CN117682061A - Concave landing gear cabin door structure and opening method - Google Patents
Concave landing gear cabin door structure and opening method Download PDFInfo
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- CN117682061A CN117682061A CN202311572381.6A CN202311572381A CN117682061A CN 117682061 A CN117682061 A CN 117682061A CN 202311572381 A CN202311572381 A CN 202311572381A CN 117682061 A CN117682061 A CN 117682061A
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000007246 mechanism Effects 0.000 claims abstract description 27
- 239000002360 explosive Substances 0.000 claims abstract description 19
- 230000000977 initiatory effect Effects 0.000 claims abstract description 19
- 229910000639 Spring steel Inorganic materials 0.000 claims description 9
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 238000004880 explosion Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 6
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005422 blasting Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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Abstract
The invention belongs to the technical field of aircraft cabin door structures, and relates to a concave landing gear cabin door structure and an opening method. The concave landing gear cabin door structure is arranged on the cabin body (7) and comprises a left cabin door (6), a right cabin door (9), 2 upper unfolding mechanisms, 2 lower unfolding mechanisms, 4 upper locking initiating explosive devices (5) and 2 spring pin lower locks (1); the hydraulic cabin door is used as a driving force for cabin door unfolding, replaces the traditional cabin door hydraulic driving mode, and is simple in structure and saves installation space. The unfolding of the concave cabin door is realized by using the translation-rotation type sliding rail, and in the unfolding process, the cabin door firstly translates downwards and then rotates, so that the problems of small installation space, interference and the like are solved. The invention has the function of realizing the unfolding of the concave cabin door in the cabin in a narrow space and ensuring the stable and reliable movement process without interference.
Description
Technical Field
The invention belongs to the technical field of aircraft cabin door structures, and relates to a concave landing gear cabin door structure and an opening method.
Background
Hypersonic aircrafts are currently put into use in various countries in the world, and amorphous products are still available. The reentry type hypersonic aircraft such as a space shuttle is usually in an outer convex shape, the space of a landing gear cabin is large, interference is not easy to occur, and the cabin door is driven to be closed and opened by a hydraulic actuating system in the process of taking off and landing. Some hypersonic aircraft cabin doors adopt a form of blasting and throwing off a initiating explosive device, so that the cabin doors have a throwing-off safety risk, and a new cabin door needs to be configured when the aircraft is started again, and the requirement of reusability cannot be met. The prior art can not meet the design requirement of the concave cabin door structure of the hypersonic aircraft at present.
Because of the air inlet requirement of the scramjet engine, the compression surface of the air inlet channel of the hypersonic aircraft needs to be designed into a concave shape. The nose landing gear door is typically positioned adjacent the compression surface and the concave profile results in a small nose landing gear compartment space, which presents difficulties in the deployment of the door structure and its drive. The concave profile structure is more prone to interference during deployment than the convex profile structure, which also presents a difficulty in door structural design.
Disclosure of Invention
The purpose of the invention is that: in order to solve the problems, the invention designs the concave cabin door structure to solve the problems of small installation space and easy interference of the structure. The hydraulic actuating system in the traditional cabin door structure is omitted, the installation space is saved, the reliability is high, the cabin door structure can be reused, and the design requirement of the hypersonic aircraft concave cabin door structure is met.
The technical scheme of the invention is as follows: the inner concave landing gear cabin door structure is arranged on a cabin body 7 and comprises a left cabin door 6, a right cabin door 9, 2 upper unfolding mechanisms, 2 lower unfolding mechanisms, 4 upper locking initiating explosive devices 5 and 2 spring pin lower locks 1; the left cabin door 6 and the right cabin door 9 are symmetrically arranged, the 2 upper unfolding mechanisms are respectively arranged at the front ends of the left cabin door 6 and the right cabin door 9 in the forward direction of the aircraft and are connected with the corresponding positions of the cabin body 7, and the 2 lower unfolding mechanisms are respectively arranged at the rear ends of the left cabin door 6 and the right cabin door 9 in the forward direction of the aircraft and are connected with the corresponding positions of the cabin body 7; one end of an upper lock initiating explosive device 5 is connected with the cabin body 7, the other end is connected with the front end and the rear end of the left cabin door 6 and the right cabin door 7 in the forward direction of the airplane, the spring pin lower lock 1 is arranged at the front end of the upper unfolding mechanism, the lower part of the crank rocker A2, and the left cabin door 6 and the right cabin door 9 are of a concave cabin door structure.
