CN114368474B - Landing gear cabin door sequential retraction linkage mechanism and linkage method - Google Patents
Landing gear cabin door sequential retraction linkage mechanism and linkage method Download PDFInfo
- Publication number
- CN114368474B CN114368474B CN202210051662.6A CN202210051662A CN114368474B CN 114368474 B CN114368474 B CN 114368474B CN 202210051662 A CN202210051662 A CN 202210051662A CN 114368474 B CN114368474 B CN 114368474B
- Authority
- CN
- China
- Prior art keywords
- connecting rod
- landing gear
- door
- linkage
- stop
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
-
- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/16—Fairings movable in conjunction with undercarriage elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
- B64C2025/125—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The present disclosure provides a landing gear door sequential retraction linkage mechanism and a linkage method, which relate to the field of aircraft landing gear design, and include: a striker; the left part and the right part of the linkage mechanism are sleeved at two ends of the collision rod and are symmetrically arranged, and each of the left part and the right part of the linkage mechanism comprises an upper connecting rod, a stop connecting rod, a middle connecting rod, an upper adjusting connecting rod, a lower adjusting connecting rod and a tension spring; one end of the tension spring is fixed on the fuselage structure of the airplane, the other end of the tension spring is connected with the upper connecting rod, one end of the upper connecting rod is fixed on the fuselage structure, the other end of the upper connecting rod is connected with one end of the stop connecting rod, the other end of the stop connecting rod is connected with the middle position of the middle connecting rod, one end of the middle connecting rod is fixed on the fuselage structure, the other end of the middle connecting rod is connected with the upper adjusting connecting rod, the upper adjusting connecting rod is connected with the lower adjusting connecting rod, and the lower adjusting connecting rod is connected to the cabin door. The cabin door folding and unfolding device is simple in structure, reliable in operation, small in size, light in weight and high in universality, does not need an additional power source, and is suitable for design and installation of landing gear and cabin door linkage folding and unfolding of a man-machine and an unmanned aerial vehicle.
Description
Technical Field
The disclosure relates to the field of aircraft landing gear design, in particular to a landing gear cabin door sequential retraction linkage mechanism and a linkage method.
Background
The traditional cabin door is driven by an independent actuator or an air source, the size is large, the weight is large, and most of the traditional cabin door linkage mechanisms are of mechanical follow-up structures, so that the traditional cabin door linkage mechanisms are easy to interfere with the landing gear in the retraction process.
Therefore, how to design a simple and reliable landing gear and cabin door retraction mechanism so that the retraction process of the landing gear and the cabin door can be successfully completed within the specified conditions and time is a difficult point in the special design work of the landing gear.
Disclosure of Invention
In view of the above, the present disclosure provides a landing gear door sequential retraction linkage mechanism and a linkage method.
In one aspect, the present disclosure provides a landing gear door sequential retraction linkage mechanism for linkage with a door and landing gear of an aircraft, comprising: a striker; the left part of the linkage mechanism and the right part of the linkage mechanism are sleeved at two ends of the collision rod and are symmetrically arranged, and each of the left part of the linkage mechanism and the right part of the linkage mechanism comprises an upper connecting rod, a stop connecting rod, a middle connecting rod, an upper adjusting connecting rod, a lower adjusting connecting rod and a tension spring; one end of the tension spring is fixed on the fuselage structure of the airplane, the other end of the tension spring is connected with the upper connecting rod, one end of the upper connecting rod is fixed on the fuselage structure, the other end of the upper connecting rod is connected with one end of the stop connecting rod, the other end of the stop connecting rod is connected with the middle position of the middle connecting rod, one end of the middle connecting rod is fixed on the fuselage structure, the other end of the middle connecting rod is connected with the upper adjusting connecting rod, the upper adjusting connecting rod is connected with the lower adjusting connecting rod, and the lower adjusting connecting rod is connected to the cabin door.
According to the embodiment of the disclosure, the two ends of the ram are provided with the screw rods, and the ram is connected with the upper connecting rods at the left part and the right part of the linkage mechanism through the screw rods respectively.
According to the embodiment of the disclosure, copper bushings are embedded in the joints of the two ends of the upper connecting rod, the joints of the two ends of the stop connecting rod, and lubricating grease is smeared on the fixed end of the middle connecting rod and the middle position of the middle connecting rod.
