the bolts can be automatically inserted into the bolt holes by utilizing the deformation effect of the elastic elements, so that the cabin cover and the cabin body are locked, and after the tightening ropes are disconnected, the bolts can be automatically popped out under the elastic effect of the elastic elements, so that the cabin body and the cabin cover are separated. This locking mechanism has changed the mode that traditional tightening rope tensioning direct locking into and has utilized the rigid bolt to realize the locking of hatch cover, and the arm of force of bolt can reduce the pulling force that the tightening rope bore, and when taut tightening rope took place length variation, the bolt can not receive the influence, even appear slightly rotating, can not cause the jump clearance to appear between hatch cover and organism yet, can realize good closed effect.

Further, the tightening rope is a cotton rope, a polyester rope or a nylon cotton rope.

Further, the push rod system comprises a pressure rod and a connecting rod, one end of the pressure rod is connected with the first end rotating pin shaft, the other end of the pressure rod is provided with a rope tying hole, and the rope tying hole is used for being connected with the tightening rope; one end of the connecting rod is connected with the middle rotating pin shaft of the pressure lever. When the cabin cover is used, the other end of the connecting rod is fixedly connected with the cabin body, the pressing rod is subjected to certain pulling force when the tightening rope is tightened, a rotating effect is formed between the pressing rod and the connecting rod, and the other end of the pressing rod provides a pushing force for the bolt, so that the bolt is inserted into the bolt hole, and the cabin cover and the cabin body are sealed.

Furthermore, both sides of the first end are fixedly connected with a first top column and a second top column respectively.

Another object of the present invention is to provide an aircraft cabin mechanism including the above-described aircraft cabin cover opening and closing mechanism.

An airplane cabin mechanism comprises a cabin cover, a cabin body and an opening and closing mechanism of the airplane cabin cover,

one end of the cabin cover is connected with the cabin body through an inserting lug, the other end of the cabin cover is provided with a first inserting pin hole, the cabin body is provided with a second inserting pin hole, and the first inserting pin hole is communicated with the second inserting pin hole;

wherein, one end of the elastic element close to the second end is fixedly connected with the cabin body;

when the tightening rope is tightened, downward tension is provided for the push rod system, so that the push rod system is displaced to push the first end to compress the elastic element, and the bolt is sequentially inserted into the second bolt hole and the first bolt hole; when the tightening rope releases tension to the push rod system, the bolt sequentially exits from the first bolt hole and the second bolt hole.

The aircraft cabin mechanism provided by the invention mainly comprises a cabin body, a cabin cover and the locking mechanism provided by the invention, wherein one end of the cabin cover is connected with the cabin body through an insert lug, the cabin body has a normal limiting effect on the insert lug, the insert lug cannot move upwards, and a step gap cannot occur at one end of the whole device in a locking state. The other end of the cabin cover is provided with a bolt hole, the cabin body is also provided with a bolt hole, the two bolt holes are communicated, and after the tightening rope is tightened, the bolt is automatically inserted into the two bolt holes, so that the cabin cover and the cabin body are sealed. Utilize the locking of rigid bolt to realize the hatch cover, the arm of force of bolt can reduce the pulling force that tightens up the rope and bear, and when taut tightening up the rope and taking place length variation, the bolt can not receive the influence, even appear slightly rotating, can not cause the jump clearance to appear between hatch cover and organism yet. The whole airplane cabin mechanism is simple in structure, strong in practicability and good in locking effect.

Further, the elastic element is a coil spring.

Furthermore, a first top column and a second top column are fixedly connected to two sides of the first end respectively; a first guide support and a second guide support are respectively arranged on two sides of the elastic element, one end of the first guide support is fixedly connected with the cabin body, a first sliding groove is formed in the first guide support, and the first support pillar is arranged in the first sliding groove; meanwhile, one end of the second guide support is fixedly connected with the cabin body, a second sliding groove is formed in the second guide support, and the second ejection column is arranged in the second sliding groove. The two top posts are matched with the corresponding sliding grooves, supporting force can be provided for the bolt, meanwhile, in the moving process of the bolt under the action of the elastic element, the sliding grooves provide a limited moving space for the bolt, the stability of the bolt is guaranteed, and the bolt can be accurately inserted into the bolt hole.

Further, the push rod system comprises a pressure lever and a connecting rod, one end of the pressure lever is connected with the first end pin shaft, the other end of the pressure lever is provided with a rope tying hole, and the rope tying hole is used for being connected with a tightening rope; one end of the connecting rod is connected with the middle pin shaft of the pressing rod, and the other end of the connecting rod is connected with the second guide support. The second guide support forms a connecting medium for the fixed connection of the connecting rod and the cabin body, and the whole system is simpler and more stable.

Furthermore, an outer barrel is sleeved outside the elastic element, one end of the outer barrel is fixedly connected with the cabin body, and the length of the outer barrel is smaller than the free length of the elastic element. On one hand, the outer cylinder is designed to provide support for the spring at the cabin end; and on the other hand, the spring is guided and limited, so that the spring is prevented from being excessively compressed.

Further, the bolt includes first bolt and second bolt, the diameter of first bolt is greater than the diameter of second bolt, first bolt with second bolt fixed connection, first bolt is used for the cover to establish elastic element, the second bolt is used for penetrating first bolt hole and second bolt hole.

Further, the cabin body is provided with a fixed seat, and the fixed seat is used for tensioning and fixing the tightening rope.

Further, the aircraft cabin mechanism further comprises a cutter and a power supply, the tightening rope penetrates into the cutter, and the power supply is used for supplying power to the cutter.

Furthermore, when the tightening rope is tightened, the bolts are sequentially inserted into the second bolt holes and the first bolt holes and are exposed out of the first bolt holes. The longer setting of bolt is when guaranteeing to tighten up the rope change greatly, also can give certain change space of bolt for the closure effect of cabin cover is stable more not influenced.

Another object of the present invention is to provide a method for opening and closing the aircraft cabin mechanism.

An opening and closing method of an airplane cabin mechanism is characterized by comprising the following steps:

step 1, installing an opening and closing mechanism of an aircraft hatch;

step 2, when the hatch cover is in an open state in the initial state, closing the hatch cover, tensioning the tightening rope, and driving the bolt to be sequentially inserted into the second bolt hole and the first bolt hole by the movement of the pressure lever to complete the closing of the hatch cover;

when the cabin cover is in a closed state in the initial state, the acting force of the tightening rope on the pressing rod is relieved, and the pressing rod drives the bolt to sequentially withdraw from the first bolt hole and the second bolt hole under the action of the elastic element, so that the cabin cover is separated from the cabin body.

The locking method of the airplane cabin mechanism provided by the invention is simple to operate, strong in structural stability, convenient to control and strong in adaptability.

Furthermore, the aircraft cabin mechanism is mainly used for a cabin of an aerial parabolic or recycling umbrella, the tightening rope is disposable, and the tightening rope is directly replaced when the aircraft is used next time.

Further, in step 1, one end of the elastic element is first fixedly connected to the cabin.

Further, in the step 1, a first top pillar is placed in the first sliding groove, and a second top pillar is placed in the second sliding groove.

Further, in the step 1, one end of the connecting rod is fixedly connected with the second guide support.

Further, in the step 1, the tightening rope is passed through the cutter and connected with the fixed seat.

In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:

1. the opening and closing mechanism of the aircraft hatch cover provided by the invention mainly comprises a bolt system, a push rod system and a tightening rope which are sequentially connected, and has a simple structure and strong operability. When the cabin cover is used, the cabin body and the cabin cover are provided with bolt holes matched with the bolts, the tightening ropes are tightened, the push rod system pushes the bolts, the bolts can be automatically inserted into the bolt holes by utilizing the deformation effect of the elastic elements, so that the cabin cover and the cabin body are locked, and the bolts can be automatically ejected out under the elastic effect of the elastic elements after the tightening ropes are disconnected. This locking mechanism has changed the mode that traditional tightening rope tensioning direct locking into and has utilized the rigid bolt to realize the locking of hatch cover, and the arm of force of bolt can reduce the pulling force that the tightening rope bore, and when taut tightening rope took place length variation, the bolt can not receive the influence, even appear slightly rotating, can not cause the jump clearance to appear between hatch cover and organism yet, can realize good closed effect.

2. The aircraft cabin mechanism mainly comprises a cabin body, a cabin cover and the opening and closing mechanism, wherein one end of the cabin cover is connected with the cabin body through an insert lug, the cabin body has a normal limiting effect on the insert lug, the insert lug cannot move upwards, a step gap cannot occur at one end of the whole device in a closed state, and the other end of the cabin cover is closed by the opening and closing mechanism provided by the invention.

3. The opening and closing method of the airplane cabin mechanism provided by the invention is simple to operate, strong in structural stability, convenient to control and strong in adaptability.

Drawings

FIG. 1 is a schematic view of the latch of the present invention.

Fig. 2 is a schematic structural view of an aircraft hatch cover opening and closing mechanism of the invention.

Fig. 3 is a schematic view of the hatch cover structure of the invention.

Fig. 4 is a schematic structural view of the airplane cabin mechanism of the invention.

Fig. 5 is a schematic structural view of a first guide support of the present invention.

Fig. 6 is a schematic view of a second guide support according to the present invention.

Icon: 1-a latch system; 11-a resilient element; 111-outer cylinder; 12-a bolt; 121-a first end; 1211-first top pillar; 1212-a second top pillar; 122-a second end; 123-a first bolt; 124-a second bolt; 2-a push rod system; 21-a pressure bar; 211-rope fastening holes; 22-a connecting rod; 3-tightening the rope; 4-a hatch cover; 41-inserting ears; 42-a first plug hole; 5-a cabin body; 52-first guide support; 521-a first chute; 53-a second guide support; 531-second runner; 54-a fixed seat; 55-a cutter; 56-Power supply.

Detailed Description

The present invention will be described in detail below with reference to the accompanying drawings.

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Example 1

As shown in fig. 1 and 2, an aircraft hatch opening and closing mechanism comprises a latch system 1, a push rod system 2 and a tightening rope 3; the tightening rope 3 is a silk rope meeting FZ66303 standard.

The bolt system 1 comprises an elastic element 11 and a bolt 12, wherein the elastic element 11 is sleeved on the bolt 12, the bolt 12 comprises a first end 121 and a second end 122, and one end of the elastic element 11 is fixedly connected with the first end 121; a first top pillar 1211 and a second top pillar 1212 are respectively fixedly connected to two sides of the first end 121, wherein the elastic element 11 is a coil spring.

The push rod system 2 comprises a pressure lever 21 and a connecting rod 22, one end of the pressure lever 21 is in pin connection with the first end 121, the other end of the pressure lever 21 is provided with a rope tying hole 211, and the rope tying hole 211 is used for being connected with the tightening rope 3; one end of the connecting rod 22 is connected with the middle pin shaft of the pressure lever 21. The push rod system 2 is used for pushing the bolt 12 when the tightening rope 3 is tightened.

This locking mechanism has changed the mode that traditional tightening rope tensioning direct locking into and has utilized the rigid bolt to realize the locking of hatch cover, and the arm of force of bolt can reduce the pulling force that the tightening rope bore, and when taut tightening rope took place length variation, the bolt can not receive the influence, even appear slightly rotating, can not cause the jump clearance to appear between hatch cover and organism yet, can realize good closed effect.

Example 2

As shown in fig. 3 and 4, embodiment 2 provides an aircraft cabin mechanism, which comprises a cabin cover 4 and a cabin body 5, and further comprises the aircraft cabin cover opening and closing mechanism of embodiment 1,

one end of the cabin cover 4 is connected with the cabin body 5 through an inserting lug 41, the other end of the cabin cover 4 is provided with a first inserting pin hole 42, the cabin body 5 is provided with a second inserting pin hole, and the first inserting pin hole 42 is communicated with the second inserting pin hole;