The concave cabin door structure is an arc-shaped structure with the angle of 140-160 degrees at the middle part of the cabin door.
The upper unfolding mechanism comprises a crank rocker A2, a slide rail support 3 and a torsion spring 4; one end of the crank rocker A2 is arranged in a sliding rail of the sliding rail support 3, the other end of the crank rocker A2 is arranged on the concave cabin door, and the torsion spring 4 is sleeved on the sliding rail support 3.
One end of the crank rocker A2 is a plane with the bottom surface and is fixedly connected with the concave cabin door; the other end is provided with arc sliding pins at two sides, and the sliding pins are inserted into the sliding rail of the sliding rail support 3.
The lower unfolding mechanism comprises a sliding rail support 3, a torsion spring 4 and a crank rocker B8; one end of a crank rocker B8 is arranged in a sliding rail of the sliding rail support 3, the other end of the crank rocker B8 is arranged on the concave cabin door, and a torsion spring 4 is sleeved on the sliding rail support 3.
One end of the crank rocker B8 is a plane with the bottom surface and is fixedly connected with the concave cabin door; the other end is provided with arc sliding pins at two sides, and a boss is arranged on the arc surface at the lower end for limiting the unfolding angle of the cabin door.
The distance between the spring pin lower lock 1 and the slide rail support 3 of the upper unfolding mechanism is 2-3cm.
The shape of the upper half part of the sliding rail support 3 is matched with the sliding pin of the crank rocker, the lower half part of the sliding rail is round, and a groove is formed in the lower left side.
The diameter of the spring steel wire of the torsion spring 4 is 3mm-5mm, the pitch is 6mm-10mm, the diameter of the main shaft is 20mm-28mm, the torsion angle is more than 90 degrees, and the material is spring steel.
The spring pin lower lock 1 consists of a spring and a positioning pin; the spring is installed on the locating pin, and the locating pin is wedge structure.
The spring pin lower lock 1 is characterized in that the diameter of a steel wire of a spring is 1.5mm-3mm, the pitch of the steel wire is 5mm-8mm, the diameter of a main shaft is 14mm-20mm, and the length of the main shaft is 35mm-45mm, and the steel wire is made of spring steel.
According to the method for opening the concave landing gear cabin door structure, when the cabin door is closed, the left cabin door 6 and the right cabin door 9 are fixedly connected with the cabin body 7 through the upper locking initiating explosive device 5, so that the locking is ensured to keep a closed state in a closed state; when the cabin door is opened, the upper locking initiating explosive device 5 is detonated, the left cabin door 6 and the right cabin door 9 are disconnected with the cabin body, and meanwhile, the impact force of the explosion of the upper locking initiating explosive device 5 gives the left cabin door 6 and the right cabin door 9 a downward initial speed, so that the cabin door can move on the sliding rail; the cabin door can rotate after being translated to the round slide rail at the lower half part of the slide rail by the slide rail and the sliding pin structure in the movement process of the upper half part of the slide rail, the cabin door is rotated and unfolded by taking the torsion spring 4 as a driving force, the boss of the arc-shaped sliding pin of the crank rocker B8 is matched with the groove on the slide rail of the slide rail support 3 to limit, and the cabin door is locked by the spring pin lower lock 1 after being unfolded in place.