According to an embodiment of the present disclosure, the lower adjusting link is connected to the hatch via a hatch link;
and the joint of the middle connecting rod and the upper adjusting connecting rod and the joint of the lower adjusting connecting rod and the cabin door connecting rod are embedded with radial spherical bearings.
According to an embodiment of the present disclosure, the upper adjusting link is threaded with the lower adjusting link to form an assembly, the length of the threaded connection being adjustable.
According to an embodiment of the present disclosure, four tabs are provided on the upper link, including a first tab, a second tab, a third tab, and a fourth tab, wherein: the first lug is fixed on the body structure; the second lug is arranged on one side close to the first lug and is connected with the tension spring; the fourth lug is connected with a stop connecting rod; the third lug is arranged on one side close to the fourth lug and is connected with the striker.
According to an embodiment of the present disclosure, the surface of the tab is provided with a convex nut stop.
According to an embodiment of the present disclosure, a protruding stopper is provided at a side of the stopper link connected to one end of the upper link.
According to an embodiment of the present disclosure, upper end single ear, middle section both arms, lower extreme oblique angle ears have been seted up on the intermediate link, wherein: the upper single lug is fixed on the machine body structure; the middle double arms are provided with bolt holes and are connected with a stop connecting rod through bolts; the lower end oblique angle double ears are provided with an oblique angle relative to the middle section double arms, and the lower end oblique angle double ears are connected with the upper adjusting connecting rod.
According to an embodiment of the present disclosure, the tension spring has a primary tension.
According to the embodiment of the disclosure, the ram is a symmetrical piece, an arc-shaped groove is formed in the center of the ram, and the radius of curvature of the arc-shaped groove is the same as the radius of the buffer strut piston of the landing gear.
Another aspect of the present disclosure provides a landing gear door linkage method based on the above landing gear door sequential retraction linkage mechanism, where the landing gear door sequential retraction linkage mechanism is in a ram impact follow-up retraction manner with a door of an aircraft and a landing gear in a linkage retraction manner, and the method includes: and (3) a stowing process: the retraction actuator works to drive the landing gear to rotate and retract, when the buffer strut piston of the landing gear impacts the collision rod, the collision rod is driven to retract upwards, meanwhile, the upper connecting rod rotates around the fixed point to drive the landing gear cabin door to retract and retract the linkage mechanism in sequence to move, and finally, the cabin door is pulled to move upwards and retract to be closed, so that the whole sequential retraction movement is completed; the laying down process is as follows: the retraction actuator works to drive the landing gear to rotate and retract, the upper connecting rod moves along with the landing gear under the tension of the tension spring to drive the landing gear cabin door to move sequentially by the retraction linkage mechanism, the upper connecting rod is limited by the stop table of the stop connecting rod to stop moving, and after the cabin door is opened, the landing gear continues to move until the landing gear is put in place, so that the whole sequential putting-down movement is completed.
Compared with the prior art, the landing gear cabin door sequential retraction linkage mechanism and the linkage method provided by the present disclosure have at least the following beneficial effects:
(1) The landing gear cabin door folding and unfolding device is simple in structure, reliable in operation and easy to understand in method principle, and solves the problem that mutual interference possibly exists in the landing gear and cabin door folding and unfolding process;
(2) The cabin door folding and unfolding device does not need an additional power source for cabin door folding and unfolding, and is small in size and light in weight;
(3) The universal door folding and unfolding mechanism is high in universality and suitable for design and installation of landing gears and cabin doors of most unmanned aerial vehicles and unmanned aerial vehicles in linkage.
