Emergency escape cabin door of airplane unit

Abstract

The invention belongs to the technical field of airplane unit emergency escape hatch door design, and particularly relates to an airplane unit emergency escape hatch door which is designed to be opened, closed and locked only through driving of one actuating cylinder, and the airplane unit emergency escape hatch door is simple in overall structure, high in system reliability and light in weight.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft crew emergency escape hatch design, and specifically relates to an aircraft crew emergency escape hatch. Background Art

[0002] Currently, there are mainly the following design schemes for aircraft crew emergency escape hatches:

[0003] 1) An escape passage is set up on the floor of the cabin near the cockpit, and a jettisonable hatch is set up at the exit of the escape passage. The escape passage and its emergency escape hatch are far away from the crew, which is not conducive to the crew's timely escape in dangerous situations;

[0004] 2) An escape passage is set on the floor of the cabin near the cockpit, and an emergency escape hatch that can be detached explosively is set at the exit of the escape passage. The escape passage and its hatch are far away from the crew, which is not conducive to the crew's timely escape in dangerous situations. In addition, the edges produced by the explosive detachment are not smooth enough, which may cause damage to the crew and their parachutes, making it difficult to ensure the safe escape of the crew in dangerous situations;

[0005] 3) An escape passage is provided on the cockpit floor, and a door that opens outward and forward is provided at the exit of the escape passage. The locking and opening of the door are driven by a separate actuator. The overall structure is complex, the system reliability is low, and the weight is large.

[0006] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0007] The purpose of the present application is to provide an aircraft crew emergency escape hatch to overcome or alleviate at least one of the known technical deficiencies.

[0008] The technical solution of this application is:

[0009] An aircraft crew emergency escape hatch, comprising:

[0010] A hatch is arranged at the exit of the escape passage and opens outwards. The inner side of the hatch is provided with a hatch opening stopper, two lock pin guide holes and a lock pin support hole;

[0011] Two locking blocks, connected to the exit of the escape passage, with locking pin openings;

[0012] Two locking pins, the side walls of which have annular protrusions, the tails of which are inserted into the two locking pin guide holes, and the heads of which extend out from the two locking pin support holes;

[0013] Two return springs, both ends of which are against the front end of the lock pin guide hole and the annular protrusion, rely on the elastic force to make the heads of the two lock pins insert into the two lock pin holes, and lock the hatch door in the closed position;

[0014] A transverse connecting rod, with both ends sleeved on the outer circumference of the two locking pins;

[0015] A driving connecting rod, one end of which is hinged to the transverse connecting rod;

[0016] A driving rocker arm, the middle part of which is hinged to the inner side of the door, and has a door opening driving block on it, one end of which is hinged to the other end of the driving connecting rod;

[0017] The actuator is hinged between the inner side of the escape passage exit and the other end of the driving rocker arm;

[0018] When the piston rod of the actuator cylinder is extended, it can drive the driving rocker arm to rotate, and then through the driving connecting rod and the transverse connecting rod, overcome the elastic force of the return spring to pull the two locking pins, so that the heads of the two locking pins are separated from the locking pin mouths, thereby releasing the lock of the hatch in the closed position, and then making the opening drive block abut against the hatch opening stop block, driving the hatch to open.

[0019] Optionally, in the above-mentioned aircraft crew emergency escape hatch, two return springs are sleeved on the outer periphery of the two locking pins.

[0020] Optionally, in the above-mentioned aircraft crew emergency escape hatch, the driving rocker arm and the driving connecting rod are hinged through a single-ear and double-ear structure.

[0021] Optionally, in the above-mentioned aircraft crew emergency escape hatch, the actuator and the inner side of the escape passage exit and the driving rocker arm are hinged through a single-ear and double-ear structure.

[0022] Optionally, in the above-mentioned aircraft crew emergency escape hatch, a hatch door closing stop block is provided on the inner side of the hatch door;

[0023] The two locking blocks are provided with outward guiding inclined surfaces;

[0024] The driving rocker arm is provided with a hatch door closing driving block;

[0025] When the piston rod of the actuator cylinder contracts, it can drive the driving rocker arm to rotate, so that the hatch closing drive block abuts against the hatch closing stop block, driving the hatch to close. During this process, the heads of the two locking pins abut against the two outward guide slopes, slide along the outward guide slopes, overcome the elastic force of the return springs to push the two locking pins, and after bypassing the outward guide slopes, under the action of the elastic force of the return springs, the heads of the two locking pins are reinserted into the two locking pin holes, locking the hatch in the closed position.

[0026] Optionally, in the above-mentioned aircraft crew emergency escape door, the driving rocker arm is located between the door opening stop block and the door closing stop block.

[0027] Optionally, in the above-mentioned aircraft crew emergency escape hatch, a skin is provided on the inner side of the hatch.

[0028] Optionally, in the above-mentioned aircraft crew emergency escape hatch, the entrance of the escape passage is opened on the floor of the cockpit, and the exit of the escape passage is opened at the lower left part of the nose.

[0029] Optionally, the above-mentioned aircraft crew emergency escape hatch further includes:

[0030] Two suspension rocker arms are connected at one end on the inner side of the door, close to the edge of one vertical side of the door, and the other end is bent and hinged on the inner side of the escape passage exit.

[0031] Optionally, in the above-mentioned aircraft crew emergency escape hatch, the two suspension rocker arms and the inner side of the escape passage exit are hinged through a single-ear and double-ear structure.

[0032] Optionally, in the above-mentioned aircraft crew emergency escape hatch, the two lock pin openings are arc-shaped openings;

[0033] The heads of the two locking pins are spherical.

[0034] Optionally, the above-mentioned aircraft crew emergency escape hatch further includes:

[0035] The transfer rod has one end connected to the transverse connecting rod and the other end hinged to the end of the driving connecting rod facing away from the driving rocker arm.

[0036] Optionally, the above-mentioned aircraft crew emergency escape hatch further includes:

[0037] Two oblique support rods are obliquely connected between the two ends of the transverse connecting rod and an end of the transfer rod facing away from the transverse connecting rod.

[0038] Optionally, the above-mentioned aircraft crew emergency escape hatch further includes:

[0039] A driving rocker arm is hinged on the inner side of the door and has two hinged joints, wherein one hinged joint is hinged to an end of the driving connecting rod facing away from the driving rocker arm;

[0040] The transmission connecting rod has one end hinged to another hinged joint, and the other end hinged to an end of the transfer rod facing away from the transverse connecting rod.

[0041] Optionally, in the above-mentioned aircraft crew emergency escape hatch, the hinged joint on the transmission rocker arm and the driving connecting rod are hinged through a single-ear and double-ear structure.

[0042] Optionally, in the above-mentioned aircraft crew emergency escape hatch, the transmission connecting rod and the hinged joint on the transmission rocker arm are hinged through a single-ear and double-ear structure.

[0043] Optionally, in the above-mentioned aircraft crew emergency escape hatch, the transmission connecting rod and the transfer rod are hinged through a single-ear and double-ear structure.

[0044] This application has at least the following beneficial technical effects:

[0045] Provided is an aircraft crew emergency escape hatch, the opening, closing and locking of which are designed to be driven by only one actuator, with a simple overall structure, high system reliability and light weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 is a schematic diagram of a hatch provided in an embodiment of the present application being locked in a closed position;

[0047] Figure 2 is a schematic diagram of the appearance of a closed hatch provided in an embodiment of the present application;

[0048] Figure 3 is a schematic diagram of releasing the lock of the hatch in the closed position provided by an embodiment of the present application;

[0049] Figure 4 is a schematic diagram of the appearance of an open hatch provided in an embodiment of the present application;

[0050] Figure 5 is a schematic diagram of providing a skin on the inner side of a hatch provided in an embodiment of the present application;

[0051] Figure 6 It is a schematic diagram of a hatch provided in an embodiment of the present application being connected in an escape passage by two suspension rocker arms;

[0052] Figure 7 It is a schematic diagram of a driving rocker arm provided in an embodiment of the present application being located between a door opening stop block and a door closing stop block;

[0053] Figure 8 It is a schematic diagram of the structural assembly relationship of the aircraft crew emergency escape hatch provided in an embodiment of the present application;

[0054] in:

[0055] 1-door; 2-escape passage; 3-door opening stop block; 4-door closing stop block; 5-lock block; 6-lock pin; 7-reset spring; 8-lateral connecting rod; 9-driving connecting rod; 10-driving rocker arm; 11-door opening driving block; 12-door closing driving block; 13-actuator; 14-suspension rocker arm; 15-transfer rod; 16-diagonal support rod; 17-transmission rocker arm; 18-transmission connecting rod.

[0056] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0057] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0058] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0059] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0060] An aircraft crew emergency escape hatch, comprising:

[0061] The hatch 1 is arranged at the exit of the escape passage 2 and opens outwards. The inner side of the hatch 1 is provided with a hatch opening stop block 3, a hatch closing stop block 4, two lock pin guide holes, and a lock pin support hole;

[0062] Two locking blocks 5 are connected to the exit of the escape passage 2 and have locking pin openings and outward guiding inclined surfaces;

[0063] Two locking pins 6, the side walls of which have an annular protrusion, the tails of which are inserted into the two locking pin guide holes, the heads of which extend out from the two locking pin support holes, and the annular protrusions are located between the locking pin guide holes and the locking pin support holes;

[0064] Two return springs 7 are sleeved on the outer circumference of the two lock pins 6, with both ends abutting against the front end of the lock pin guide hole and the annular protrusion. Relying on the elastic force, the heads of the two lock pins 6 are inserted into the two lock pin holes to lock the hatch 1 in the closed position. Figure 1-Figure 2 As shown;

[0065] The two ends of the transverse connecting rod 8 are sleeved on the outer periphery of the two locking pins 6;

[0066] A driving connecting rod 9, one end of which is hinged on the transverse connecting rod 8;

[0067] The driving rocker arm 10 is hinged at the middle part to the inner side of the door 1, and has a door opening driving block 11 and a door closing driving block 12, one end of which is hinged to the other end of the driving connecting rod 9, and can be specifically hinged by a single-ear and double-ear structure;

[0068] The actuator 13 is hinged between the inner side of the exit of the escape passage 2 and the other end of the driving rocker arm 10, and can be hinged by a single-ear and double-ear structure;

[0069] When the piston rod of the actuator 13 is extended, it can drive the driving rocker arm 10 to rotate, thereby pulling the driving connecting rod 9, so that the transverse connecting rod 8 moves, and the two ends abut against the two annular protrusions, overcoming the elastic force of the return spring 7 to pull the two locking pins 6, so that the heads of the two locking pins 6 are separated from the locking pin openings, such as Figure 3 As shown, the lock of the hatch door 1 in the closed position is released, so that the opening drive block 11 abuts against the hatch door opening stop block 3, and the hatch door 1 is driven to open, as shown in FIG. Figure 4 As shown;

[0070] When the piston rod of the actuator 13 contracts, it can drive the driving rocker arm 10 to rotate, and then push the driving connecting rod 9, so that the transverse connecting rod 8 moves, and the two ends are disengaged from the two annular protrusions. Under the elastic force of the reset spring 7, the two locking pins 6 are automatically reset, so that the hatch closing drive block 12 abuts against the hatch closing stop block 4, driving the hatch to close. In this process, the heads of the two locking pins 6 abut against the two outward guide slopes and slide along the outward guide slopes, overcoming the elastic force of the reset spring 7 to push the two locking pins 6. After bypassing the outward guide slopes, under the elastic force of the reset spring 7, the two locking pins 6 are automatically reset, and the heads of the two locking pins 6 are reinserted into the two locking pin orifices to lock the hatch 1 in the closed position.

[0071] The aircraft crew emergency escape hatch disclosed in the above embodiment is designed to be opened, closed and locked by only one actuator, and has a simple overall structure, high system reliability and light weight.

[0072] In order to prevent the crew from being scratched or the parachute from being scratched when escaping and to ensure the crew's safe escape in dangerous situations, a skin can be provided on the inner side of the door 1 to cover the structure provided on the inner side of the door 1 and ensure the smoothness of the inner side of the door 1, such as Figure 5 shown.

[0073] In order to shorten the distance from the crew to the escape passage 2 and ensure the timely escape of the crew in dangerous situations, the entrance of the escape passage 2 can be opened on the floor of the cockpit, and the exit of the escape passage 2 can be opened at the lower left part of the nose.

[0074] In some optional embodiments, the above-mentioned aircraft crew emergency escape hatch further includes:

[0075] Two suspension rocker arms 14 are connected at one end to the inner side of the door 1, close to the edge of the vertical side of the door 1, and the other end is bent and hinged to the inner side of the exit of the escape passage 2. Specifically, the single-double-ear structure can be hinged, such as Figure 6 As shown, when the door 1 is opened outward, it deflects forward 90° to form a windshield on the exit side of the escape passage 2, which can reduce the interference of airflow when the crew escapes in dangerous situations and reduce the danger of escape.

[0076] In some optional embodiments, in the above-mentioned aircraft crew emergency escape hatch, the two lock pin openings are arc-shaped openings;

[0077] The heads of the two locking pins 6 are spherical, which can reduce the sliding of the two locking pins 6 on the outward guiding inclined surface, as well as the jamming when inserting and removing from the locking pin openings, and can reduce the wear between the structures.

[0078] In some optional embodiments, in the above-mentioned aircraft crew emergency escape hatch, the driving rocker arm 10 is located between the hatch opening stop block 3 and the hatch closing stop block 4, such as Figure 7 shown.

[0079] In some optional embodiments, the above-mentioned aircraft crew emergency escape hatch further includes:

[0080] The transfer rod 15 has one end connected to the transverse connecting rod 8 and the other end hinged to the end of the driving connecting rod 9 facing away from the driving rocker arm 10 .

[0081] In some optional embodiments, the above-mentioned aircraft crew emergency escape hatch further includes:

[0082] Two diagonal bracing rods 16 are obliquely connected between the two ends of the transverse link 8 and one end of the transfer rod 15 facing away from the transverse link 8 to form a triangular stable supporting structure.

[0083] In some optional embodiments, the above-mentioned aircraft crew emergency escape hatch further includes:

[0084] The driving rocker arm 17 is hinged on the inner side of the door 1 and has two hinged joints, wherein one hinged joint is hinged to the end of the driving connecting rod 9 facing away from the driving rocker arm 10, and can be specifically hinged by a single-double-ear structure;

[0085] The transmission connecting rod 18 has one end hinged to another hinged joint, specifically through a single-double ear structure, and the other end hinged to one end of the transfer rod 15 facing away from the transverse connecting rod 8, specifically through a single-double ear structure, to transmit between the driving connecting rod 9 and the transverse connecting rod 8.

[0086] The above embodiment discloses the assembly relationship of the partial structure of the aircraft crew emergency escape hatch, such as Figure 8 shown.

[0087] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0088] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An emergency escape hatch for an aircraft crew, characterized in that: include: A hatch (1) is arranged at the exit of the escape passage (2) and opens outwards, and the inner side of the hatch (1) is provided with a hatch opening stopper (3) and two lock pin guide holes and a lock pin support hole; Two locking blocks (5) are connected to the exit of the escape passage (2) and have locking pin openings; Two locking pins (6) have an annular protrusion on the side wall, the tails are inserted into the two locking pin guide holes, and the heads extend out of the two locking pin support holes; Two return springs (7) have their two ends pressed against the front end of the lock pin guide hole and the annular protrusion, and rely on elastic force to insert the heads of the two lock pins (6) into the two lock pin holes, thereby locking the hatch (1) in a closed position; A transverse connecting rod (8), both ends of which are sleeved on the outer circumference of the two locking pins (6); A driving connecting rod (9), one end of which is hinged on the transverse connecting rod (8); A driving rocker arm (10), the middle part of which is hinged to the inner side of the door (1), and a door opening driving block (11) is provided thereon, one end of which is hinged to the other end of the driving connecting rod (9); An actuator (13) is hinged between the inner side of the exit of the escape passage (2) and the other end of the driving rocker arm (10); When the piston rod of the actuator (13) is extended, it can drive the driving rocker arm (10) to rotate, and then through the driving connecting rod (9) and the transverse connecting rod (8), overcome the elastic force of the return spring (7) to pull the two locking pins (6), so that the heads of the two locking pins (6) are separated from the locking pin openings, thereby releasing the lock of the cabin door (1) in the closed position, and then the opening drive block (11) is pressed against the cabin door opening stop block (3), driving the cabin door (1) to open.

2. The aircraft crew emergency escape hatch according to claim 1, characterized in that: Two return springs (7) are sleeved on the outer circumferences of the two lock pins (6).

3. The aircraft crew emergency escape hatch according to claim 1, characterized in that: The driving rocker arm (10) and the driving connecting rod (9) are hingedly connected via a single-ear and double-ear structure.

4. The aircraft crew emergency escape hatch according to claim 1, characterized in that: The actuator (13) is hinged to the inner side of the exit of the escape passage (2) and the driving rocker arm (10) through a single-ear and double-ear structure.

5. The aircraft crew emergency escape hatch according to claim 1, characterized in that: The inner side of the door (1) is provided with a door closing stopper (4); The two locking blocks (5) are provided with outward guiding inclined surfaces; A hatch door closing drive block (12) is provided on the driving rocker arm (10); When the piston rod of the actuator (13) contracts, it can drive the driving rocker arm (10) to rotate, so that the hatch door closing drive block (12) abuts against the hatch door closing stop block (4), driving the hatch door to close. During this process, the heads of the two lock pins (6) abut against the two outward guide slopes and slide along the outward guide slopes, overcoming the elastic force of the return spring (7) to push the two lock pins (6). After bypassing the outward guide slopes, under the action of the elastic force of the return spring (7), the heads of the two lock pins (6) are reinserted into the two lock pin holes, locking the hatch door (1) in the closed position.

6. The aircraft crew emergency escape hatch according to claim 5, characterized in that: The driving rocker arm (10) is located between the cabin door opening stop block (3) and the cabin door closing stop block (4).

7. The aircraft crew emergency escape hatch according to claim 1, characterized in that: A skin is arranged on the inner side of the hatch (1).

8. The aircraft crew emergency escape hatch according to claim 1, characterized in that: The inlet of the escape passage (2) is opened on the floor of the cockpit, and the outlet of the escape passage (2) is opened at the lower left part of the nose of the aircraft.

9. The aircraft crew emergency escape hatch according to claim 1, characterized in that: Also includes: Two suspension rocker arms (14) have one end connected to the inner side of the door (1) close to the edge of one vertical side of the door (1), and the other end bent and hinged to the inner side of the exit of the escape passage (2).

10. The aircraft crew emergency escape hatch according to claim 9, characterized in that: The two suspension rocker arms (14) and the inner side of the exit of the escape passage (2) are hingedly connected through a single-double-ear structure.

11. The aircraft crew emergency escape hatch according to claim 1, characterized in that: The two lock pin openings are arc-shaped openings; The heads of the two locking pins (6) are spherical.

12. The aircraft crew emergency escape hatch according to claim 1, characterized in that: Also includes: The transfer rod (15) has one end connected to the transverse connecting rod (8) and the other end hinged to an end of the driving connecting rod (9) facing away from the driving rocker arm (10).

13. The aircraft crew emergency escape hatch according to claim 12, characterized in that: Also includes: Two oblique bracing rods (16) are obliquely connected between the two ends of the transverse connecting rod (8) and one end of the transfer rod (15) facing away from the transverse connecting rod (8).

14. The aircraft crew emergency escape hatch according to claim 12, characterized in that: Also includes: A driving rocker arm (17) is hinged on the inner side of the cabin door (1) and has two hinged joints, wherein one of the hinged joints is hinged to an end of the driving connecting rod (9) facing away from the driving rocker arm (10); The transmission connecting rod (18) has one end hinged to another hinged joint, and the other end hinged to one end of the transfer rod (15) facing away from the transverse connecting rod (8).

15. The aircraft crew emergency escape hatch according to claim 14, characterized in that: The upper articulated joint of the transmission rocker arm (17) and the driving connecting rod (9) are articulated by a single-double-ear structure.

16. The aircraft crew emergency escape hatch according to claim 14, characterized in that: The transmission connecting rod (18) and the upper hinge joint of the transmission rocker arm (17) are hinged through a single-double-ear structure.

17. The aircraft crew emergency escape hatch according to claim 14, characterized in that: The transmission connecting rod (8) and the transfer rod (15) are hingedly connected through a single-double-ear structure.

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