CN111204443A - Emergency slide bar mechanism for cabin door of airplane - Google Patents
Emergency slide bar mechanism for cabin door of airplane Download PDFInfo
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- CN111204443A CN111204443A CN202010078698.4A CN202010078698A CN111204443A CN 111204443 A CN111204443 A CN 111204443A CN 202010078698 A CN202010078698 A CN 202010078698A CN 111204443 A CN111204443 A CN 111204443A
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- bar mechanism
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- slide bar
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/24—Steps mounted on, and retractable within, fuselages
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Power-Operated Mechanisms For Wings (AREA)
Abstract
The emergency slide rod mechanism of the airplane cabin door comprises a driving rod, a slide pre-positioning shaft and a slide pre-positioning switching rod. The upper end of the driving rod is connected with an emergency handle on the cabin door of the airplane, so that the driving rod moves up and down by rotating the emergency handle. The emergency slide bar mechanism of the airplane cabin door can be switched between a pre-positioning state and a pre-positioning releasing state through a first transmission assembly between the slide pre-positioning shaft and the driving rod and a second transmission assembly between the slide pre-positioning switching bar and the slide pre-positioning shaft. The emergency slide bar mechanism of the airplane cabin door with the structure can simply and reliably realize the switching between the pre-positioning state and the de-pre-positioning state.
Description
Technical Field
The present invention relates to an emergency evacuation system for aircraft. In particular, the present invention relates to a hatch emergency slide bar mechanism for an aircraft for controlling the position of the slide bar to set it in a pre-position or de-pre-position condition.
Background
Aircraft, particularly large passenger aircraft, often include emergency slides that are automatically inflated for deployment immediately after opening an aircraft door when the aircraft encounters an emergency condition, such as an emergency descent. According to the provisions of the terms of the aircraft compliance standard CCAR25.810(a) (1) (i), the design of an emergency slide on an aircraft should meet the following requirements: firstly, the slide bag needs to be automatically unfolded in the process of rotating a cabin door inner handle from the inside of an airplane to start a door opening device until the cabin door is completely opened; secondly, in non-emergency situations, i.e. during normal opening of the aircraft, both from the inside of the cabin door and from the outside of the cabin door, the slide pack is prevented from unfolding.
For this purpose, an emergency slide bar mechanism is provided on the aircraft door, which can be switched between a pre-position state in which the slide bar cooperates with a floor clip provided on the floor of the aircraft, so that when the door is opened, the emergency slide is inflated in response to the emergency slide, so that the emergency slide is deployed, and a release pre-position state in which the triggering connection between the slide bar and the floor is released, so that the slide does not deploy as the door is opened.
In order to fulfill the above requirements, a variety of aircraft door emergency slide bar mechanisms have been developed in the field of aircraft design. The existing airplane cabin door emergency slide bar mechanism is provided with a hook part, a groove, a binding bar and the like, and the slide bar is switched between a pre-positioning state and a pre-positioning releasing state through mutual matching among the hook part, the groove and the binding bar. The mechanism is relatively complex in construction, includes a large number of parts, and requires interaction between the parts to determine the position of the lashing rod, and is also relatively complex and costly to operate.
In addition, in the field of aircraft design, there are also emergency slides that are controlled by electrical connectors, slide bars that are triggered by spring-loaded pin structures, and the like to control the deployment of the emergency slides.
However, in the field of aircraft design, there is still a need for an improved aircraft door emergency slide bar mechanism which simplifies its structure and which can be reliably switched between a pre-position state and an un-pre-position state.
Disclosure of Invention
The present invention has been made to solve the above-mentioned problems occurring in the prior art. The object of the invention is to provide an aircraft door emergency slide bar mechanism which can be reliably switched between a pre-position state and a release pre-position state with simple operation.
The emergency slide bar mechanism of the airplane cabin door comprises: the upper end of the driving rod is connected with an emergency handle on the cabin door of the airplane, so that the driving rod can move up and down by rotating the emergency handle;
the slide pre-positioning shaft is connected with the driving rod through a first transmission assembly, so that the vertical motion of the driving rod is converted into the rotary motion of the slide pre-positioning shaft through the first transmission assembly; and
the slide pre-positioning switching rod is connected with the slide pre-positioning shaft through a second transmission assembly, so that the rotary motion of the slide pre-positioning switching rod is converted into switching motion between a first position of the slide pre-positioning shaft, which is matched with the floor clamp, and a second position, which is matched with the storage hook, through the second transmission assembly, wherein the floor clamp is fixed on the floor of the airplane;
the emergency slide bar mechanism of the airplane cabin door is in a pre-positioning state at the first position, and is in a pre-positioning releasing state at the second position.