Drawings
The above and other objects, features and advantages of the present disclosure will become more apparent from the following description of embodiments thereof with reference to the accompanying drawings in which:
FIG. 1 schematically illustrates an isometric view of a landing gear door sequential retraction linkage according to an embodiment of the present disclosure;
FIG. 2 schematically illustrates a front view of an upper link according to an embodiment of the present disclosure;
FIG. 3 schematically illustrates a front view of a stop link according to an embodiment of the present disclosure;
FIG. 4 (a) schematically illustrates a front view of an intermediate link according to an embodiment of the present disclosure;
FIG. 4 (b) schematically illustrates a side view of an intermediate link according to an embodiment of the present disclosure;
FIG. 5 schematically illustrates a front view of an upper adjustment link according to an embodiment of the present disclosure;
FIG. 6 schematically illustrates a front view of a lower adjustment link according to an embodiment of the present disclosure;
FIG. 7 schematically illustrates a front view of a tension spring according to an embodiment of the present disclosure;
FIG. 8 schematically illustrates a front view of a striker rod according to an embodiment of the present disclosure;
FIG. 9 (a) schematically illustrates a state of motion diagram of a landing gear door linkage method when the landing gear is down in place, according to an embodiment of the present disclosure;
FIG. 9 (b) schematically illustrates a state of motion of the gear door linkage method in the gear up-strike ram position/down-disengage ram position according to an embodiment of the present disclosure;
fig. 9 (c) schematically illustrates a state of motion diagram of the landing gear door linkage method when the landing gear is in place according to an embodiment of the present disclosure.
[ reference numerals description ]
100-linkage mechanism; 110-left part of the linkage mechanism; 120-right part of the linkage mechanism; 111-upper links;
111A-a first ear; 111B-a second ear; 111C-a third ear; 111D-fourth ear;
1111-nut stop; 112-stop link; 1121—a stop table; 113-an intermediate link;
113A-upper ear; 113B-middle double arm; 113C-lower bevel ears;
114-upper adjustment link; 115-lower adjustment link; 116-tension springs; 130-a striker;
1301-arc grooves; 200-cabin door; 210-left hatch; 211-cabin door links;
220-right hatch door; 300-landing gear; 310-cushion strut piston.
Detailed Description
For the purposes of promoting an understanding of the principles and advantages of the disclosure, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same. It will be apparent that the described embodiments are some, but not all, of the embodiments of the present disclosure. Based on the embodiments in this disclosure, all other embodiments that a person of ordinary skill in the art would obtain without making any inventive effort are within the scope of protection of this disclosure.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. The terms "comprises," "comprising," and/or the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.
In the present disclosure, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may communicate with each other; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the terms in this disclosure will be understood by those of ordinary skill in the art as the case may be.
All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art unless otherwise defined. It should be noted that the terms used herein should be construed to have meanings consistent with the context of the present specification and should not be construed in an idealized or overly formal manner.
Fig. 1 schematically illustrates an isometric view of a landing gear door sequential retraction linkage according to an embodiment of the present disclosure.
As shown in fig. 1, the landing gear door sequential retraction linkage according to this embodiment, for linkage with a door 200 of an aircraft and a landing gear 300, includes: a striker 130; the left linkage 110 and the right linkage 120 are sleeved at two ends of the striker 130 and are symmetrically arranged, and the left linkage 110 and the right linkage 120 comprise an upper connecting rod 111, a stop connecting rod 112, a middle connecting rod 113, an upper adjusting connecting rod 114, a lower adjusting connecting rod 115 and a tension spring 116.
Wherein, one end of the tension spring 116 is fixed to the fuselage structure of the aircraft and the other end is connected with the upper link 111, one end of the upper link 111 is fixed to the fuselage structure and the other end is connected with one end of the stop link 112, the other end of the stop link 112 is connected with the middle position of the middle link 113, one end of the middle link 113 is fixed to the fuselage structure and the other end is connected with the upper adjusting link 114, the upper adjusting link 114 is connected with the lower adjusting link 115, and the lower adjusting link 115 is connected to the cabin door 200.
Thus, the left linkage 110 and the right linkage 120 are symmetrical to each other, are connected via the striker 130, and are linked by the landing gear 300 striking the striker 130, thereby completing the sequential linkage retraction process of the landing gear and the door.
The following describes in detail the respective components of the landing gear door sequential retraction linkage according to the embodiments of the present disclosure with reference to fig. 2 to 8, respectively.
Fig. 2 schematically illustrates a front view of an upper link according to an embodiment of the present disclosure.