The invention has the following effects: the hydraulic cabin door is used as a driving force for cabin door unfolding, replaces the traditional cabin door hydraulic driving mode, and is simple in structure and saves installation space. The unfolding of the concave cabin door is realized by using the translation-rotation type sliding rail, and in the unfolding process, the cabin door firstly translates downwards and then rotates, so that the problems of small installation space, interference and the like are solved. The invention has the function of realizing the unfolding of the concave cabin door in the cabin in a narrow space and ensuring the stable and reliable movement process without interference.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is an enlarged view of portion A of FIG. 1;
FIG. 3 is an enlarged view of part B of FIG. 1;
fig. 4 is a schematic structural diagram of crank rocker A2 and crank rocker B8;
fig. 5 is a schematic structural view of the slide rail support 3;
fig. 6 is a schematic view of the concave cabin door body 6 (with crank rocker A2 and crank rocker B8 installed);
FIG. 7 is a schematic view of the door assembly (closed) mounted to the cabin assembly;
FIG. 8 is a schematic view of the translational movement of the door assembly over the hatch body assembly;
FIG. 9 is a schematic view of the rotational movement of the door assembly on the hatch body assembly;
FIG. 10 is a schematic view of the door assembly deployed in position on the cabin assembly;
wherein: the lower lock of the 1-spring pin, the 2-crank rocker A, the 3-slide rail support, the 4-torsion spring, the initiating explosive device of the 5-upper lock, the 6-left cabin door, the 7-cabin body, the 8-crank rocker B and the 9-right cabin door.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
as shown in fig. 1, 2 and 3, the concave landing gear cabin door structure is mounted on a cabin body 7 and comprises a left cabin door 6, a right cabin door 9, 2 upper unfolding mechanisms, 2 lower unfolding mechanisms, 4 upper locking initiating explosive devices 5 and 2 spring pin lower locks 1; the left cabin door 6 and the right cabin door 9 are symmetrically arranged, the 2 upper unfolding mechanisms are respectively arranged at the front ends of the left cabin door 6 and the right cabin door 9 in the forward direction of the aircraft and are connected with the corresponding positions of the cabin body 7, and the 2 lower unfolding mechanisms are respectively arranged at the rear ends of the left cabin door 6 and the right cabin door 9 in the forward direction of the aircraft and are connected with the corresponding positions of the cabin body 7; one end of an upper lock initiating explosive device 5 is connected with the cabin body 7, the other end is connected with the front end and the rear end of the left cabin door 6 and the right cabin door 7 in the forward direction of the airplane, the spring pin lower lock 1 is arranged at the front end of the upper unfolding mechanism, the lower part of the crank rocker A2, and the left cabin door 6 and the right cabin door 9 are of a concave cabin door structure.
The distance between the spring pin lower lock 1 and the slide rail support 3 of the upper unfolding mechanism is 2-3cm; the spring pin lower lock 1 consists of a spring and a positioning pin; the spring is arranged on the positioning pin, and the positioning pin is of a wedge-shaped structure; the diameter of the steel wire of the spring is 1.5mm-3mm, the pitch is 5mm-8mm, the diameter of the main shaft is 14mm-20mm, and the length is 35mm-45mm, and the material is spring steel.
The concave cabin door structure is an arc-shaped structure with the angle of 140-160 degrees at the middle part of the cabin door.
The upper unfolding mechanism comprises a crank rocker A2, a slide rail support 3 and a torsion spring 4; one end of the crank rocker A2 is arranged in a sliding rail of the sliding rail support 3, the other end of the crank rocker A2 is arranged on the concave cabin door, and the torsion spring 4 is sleeved on the sliding rail support 3.
As shown in fig. 4 and 6, one end of the crank rocker A2 is a plane with the bottom surface and is fixedly connected with the concave cabin door; the other end is provided with arc sliding pins at two sides, and the sliding pins are inserted into the sliding rail of the sliding rail support 3, so that the crank can move on the sliding rail. One end of the crank rocker B8 is a plane with the bottom surface and is fixedly connected with the concave cabin door; the other end is provided with arc sliding pins at two sides, and a boss is arranged on the arc surface at the lower end for limiting the unfolding angle of the cabin door.
As shown in fig. 5, the lower unfolding mechanism comprises a sliding rail support 3, a torsion spring 4 and a crank rocker B8; one end of a crank rocker B8 is arranged in a sliding rail of the sliding rail support 3, the other end of the crank rocker B8 is arranged on the concave cabin door, and a torsion spring 4 is sleeved on the sliding rail support 3.