wherein, one end of the elastic element 11 close to the second end 122 is fixedly connected with the cabin 5; a first guide support 52 and a second guide support 53 are respectively arranged on two sides of the elastic element 11, as shown in fig. 5, one end of the first guide support 52 is fixedly connected with the cabin 5, a first sliding groove 521 is arranged on the first guide support 52, and the first top post 1211 is arranged in the first sliding groove 521; meanwhile, as shown in fig. 6, one end of the second guide support 53 is fixedly connected to the cabin 5, a second sliding groove 531 is disposed on the second guide support 53, and the second top post 1212 is disposed in the second sliding groove 531. The outer sleeve of elastic element 11 is equipped with urceolus 111, the one end and the cabin body 5 fixed connection of urceolus 111, the length of urceolus 111 is less than elastic element 11's recovery length. The bolt 12 comprises a first bolt 123 and a second bolt 124, the diameter of the first bolt 123 is larger than that of the second bolt 124, the first bolt 123 is fixedly connected with the second bolt 124, the first bolt 123 is used for sleeving the elastic element 11, and the second bolt 124 is used for penetrating the first bolt hole 42 and the second bolt hole.

The push rod system 2 comprises a pressure lever 21 and a connecting rod 22, one end of the pressure lever 21 is connected with the first end 121 through a rotary pin shaft, the other end of the pressure lever 21 is provided with a rope tying hole 211, and the rope tying hole 211 is used for being connected with a tightening rope 3; one end of the connecting rod 22 is connected with the middle rotating pin shaft of the pressure lever 21, and the other end of the connecting rod 22 is connected with the second guide support 53.

When the tightening rope 3 is tightened, the push rod system 2 pushes the first end 121 to compress the elastic element 11, so that the bolt 12 is inserted into the second bolt hole and the first bolt hole 42 in sequence; the tightening rope 3 is disconnected, and the latch 12 sequentially exits from the first latch hole and the second latch hole 42 under the restoring force of the elastic element 11.

Preferably, the cabin 5 is provided with a fixing seat 54, and the fixing seat 54 is used for tightening and fixing the tightening rope 3.

Preferably, the aircraft cabin mechanism further comprises a cutter 55 and a power source 56, the cinch cord 3 passing through the cutter 55, the power source 56 for powering the cutter 55.

Preferably, when the tightening rope 3 is tightened, the plug 12 is inserted into the second plug hole and the first plug hole 42 in sequence and exposed out of the first plug hole 42.

The aircraft cabin mechanism mainly comprises a cabin body, a cabin cover and the opening and closing mechanism, wherein one end of the cabin cover is connected with the cabin body through an insert lug, the cabin body has a normal limiting effect on the insert lug, the insert lug cannot move upwards, a step gap cannot occur at one end of the whole device in a closed state, and the other end of the cabin cover is closed by the opening and closing mechanism provided by the invention.

Example 3

Embodiment 3 provides the opening and closing method of the aircraft cabin mechanism of embodiment 2, comprising the steps of:

step 1, installing an aircraft hatch cover opening and closing mechanism: first, one end of the elastic element 11 is fixedly connected with the cabin 5, the first top pillar 1211 and the second top pillar 1212 are respectively disposed in the first sliding slot 521 and the second sliding slot 531, then, one end of the connecting rod 22 is fixedly connected with the second guiding support 53, and the tightening rope 3 passes through the cutter 55 and is connected with the fixed seat 54.

Step 2, when the hatch cover 4 is in an open state in the initial state, closing the hatch cover 4, tensioning the tightening rope 3, moving the pressure lever 21 and driving the bolt 12 to be sequentially inserted into the second bolt hole and the first bolt hole 42 to complete the closing of the hatch cover 4;

when the hatch cover 4 is in a closed state in the initial state, the acting force of the tightening rope 3 on the pressing rod 21 is released, and the pressing rod 21 drives the bolt 12 to sequentially withdraw from the first bolt hole 42 and the second bolt hole under the action of the elastic element 11, so that the hatch cover 4 is separated from the cabin body 5.

The opening and closing method of the airplane cabin mechanism provided by the invention is simple to operate, strong in structural stability, convenient to control and strong in adaptability.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.