As shown in fig. 2, the upper link 111 is provided with four tabs, including a first tab 111A, a second tab 111B, a third tab 111C, and a fourth tab 111D, and tab holes are connected to other members by bolts. The first lug 111A is fixed on the body structure, the second lug 111B is disposed on a side close to the first lug 111A and is connected with the tension spring 116, the fourth lug 111D is connected with the stop link 112, and the third lug 111C is disposed on a side close to the fourth lug 111D and is connected with the striker 130.
Further, the surface of the tab is provided with a convex nut stop 1111 for preventing the rotation of the bolt.
Fig. 3 schematically illustrates a front view of a stop link according to an embodiment of the present disclosure.
As shown in fig. 3, two lugs are respectively provided at both ends of the stopper link 112, and the upper link 111 and the intermediate link 113 are respectively connected by bolts from top to bottom. A stopper link 112 at one end connected to the upper link 111 is provided at a side thereof with a protruding stopper 1121 for restricting movement of the upper link 111.
Fig. 4 (a) schematically illustrates a front view of an intermediate link according to an embodiment of the present disclosure. Fig. 4 (b) schematically illustrates a side view of an intermediate link according to an embodiment of the present disclosure.
As shown in fig. 4 (a) and 4 (B), to avoid motion interference, the middle link 113 is provided with an upper single lug 113A, a middle double arm 113B, and a lower bevel double ear 113C. Wherein, upper end monaural 113A is fixed in the fuselage structure, and each arm on the middle section both arms 113B corresponds the position and all has seted up the bolt hole, through bolted connection locking connecting rod 112, and lower extreme oblique angle ears 113C has an oblique angle for middle section both arms 113B, and lower extreme oblique angle ears 113C connect and go up adjusting connecting rod 114.
Fig. 5 schematically illustrates a front view of an upper adjustment link according to an embodiment of the present disclosure. Fig. 6 schematically illustrates a front view of a lower adjustment link according to an embodiment of the present disclosure.
As shown in fig. 5 and 6, in the embodiment of the present disclosure, the upper adjustment link 114 is threaded with the lower adjustment link 115 to form an assembly, and the length of the threaded connection is adjustable.
Specifically, the upper single lug of the upper adjusting connecting rod 114 is connected with the middle connecting rod 113 through a bolt, and the lower end is provided with a blind hole internal thread. An external threaded screw rod is arranged at the upper end of the lower adjusting connecting rod 115, and is in matched connection with the internal threads of the blind hole at the lower end of the upper adjusting connecting rod 114 to form an adjustable connecting rod assembly.
The lower single lug of the lower adjusting link 115 is connected with a cabin door link 211 by a bolt, and the cabin door link 211 is fixedly installed on the cabin door 210. Thereby, the lower adjustment link 115 is connected to the door 200 by the door link 211.
In the embodiment of the disclosure, the joint of the middle connecting rod 113 and the upper adjusting connecting rod 114 and the joint of the lower adjusting connecting rod 115 and the cabin door connecting rod 211 are embedded with radial joint bearings. That is, one end of the adjustable link assembly is connected to one end tab of the intermediate link 113 by a bolt and a radial spherical plain bearing, and the other end of the adjustable link assembly is connected to the hatch link 211 by a bolt and a radial spherical plain bearing. Therefore, the bolt penetrates through the radial spherical plain bearing to be connected with the part, and the adjustable connecting rod assembly can be guaranteed to rotate freely under the designed movement relation.
In the embodiment of the disclosure, copper bushings are embedded in the joints of the two ends of the upper connecting rod 111, the joints of the two ends of the stop connecting rod 112, and the fixed end of the middle connecting rod 113 and the middle position of the middle connecting rod 113, and lubricating grease is smeared on the copper bushings. Therefore, copper bushings are embedded in connecting lugs of other parts and are connected with bolts and coated with lubricating grease, so that the mechanism moves smoothly without clamping stagnation. The bolt passes through the copper bush to connect the parts, so that the parts are guaranteed to rotate around the connection part.
It should be noted that the length of the threaded connection of the adjustable connecting rod assembly can be adjusted according to the situation of the in-place movement of the cabin door, so as to meet the design requirements of the retraction movement and in-place closing of the cabin door and avoid the phenomena of interference of the movement of the left cabin door and the right cabin door and untight closing.
Fig. 7 schematically illustrates a front view of a tension spring according to an embodiment of the present disclosure.