The shape of the upper half part of the sliding rail support 3 is matched with the sliding pin of the crank rocker, so that the translational movement of the crank rocker can be realized, the lower half part of the sliding rail is circular, and a groove is formed in the lower left side and used for limiting the unfolding angle of the cabin door.
The diameter of the spring steel wire of the torsion spring 4 is 3mm-5mm, the pitch is 6mm-10mm, the diameter of the main shaft is 20mm-28mm, the torsion angle is more than 90 degrees, and the material is spring steel.
The sliding rail support 3 is fixed on the cabin 7 in a screw connection mode, and the spring pin lower lock 1 and the torsion spring 4 are arranged on the sliding rail support 3. One end of the crank rocker A2 and one end of the crank rocker B8 are fixedly arranged on the left cabin door 6 and the right cabin door 9 in a screw connection mode, and sliding pins at the other ends of the crank rocker A2 and the crank rocker B8 are inserted into sliding rails of the sliding rail support 3, and as shown in fig. 7, the sliding pins can move in the sliding rails. The crank rocker A2, the slide rail support 3 and the torsion spring 4 form an unfolding mechanism, the left cabin door 6 and the right cabin door 9 are connected with the cabin body 7, and the unfolding movement of the cabin doors is realized.
Working principle: when the cabin door is closed, the left cabin door 6, the right cabin door 9 and the cabin body 7 are connected and fixed through the upper locking initiating explosive device 5, so that the locking and keeping of the closed state are ensured.
When the cabin door is opened, the upper locking initiating explosive device 5 is detonated, the left cabin door 6 and the right cabin door 9 are disconnected from the cabin body, and meanwhile, the impact force of the explosion of the upper locking initiating explosive device 5 gives the left cabin door 6 and the right cabin door 9 a downward initial speed, so that the cabin door can move on the sliding rail as shown in fig. 7.
The cabin door can not rotate due to the limitation of the appearance of the sliding rail and the sliding pin structure in the movement process of the upper half part of the sliding rail, and can only do translational movement, as shown in fig. 8. The lower half part of the sliding rail (the circular sliding rail) can rotate after translating, as shown in fig. 9, the torsional spring 4 is used as driving force for rotary unfolding motion, the boss of the arc sliding pin of the crank rocker B8 is matched with the groove on the sliding rail of the sliding rail support 3 to limit in the unfolding process, and the lower lock 1 of the spring pin is locked after unfolding in place, as shown in fig. 10.
Claims (10)
1. The inner concave landing gear cabin door structure is characterized in that the inner concave landing gear cabin door structure is arranged on a cabin body (7) and comprises a left cabin door (6), a right cabin door (9), 2 upper unfolding mechanisms, 2 lower unfolding mechanisms, 4 upper locking initiating explosive devices (5) and 2 spring pin lower locks (1); the left cabin door (6) and the right cabin door (9) are symmetrically arranged, the 2 upper unfolding mechanisms are respectively arranged at the front ends of the left cabin door (6) and the right cabin door (9) in the advancing direction of the airplane and are connected with the corresponding positions of the cabin body (7), and the 2 lower unfolding mechanisms are respectively arranged at the rear ends of the left cabin door (6) and the right cabin door (9) in the advancing direction of the airplane and are connected with the corresponding positions of the cabin body (7); one end of an upper lock initiating explosive device (5) is connected with the cabin body (7), the other end of the upper lock initiating explosive device is connected with the front end and the rear end of the left cabin door (6) and the right cabin door (7) in the forward direction of the aircraft, the spring pin lower lock (1) is arranged at the front end of the upper unfolding mechanism, the lower part of the crank rocker A (2) is provided with a concave cabin door structure, and the left cabin door (6) and the right cabin door (9) are provided with a concave cabin door structure.
2. The recessed landing gear door structure according to claim 1, wherein the recessed door structure is an arc-shaped structure having an angle of 140 ° -160 ° in the middle of the door.
3. The recessed landing gear door structure according to claim 1, wherein the upper deployment mechanism comprises a crank rocker a (2), a slide rail support (3), a torsion spring (4); one end of the crank rocker A (2) is arranged in a sliding rail of the sliding rail support (3), the other end of the crank rocker A is arranged on the concave cabin door, and the torsion spring (4) is sleeved on the sliding rail support (3); one end of the crank rocker A (2) is provided with a plane bottom surface and is fixedly connected with the concave cabin door; the other end is provided with arc-shaped sliding pins at two sides, and the sliding pins are inserted into the sliding rails of the sliding rail support 3.
4. The recessed landing gear door structure according to claim 1, wherein the lower deployment mechanism comprises a slide rail support (3), a torsion spring (4), a crank rocker B (8); one end of a crank rocker B (8) is arranged in a sliding rail of the sliding rail support (3), the other end of the crank rocker B is arranged on the concave cabin door, and a torsion spring (4) is sleeved on the sliding rail support (3); one end of the crank rocker B8 is a plane with the bottom surface and is fixedly connected with the concave cabin door; the other end is provided with arc sliding pins at two sides, and a boss is arranged on the arc surface at the lower end for limiting the unfolding angle of the cabin door.
5. The recessed landing gear door structure according to claim 1, wherein the distance between the latch down lock (1) and the side of the slide rail support (3) of the upper deployment mechanism is 2-3cm.
6. The concave landing gear door structure according to claim 1, wherein the sliding rail support (3) is provided with a sliding rail, the upper half part of the sliding rail is matched with the sliding pin of the crank rocker, the lower half part of the sliding rail is circular, and the lower left part of the sliding rail is provided with a groove.
7. The concave landing gear door structure according to claim 1, wherein the spring steel wire of the torsion spring (4) has a diameter of 3mm-5mm, a pitch of 6mm-10mm, a main shaft diameter of 20mm-28mm, and a torsion angle of more than 90 degrees, and is made of spring steel.
8. The recessed landing gear door structure according to claim 1, wherein the spring pin down lock (1) consists of a spring and a locating pin; the spring is installed on the locating pin, and the locating pin is wedge structure.
9. The structure of the cabin door of the concave landing gear according to claim 8, wherein the steel wire of the spring has a diameter of 1.5mm-3mm, a pitch of 5mm-8mm, a main shaft has a diameter of 14mm-20mm and a length of 35mm-45mm, and the material is spring steel.
10. The method for opening the door structure of the concave landing gear according to any one of claims 1 to 9, wherein when the door is closed, the left door (6) and the right door (9) are fixedly connected with the cabin body 7 through an upper locking initiating explosive device (5), so that the door is locked and kept in a closed state;
when the cabin door is opened, the upper locking initiating explosive device (5) is detonated, the left cabin door (6) and the right cabin door (9) are disconnected from the cabin body, and meanwhile, the impact force of the explosion of the upper locking initiating explosive device (5) gives the left cabin door (6) and the right cabin door (9) a downward initial speed, so that the cabin door can move on the sliding rail;
the cabin door can rotate after being translated to the round slide rail at the lower half part of the slide rail by the slide rail and the sliding pin structure in the movement process of the upper half part of the slide rail, the cabin door is rotated and unfolded by taking the torsion spring (4) as a driving force, the boss of the arc-shaped sliding pin of the crank rocker B (8) is matched with the groove on the slide rail of the slide rail support (3) to limit, and the cabin door is locked by the spring pin lower lock (1) after being unfolded in place.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311572381.6A CN117682061A (en) | 2023-11-23 | 2023-11-23 | Concave landing gear cabin door structure and opening method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311572381.6A CN117682061A (en) | 2023-11-23 | 2023-11-23 | Concave landing gear cabin door structure and opening method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117682061A true CN117682061A (en) | 2024-03-12 |
Family
ID=90125517
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311572381.6A Pending CN117682061A (en) | 2023-11-23 | 2023-11-23 | Concave landing gear cabin door structure and opening method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117682061A (en) |
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2023
- 2023-11-23 CN CN202311572381.6A patent/CN117682061A/en active Pending
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