In the aircraft cabin door emergency slide rod mechanism with the structure, the first transmission component between the slide pre-positioning shaft and the driving rod and the second transmission component between the slide pre-positioning shaft and the slide pre-positioning switching rod can reliably realize the conversion between the pre-positioning state and the pre-positioning releasing state of the aircraft cabin door emergency slide rod mechanism by simple structure and operation.
For the first transmission assembly, an exemplary preferred structure includes a crank having one end connected to the slide preposition shaft and the other end connected to a fork lug that is relatively pivotally connected to the drive rod such that movement of the drive rod in an up-and-down direction pivots the fork lug and rotates the slide preposition shaft via the crank 112.
Preferably, the drive rod is provided with a drive rod support, and the drive rod support is connected to the door of the airplane. In this way, the drive rod can be raised and lowered with the aircraft door when the aircraft door is opened and closed. For example, the drive rod support may be connected to a transom of an aircraft door.
An exemplary preferred structure of the second transmission assembly includes a rocker arm, one end of the rocker arm is connected to the slide preposition shaft, and a latch is provided at the other end of the rocker arm and connected to the slide preposition switching rod, so that the rotational movement of the slide preposition shaft causes the latch to swing along with the rocker arm, thereby causing the slide preposition switching rod to perform switching movement between a first position and a second position.
Preferably, a flat plate part is arranged on the slide pre-position switching rod, and a hole is formed in the flat plate part and used for receiving the bolt. The slide pre-position switching rod is switched between a first position and a second position through the matching between the hole and the bolt.
Preferably, the bore has an inclined portion formed therein, the inclined portion being arranged to allow the angle of the spigot received in the bore relative to the horizontal of the aircraft to be varied. For example, by providing the inclined portion, in the unseated state, the plug received in the hole is substantially at an acute angle with respect to the horizontal direction, and in the unseated state, the plug extends in the hole substantially perpendicular to the horizontal direction.
Preferably, a cylindrical barrel is provided on the storage hook, the cylindrical barrel extending through the bushing into the holder housing and being slidable along a longitudinal axis of the cylindrical barrel.
Preferably, the shaft sleeve is provided with at least one long hole, at least one pin shaft penetrates through the long hole, and the pin shaft can move between the upper end and the lower end of the long hole. The cooperation of round pin axle and slot hole has realized depositing the spacing effect of the motion of hook relative to the floor clamping.
Further, a plug and/or a stop ring is provided in the bearing housing, which further optimizes the above-mentioned stop action. Preferably, a spring is also provided on the cylinder housing for storing the hook. In this way, the storage hook is cushioned during the closing of the aircraft door and the movement of the storage hook under the line close to the floor clip
Preferably, at least one bearing is mounted on the slide pre-positioning shaft, the bearing being fixed to the aircraft door.
Drawings
The accompanying drawings illustrate a schematic diagram of a preferred structure of the present invention, and the structure shown in the drawings should not be construed as limiting the scope of the invention, in which:
fig. 1 shows an exemplary perspective view of the aircraft door panic bar mechanism of the present invention.
Fig. 2 shows a side view of the aircraft door emergency slide bar mechanism of the present invention showing the slide pre-position switch bar mated with the floor clips so that the aircraft door emergency slide bar mechanism is in a pre-position.
Fig. 3 shows another side view of the aircraft door emergency slide bar mechanism of the present invention showing the slide pre-position switch bar in cooperation with the storage hook so that the aircraft door emergency slide bar mechanism is in a de-pre-position state.
Fig. 4 shows a partial perspective view of the aircraft door emergency slide bar mechanism of the invention showing the movement of the pin in the pin when opening the aircraft door in the disarmed state.
Fig. 5 shows another partial perspective view of the aircraft door emergency slide bar mechanism of the present invention showing the movement of the pin in the pin when closing the aircraft door in the unseated state.
Fig. 6 shows a partial cross-sectional view of the aircraft door emergency slide bar mechanism 100 of the present invention showing the movement of the latch pin in the hole when closing the aircraft door in the unseated state.
Fig. 7a shows a partial cross-sectional view of the aircraft door emergency slide bar mechanism showing the angle of the latch relative to horizontal in the unset condition.
Fig. 7b shows another partial cross-sectional view of the aircraft door emergency slide bar mechanism showing the angle of the latch relative to horizontal in the pre-position.
Detailed Description
In order to facilitate understanding of the present invention, preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It is to be understood that the preferred embodiments of the present invention are shown in the drawings only, and are not to be considered limiting of the scope of the invention. Various obvious modifications, variations and equivalents of the present invention may be made by those skilled in the art based on the embodiments shown in the drawings, and fall within the scope of the present invention.
In the following description of the specific embodiments, the terms "upper", "lower", and the like used to indicate orientation and position are based on the orientation of the aircraft in use.
A schematic perspective view of the aircraft door emergency slide bar mechanism 100 of the present invention is shown in fig. 1. As shown, the aircraft door emergency slide bar mechanism 100 includes a drive rod 110, which drive rod 110 is connected to an emergency handle (not shown) on the aircraft door. The operator may move the drive rod 110 in an up-and-down direction by rotating the panic handle. Optionally, a drive rod support 111 is provided on the drive rod 110 to connect the drive rod 110 to a component such as an aircraft door, for example to a transom of the aircraft door, in a relatively movable manner.
The aircraft door emergency slide bar mechanism 100 further comprises a slide pre-position shaft 120, the slide pre-position shaft 120 being connected to the drive rod 110. A transmission assembly is provided between the slide repositioning shaft 120 and the drive rod 110 such that the movement of the drive rod 110 in the up-down direction is converted into a rotational movement of the slide repositioning shaft 120 about its longitudinal axis.
Specifically, in the specific structure shown in the drawings, a crank 112 is connected to the slide pre-positioning shaft 120, and a fork lug 113 is provided on a free end of the crank 112. For example, a toothed surface is provided at an interface between the fork ear 113 and the crank 112, so that the fork ear 113 and the crank 112 are attached to each other by the toothed surface and are connected together via a fastener such as a bolt.
The swing arm 121 is connected to the slide pre-positioning shaft 120 by a fastener such as a bolt, so that the swing arm 121 is rotated by the rotation of the slide pre-positioning shaft 120. A latch 122 is provided on the free end of the rocker arm 121. The latch 122 has one end connected to the free end of the swing arm 121 and the other end extending into the slide preset switching lever 130.
In one specific structure, a guide plate 123 for guiding the plug pin 122 is mounted on the slide pre-position switching lever 130, and a flat plate portion 131 is also mounted. For example, the guide plate 123 and the flat plate portion 131 may be connected to the slide preset switching lever 130 by a fastener such as a rivet.
A hole 132 is formed in the flat plate portion 131, and the plug 122 can extend into the hole 132 (see fig. 6) and be guided by the hole 132. As the swing arm 121 rotates, the latch 122 swings, so that the slide preset switching lever 130 swings in a direction perpendicular to the longitudinal axis of the slide preset switching lever 130 by the interaction between the latch 122 and the hole 132. The swinging motion of the slide pre-positioning switch lever 130 realizes the conversion of the airplane door emergency slide lever mechanism 100 between the pre-positioning state and the de-pre-positioning state.
Preferably, an inclined portion 133 is formed in the hole 132, and the inclined portion 133 allows the angle of the plug 122 inserted into the hole 132 with respect to the horizontal direction to be variable. For example, as shown in FIG. 7a, in the unseated state, the latch 122 is at an acute angle to the horizontal, such as about 56 degrees as shown in FIG. 7 a. Such a relative angle may reduce or avoid the risk of interference between the pin 122 and the hole 132 in the unseated state.
When the aircraft door emergency slide bar mechanism 100 is switched to the armed position as shown in fig. 7b, the angle between the latch 122 and the horizontal is close to or at right angles, e.g., more than 89 degrees as shown in fig. 7 b.
Here, the horizontal direction refers to a direction substantially perpendicular to the extending direction of the floor of the aircraft (also the extending direction of the slide positioning switch lever 130), or in other words, the extending direction of the door of the aircraft (also the extending direction of the slide positioning switch lever 130).
A floor clip 140 and a storage hook 151 are provided corresponding to the slide-preset switching lever 130, and the slide-preset switching lever 130 can be switched between a position engaged with the floor clip 140 and a position engaged with the storage hook 151 by the swinging movement of the slide-preset switching lever 130 in accordance with the rotation of the swing arm 121. The floor clips 140 are fixedly attached to the floor of the nacelle. The storage hook 151 is provided with a cylindrical barrel which extends through the bushing 152 into the seat housing 156 and is slidable along its longitudinal axis. At least one pin 153 is provided on the bushing 152, at least one pin 153 is provided through the elongated hole 154, and the pin 153 is movable between an upper end position and a lower end position of the elongated hole 154. The bearing housing 156 is connected to the cross member of the aircraft, for example by fasteners such as bolts.
Specifically, when the slide pre-position switch lever 130 is moved to a position to engage the floor clip 140, as shown in fig. 2, the aircraft door emergency slide lever mechanism 100 is in a pre-position state. When the slide rod 130 is moved to a position where it engages the storage hook 151, as shown in fig. 3, the aircraft door emergency slide rod mechanism 100 is now in the disarmed state. As shown, both the floor clips 140 and the storage hooks 151 are formed with an open slot configuration to receive the slide pre-position bar 130, such as to receive an end of the slide pre-position bar 130. Of course, other forms of releasable engagement between the slide pre-position bar 130 and the floor clips 140 and storage hooks 151 are possible and within the scope of the present invention.
Preferably, a spring 155 is provided between the pin 153 and the storage hook 151 to serve as a buffer structure between the pin 153 and the storage hook 151.
It is further preferred that a stopper 157 and a stopper ring 158 are provided in the holder housing 156 to serve as a stopper structure for the cylinder barrel, limiting the range of movement of the cylinder barrel.
Preferably, as shown, at least one bearing 160 is also provided on the slide pre-position shaft 120, the bearing housing of the bearing 160 being bolted or otherwise attached to the aircraft door, such as to the stringer bulkhead.
In the configuration shown in the drawing, the rocker arm 121, the latch 122, the floor clip 140, the storage hook 151, the boss 152, and the like are provided at one ends of the slide home shaft 120 and the slide home lever 130, and the same configuration is provided at the other ends of the slide home shaft 120 and the slide home lever 130. The same structure will not be described repeatedly herein.
The mode of operation of the aircraft door emergency slide bar mechanism 100 will now be described in connection therewith.
< Pre-positioning mode >
When an emergency situation is encountered after the aircraft door is closed, the panic handle on the door, which is connected to the drive rod 110 of the aircraft door panic slide bar mechanism 100, is turned, and when the panic handle is turned in a first direction, the drive rod 110 will move upwards, which in turn pivots the crank 112 via the fork ear 113. At this point, pivoting of the crank 112 causes the slide pre-position shaft 120 to rotate about its longitudinal axis in a first rotational direction, which in turn causes the rocker arm 121 to pivot in a first pivot direction. At this time, the latch 122 inserted into the guide plate 123 and the flat plate portion 131 drives the slide pre-positioning rod 130 to translate, so that the slide pre-positioning rod 130 moves to a position where it is engaged with the floor clip 140, as shown in fig. 2. At this point, if the hatch door is opened, the slide pack is actuated by the interaction between the slide pre-position rod 130 and the floor clip 140, thereby deploying the emergency slide.
Furthermore, it should be further noted that the panic handle may alternatively be rotated by the aircraft crew inside the aircraft door or by rescue personnel outside the aircraft door to set the aircraft door panic bar mechanism 100 into the pre-position state.
< Pre-positioning Release mode >
To set the aircraft door emergency slide bar mechanism 100 in the pre-positioned contact state, the emergency handle is rotated in a second direction after the aircraft door is closed. At this point, the panic handle will cause the drive rod 110 to move downward, which in turn causes the crank 112 to pivot via the fork ear 113. At this time, the pivoting of the crank 112 causes the slide pre-position shaft 120 to rotate about its longitudinal axis in the second rotational direction, which in turn causes the rocker arm 121 to pivot in the second pivoting direction. At this time, the latch 122 moves the slide pre-positioning lever 130 toward the storage hook 151 and moves to a position to be engaged with the storage hook 151, as shown in fig. 3. At this point, the slide pack is not actuated when the aircraft door is opened because the slide pre-bar 130 is disengaged from the floor clips 140.
In this state of the aircraft door emergency slide bar mechanism 100, if the aircraft door is opened, the pin 153 will gradually move up from the lower end position to the upper end position of the long hole 154 on the bushing 152, as schematically shown in fig. 4. During this process, the storage hook 151 will remain stationary.
After the pin 153 moves to the upper end position of the long hole 154, as the pin 153 continues to move upward, the pin 153 drives the sleeve 152 to move upward together, and further drives the storage hook 151 to move upward. At this time, the slide pre-positioning rod 130 engaged with the storage hook 151 is also moved upward. In this way, the opening action of the aircraft door does not trigger the inflation of the slide pack and thus the deployment of the emergency slide.
When closing an aircraft door with the aircraft door emergency slide bar mechanism 100 in the pre-positioned contact state, the storage hook 151 will descend with the aircraft door until the storage hook 151 contacts the floor clips 140. At this time, the storage hook 151 is supported by the floor clips 140 and stops moving downward. Since the support housing 156 is connected to the door cross member, it will continue to move downwards, thereby compressing the spring 155 downwards, until the pin 153 moves in the elongated hole 154 from its upper end position to a predetermined position, for example the lower end position of the elongated hole 154. This process is illustrated in fig. 5.
In this way, it is ensured that storage hook 151 moves to a prescribed position relative to floor clip 140, for example, to a position where storage hook 151 is flush with the lower surface of floor clip 140. In this process, the spring 155 serves as a buffer, and the pin 153 serves as a movement position restriction.
Further, in case bearings 160 are provided, since the bearings 160 are attached to the aircraft door, e.g. to the stringer bulkhead thereof, they will move downwards along with the aircraft door, bringing the slide prerotation shaft 120 and other components associated therewith also downwards. Also, during this process, the pin 122 will be inserted deeper into the hole 132 and/or the angle of the pin 122 relative to the hole 132 will be adjusted to the most appropriate position. This movement is shown adaptively in fig. 6. In this way, the latch 122 can more reliably move the slide detent shaft 120 from the storage hook 151 into the floor clip 140 during setting of the aircraft door emergency slide bar mechanism 100 to the detent state after the aircraft door is closed.
< other modifications >
The construction of the preferred embodiment of the invention has been described in detail with reference to the accompanying drawings, and it is within the scope of the invention that obvious modifications and variations can be made to the construction of the emergency slide bar mechanism for aircraft doors of the invention by those skilled in the art after reading the above disclosure.
For example, in the above-described structure, the transmission assembly between the drive lever 110 and the slide pre-position shaft 120 specifically includes the crank 112 and the fork lug 113. Besides, the transmission assembly may have other structures as long as it can convert the movement of the driving rod 110 in the up-down direction into the rotation of the slide pre-positioning shaft 120. For example, a crank structure or the like in which a plurality of rods are coupled may be provided between the slide pre-position shaft 120 and the drive lever 110.
Also, as for the transmission assembly disposed between the slide preset switching lever 130 and the slide preset shaft 120 described in detail above, other transmission structures known in the art may be employed in addition to the swing arm 121, the latch 122 on the swing arm 121, and the hole 132 disposed on the flat plate portion 131 to be engaged with the latch 122, as long as the rotational movement of the slide preset shaft 120 can be converted into the switching movement of the slide preset switching lever 130 between the floor clips 140 and the storage hooks 151. For example, a link mechanism, a cam mechanism, or the like may be provided between the slide preset shaft 120 and the slide preset switching lever 130.
In the specific structure shown in the figure, two swing arms 122 and two floor clips 140, two storage hooks 151 and related components corresponding thereto are provided at both ends of the slide preset shaft 120 and the slide preset switching lever 130, respectively. It will be clear to the person skilled in the art that only one rocker arm 121, one floor clip 140, one storage hook 151 and the parts associated therewith may be provided, as well as being able to substantially fulfill the function of the aircraft door emergency slide bar mechanism 100. Alternatively, three or more swing arms 121, floor clips 140, storage hooks 151, and the like may be provided as needed.
In the particular structure disclosed above, the aircraft door emergency slide bar mechanism 100 is arranged to set the aircraft door emergency slide bar mechanism 100 to the pre-position state when the drive rod 110 moves upward, and the aircraft door emergency slide bar mechanism 100 is set to the Roc release pre-position state when the drive rod 110 moves downward. It will be appreciated by those skilled in the art that the aircraft door emergency slide bar mechanism 100 may also be configured to engage the slide pre-position bar 130 with the floor clips 140 as the drive rod 110 moves downwardly. The positions of the floor clips 140 and the storage hooks 151 need only be interchanged.
In the specific implementation shown in the figures, the floor clips 140 and the storage hooks 151 are formed with open slots, and the slide repositioning lever 130 releasably retains the slide repositioning lever 130 in the first and second positions by snap-fitting into respective slots of the floor clips 140 and the storage hooks 151, respectively. Those skilled in the art will appreciate that the releasable engagement between the slide preposition switch lever 130 and the floor clips 140 and storage hooks 151 may be accomplished in other ways, such as other mechanical structures known in the art, and may even be magnetic, electric, etc.
Claims (10)
1. An aircraft hatch emergency slide bar mechanism, comprising:
the upper end of the driving rod is connected with an emergency handle on a door of the airplane, so that the driving rod can move in the up-and-down direction by rotating the emergency handle;
a slide pre-positioning shaft connected with the driving rod through a first transmission assembly, such that the movement of the driving rod in the up-down direction is converted into a rotational movement of the slide pre-positioning shaft via the first transmission assembly; and
the slide pre-positioning switching rod is connected with the slide pre-positioning shaft through a second transmission assembly, so that the rotary motion of the slide pre-positioning switching rod is converted into switching motion between a first position of the slide pre-positioning shaft, which is matched with a floor clamp, and a second position, which is matched with a storage hook, through the second transmission assembly, wherein the floor clamp is fixed on the floor of the airplane;
wherein, in the first position, the aircraft cabin door emergency slide bar mechanism is in a pre-position state, and in the second position, the aircraft cabin door emergency slide bar mechanism is in a pre-position releasing state.
2. The aircraft door emergency slide bar mechanism of claim 1, wherein said first transmission assembly comprises a crank having one end connected to said slide pre-position shaft and another end connected to a fork lug relatively pivotally connected to said drive rod, such that said movement of said drive rod in an up-and-down direction causes said fork lug to pivot and rotate said slide pre-position shaft via said crank 112.
3. The aircraft door emergency slide bar mechanism of claim 1, wherein a drive bar support is mounted on said drive bar, said drive bar support being attached to said aircraft door.
4. The aircraft door emergency slide bar mechanism of claim 1 or 2, wherein said second transmission assembly comprises a rocker arm having one end connected to said slide preposition shaft and another end provided with a latch connected to said slide preposition switch lever, such that said rotational movement of said slide preposition shaft causes said latch to swing with said rocker arm, thereby causing said slide preposition switch lever to perform said switching movement between said first position and said second position.
5. The aircraft door emergency slide bar mechanism of claim 4, wherein a flat plate portion is mounted on said slide pre-positioning switch bar, said flat plate portion having a hole therein for receiving said latch.
6. The aircraft door emergency slide bar mechanism of claim 5, wherein a beveled portion is formed in said bore, said beveled portion being configured to allow the angle of said latch pin received in said bore to be varied relative to the horizontal of said aircraft.
7. The aircraft door emergency slide bar mechanism of claim 1, wherein a cylindrical barrel is provided on said storage hook, said cylindrical barrel extending through a bushing into a seat housing and being slidable along a longitudinal axis of said cylindrical barrel.
8. An aircraft door emergency slide bar mechanism according to claim 7, wherein at least one slot is provided in said sleeve, at least one pin is provided through said slot, said pin being movable between an upper end and a lower end of said slot.
9. The aircraft door emergency slide bar mechanism of claim 7, wherein a plug and/or a stop collar is provided in the seat housing.
10. The aircraft door emergency slide bar mechanism of claim 1, wherein at least one bearing is mounted on said slide pre-position shaft, said bearing being affixed to said aircraft door.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010078698.4A CN111204443A (en) | 2020-02-03 | 2020-02-03 | Emergency slide bar mechanism for cabin door of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010078698.4A CN111204443A (en) | 2020-02-03 | 2020-02-03 | Emergency slide bar mechanism for cabin door of airplane |
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| Publication Number | Publication Date |
|---|---|
| CN111204443A true CN111204443A (en) | 2020-05-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010078698.4A Pending CN111204443A (en) | 2020-02-03 | 2020-02-03 | Emergency slide bar mechanism for cabin door of airplane |
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| Country | Link |
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| CN (1) | CN111204443A (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112173063A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Emergency window sealed with helicopter cabin door |
| CN112278292A (en) * | 2020-11-09 | 2021-01-29 | 中国民用航空飞行学院 | Cabin door emergency slide bar mechanism applied to civil aircraft |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173063A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Emergency window sealed with helicopter cabin door |
| CN112173063B (en) * | 2020-09-25 | 2022-07-15 | 中国直升机设计研究所 | Emergency window sealed with helicopter cabin door |
| CN112278292A (en) * | 2020-11-09 | 2021-01-29 | 中国民用航空飞行学院 | Cabin door emergency slide bar mechanism applied to civil aircraft |
| CN112278292B (en) * | 2020-11-09 | 2022-03-01 | 中国民用航空飞行学院 | Cabin door emergency slide bar mechanism applied to civil aircraft |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200529 |