As shown in fig. 7, the tension spring 116 has a hook shape at both ends, one end is connected to the upper link 111 by a bolt, and the other end is connected to the body structure by a bolt.
In the disclosed embodiment, the tension spring 116 has an initial tension. When the landing gear is in the lowered position, the tension spring 116 is connected, and when connected, the micro-tension applies a pretension to the upper link 111.
Fig. 8 schematically illustrates a front view of a striker rod according to an embodiment of the present disclosure.
As shown in fig. 8, male screws are provided at both ends of the striker 130, and the striker 130 is connected to the upper link 111 symmetrically provided to the left and right link parts 110 and 120, respectively, through the male screws.
In the embodiment of the disclosure, the plunger 130 is a symmetrical piece, an arc-shaped groove 1301 is formed in the center of the plunger 130, the radius of curvature of the arc-shaped groove 1301 is the same as the radius of the buffer post piston 310 of the landing gear 300, and the buffer post piston 310 has a guiding function in the following process after the impact with the plunger 130.
Based on the disclosure, the disclosure further provides a landing gear door linkage method based on the landing gear door sequential retraction linkage mechanism, wherein the linkage retraction mode of the landing gear door sequential retraction linkage mechanism and the aircraft door 200 and landing gear 300 is a ram impact follow-up retraction mode. The landing gear door linkage method will be described in detail below in connection with fig. 9 (a), 9 (b), 9 (c).
Fig. 9 (a), 9 (b), 9 (c) are three stage position diagrams illustrating the movement of the landing gear door linkage method. Fig. 9 (a) schematically illustrates a state of motion diagram of a landing gear door linkage method when the landing gear is put down in place according to an embodiment of the present disclosure. Fig. 9 (b) schematically illustrates a state of motion of the landing gear door linkage method according to the embodiment of the present disclosure when the landing gear is retracted to strike/to be released from the ram position. Fig. 9 (c) schematically illustrates a state of motion diagram of the landing gear door linkage method when the landing gear is in place according to an embodiment of the present disclosure.
As shown in fig. 9 (a), 9 (b) and 9 (c), the landing gear door linkage method is divided into a stow process and a drop process, for example:
(1) And (3) a stowing process: the retraction actuator works to drive the landing gear 300 to rotate and retract, when the buffer strut piston 310 of the landing gear 300 impacts the ram 130, the ram 130 is driven to retract upwards together, meanwhile, the upper connecting rod 111 rotates around a fixed point to drive the landing gear cabin door sequential retraction linkage mechanism 100 to move together, and finally, the cabin door 200 is pulled to move upwards to retract and close, so that the whole sequential retraction movement is completed;
(2) The laying down process is as follows: the retraction actuator works to drive the landing gear 300 to rotate and retract, the tension spring 116 of the upper connecting rod 111 moves along with the landing gear 300 to drive the landing gear cabin door sequence retraction linkage mechanism 100 to move, the upper connecting rod 111 is limited by the stop table 1121 of the stop connecting rod 112 to stop moving, the cabin door 200 is completely opened, the landing gear 300 continues to move until the landing gear 300 is in place, and the whole sequence retraction movement is completed.
It should be appreciated that the particular order or hierarchy of steps in the stow and put down processes described above is an example of an exemplary method. Based on design preferences, it is understood that the specific order or hierarchy of steps in the processes may be rearranged without departing from the scope of the present disclosure. The accompanying method claims present elements of the various steps in a sample order, and are not meant to be limited to the specific order or hierarchy.
The above is merely an exemplary illustration, and the present embodiment is not limited thereto, and several examples are given below:
in some embodiments, other components of the landing gear door sequencing retraction linkage disclosed in the above embodiments are not externally loaded, except for the tension spring 116.
In some embodiments, the landing gear door sequential retraction linkage disclosed in the above embodiments may at least also form a complete linkage with the door links, the door, and the landing gear.
In some embodiments, the landing gear door sequential retraction linkage disclosed in the above embodiments is not limited to the retraction design of the double-opening door and the nose landing gear shown in fig. 9 (a), but may be used for retraction designs of any door landing gear combination of the double-opening door, the main landing gear, and the like.
In some embodiments, the landing gear cabin door sequential retraction linkage mechanism disclosed in the above embodiments can realize the locking of the landing gear in upper and lower positions by means of an electromagnetic lock built in a retraction actuator, and one of ordinary skill in the art can change the locking form of the upper and lower positions as required.
Thus, embodiments of the present disclosure have been described in detail with reference to the accompanying drawings. From the foregoing description, those skilled in the art will readily recognize the sequential retraction linkage of landing gear doors provided by embodiments of the present disclosure.
It should be noted that, in the drawings or the text of the specification, implementations not shown or described are all forms known to those of ordinary skill in the art, and not described in detail. Furthermore, the above definitions of the elements and methods are not limited to the specific structures, shapes or modes mentioned in the embodiments, and may be modified, replaced or increased simply by those of ordinary skill in the art.
In summary, the embodiment of the disclosure provides a sequential retraction linkage mechanism and a linkage method for a landing gear door of an aircraft and a landing gear, wherein the linkage mechanism comprises a ram and a symmetrically arranged left part and right part of the linkage mechanism, the structure is simple and reliable, the principle of the method is easy to understand, the retraction of the landing gear door does not need an additional power source, the weight is light, the universality is strong, and the linkage mechanism is suitable for the design and installation of the landing gear and the landing gear of most of man-machine and unmanned aerial vehicles.
It should be noted that, the landing gear cabin door sequential retraction linkage mechanism provided by the present disclosure has been successfully applied to landing gear design engineering projects of certain aircraft.
It should be further noted that, the directional terms mentioned in the embodiments, such as "upper", "lower", "front", "rear", "left", "right", etc., are only referring to the directions of the drawings, and are not intended to limit the scope of the present disclosure. Like elements are denoted by like or similar reference numerals throughout the drawings. Conventional structures or constructions will be omitted when they may cause confusion in understanding the present disclosure.
And the shapes and dimensions of the various elements in the drawings do not reflect actual sizes and proportions, but merely illustrate the contents of the embodiments of the present disclosure. In addition, in the claims, any reference signs placed between parentheses shall not be construed as limiting the claim.
Furthermore, the word "comprising" does not exclude the presence of elements or steps not listed in a claim. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements.
Similarly, it should be appreciated that in the above description of exemplary embodiments of the disclosure, various features of the disclosure are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various disclosed aspects. However, the disclosed method should not be construed as reflecting the intention that: i.e., the claimed disclosure requires more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive aspects lie in less than all features of a single foregoing disclosed embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of this disclosure.
While the foregoing embodiments have been described in some detail for purposes of clarity of understanding, it will be understood that the foregoing embodiments are merely illustrative of the invention and are not intended to limit the invention, and that any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the present disclosure are intended to be included within the scope of the present disclosure.
Claims (11)
1. A landing gear door sequential retraction linkage mechanism for linkage with a door (200) and landing gear (300) of an aircraft, comprising:
a striker (130);
the left part (110) and the right part (120) of the linkage mechanism are sleeved at two ends of the collision rod (130) and are symmetrically arranged, and the left part (110) and the right part (120) of the linkage mechanism comprise an upper connecting rod (111), a stop connecting rod (112), a middle connecting rod (113), an upper adjusting connecting rod (114), a lower adjusting connecting rod (115) and a tension spring (116);
one end of the tension spring (116) is fixed on a fuselage structure of an airplane, the other end of the tension spring is connected with the upper connecting rod (111), one end of the upper connecting rod (111) is fixed on the fuselage structure, the other end of the upper connecting rod is connected with one end of the stop connecting rod (112), the other end of the stop connecting rod (112) is connected with the middle position of the middle connecting rod (113), one end of the middle connecting rod (113) is fixed on the fuselage structure, the other end of the middle connecting rod is connected with the upper adjusting connecting rod (114), the upper adjusting connecting rod (114) is connected with the lower adjusting connecting rod (115), and the lower adjusting connecting rod (115) is connected to the cabin door (200);
four lugs are arranged on the upper connecting rod (111), and the four lugs comprise a first lug (111A), a second lug (111B), a third lug (111C) and a fourth lug (111D), wherein:
-the first tab (111A) is fixed to the fuselage structure;
the second lug (111B) is arranged on one side close to the first lug (111A) and is connected with the tension spring (116);
the fourth lug (111D) is connected with the stop link (112);
the third tab (111C) is provided on a side close to the fourth tab (111D) and is connected to the striker (130).
2. The landing gear cabin door sequential retraction linkage mechanism according to claim 1, wherein screw rods are arranged at two ends of the ram (130), and the ram (130) is connected with the upper connecting rod (111) of the left part (110) and the right part (120) of the linkage mechanism through the screw rods respectively.
3. The landing gear cabin door sequential retraction linkage mechanism according to claim 1, wherein copper bushings are embedded in the fixed end of the middle connecting rod (113) and the middle position of the middle connecting rod (113) at the connection position of the two ends of the upper connecting rod (111) and the connection position of the two ends of the stop connecting rod (112) respectively, and lubricating grease is smeared on the fixed end and the middle position.
4. Landing gear door sequential retraction linkage according to claim 1, characterized in that the lower adjustment link (115) is connected to the door (200) by a door link (211);
and a centripetal joint bearing is embedded at the joint of the middle connecting rod (113) and the upper adjusting connecting rod (114) and the joint of the lower adjusting connecting rod (115) and the cabin door connecting rod (211).
5. The landing gear door sequencing retraction linkage according to claim 1, wherein the upper adjustment link (114) is threadedly connected to the lower adjustment link (115) to form an assembly, the threaded connection being adjustable in length.
6. Landing gear door sequential retraction linkage according to claim 1, characterized in that the surface of the fourth tab (111D) is provided with a protruding nut stop (1111).
7. Landing gear door sequential retraction linkage according to claim 1, characterized in that the side of the stop link (112) connected to one end of the upper link (111) is provided with a protruding stop table (1121).
8. The landing gear door sequential retraction linkage according to claim 1, wherein the intermediate link (113) is provided with an upper end single lug (113A), a middle section double arm (113B) and a lower end oblique angle double lug (113C), wherein:
the upper end lug (113A) is fixed to the fuselage structure;
the middle section double arm (113B) is provided with a bolt hole and is connected with the stop connecting rod (112) through a bolt;
the lower end bevel angle double ears (113C) are provided with a bevel angle relative to the middle section double arms (113B), and the lower end bevel angle double ears (113C) are connected with the upper adjusting connecting rod (114).
9. The landing gear door sequencing retraction linkage of claim 1 wherein the tension spring (116) has an initial tension.
10. The landing gear cabin door sequential retraction linkage mechanism according to claim 1, wherein the ram (130) is a symmetrical piece, an arc-shaped groove (1301) is formed in the center position of the ram (130), and the radius of curvature of the arc-shaped groove (1301) is the same as the radius of the buffer strut piston (310) of the landing gear (300).
11. A landing gear door linkage method based on a landing gear door sequential retraction linkage mechanism according to any one of claims 1 to 10, wherein the linkage retraction of the landing gear door sequential retraction linkage mechanism with a door (200) of the aircraft and a landing gear (300) is in a ram impact follow-up retraction mode, the method comprising:
and (3) a stowing process: the retraction actuator works to drive the landing gear (300) to rotate and retract, when the buffer strut piston (310) of the landing gear (300) impacts the collision rod (130), the collision rod (130) is driven to retract upwards together, meanwhile, the upper connecting rod (111) rotates around a fixed point to drive the landing gear cabin door sequential retraction linkage mechanism to move, and finally the cabin door (200) is pulled to move upwards and retract to be closed, so that the whole sequential retraction movement is completed;
the laying down process is as follows: the retraction actuator works to drive the landing gear (300) to rotate and retract, the upper connecting rod (111) moves along with the landing gear (300) under the tension of the tension spring (116), the landing gear cabin door sequential retraction linkage mechanism is driven to move, the upper connecting rod (111) is limited by the stop table (1121) of the stop connecting rod (112) to stop moving, the cabin door (200) is completely opened, and the landing gear (300) continues to move until the landing gear is retracted, so that the whole sequential retraction movement is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210051662.6A CN114368474B (en) | 2022-01-17 | 2022-01-17 | Landing gear cabin door sequential retraction linkage mechanism and linkage method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210051662.6A CN114368474B (en) | 2022-01-17 | 2022-01-17 | Landing gear cabin door sequential retraction linkage mechanism and linkage method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114368474A CN114368474A (en) | 2022-04-19 |
| CN114368474B true CN114368474B (en) | 2023-08-15 |
Family
ID=81143652
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210051662.6A Active CN114368474B (en) | 2022-01-17 | 2022-01-17 | Landing gear cabin door sequential retraction linkage mechanism and linkage method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114368474B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB847382A (en) * | 1956-06-21 | 1960-09-07 | Transair Ltd | Improvements in douglas d.c. 3 and like aircraft |
| CN103600837A (en) * | 2013-10-25 | 2014-02-26 | 中国商用飞机有限责任公司 | Link mechanism used for controlling doors of undercarriage |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN104527972A (en) * | 2014-12-05 | 2015-04-22 | 中国航天空气动力技术研究院 | Unmanned plane undercarriage cabin door retraction-extension servo mechanism |
| CN212890903U (en) * | 2020-08-07 | 2021-04-06 | 四川腾盾科技有限公司 | Unmanned aerial vehicle undercarriage cabin door folding and unfolding system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20110091538A (en) * | 2008-12-05 | 2011-08-11 | 메씨에르-다우티 인코포레이티드 | Landing gear bay door with double hook mechanism |
-
2022
- 2022-01-17 CN CN202210051662.6A patent/CN114368474B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB847382A (en) * | 1956-06-21 | 1960-09-07 | Transair Ltd | Improvements in douglas d.c. 3 and like aircraft |
| CN103600837A (en) * | 2013-10-25 | 2014-02-26 | 中国商用飞机有限责任公司 | Link mechanism used for controlling doors of undercarriage |
| CN104176244A (en) * | 2014-09-17 | 2014-12-03 | 江西洪都航空工业集团有限责任公司 | Linked landing gear cabin door folding and unfolding device |
| CN104527972A (en) * | 2014-12-05 | 2015-04-22 | 中国航天空气动力技术研究院 | Unmanned plane undercarriage cabin door retraction-extension servo mechanism |
| CN212890903U (en) * | 2020-08-07 | 2021-04-06 | 四川腾盾科技有限公司 | Unmanned aerial vehicle undercarriage cabin door folding and unfolding system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114368474A (en) | 2022-04-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8985511B2 (en) | Method of positioning landing gear | |
| US2712421A (en) | Folding wing aircraft | |
| US8946607B2 (en) | Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles | |
| EP3689739B1 (en) | Wing hinge assembly including hinged torque boxes | |
| AU2010314745B2 (en) | A compound motion structure | |
| CN105000168B (en) | System for locking and locking foldable aerofoil | |
| EP1663777B1 (en) | Support structure for a retractable and extendable flap, and use of said structure | |
| EP3789289B1 (en) | Double over center crankshaft flap mechanism | |
| CN105000169B (en) | Novel folding wing and driving and deadlocking mechanism | |
| EP3543110B1 (en) | Hinge pins for foldable aircraft wings | |
| DE102009052641A1 (en) | Trailing edge flap system | |
| US11427309B2 (en) | Hinged truck assembly for aircraft landing gear | |
| CN114030597B (en) | Landing gear cabin door linkage mechanism, landing gear cabin door linkage system and unmanned aerial vehicle | |
| CN106516087A (en) | Novel high-strength high-compactness lightweight aircraft landing gear | |
| DE102009037707A1 (en) | Adjustment mechanism of an adjusting device for coupling an adjustment flap to a main wing and such adjustment | |
| CN114368474B (en) | Landing gear cabin door sequential retraction linkage mechanism and linkage method | |
| CN210364359U (en) | Aircraft with undercarriage | |
| CN110733632B (en) | Undercarriage receive and releases structure | |
| CN218463869U (en) | Unmanned vehicles undercarriage and hatch door linkage jack | |
| EP4122821A1 (en) | Aircraft landing gear shock absorber strut | |
| CN115535222A (en) | Unmanned vehicles undercarriage and hatch door linkage jack | |
| CN115523806A (en) | Resistance rudder and hanging cable recovery integrated mechanism and recovery method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |