CN214729620U - Cabin door opening and closing mechanism - Google Patents
Cabin door opening and closing mechanism Download PDFInfo
- Publication number
- CN214729620U CN214729620U CN202022297180.8U CN202022297180U CN214729620U CN 214729620 U CN214729620 U CN 214729620U CN 202022297180 U CN202022297180 U CN 202022297180U CN 214729620 U CN214729620 U CN 214729620U
- Authority
- CN
- China
- Prior art keywords
- cabin door
- retractable
- connecting rod
- hinge
- side plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Abstract
The utility model discloses a cabin door opening and closing mechanism, which comprises a cabin door, a cabin door hinge, a connecting rod 1, a connecting rod 2, a connecting rod 3, a rotary joint, a cabin door side plate connecting block and other parts, if a retractable supporting rod 20 moves towards the retractable outer cylinder 12 along the axis of the retractable outer cylinder 12 to drive the retractable part 1 to rotate around a pin shaft 4, the retractable part 1 rotates and simultaneously drives the connecting rod 1(7) connected with the retractable part 1 to move, and simultaneously drives the connecting rod 2(9), the rotary joint 19 and the connecting rod 3(18) to move, under the drive of the connecting rod 3(18), a cabin door 16 rotates around a rotating shaft of a cabin door hinge 6 to close the cabin door 16, the cabin door opening and closing mechanism of the utility model can realize that one set of actuating mechanisms simultaneously finishes the retraction and the opening and closing of the cabin door, can be used for the occasions of the combined opening and closing of the aircraft and the cabin door, including the aircraft landing gear cabin, and also can be used for the occasions of the combined opening and closing of other parts and the cabin door, including aircraft load compartments.
Description
Technical Field
The invention relates to a cabin door opening and closing mechanism, and belongs to the technical field of reliability design of airplane bodies.
Background
The existing aircraft landing gear cabin door and the existing landing gear are mainly controlled independently, so that the existing aircraft landing gear cabin door and the existing landing gear are suitable for large-sized aircraft, and if the existing aircraft landing gear cabin door and the existing landing gear are used on small-sized aircraft, the following defects exist:
1. the small airplane is light in weight, and if the retraction and release of the landing gear and the opening and closing of the door of the landing gear are independently controlled, at least two sets of executing devices are needed, so that the extra weight is increased, and the load capacity of the small airplane is reduced.
2. The small airplane has compact space, and the arrangement of more than two sets of executing devices occupies too much space, and influences the equipment or function layout of the airplane and the like.
3. The power and energy of the small aircraft are limited, and the energy distribution and the flight performance are influenced by arranging more than two sets of executing devices.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, and the cabin door opening and closing mechanism is provided, so that a set of actuating mechanism can simultaneously complete part folding and unfolding and the opening and closing of the cabin door, can be used for occasions where the landing gear and the cabin door of the airplane are jointly opened and closed, and can also be used for occasions where other parts and the cabin door are jointly opened and closed.
The technical scheme of the invention is as follows: a hatch door opening and closing mechanism comprising: the device comprises a retractable part (1), a cabin door hinge, a pin shaft (4), a lug (5), a first connecting rod (7), a connecting block (8) of a side plate of a machine body, a second connecting rod (9), a connecting pin (10) of the side plate of the cabin door, a retractable outer cylinder (12), a retractable connecting lug (14), a retractable connecting pin (15), the cabin door (16), a connecting block (17) of the cabin door, a third connecting rod (18), a rotary joint (19) and a retractable support rod (20);
a hatch hinge comprising: a lower door hinge end (3) and an upper door hinge end (6); one end of the cabin door hinge is a cabin door hinge lower end (3), and the other end is a cabin door hinge upper end (6);
the frame plate (2), the side plate (11) of the machine body and the retractable connecting frame plate (13) are used as the frame part of the cabin door opening and closing mechanism; the lug (5) is connected with the frame plate (2) through a fastener; the side plate connecting block (8) of the machine body is connected with the side plate (11) of the machine body through a fastener; the upper end (6) of the cabin door hinge is connected with a connecting block (8) of a side plate of the fuselage, and the lower end (3) of the cabin door hinge is connected with a cabin door (16); the retractable connecting lug (14) is connected with the retractable connecting frame plate (13) through a fastener;
one end of the retractable part (1) is hinged with the lug plate (5) through a pin shaft (4), and the middle part of the retractable part (1) is hinged with one end of the retractable stay bar (20); the other end of the retractable support rod (20) is connected with one end of the retractable outer cylinder (12) and can be retracted into and extended out of one end of the retractable outer cylinder (12); the other end of the retractable outer cylinder (12) is hinged with a retractable connecting lug (14);
one end of the part (1) is provided with a raised cylindrical structure (1A), one end of a first connecting rod (7) is hinged with the cylindrical structure (1A), and a hinged shaft of the first connecting rod (7) hinged with the cylindrical structure (1A) is parallel to a hinged shaft of the part (1) hinged with the lug piece (5);
the other end of the first connecting rod (7) is hinged with one end of a second connecting rod (9), the middle part of the second connecting rod (9) is provided with a shaft hole, and the shaft hole can penetrate through a cabin door side plate connecting pin (10) and extend into the machine body side plate connecting block (8), so that the second connecting rod (9) rotates relative to the machine body side plate connecting block (8) by taking the cabin door side plate connecting pin (10) as a shaft; the other end of the second connecting rod (9) is connected with one end of a third connecting rod (18) through a rotating joint (19), and the other end of the third connecting rod (18) is connected with a cabin door connecting block (17); the cabin door connecting block (17) is connected with the cabin door through a fastener.
Preferably, the frame plate (2), the side plate (11) of the machine body and the folding and unfolding connecting frame plate (13) are used as a rack part of the cabin door opening and closing mechanism, and the constraint space has 6 degrees of freedom; the lug (5) is connected with the frame plate (2) through a fastener, and the lug (5) is restrained in 6 degrees of freedom in space; the side plate connecting block (8) of the machine body is connected with the side plate (11) of the machine body through a fastener, and the side plate connecting block (8) of the machine body is restrained to have 6 degrees of freedom in space; one end of the cabin door hinge (6) is connected with the connecting block (8) of the side plate of the fuselage and the cabin door (16); the retractable connecting lug (14) is connected with the retractable connecting frame plate (13) through a fastener, and the retractable connecting lug (14) is restrained in the space with 6 degrees of freedom.
Preferably, one end of the part (1) is provided with a pin hole, the lug (5) is provided with a pin hole, the pin hole on the part (1) and the pin hole on the lug (5) are connected through a pin shaft (4), so that the part (1) and the lug (5) form hinge constraint, and the part (1) is constrained for 5 spatial degrees of freedom and can only rotate around the axis direction of the pin shaft (4); receive and release and have cylindrical structure (1A) on part (1), the axis of this cylindrical structure (1A) is parallel with round pin axle (4) axis, and this cylindrical structure (1A) is through the part that will have cylindrical structure with receive and release part (1) and be connected the realization through the fastener.
Preferably, one end (7A) of the first connecting rod (7) and the cylindrical structure (1A) of the retractable part (1) are in hinge constraint or ball hinge constraint, the ball hinge constraint can avoid the situation that the motion clamping stagnation of the cabin door opening and closing mechanism is caused by the fact that the processing precision of the first connecting rod (7) does not reach the standard, and the other end (7B) of the connecting rod (1) and one end (9A) of the second connecting rod (9) are in hinge constraint; the axes constrained by the hinges at the two ends of the first connecting rod (7) are parallel to the axis of the pin shaft (4).
Preferably, one end (9A) of the second connecting rod (9) and the other end (7B) of the first connecting rod (7) are constrained by a hinge, and the axis of a hinge shaft constrained by the hinge is parallel to the axis of the pin shaft (4); the middle part (9B) of the second connecting rod (9) forms hinge constraint with the machine body side plate connecting block (8) through a cabin door side plate connecting pin (10), and the axis of the cabin door side plate connecting pin (10) is parallel to the axis of the pin shaft (4); the other end (9C) of the second connecting rod (9) and one end (19B) of the rotating joint (19) are constrained by a hinge, one end (19B) of the rotating joint (19) is a rotating shaft, and the axis of the rotating shaft is parallel to the normal plane of the axis of the pin shaft (4); one end (9B) of the second link (9) changes the position of a third link (18) connected to the other end (19A) of the rotary joint (19) while ensuring that the direction of the axis of rotation thereof does not change.
Preferably, one end (19B) of the rotating joint (19) and the other end (9C) of the second connecting rod (9) are constrained by a hinge; the other end (19A) of the rotating joint (19) and one end (18A) of the third connecting rod (18) are constrained by a hinge; the axis of the rotating shaft at one end of the rotating joint (19) is perpendicular to the hinge shaft of the other end (19A) of the rotating joint (19).
Preferably, one end (18A) of the third connecting rod (18) and the other end (19A) of the rotating joint (19) are in hinge constraint; the other end (18B) of the third connecting rod (18) and the hinged end (17A) of the cabin door connecting block (17) are in ball-and-socket constraint.
Preferably, the middle part of the retractable part (1) is provided with a cylindrical structure (1B), the axis of the cylindrical structure (1B) is parallel to the axis of the pin shaft (4), and the cylindrical structure (1B) can also be realized by connecting the part with the cylindrical structure and the retractable part (1) in other connection modes; one end (20A) of the retractable support rod (20) and the middle cylindrical structure (1B) of the retractable part (1) are in hinge constraint or spherical hinge constraint, and the spherical hinge constraint can avoid the motion clamping stagnation of the cabin door opening and closing mechanism caused by the failure in standard machining precision of the retractable support rod (20); the other end of the retractable outer cylinder (12) is provided with a lug structure (12A), and the lug structure (12A) is provided with a shaft hole; the retractable connecting lug (14) is provided with a hinged end, penetrates through a shaft hole on the lug structure (12A) through a retractable connecting pin (15), and is hinged with the other end of the retractable outer cylinder (12); the axis of the shaft hole of the lug structure (12A) is parallel to the axis of the pin shaft (4), and the lug structure can also be realized by connecting a part with the lug structure with the retractable outer cylinder (12) in other connecting modes; the other end (12A) of the retractable outer cylinder (12) and the retractable connecting lug (14) form hinge restraint through a retractable connecting pin (15).
Compared with the prior art, the invention has the advantages that:
(1) after the airplane takes off, the retractable support rod moves upwards under the action of a power source, drives a series of connecting rods to move and close the cabin door while driving the retractable parts to be retracted into the airplane body cabin, and moves downwards before the airplane lands, and closes the cabin door while driving the retractable parts to come out of the airplane body cabin. The mechanism can realize the retraction of the landing gear and the opening and closing of the cabin door at the same time, and can also be used for the retraction of special loads on the airplane and the opening and closing of the load cabin door.
(2) In the invention, in the process that the retractable support rod moves upwards to the limit position, the cabin door is opened at a certain angle and then closed, so that the interference between the cabin door and the retractable support rod or retractable parts when the cabin door is closed can be avoided to a limited extent.
(3) In the invention, the connecting rods and the retractable support rods are uniformly distributed at the positions close to the side plate of the machine body, and when the retractable parts are put down, the reserved space is favorable for maintaining the device in the cabin, thereby improving the accessibility and the maintainability.
(4) In the invention, most parts adopt the low-pair connection relationship, the pressure intensity at the connection position is small, the connection relationship is simple, the stress of each connecting rod is small, and the reliability is improved.
Drawings
FIG. 1 is a schematic view of the non-retracted position of the components of the present invention.
FIG. 2 is a schematic view of the invention in a retracted intermediate position
FIG. 3 is a schematic view of the fully retracted position of the components of the present invention
FIG. 4 is a schematic view of a portion of the first link according to the present invention.
FIG. 5 is a schematic view of a portion of a second link according to the present invention.
FIG. 6 is a schematic view of a partial position of the outer cylinder of the present invention.
FIG. 7 is a schematic view of a partial position of the retractable stay of the present invention.
In the figure: 1-retracting parts, 2-frame plates, 3-lower ends of cabin door hinges, 4-pin shafts, 5-lugs, 6-upper ends of cabin door hinges, 7-first connecting rods, 8-connecting blocks of the side plates of the fuselage, 9-second connecting rods, 10-connecting pins of the side plates of the cabin doors, 11-side plates of the fuselage, 12-retracting outer cylinders, 13-retracting connecting frame plates, 14-retracting connecting lugs, 15-retracting connecting pins, 16-cabin doors, 17-connecting blocks of the cabin doors, 18-third connecting rods, 19-rotary joints and 20-retracting support rods; 1A-cylindrical structure.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
The invention discloses a cabin door opening and closing mechanism which comprises a cabin door, a cabin door hinge, a first connecting rod, a second connecting rod, a third connecting rod, a rotary joint, a cabin door side plate connecting block and the like, wherein if a retracting and releasing support rod 20 moves towards a retracting and releasing outer cylinder 12 along the axis of the retracting and releasing outer cylinder 12, the retracting and releasing part 1 is driven to rotate around a pin shaft 4, the retracting and releasing part 1 simultaneously drives a first connecting rod 7 connected with the retracting and releasing part 1 to move, and simultaneously drives a second connecting rod 9, a rotary joint 19 and a third connecting rod 18 to move, under the drive of the third connecting rod 18, a cabin door 16 rotates around a rotary shaft of a cabin door hinge 6 to close a cabin door 16, and similarly, if the retracting and releasing support rod 20 moves towards the outside of the retracting and releasing outer cylinder 12 along the axis of the retracting and releasing outer cylinder 12, the retracting and the retracting part 1 simultaneously drives the first connecting rod connected with the retracting and releasing part 1 to move, and simultaneously drives the second connecting rod, the rotary joint 19, The third connecting rod moves, and the cabin door 16 rotates around the rotating shaft of the cabin door hinge 6 under the driving of the third connecting rod, so that the cabin door 16 is opened; the cabin door opening and closing mechanism can realize that one set of actuating mechanism can simultaneously complete the folding and unfolding of parts and the opening and closing of the cabin door, can be used for the occasions of combined opening and closing of the undercarriage and the cabin door, including the undercarriage cabin, and can also be used for the occasions of combined opening and closing of other parts and the cabin door, including the loading cabin of an airplane.
The mechanism is used for realizing that a set of actuating device simultaneously controls the retraction and the opening and the closing of the landing gear door of the small aircraft, and can also be used for realizing the linkage of the retraction and the opening and the closing of special load equipment on the aircraft and the opening and the closing of the load door. After the mechanism is adopted, the weight increasing problem caused by adopting two or more sets of executing devices can be effectively solved, the connecting rods are relatively small in stress, the connection relation is simple, the reliability is high, in addition, the connecting rods and the retractable support rods are uniformly distributed at the positions close to the side plates of the machine body, when the retractable parts are put down, the reserved space is favorable for maintaining the devices in the cabin, and the accessibility and the maintainability are improved.
As shown in fig. 1, the preferred scheme is: the frame plate 2, the side plate 11 of the machine body and the retractable connecting frame plate 13 are used as a rack part of the cabin door opening and closing mechanism, and the specific requirements are as follows: the included angle between the normal of the plane of the frame plate 2 and the normal of the plane of the retractable connecting frame plate 13 is not more than 20 degrees, and the plane of the side plate 11 of the machine body is vertical to the plane of the frame plate 2 and the plane of the retractable connecting frame plate 13.
The mechanism of the present invention comprises: the device comprises a retractable part 1, a cabin door hinge, a pin shaft 4, a lug 5, a first connecting rod 7, a body side plate connecting block 8, a second connecting rod 9, a cabin side plate connecting pin 10, a retractable outer cylinder 12, a retractable connecting lug 14, a retractable connecting pin 15, a cabin door 16, a cabin door connecting block 17, a third connecting rod 18, a rotary joint 19 and a retractable support rod 20;
a hatch hinge comprising: a cabin door hinge lower end 3 and a cabin door hinge upper end 6; one end of the cabin door hinge is a cabin door hinge lower end 3, and the other end is a cabin door hinge upper end 6;
the frame plate 2, the side plate 11 of the machine body and the folding and unfolding connecting frame plate 13 are used as a frame part of the cabin door opening and closing mechanism; the lug 5 is connected with the frame plate 2 through a fastener; the side plate connecting block 8 of the machine body is connected with the side plate 11 of the machine body through a fastener; the upper end 6 of the cabin door hinge is connected with a connecting block 8 of a side plate of the fuselage, and the lower end 3 of the cabin door hinge is connected with a cabin door 16; the retractable connecting lug 14 is connected with the retractable connecting frame plate 13 through a fastener;
one end of the retractable part 1 is hinged with the lug 5 through a pin shaft 4, and the middle part of the retractable part 1 is hinged with one end of a retractable stay bar 20; the other end of the retractable support rod 20 is connected with one end of the retractable outer cylinder 12 and can be retracted into and extended out of one end of the retractable outer cylinder 12; the other end of the retractable outer cylinder 12 is hinged with a retractable connecting lug 14;
one end of the part 1 is provided with a raised cylindrical structure 1A, one end of a first connecting rod 7 is hinged with the cylindrical structure 1A, and a hinged shaft of the first connecting rod 7 hinged with the cylindrical structure 1A is parallel to a hinged shaft of the part 1 hinged with the lug 5;
the other end of the first connecting rod 7 is hinged with one end of a second connecting rod 9, the middle part of the second connecting rod 9 is provided with a shaft hole which can penetrate through a cabin door side plate connecting pin 10 and extend into the machine body side plate connecting block 8, so that the second connecting rod 9 rotates relative to the machine body side plate connecting block 8 by taking the cabin door side plate connecting pin 10 as a shaft; the other end of the rod 29 is connected with one end of a third connecting rod 18 through a rotary joint 19, and the other end of the third connecting rod 18 is connected with the cabin door connecting block 17; the hatch connecting block 17 is connected with the hatch through a fastener.
The preferred scheme is as follows: the frame plate 2, the side plate 11 of the machine body and the folding and unfolding connecting frame plate 13 are used as a rack part of the cabin door opening and closing mechanism, and the confined space has 6 degrees of freedom; the lug 5 is connected with the frame plate 2 through a fastener, and the lug 5 is restrained in 6 degrees of freedom in space; the side plate connecting block 8 of the machine body is connected with the side plate 11 of the machine body through a fastener, and the side plate connecting block 8 of the machine body is restrained to have 6 degrees of freedom in space; one end of the cabin door hinge 6 is connected with a connecting block 8 of the side plate of the fuselage and a cabin door 16; the retractable connecting lug 14 is connected with the retractable connecting frame plate 13 through a fastener, and the retractable connecting lug 14 is restrained in the space with 6 degrees of freedom.
The preferred scheme is as follows: one end of the part 1 is provided with a pin hole, the lug 5 is provided with a pin hole, the pin hole on the part 1 and the pin hole on the lug 5 are connected through a pin shaft 4, so that the part 1 and the lug 5 form hinge constraint, and the part 1 is constrained for 5 spatial degrees of freedom and can only rotate around the axis direction of the pin shaft 4; receive and release and have cylindrical structure 1A on the part 1, this cylindrical structure 1A's axis is parallel with 4 axes of round pin axle, and this cylindrical structure 1A realizes through the part with cylindrical structure with receive and release part 1 and be connected through the fastener.
The preferred scheme is as follows: one end 7A of the first connecting rod 7 and the cylindrical structure 1A of the retractable part 1 are in hinge constraint or spherical hinge constraint, the spherical hinge constraint can avoid the situation that the motion of the cabin door opening and closing mechanism is blocked due to the fact that the machining precision of the first connecting rod 7 does not meet the standard, and the other end 7B of the connecting rod 1 and one end 9A of the second connecting rod 9 are in hinge constraint; the axes constrained by the hinges at the two ends of the first connecting rod 7 are parallel to the axis of the pin shaft 4.
The preferred scheme is as follows: one end 9A of the second connecting rod 9 and the other end 7B of the first connecting rod 7 are constrained by a hinge, and the axis of a hinged shaft constrained by the hinge is parallel to the axis of the pin shaft 4; the middle part 9B of the second connecting rod 9 forms hinge constraint with the body side plate connecting block 8 through a cabin door side plate connecting pin 10, and the axis of the cabin door side plate connecting pin 10 is parallel to the axis of the pin shaft 4; the other end 9C of the second connecting rod 9 and one end 19B of the rotating joint 19 are in hinge constraint, one end 19B of the rotating joint 19 is a rotating shaft, and the axis of the rotating shaft is parallel to the normal plane of the axis of the pin shaft 4; one end 9B of the second link 9 changes the position of the third link 18 connected to the other end 19A of the rotary joint 19 while securing the direction of the rotational axis thereof unchanged.
The preferred scheme is as follows: one end 19B of the rotating joint 19 and the other end 9C of the second connecting rod 9 are constrained by a hinge; the other end 19A of the rotating joint 19 and one end 18A of the third connecting rod 18 are constrained by a hinge; the axis of the rotary shaft at one end of the rotary joint 19 is perpendicular to the hinge axis of the other end 19A of the rotary joint 19.
The preferred scheme is as follows: one end 18A of the third connecting rod 18 and the other end 19A of the rotating joint 19 are constrained by a hinge; the other end 18B of the third link 18 is ball-and-socket constrained with the hinged end 17A of the door connector block 17.
The preferred scheme is as follows: the middle part of the retractable part 1 is provided with a cylindrical structure 1B, the axis of the cylindrical structure 1B is parallel to the axis of the pin shaft 4, and the cylindrical structure 1B can also be realized by connecting a part with a cylindrical structure with the retractable part 1 in other modes; one end 20A of the retractable support rod 20 and the middle cylindrical structure 1B of the retractable part 1 are in hinge constraint or spherical hinge constraint, and the spherical hinge constraint can avoid the motion clamping stagnation of the cabin door opening and closing mechanism caused by the failure in standard machining precision of the retractable support rod 20; the other end of the retractable outer cylinder 12 is provided with a lug structure 12A, and the lug structure 12A is provided with a shaft hole; the retractable connecting lug 14 is provided with a hinged end, penetrates through a shaft hole on the lug structure 12A through a retractable connecting pin 15 and is hinged with the other end of the retractable outer cylinder 12; the axis of the shaft hole of the lug structure 12A is parallel to the axis of the pin shaft 4, and the lug structure can also be realized by connecting a part with the lug structure with the retractable outer cylinder 12 in other connection modes; the other end 12A of the retractable outer cylinder 12 and the retractable connecting lug 14 form hinge constraint through a retractable connecting pin 15.
The preferred scheme is as follows: the lower end 3 of the cabin door hinge is connected with the cabin door 16 through a fastener; the upper end 6 of the cabin door hinge is connected with the side plate 11 of the fuselage through a fastener; the upper end 6 of the cabin door hinge and the lower end 3 of the cabin door hinge form hinge restriction, the axis of the hinge is vertical to the axis of the pin shaft 4, and the cabin door 16 can rotate around the side plate 11 of the fuselage.
The further preferable scheme is as follows: the retractable support rod 20 and the retractable outer cylinder 12 are in movement restriction and are realized in a hydraulic, electric or pneumatic mode; under the action of a power source, the retractable support rod 20 moves upwards along the axis direction of the retractable outer cylinder 12 to drive the retractable part 1 to rotate around the axis direction of the pin shaft 4, the cylindrical structure 1A of the retractable part 1 drives one end 7A of the first connecting rod 7 to move, the other end 7B of the first connecting rod 7 drives one end 9A of the second connecting rod 9 to move, the middle part of the second connecting rod 9 rotates around the cabin door side plate connecting pin 10, the other end 9C of the second connecting rod 9 drives the rotary joint 19 to move, the cabin door connecting block 17 is further pulled through the third connecting rod 18, and the cabin door connecting block 17 is connected with the cabin door 16 through a fastener, so that the third connecting rod 18 pulls the cabin door 16 simultaneously, and finally the cabin door 16 rotates around the machine body side plate 11 to realize the opening and closing of the cabin door.
The further preferable scheme is as follows: in the process that the retractable support rod 20 moves upwards along the axial direction of the retractable outer cylinder 12, the cabin door 16 firstly rotates 10 degrees to 15 degrees outwards around the side plate 11 of the fuselage and then rotates inwards until the closing is realized, so that the interference between the cabin door 16 and the retractable part 1 or the support rod 20 when directly rotating inwards can be avoided.
The further preferable scheme is as follows: all the connecting rods, the retractable support rods 20 and the retractable outer cylinder 12 are uniformly arranged at positions close to the side plate 11 of the machine body, and when retractable parts are put down, enough space is reserved in the cabin for checking and maintaining internal parts or devices.
The further preferable scheme is as follows: if the retractable support rod 20 moves towards the retractable outer cylinder 12 along the axis of the retractable outer cylinder 12 to drive the retractable part 1 to rotate around the pin shaft 4, the retractable part 1 rotates and simultaneously drives the first connecting rod 7 connected with the retractable part to move, and simultaneously drives the second connecting rod 9, the rotary joint 19 and the third connecting rod 18 to move, under the drive of the third connecting rod 18, the cabin door 16 rotates around the rotating shaft of the cabin door hinge 6 to close the cabin door 16, similarly, if the retractable support rod 20 moves towards the outside of the retractable outer cylinder 12 along the axis of the retractable outer cylinder 12 to drive the retractable part 1 to rotate around the pin shaft, the retractable part 1 rotates and simultaneously drives the first connecting rod 7 connected with the retractable part to move, and simultaneously drives the second connecting rod 9, the rotary joint 19 and the third connecting rod 18 to move, under the drive of the third connecting rod 18, the cabin door 16 rotates around the rotating shaft of the cabin door hinge 6 to open the cabin door 16; the cabin door opening and closing mechanism can realize that one set of actuating mechanism can simultaneously complete the folding and unfolding of parts and the opening and closing of the cabin door, is used for the occasions of combined opening and closing of the aircraft landing gear and the cabin door, comprises an aircraft landing gear cabin, and can also be used for the occasions of combined opening and closing of other parts and the cabin door, comprises an aircraft load cabin.
The preferred scheme is as follows: the retractable part 1 is not fixed in shape, can represent an undercarriage on an airplane, can also represent a load device on the airplane or any other device needing the retractable function, and the retractable part 1 needs to meet the following conditions that a cylindrical structure capable of rotating around a pin shaft 4 is arranged on the retractable part, and the axis of the cylindrical structure 1A and the axis of the cylindrical structure 1B are both parallel to the axis of the pin shaft 4.
The preferred scheme is as follows: the retractable support rod 20 moves along the axis of the retractable outer cylinder 12 through an external power source, the external power source can be electric, hydraulic or pneumatic, and if the external power source is driven by a motor, the interior of the retractable outer cylinder 12 is connected with the retractable support rod 20 through a ball screw structure; if the hydraulic cylinder or the air cylinder is adopted for driving, the retractable support rod 20 is connected with a piston rod of the hydraulic cylinder or the air cylinder, and the piston rod is pushed to move through hydraulic pressure or air pressure, so that the retractable support rod 20 is driven to move.
As shown in fig. 1 to 7, a preferred embodiment of a hatch opening and closing mechanism is: wherein the frame plate, the side plate of the machine body and the retractable connecting frame plate are used as a frame part of the mechanism, and the constrained space has 6 degrees of freedom; the lug plate is connected with the frame plate through a fastener, and the space of the lug plate is restrained by 6 degrees of freedom; the connecting block of the side plate of the machine body is connected with the side plate of the machine body through a fastening piece to restrict the space of the connecting block of the side plate of the machine body to 6 degrees of freedom; the upper end of the cabin door hinge is connected with the connecting block of the side plate of the fuselage through a fastener, so that the space of the cabin door hinge is restrained by 6 degrees of freedom; the retractable connecting lug plate and the retractable connecting frame plate are connected through a fastener, and 6 degrees of freedom of the space are restricted.
The pin holes on the retractable parts and the pin holes on the lugs are connected through pin shafts, so that the retractable parts and the lugs form hinge constraint, and the retractable parts are constrained for 5 spatial degrees of freedom and can only rotate around the axis direction of the pin shafts; the part that receive and releases has cylindrical structure 1A on the part, and the axis of this cylindrical structure is parallel with round pin axle axis, and this cylindrical structure also can be realized through passing through the fastener with the part that has cylindrical structure with receive and release the part and be connected.
The two ends of the first connecting rod can be connected with other parts to form movement restriction; one end 7A of the first connecting rod and the cylindrical structure 1A of the retractable part are in hinge constraint or spherical hinge constraint, the spherical hinge constraint can avoid mechanism motion clamping stagnation caused by poor part machining precision, and the other end 7B of the first connecting rod and one end 9A of the second connecting rod are in hinge constraint; the axes constrained by the hinges at the two ends of the first connecting rod are parallel to the axis of the pin shaft 4.
The two ends and the middle part of the second connecting rod can be connected with other parts to form movement restriction; one end 9A of the second connecting rod and one end 7B of the first connecting rod are constrained by a hinge, and the direction is parallel to the axis of the pin shaft; the middle part 9B of the second connecting rod forms hinge constraint with a connecting block of a side plate of the machine body through a connecting pin of the side plate of the cabin door, and the direction of the hinge constraint is parallel to the axis of the pin shaft; the other end 9C of the second connecting rod and one end 19B of the rotary joint are constrained by a hinge, and the direction is parallel to the normal plane of the axis of the pin shaft; the second link middle part 9B can change its position while ensuring that its rotational axis direction is unchanged, but is interposed between the second link ends 9A and 9C.
The two ends of the rotary joint can be connected with other parts to form movement constraint; one end 19B of the rotary joint and one end 9C of the second connecting rod are constrained by a hinge; the other end 19A of the rotating joint and one end 18A of the third connecting rod are constrained by a hinge; the rotation axes of the two ends of the rotary joint are perpendicular to each other.
The two ends of the third connecting rod can be connected with other parts to form movement restriction; one end 18A of the third connecting rod and one end 19A of the rotating joint are constrained by a hinge; the other end 18B of the third connecting rod and one end 17A of the cabin door connecting block are in ball-and-socket constraint.
The retractable part is provided with a cylindrical structure 1B, the axis of the cylindrical structure is parallel to the axis of the pin shaft, and the cylindrical structure can also be realized by connecting the part with the cylindrical structure and the retractable part in other connection modes; one end 20A of the retractable stay bar and one end 1B of the retractable part are in hinge constraint or spherical hinge constraint, and the spherical hinge constraint can avoid mechanism motion clamping stagnation caused by poor part machining precision; the retractable outer barrel is provided with a lug structure 12A, the axis of the lug structure is parallel to the axis of the pin shaft, and the lug structure can also be realized by connecting a part with the lug structure with the retractable outer barrel in other connecting modes; one end 12A of the retractable outer cylinder and the retractable connecting lug form hinge restraint through the retractable connecting pin.
The lower end of the cabin door hinge is connected with the cabin door through a fastener; the upper end of the cabin door hinge is connected with the side plate of the fuselage through a fastener; because the upper end of the cabin door hinge and the lower end of the cabin door hinge form hinge constraint, and the hinge axis is vertical to the axis of the pin shaft, the cabin door can rotate around the side plate of the fuselage.
The retractable support rod and the retractable outer cylinder are movably constrained and can be realized in a hydraulic, electric or pneumatic mode and the like; under the effect of the power source, the retractable supporting rod can move upwards along the axial direction of the retractable outer cylinder, the retractable part is driven to rotate around the axial direction of the pin shaft, one end 1A of the retractable part drives one end 7A of the first connecting rod to move, the other end 7B of the first connecting rod drives one end 9A of the second connecting rod to move, the second connecting rod rotates around the lateral plate connecting pin of the cabin door, the other end 9C of the second connecting rod drives the rotary joint to move, the cabin door connecting block is further pulled through the third connecting rod, the cabin door connecting block is connected with the cabin door through the fastener, therefore, the cabin door is pulled simultaneously through the third connecting rod, and finally, the cabin door rotates around the side plate of the machine body.
The preferable working mode of the hatch door opening and closing mechanism is as follows:
as shown in fig. 1, when the retractable elements are in the non-retracted position, the retractable stay is in the longest extended position, the angle between the cabin door and the side plate of the fuselage is greater than 90 degrees, and the first connecting rod and the second connecting rod are not in the parallel position.
As shown in fig. 2, 3, 4, 5, 6 and 7, under the action of a power source, because the retractable part and the lug are in hinge connection, one end 20A of the retractable stay bar is in hinge connection with one end 1B of the retractable part, the retractable stay bar can pull the retractable part to rotate around the pin shaft when moving upwards along the axis of the retractable outer cylinder, and because one end 7A of the first connecting rod is in hinge connection with the retractable part, the retractable part lifts the end of the first connecting rod while rotating, the first connecting rod is driven to pull one end 9A of the second connecting rod to rotate around the cabin door side plate connecting pin, and the other end 9C of the second connecting rod, one end 19A of the rotary joint and one end 18A of the third connecting rod are driven to lift. Finally, the third connecting rod pulls the cabin door connecting block fixedly connected with the cabin door, so that the cabin door rotates around the cabin door hinge rotating shaft, and the cabin door is closed.
As shown in fig. 2, when the retractable part is in the retracted middle position, the retractable part rotates by a certain angle, a part of the retractable stay bar extends out of the retractable outer cylinder, the angle between the cabin door and the side plate of the fuselage is greater than 90 degrees, and the first connecting rod and the second connecting rod are not in a parallel position.
As shown in fig. 3, when the retractable part is in the fully retracted position, the retractable part rotates by approximately 90 degrees, the retractable stay bar fully extends into the retractable outer cylinder, the angle between the cabin door and the side plate of the fuselage is approximately 90 degrees, and the first connecting rod and the second connecting rod are in an approximately parallel position.
In the state of fig. 3, if the retractable stay bar extends out of the retractable outer cylinder, the retractable parts can be put down, and the cabin door is opened, and the process is similar to the process described above.
In the whole process of folding and unfolding and opening the cabin door, the folding and unfolding parts move stably, the opening and unfolding position of the cabin door is accurate, and the whole mechanism is small in mass, compact in space and convenient to use and maintain.
The invention realizes the improvement of the stability of the mechanism. Further scheme: setting the plane of the side plate 11 of the machine body as a projection plane; the length of the distance from the axis of the pin shaft 4 to the axis of the cylindrical structure 1A of the retractable part 1 on a projection plane is L1; let a distance from one end 7A of the first link 7 to the other end 7B of the first link 7 be L2 in the projection plane length, and let a distance from one end 9A of the second link 9 to the middle 9B of the second link 9 be L3 in the projection plane length; if the length of the projection plane from the axis of the pin 4 to the middle part 9B of the second link 9 is L4, the constraint condition L3+ L4 is satisfied, i.e., L1+ L2 is greater than or equal to L1, so that the stability of the mechanism can be improved, if L3+ L4 is L1+ L2, and the stability is 1 at this time, then L3+ L4 is K (L1+ L2), K is a coefficient, and the value is greater than 1, so that the stability is improved by K-1/K.
The invention realizes a further scheme for improving the safety of the mechanism: setting the mass of the retractable part 1 as M, the tension of the retractable stay bar 20 as F, the included angle between the axis of the retractable stay bar 20 and the plane of the retractable connecting frame plate 13 as theta, and the maximum theta angle theta exists in the retractable movementmaxIf (1) satisfies the constraint condition F ≥
10M*cosθmaxIf the safety is 1 when F is 10m × cos θ, F is K × 10m × cos θmaxK is a coefficient, the value is more than 1, and the safety is improved by K-1/K.
Through simulation, in the mechanism, the retractable part 1 is a landing gear, the exposed length of the retractable stay bar 20 is 430 mm, at the speed of 500 mm/min and after 48s, the retractable part 1 rotates 87 degrees around the pin shaft 4 and is retracted into a landing gear cabin, the retractable stay bar 20 is retracted into the retractable outer cylinder 12 and is exposed for 30 mm, the cabin door 16 firstly rotates 10 degrees outwards around a cabin door hinge and then rotates 90 degrees inwards to realize the closing of the cabin door, and in actual use, if the rotation angle of the cabin door does not meet the requirement, the retractable amount of the retractable stay bar can be increased, so that the cabin door rotates more than 90 degrees inwards to meet the use requirement. The mechanism has good retraction effect, no motion mutation in the retraction process, smooth process and certain use value.
Claims (7)
1. A hatch door opening and closing mechanism characterized by comprising: the device comprises a retractable part (1), a cabin door hinge, a pin shaft (4), a lug (5), a first connecting rod (7), a connecting block (8) of a side plate of a machine body, a second connecting rod (9), a connecting pin (10) of the side plate of the cabin door, a retractable outer cylinder (12), a retractable connecting lug (14), a retractable connecting pin (15), the cabin door (16), a connecting block (17) of the cabin door, a third connecting rod (18), a rotary joint (19) and a retractable support rod (20);
a hatch hinge comprising: a lower door hinge end (3) and an upper door hinge end (6); one end of the cabin door hinge is a cabin door hinge lower end (3), and the other end is a cabin door hinge upper end (6);
the frame plate (2), the side plate (11) of the machine body and the retractable connecting frame plate (13) are used as the frame part of the cabin door opening and closing mechanism; the lug (5) is connected with the frame plate (2) through a fastener; the side plate connecting block (8) of the machine body is connected with the side plate (11) of the machine body through a fastener; the upper end (6) of the cabin door hinge is connected with a connecting block (8) of a side plate of the fuselage, and the lower end (3) of the cabin door hinge is connected with a cabin door (16); the retractable connecting lug (14) is connected with the retractable connecting frame plate (13) through a fastener;
one end of the retractable part (1) is hinged with the lug plate (5) through a pin shaft (4), and the middle part of the retractable part (1) is hinged with one end of the retractable stay bar (20); the other end of the retractable support rod (20) is connected with one end of the retractable outer cylinder (12) and can be retracted into and extended out of one end of the retractable outer cylinder (12); the other end of the retractable outer cylinder (12) is hinged with a retractable connecting lug (14) through a retractable connecting pin (15);
one end of the part (1) is provided with a raised cylindrical structure (1A), one end of a first connecting rod (7) is hinged with the cylindrical structure (1A), and a hinged shaft of the first connecting rod (7) hinged with the cylindrical structure (1A) is parallel to a hinged shaft of the part (1) hinged with the lug piece (5);
the other end of the first connecting rod (7) is hinged with one end of a second connecting rod (9), the middle part of the second connecting rod (9) is provided with a shaft hole, and the shaft hole can penetrate through a cabin door side plate connecting pin (10) and extend into the machine body side plate connecting block (8), so that the second connecting rod (9) rotates relative to the machine body side plate connecting block (8) by taking the cabin door side plate connecting pin (10) as a shaft; the other end of the second connecting rod (9) is connected with one end of a third connecting rod (18) through a rotating joint (19), and the other end of the third connecting rod (18) is connected with a cabin door connecting block (17); the cabin door connecting block (17) is connected with the cabin door through a fastener.
2. The hatch opening and closing mechanism according to claim 1, characterized in that: the frame plate (2), the side plate (11) of the machine body and the folding and unfolding connecting frame plate (13) are used as the frame part of the cabin door opening and closing mechanism, and the constrained space has 6 degrees of freedom; the lug (5) is connected with the frame plate (2) through a fastener, and the lug (5) is restrained in 6 degrees of freedom in space; the side plate connecting block (8) of the machine body is connected with the side plate (11) of the machine body through a fastener, and the side plate connecting block (8) of the machine body is restrained to have 6 degrees of freedom in space; one end of the upper end (6) of the cabin door hinge is connected with a connecting block (8) of a side plate of the fuselage and a cabin door (16); the retractable connecting lug (14) is connected with the retractable connecting frame plate (13) through a fastener, and the retractable connecting lug (14) is restrained in the space with 6 degrees of freedom.
3. The hatch opening and closing mechanism according to claim 1, characterized in that: one end of the part (1) is provided with a pin hole, the lug (5) is provided with a pin hole, the pin hole on the part (1) and the pin hole on the lug (5) are connected through a pin shaft (4), so that the part (1) and the lug (5) form hinge constraint, and the part (1) is constrained for 5 spatial degrees of freedom and can only rotate around the axis direction of the pin shaft (4); receive and release and have cylindrical structure (1A) on part (1), the axis of this cylindrical structure (1A) is parallel with round pin axle (4) axis, and this cylindrical structure (1A) is through the part that will have cylindrical structure with receive and release part (1) and be connected the realization through the fastener.
4. The hatch opening and closing mechanism according to claim 1, characterized in that: one end of the first connecting rod (7) and the cylindrical structure (1A) of the retractable part (1) are in hinge constraint or spherical hinge constraint, the spherical hinge constraint can avoid the situation that the motion clamping stagnation of the cabin door opening and closing mechanism is caused by the fact that the processing precision of the first connecting rod (7) does not meet the standard, and the other end of the first connecting rod (7) and one end of the second connecting rod (9) are in hinge constraint; the axes constrained by the hinges at the two ends of the first connecting rod (7) are parallel to the axis of the pin shaft (4).
5. The hatch opening and closing mechanism according to claim 1, characterized in that: one end of the second connecting rod (9) and the other end of the first connecting rod (7) are constrained by a hinge, and the axis of a hinged shaft constrained by the hinge is parallel to the axis of the pin shaft (4); the middle part of the second connecting rod (9) forms hinge constraint with the connecting block (8) of the side plate of the fuselage through a connecting pin (10) of the side plate of the cabin door, and the axis of the connecting pin (10) of the side plate of the cabin door is parallel to the axis of the pin shaft (4); the other end of the second connecting rod (9) and one end of the rotating joint (19) are constrained by a hinge, one end of the rotating joint (19) is a rotating shaft, and the axis of the rotating shaft is parallel to the normal plane of the axis of the pin shaft (4); one end of the second link (9) changes the position of a third link (18) connected to the other end of the rotary joint (19) while ensuring that the direction of the axis of rotation thereof is unchanged.
6. The hatch opening and closing mechanism according to claim 1, characterized in that: one end of the rotating joint (19) and the other end (9C) of the second connecting rod (9) are constrained by a hinge; the other end of the rotating joint (19) and one end of the third connecting rod (18) are constrained by a hinge; the axis of the rotating shaft at one end of the rotating joint (19) is vertical to the hinging shaft at the other end of the rotating joint (19).
7. The hatch opening and closing mechanism according to claim 1, characterized in that: one end of the third connecting rod (18) and the other end of the rotating joint (19) are constrained by a hinge; the other end of the third connecting rod (18) and the hinged end of the cabin door connecting block (17) are constrained by a ball hinge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022297180.8U CN214729620U (en) | 2020-10-15 | 2020-10-15 | Cabin door opening and closing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022297180.8U CN214729620U (en) | 2020-10-15 | 2020-10-15 | Cabin door opening and closing mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214729620U true CN214729620U (en) | 2021-11-16 |
Family
ID=78574231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022297180.8U Active CN214729620U (en) | 2020-10-15 | 2020-10-15 | Cabin door opening and closing mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214729620U (en) |
-
2020
- 2020-10-15 CN CN202022297180.8U patent/CN214729620U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5596218B2 (en) | Semi-lever landing gear and related method | |
| CN102431644B (en) | Plane main undercarriage space retraction/extension mechanism and retraction/extension method | |
| US11155330B2 (en) | Foldable wing extensions for aircraft | |
| CN105667757A (en) | Double-bent-section and semi-blocking type cargo space door of civil airplane | |
| CA2814535A1 (en) | Landing gear for an aircraft | |
| CN108118999B (en) | A kind of cargo door opening mechanism of integrated motor pressurized strut | |
| JP2004142737A (en) | Aircraft, apparatus, and method for manufacturing aircraft | |
| CN108839790B (en) | Folding type retractable structure of undercarriage and retractable method thereof | |
| WO2019085148A1 (en) | Unmanned aerial vehicle and lifting and landing gear thereof | |
| CN110905608B (en) | Ram air turbine system structure | |
| CN112224390A (en) | Cabin door opening and closing mechanism | |
| CN111470034A (en) | Linkage mechanism of follow-up switch of landing gear cabin door of airplane | |
| CN214729620U (en) | Cabin door opening and closing mechanism | |
| CN208665533U (en) | A kind of small drone is risen and fallen frame locking means | |
| CN112173074B (en) | Reusable high-temperature speed reducing plate mechanism | |
| CN211731795U (en) | Undercarriage uplock structure for aviation emergency | |
| CN110641733B (en) | Loading mechanism forming fixed angle with rotating surface | |
| CN115402506A (en) | Large unmanned aerial vehicle wing flap actuator and mounting structure thereof | |
| CN111301664A (en) | Driving method of open type wing tip speed reducing plate | |
| CN220221112U (en) | Aircraft cabin door pull rod with good safety | |
| CN216424792U (en) | Directional load loading device for rotating mechanism | |
| CN115195998B (en) | Undercarriage winding and unwinding devices and aircraft | |
| CN110733632A (en) | landing gear retraction structure | |
| CN219277779U (en) | Vertical lifting aircraft | |
| CN219545066U (en) | Tilting mechanism capable of passing through transmission system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |