CN114408165B - Link mechanism and undercarriage and aircraft comprising same - Google Patents
Link mechanism and undercarriage and aircraft comprising same Download PDFInfo
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- CN114408165B CN114408165B CN202210321027.5A CN202210321027A CN114408165B CN 114408165 B CN114408165 B CN 114408165B CN 202210321027 A CN202210321027 A CN 202210321027A CN 114408165 B CN114408165 B CN 114408165B
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- link
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- 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
- B64C25/18—Operating mechanisms
- B64C25/20—Operating mechanisms mechanical
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Abstract
The invention provides a link mechanism and an undercarriage and an aircraft comprising the link mechanism, wherein the link mechanism has an extension state and a contraction state, and comprises: base, first connecting rod, second connecting rod, third connecting rod, drive shaft and locking ware. The base is fixedly installed; the first connecting rod is rotationally connected with a first position of the base; a first limiting structure used for limiting in an extending state is arranged between the first connecting rod and the base; the second connecting rod is rotationally connected with the first connecting rod; the third connecting rod is respectively and rotatably connected with the second connecting rod and the second position of the base; a second limiting structure used for limiting in an extending state is arranged between the third connecting rod and the second connecting rod; the driving shaft is driven by the power assembly to rotate bidirectionally so as to drive the linkage mechanism to switch between an extension state and a contraction state; the lock is driven by the drive shaft to lock the link mechanism in the collapsed state and unlock the link mechanism in a state other than the collapsed state.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a link mechanism, and an undercarriage and an aircraft comprising the link mechanism.
Background
The three-link mechanism is widely applied to mechanical equipment in various fields due to unique motion characteristics, wherein most application scenes require that the motion starting point and the motion ending point of the three-link mechanism have a locking function, for example, locking is required when the undercarriage of an airplane is contracted or unfolded, and locking is required when the mechanical arm is grabbed and loosened. The existing common three-link mechanism with the locking function has the defects that a plurality of motors respectively realize the driving and the locking of the link mechanism, so that the whole three-link mechanism has a complex structure, heavy weight and large volume, is difficult to adapt to the demand tendency of the modern market on the miniaturization and the light weight of mechanical equipment, and seriously limits the application scene of the three-link mechanism; in addition, the existing three-link mechanism is locked by the braking force of the motor, and when the motor fails or the load moment is greater than the braking force of the motor, the locking fails, so that the reliability of the scheme is very poor. There is therefore a great need for a linkage mechanism and landing gear, aircraft incorporating the linkage mechanism to ameliorate the above problems.
Disclosure of Invention
In view of the shortcomings of the prior art, the invention provides a link mechanism, and an undercarriage and an aircraft comprising the link mechanism, so as to solve the problem that the driving and locking of the existing three-link mechanism are respectively controlled by a plurality of motors, which results in the complex structure of the three-link mechanism.
To achieve the above and other related objects, the present invention provides a link mechanism having an extended state and a retracted state, comprising: base, first connecting rod, second connecting rod, third connecting rod, drive shaft and locking ware. The base is fixedly installed; the first connecting rod is rotationally connected with a first position of the base; a first limiting structure used for limiting in an extending state is arranged between the first connecting rod and the base; the second connecting rod is rotationally connected with the first connecting rod; the third connecting rod is respectively and rotatably connected with the second connecting rod and the second position of the base; a second limiting structure used for limiting in an extending state is arranged between the third connecting rod and the second connecting rod; the driving shaft is driven by the power assembly to rotate bidirectionally so as to drive the link mechanism to switch between an extension state and a contraction state; the locker is driven by the drive shaft to lock the link mechanism in the collapsed state and unlock the link mechanism in a state other than the collapsed state.
In an embodiment of the link mechanism, a clutch driving structure is disposed between the driving shaft and the third link, and the clutch driving structure enables the driving shaft to continue to rotate after the link mechanism is locked, so as to provide unlocking or locking power for the lock.
In an embodiment of the link mechanism, the clutch driving structure includes a first driving body and a second driving body respectively disposed on the driving shaft and the third link, and the driving shaft rotates in a first direction until the first driving body contacts with the second driving body, so as to drive the third link to drive the link mechanism to perform an extending motion; and the driving shaft rotates along a second direction until the first driving body is contacted with the second driving body, and the third connecting rod is driven to drive the connecting rod mechanism to do contraction motion.
In an embodiment of the link mechanism according to the present invention, a gap for the driving shaft to drive the locker to unlock or lock is provided in a circumferential direction between the first driving body and the second driving body.
In an embodiment of the link mechanism of the present invention, a first rotating shaft hole is disposed on the base, and a hinge rotating shaft is disposed on the third link, and the hinge rotating shaft is rotatably mounted in the first rotating shaft hole.
In an embodiment of the link mechanism of the present invention, the third link is provided with a second rotating shaft hole, and the second rotating shaft hole is coaxial with the first rotating shaft hole; the second driving body is arranged on the second rotating shaft hole, the first driving body is arranged on the driving shaft, the driving shaft is inserted into the second rotating shaft hole, and the first driving body correspondingly extends to the position of the second driving body.
In an embodiment of the link mechanism of the present invention, the first limiting structure limits the extending movement of the first link when the link mechanism is in the extending state.
In an embodiment of the link mechanism of the present invention, the first limiting structure includes at least one stopping body, and the stopping body is disposed on the base and/or the first link and limits the first link from continuing to perform the extending action when the link mechanism reaches the extending state.
In an embodiment of the link mechanism of the present invention, the second limiting structure limits the relative extension movement between the second link and the third link when the link mechanism is in the extension state.
In an embodiment of the link mechanism of the present invention, the second limiting structure includes at least one stopping body, and the stopping body is disposed on the second link and/or the third link and limits a continued extending action between the second link and the third link when the link mechanism reaches the extended state.
In one embodiment of the link mechanism of the present invention, the locking device includes a locking device driving body, an extendable member, and a locking hole, the extendable member is disposed on one of the third link and the base, the locking hole is correspondingly disposed on the other of the third link and the base, and the locking device driving body is driven by a driving shaft to operate, and drives the extendable member to be inserted into or withdrawn from the locking hole, so as to correspondingly lock or unlock the third link and the base.
The invention also provides a landing gear comprising any one of the link mechanisms described above.
The invention also provides an aircraft which comprises a fuselage, wings, a power system and a landing gear, wherein the landing gear comprises any one of the link mechanisms.
According to the link mechanism, the landing gear and the aircraft comprising the link mechanism, when the link mechanism (landing gear) is in a contraction state, motion locking is achieved through the locking device, and when the link mechanism (landing gear) is in an extension state (namely a put-down state), motion locking is achieved through the motion relation of the three link mechanisms, the first limiting structure and the second limiting structure. The retractable movement and the extension movement of the whole landing gear system and the locking and unlocking of the retractable state and the extension state can realize the driving and the control of the whole mechanism only by the simple torque output of one power assembly, and the inertia force of the landing gear in the retractable state and the loaded torque in the extension state can not be transmitted to the power assembly, thereby improving the safety performance of the power assembly. In addition, the link mechanism can meet the functional requirements of most aircrafts on the retraction and extension of the landing gear, and only one power assembly is input, so the landing gear is simple in structure, small in size, light in weight and capable of being adapted to small aircrafts with limited space and loads. Meanwhile, the invention has high locking reliability, can effectively avoid the conditions of accidental extension of the undercarriage during overload flight and accidental contraction of the undercarriage during landing, and ensures the flight safety.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is an overall view of one embodiment of a linkage mechanism of the present invention.
Fig. 2 is an exploded view of one embodiment of the linkage mechanism of the present invention.
Fig. 3 is a partial cross-sectional view of one embodiment of the linkage mechanism of the present invention.
Fig. 4 is a partial cross-sectional view of an embodiment of a linkage mechanism of the present invention with a third link unlocked from a base.
FIG. 5 is a partial cross-sectional view of a third link locked to the base in an embodiment of the linkage mechanism of the present invention.
FIG. 6 is a side view of an embodiment of a linkage mechanism of the present invention in a contracted state and locked.
FIG. 7 is a side view of an embodiment of a linkage mechanism of the present invention in a contracted state after unlocking.
FIG. 8 is a schematic view of a linkage mechanism at a knee position in an embodiment of the linkage mechanism of the present invention.
FIG. 9 is a side view of an extended state of a linkage mechanism of an embodiment of the present invention in a locked position.
Fig. 10 is a side view of an extended state of an embodiment of a linkage mechanism of the present invention when unlocked.
In the figure, 1, a base; 11. a first seat body; 110. a first position; 111. a first stopper body; 12. a second seat body; 120. a second position; 121. a first spindle hole; 122. a locking hole; 2. a first link; 21. a second stopper body; 3. a first limit structure; 4. A second link; 41. a third stopper body; 5. a third link; 50. a second driving body; 51. an extension butt joint structure; 52. a contracting and butting structure; 53. a locking member mounting hole; 54. a fourth stopper body; 55. a hinge shaft; 56. a second spindle hole; 57. a through hole; 6. a power assembly; 7. a drive shaft; 70. a first driving body; 71. an extension drive structure; 72. a retraction drive structure; 73. a latch driver body; 8. a lock; 81. A locking pin; 811. a stressed structure; 82. A spring; 9. a second limit structure; 10. and (7) supporting legs.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. It is also to be understood that the terminology used in the examples is for the purpose of describing particular embodiments only, and is not intended to limit the scope of the present invention. Test methods in which specific conditions are not specified in the following examples are generally carried out under conventional conditions or under conditions recommended by the respective manufacturers.
When numerical ranges are given in the examples, it is understood that both endpoints of each of the numerical ranges and any number between the two endpoints are optional unless otherwise specified in the invention. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs and the description of the present invention, and any methods, apparatuses, and materials similar or equivalent to those described in the examples of the present invention may be used to practice the present invention.
It should be understood that the terms "upper", "lower", "left", "right", "middle" and "one" used herein are for clarity of description only, and are not intended to limit the scope of the invention, and that changes or modifications in the relative relationship may be made without substantial technical changes and modifications.
Referring to fig. 1 to 10, the present invention provides a link mechanism, and an undercarriage and an aircraft including the link mechanism, so as to solve the problem that the driving and locking of the conventional three-link mechanism are respectively controlled by a plurality of motors, which results in a complicated structure of the three-link mechanism.
Referring to fig. 1 to 2, the present invention provides a link mechanism having an extended state and a retracted state, the link mechanism including: the device comprises a base 1, a first connecting rod 2, a second connecting rod 4, a third connecting rod 5, a driving shaft 7 and a locking device 8. The base 1 of the present invention is not limited in its structural form, and may be a fuselage of an apparatus, such as an aircraft fuselage, or may be other fixtures, such as a ground or ground fixture. In an embodiment of the present invention, the base 1 includes a first base 11 and a second base 12, and the first base 11 and the second base 12 are fixed relatively. The first end of the first link 2 is rotatably connected to the first position 110 of the first seat 11. A first limiting structure 3 for limiting in an extending state is arranged between the first connecting rod 2 and the first base 11; the first end of the second connecting rod 4 is rotatably connected with the second end of the first connecting rod 2; a first end of the third connecting rod 5 is rotatably connected with a second end of the second connecting rod 4, a second end of the third connecting rod 5 is rotatably connected with a second position 120 on the second seat 12, and a second limiting structure 9 for limiting in an extending state is arranged between the third connecting rod 5 and the second connecting rod 4; a three-link mechanism is formed among the base 1, the first connecting rod 2, the second connecting rod 4 and the third connecting rod 5, and the three-link mechanism has an extending state and a contracting state. The driving shaft 7 is driven by the power assembly 6 to bidirectionally reciprocate so as to drive the linkage mechanism to switch between an extension state and a contraction state; for example, as shown in fig. 8 and 9, when the driving shaft 7 rotates in a first direction (counterclockwise direction), the third link 5 is driven to drive the link mechanism to perform an extending motion; when the third link 5 rotates counterclockwise to a certain angle, the second limit structure 9 will prevent the third link 5 from continuing to rotate counterclockwise. When the first connecting rod 2 rotates anticlockwise to a certain angle, the first limiting structure 3 prevents the first connecting rod 2 from rotating anticlockwise continuously. And the driving shaft 7 is fixedly connected with an output shaft of the power assembly 6, and the power assembly 6 provides power for the whole landing gear structure. When the driving shaft 7 rotates in a second direction (clockwise direction), the third connecting rod 5 is driven to drive the connecting rod mechanism to do contraction movement. During the rotation of the drive shaft 7, the lock 8 is driven by the drive shaft 7 to lock the link mechanism when the link mechanism reaches the contracted state and unlock the link mechanism when the link mechanism is in a state other than the contracted state. It should be noted that the first end and the second end are defined for convenience of description, and it can be understood by those skilled in the art that the first end and the second end may also be middle portions of corresponding links or any other positions capable of satisfying the motion state of the three-bar linkage according to the variety of application scenarios of the three-bar linkage. The power assembly 6 may be any power assembly having a rotary output shaft and capable of providing a corresponding torque output, such as a rotary motor or a combination of a motor and a speed reducer, and the link mechanism may not include the power assembly 6 but provide a driving force for the driving shaft 7 by means of an additional purchased configuration.
Referring to fig. 2, the locking device 8 of the present invention can be any suitable locking device type capable of locking and unlocking the base 1 and the third link 5 under the driving of the driving shaft 7, for example, a spring pin type locking device is set between the base 1 and the third link 5, and the locking device is activated or closed by the direct or indirect touch of the driving shaft 7 to complete the relative locking and unlocking between the base and the third link 5. In an embodiment of the present invention, a clutch driving structure is disposed between the driving shaft 7 and the third link 5, when the clutch driving structure is in a disengaged state, the driving shaft 7 and the third link 5 are disengaged in a circumferential direction, and the driving shaft 7 and the third link 5 can act independently within a set range, so that the driving shaft 7 can continue to rotate after the link mechanism is locked, and an unlocking or locking power is provided for the lock 8. And this arrangement avoids impact of the load on the power assembly 6. When the driving shaft 7 is combined with the third link 5, the driving shaft 7 provides a driving force to the third link 5 and drives the third link 5 to perform an extending motion or a retracting motion.
Referring to fig. 2, in an embodiment of the link mechanism according to the present invention, the clutch driving structure includes a first driving body 70 disposed on the driving shaft 7 and a second driving body 50 disposed on the third link 5, respectively, and the driving shaft 7 rotates along a first direction until the first driving body 70 contacts the second driving body 50, and drives the third link 5 to drive the link mechanism to perform an extending motion; the driving shaft 7 rotates in the second direction until the first driving body 70 contacts the second driving body 50, and drives the third link 5 to drive the link mechanism to perform a retracting motion. A gap is provided in a circumferential direction between the first drive body 70 and the second drive body 50, and the drive shaft 7 drives the locker 8 to unlock or lock. An extension driving structure 71 and a retraction driving structure 72 are arranged on the first driving body 70, and an extension abutting structure 51 and a retraction abutting structure 52 are arranged on the third connecting rod 5; when the driving shaft 7 rotates along the first direction and the extension driving structure 71 contacts with the extension abutting structure 51, the third connecting rod 5 is driven to drive the connecting rod mechanism to make extension movement until the extension state is reached; when the driving shaft 7 rotates in the second direction until the contraction driving structure 72 contacts the contraction butt joint structure 52, the third link 5 is driven to drive the link mechanism to perform contraction movement until the contraction state is reached, the locking device 8 locks the base 1 and the third link 5, and at this time, the three link mechanism enters the contraction locking state. As shown in fig. 7, when the three-bar linkage needs to be extended from the retracted locking state, the power assembly 6 drives the driving shaft 7 to rotate in the first direction (counterclockwise), and the driving shaft 7 drives the lock 8 to unlock the base 1 and the third bar linkage 5 during the process from the separation of the retracted driving structure 72 from the retracted docking structure 52 to the contact of the extended driving structure 71 with the extended docking structure 51.
Referring to fig. 2 and 4, the rotating connection structure between the base 1 and the third link 5 is not limited in the present invention, and in an embodiment of the link mechanism of the present invention, a first pivot hole 121 is formed on the base 1, a hinge shaft 55 is formed on the third link 5, and the hinge shaft 55 is rotatably installed in the first pivot hole 121. A second rotating shaft hole 56 is formed in the third connecting rod 5, and the second rotating shaft hole 56 is coaxially arranged with the first rotating shaft hole 121; the second driving body 50 is disposed at an end of the second rotating shaft hole 56 facing away from the power assembly 6, and the first driving body 70 is disposed at an end of the driving shaft 7 facing away from the power assembly 6; the driving shaft 7 is inserted into the second rotating shaft hole 56, and the first driving body 70 correspondingly extends to the position of the second driving body 50.
Referring to fig. 3, when the link mechanism is in the extended state, the first limiting structure 3 limits the extension motion of the first link 2. The first limiting structure 3 in the present invention may be any suitable structure capable of limiting the first connecting rod 2 from further extending relative to the base 1 in the extending state, in another embodiment of the present invention, there are two stop bodies, which are respectively a first stop body 111 disposed on the base and a second stop body 21 disposed on the first connecting rod 2, and the first stop body 111 and the second stop body 21 contact and abut against each other when the connecting rod mechanism reaches the extending state to limit the first connecting rod 2 from continuing to extend. In another embodiment of the present invention, the first position-limiting structure 3 only includes a first stopping body 111, and the first stopping body 111 is disposed on the base 1 and abuts against the first link 2 when the link mechanism reaches the extended state, so as to limit the first link 2 to continue the extending action. In another embodiment of the present invention, the first position-limiting structure 3 only comprises a second stop body 21, and the second stop body 21 is disposed on the first connecting rod 2 and contacts and abuts against the base 1 when the link mechanism reaches the extended state to limit the first connecting rod 2 from continuing the extending motion. Of course, it will be understood by those skilled in the art that the number of the first and second stop bodies 111 and 21 may be more in the present invention, as long as the first link 2 can be simultaneously restrained by abutting contact when the extended state is reached.
Referring to fig. 2 and 9, in the present invention, the second limiting structure 9 limits the relative extending movement between the second connecting rod 4 and the third connecting rod 5 when the connecting rod mechanism is in the extending state. The second limit structure 9 in the present invention may be any suitable structure capable of limiting the second link 4 and the third link 5 from further extending relatively in the extending state, in an embodiment of the present invention, the second limit structure 9 includes a third stop body 41 and a fourth stop body 54, the third stop body 41 is disposed on the second link 4, the fourth stop body 54 is disposed on the third link 5, and the third stop body 41 and the fourth stop body 54 contact and abut against each other when the link mechanism reaches the extending state to limit the further extending action between the second link 4 and the third link 5. In another embodiment of the present invention, the second limit structure 9 only includes the third stop body 41, the third stop body 41 is disposed on the second link 4, and the third stop body 41 contacts and abuts against the third link 5 when the link mechanism reaches the extended state, so as to limit the further extension action of the third link 5 relative to the second link 4. In a further embodiment of the invention, the second limit structure 9 comprises only the fourth stop body 54, the fourth stop body 54 is arranged on the third connecting rod 5, and the fourth stop body 54 contacts and abuts against the second connecting rod 4 when the connecting rod mechanism reaches the extended state, so as to limit the continued extension action of the second connecting rod 4 relative to the third connecting rod 5. Of course, it will be understood by those skilled in the art that the number of the third and fourth stopping bodies 41 and 54 may be more, as long as the first and second links 2 and 4 can be prevented from further extending by simultaneously abutting contact when the extended state is reached.
Referring to fig. 4 and 5, in the present invention, the structure and the installation manner of the locking device 8 may be any suitable locking structure that can be driven by the driving shaft 7 to trigger locking and unlocking, in an embodiment of the link mechanism of the present invention, the locking device 8 includes a locking device driving body 73, a telescopic member and a locking hole 122, the telescopic member includes a locking pin 81 and a spring 82, a locking device installation hole 53 is formed on one side of the third link 5 facing the base 1, the diameter of the locking device installation hole 53 is greater than the outer diameter of the spring 82, and a through hole 57 for the small end of the locking pin 81 to pass through is formed at the bottom of the locking device installation hole 53; the diameter of the through hole 57 is smaller than the diameter of the large end of the lock bolt 81, the depth of the lock member mounting hole 53 can completely accommodate the large end of the lock bolt 81, the spring 82 is mounted in the lock member mounting hole 53, the small end of the lock bolt 81 passes through the inner hole of the spring 82 and further protrudes from the through hole 57 to the side of the third connecting rod 5 facing the power assembly 6; a force receiving structure 811 is provided at a portion where a small end of the lock pin 81 is exposed to the outside of the third link 5, the lock hole 122 is provided in the base 1 and corresponds to a position of the lock pin 81 when the link mechanism is in the contracted state, the lock driver 73 is provided in the drive shaft 7, when the link mechanism reaches the contracted state, the lock hole 122 reaches a position corresponding to the lock pin 81, at this time, the lock driver 73 releases the action on the lock pin 81, and a large end of the lock pin 81 is ejected out of the lock hole 122 in the base by an elastic force of a spring 82, thereby achieving locking between the third link 5 and the base. When the link mechanism is in a state other than the retracted state, the driving shaft 7 drives the lock driver body 73 to act on the force receiving structure 811 on the lock pin 81, so that the lock pin 81 is retracted into the lock attachment hole 53, thereby unlocking the third link 5 from the base. The driving mechanism 73 can be any suitable structure capable of driving the locking pin 81 to retract, in this embodiment, the driving mechanism 73 is a wedge disposed on the driving shaft, the force-receiving structure 811 on the locking pin 81 is a groove into which the wedge is gradually inserted during rotation, and the wedge further pulls the locking pin 81 into the locking pin receiving hole 53.
Referring to fig. 4, 6 and 7, it should be emphasized that when the link mechanism is in the contracted state, the contraction driving structure 72 of the driving shaft 7 is in contact with the contraction abutting structure 52 of the third link 5, and at this time, because there is a gap between the extension driving structure 71 and the extension abutting structure 51, when the link mechanism is unlocked, because there is a gap between the extension driving structure 71 and the extension abutting structure 51, the extension driving structure 71 and the extension abutting structure 51 are separated, at this time, only the driving shaft 7 rotates, the third link 5 is kept in the locked position, the driving shaft 7 drives the locking device driving body 73 to act on the force-receiving structure 811 on the locking pin 81, so as to pull the large end of the locking pin 81 back into the locking device mounting hole 53, thereby relatively unlocking the third link 5 and the base, and after the extension driving structure 71 is in contact with the extension abutting structure 51, the driving shaft 7 and the third link 5 rotate synchronously, the driving latch mechanism 73 is always applied to the force receiving structure 811 of the locking pin 81 or the locking pin 81 is always compressed by the second fastening structure 12 into the locking member mounting hole 53, so as to ensure that the locking pin 81 is retracted into the locking member mounting hole 53 in all processes except the retracted state, and the relative movement between the third connecting rod 5 and the base is not affected.
Although the embodiment described above is described in which the drive latch body 73 releases the biasing force applied to the latch pin 81 when locked, and the latch pin 81 is inserted into the locking hole 122 and locked by the return elastic force of the spring 82, the drive latch body 73 maintains the biasing force applied to the latch pin 81 when in a state other than the locked state, and the unlocked state is maintained. However, it will be understood by those skilled in the art that if the pulling force of the tension spring is used to keep the locking pin 81 in the state of normally retracting to the locking member mounting hole 53, the small end of the locking pin 81 can be pushed and extended by the locking member driving body 73 when locking, so that the large end of the locking pin 81 breaks the locking state of normally inserting into the locking hole 122, and in other states except locking, the locking pin 81 is automatically retracted or retracted under the action of gravity under the action of the tension spring.
Referring to figures 1 and 2, the invention also provides a landing gear including a linkage as described in any of the embodiments above. The landing leg 10 of the landing gear is installed at one end of the first connecting rod 2, which is far away from the first seat body 11, and extends along the extending direction of the first connecting rod 2, and when the connecting rod mechanism is in the extending state, the landing leg 10 extends downwards, and when the connecting rod mechanism is in the retracting state, the landing leg 10 moves to one side along with the first connecting rod 2 and retracts. In an embodiment of the present invention, the link mechanism includes: the device comprises a base 1, a first connecting rod 2, a second connecting rod 4, a third connecting rod 5, a driving shaft 7 and a locking device 8. In an embodiment of the landing gear of the present invention, the base 1 includes a first seat body 11 and a second seat body 12, the first seat body 11 and the second seat body 12 are both connected to the fuselage, and a first end of the first link 2 is rotatably connected to the first seat body 11. The first end of the second connecting rod 4 is rotatably connected with the second end of the first connecting rod 2; the first end of the third connecting rod 5 is rotatably connected with the second end of the second connecting rod 4, the second end of the third connecting rod 5 is rotatably connected with the second seat 12, the three-connecting-rod mechanism is formed among the first seat 11, the second seat 12, the first connecting rod 2, the second connecting rod 4 and the third connecting rod 5, and the three-connecting-rod mechanism has an extending state and a contracting state.
The invention further provides an aircraft, which comprises a fuselage, wings, a power system and a landing gear, wherein the landing gear comprises the link mechanism in any one of the embodiments. Referring to fig. 1, a landing leg 10 of the landing gear is mounted at an end of the first link 2 away from the base 1 and extends along an extending direction of the first link 2, the landing leg 10 extends downward when the link mechanism is in an extended state, and the landing leg 10 moves to one side along with the first link 2 and retracts when the link mechanism is in a retracted state.
The movement process of the connecting rod mechanism as a landing gear on an aircraft is as follows: as shown in fig. 6, when the linkage is in the retracted locking state, the first link 2 is in the horizontal state, the large end of the locking pin 81 is inserted into the locking hole 122, and the power unit 6 continues to drive the drive shaft 7 to rotate counterclockwise when the landing gear is lowered in order to extend the linkage. The driving shaft 7 rotates a certain angle, which is an unlocking stage, as shown in fig. 4, in the unlocking stage, the locking device driving body 73 presses the stress structure 811 on the locking pin 81, so as to pull the locking pin 81 out of the locking hole 122 and completely contract the locking device mounting hole 53, after unlocking is completed, the fixed connection between the third connecting rod 5 and the base is released, the third connecting rod 5 can rotate freely, as shown in fig. 7, the driving shaft 7 continues to rotate counterclockwise, at this time, in the landing gear lowering stage, the extension driving structure 71 contacts with the extension abutting structure 51 and performs torque transmission, and at this time, the driving shaft 7 starts to drive the third connecting rod 5 to rotate counterclockwise. As shown in fig. 3 and 8, under the conduction of the three links, the first link 2 rotates counterclockwise, gradually approaches to a completely laid-down state, the included angle between the third link 5 and the second link 4 gradually approaches to 180 °, when the included angle between the third link 5 and the second link 4 is 180 °, the three-link mechanism is in an inflection point position (as shown in fig. 8), at this time, the first link 2 has reached the farthest position of counterclockwise rotation, and the first limiting structure 3 starts to limit. The driving shaft 7 further rotates counterclockwise for a certain angle, the included angle between the third connecting rod 5 and the second connecting rod 4 exceeds 180 degrees, the third stopping body 41 on the second limiting structure 9 contacts with the fourth stopping body 54 on the third connecting rod 5, the driving shaft 7 stops rotating, as shown in fig. 9, at this time, the connecting rod mechanism is in an extending state and is locked through the first limiting structure 3 and the second limiting structure 9, the corresponding landing gear is in a down locking state, the aircraft can land, and the first connecting rod 2 can be directly or indirectly stressed in a contact mode. When the linkage mechanism is in an extension locking state: if the bottom end of the first connecting rod 2 is subjected to impact force in the opposite direction of STA, torque for driving the third connecting rod 5 to rotate anticlockwise can be generated after the impact force is transmitted by the three-connecting-rod mechanism, the third connecting rod 5 cannot rotate anticlockwise further under the action of the second limiting structure 9, the angle of the first connecting rod 2 cannot be changed, the impact force can be transmitted to an aircraft fuselage through the first connecting rod 2, the second connecting rod 4, the third connecting rod 5 and the base 1, and no load can be generated on the power assembly 6, so that the connecting-rod mechanism can support forward thrust landing of the aircraft; if the bottom end of the first connecting rod 2 is impacted by STA forward direction, can produce the moment of torsion that drives the first connecting rod 2 to rotate anticlockwise, after the first connecting rod 2 rotates anticlockwise by a slight angle, the three-bar linkage mechanism enters the inflection point position, the included angle of the third connecting rod 5 and the second connecting rod 4 is 180 degrees, prevent the first connecting rod 2 from further rotating anticlockwise, simultaneously, the effect of the first limit structure 1 is acted, also produce the effect that prevents the first connecting rod 2 from further rotating anticlockwise, the angle of the first connecting rod 2 no longer changes, part of the impact force can pass through the first connecting rod 2, the second connecting rod 4, the third connecting rod 5, the aircraft fuselage is transmitted to the base 1, another part of the impact force can pass through the first connecting rod 2, the base 1 transmits the aircraft fuselage, can not produce the load to the power component 6, so the connecting rod mechanism can support the aircraft to dash and fall.
When the linkage is in the lowered locked condition, as shown in figure 9, the power assembly 6 continues to drive the drive shaft 7 in a clockwise rotation if the linkage is to be retracted. The driving shaft 7 rotates by a certain angle, the driving latch body 73 departs from the stress structure 811 on the locking pin 81, the locking pin 81 generates a movement trend of popping out the locking piece mounting hole 53 under the action of the spring 82, but because the outlet of the locking piece mounting hole 53 is blocked by the second seat body 12, the locking pin 81 cannot pop out, the extension driving structure 71 is separated from the extension butting structure 51, then the retraction driving structure 72 contacts with the retraction butting structure 52 and performs torque transmission, the driving shaft 7 starts to drive the third connecting rod 5 to rotate clockwise, as shown in fig. 10, at this time, in an extension unlocking stage, when an included angle between the third connecting rod 5 and the second connecting rod 4 is smaller than 180 degrees, the connecting rod mechanism is in an extension locking state and is unlocked. The driving shaft 7 continues to rotate clockwise, and at this time, in a contraction stage, under the conduction of the three-link mechanism, the first link 2 rotates clockwise, and gradually approaches a completely contracted state, and the included angle between the third link 5 and the second link 4 becomes smaller and smaller. When the third connecting rod 5 rotates to the locking piece mounting hole 53 and the locking pin 81 fixing hole are completely coaxially aligned, the locking pin 81 pops out, part of the locking pin 81 is inserted into the locking pin 81 fixing hole, the third connecting rod 5 and the base are fixedly connected by the locking pin 81, as shown in fig. 5, at the moment, the connecting rod mechanism is in a contraction locking state, the power assembly 6 stops rotating, the third connecting rod 5 cannot rotate, the first connecting rod 2 is in a horizontal state and cannot rotate, and the aircraft can normally fly. When the link mechanism is in a contraction locking state, the inertia force borne by the first link 2 is transmitted to the aircraft body through the first link 2, the second link 4, the third link 5, the locking pin 81 and the base 1, and no load is generated on the power assembly 6, so that the link mechanism can support the aircraft to perform overload flight. The contraction locking state and the put-down locking state of the link mechanism are completely maintained by the mechanical structure, and even if the power assembly 6 fails, the contraction locking state and the put-down locking state cannot be released accidentally. It should be noted that, in the present invention, STA, BL, and WL are english abbreviations commonly used in the aviation industry system, where STA is an aircraft heading, the positive direction is the forward direction and the negative direction is the rear direction, BL is a spreading direction, the positive direction is the left direction and the negative direction is the right direction, WL is the longitudinal direction, and the positive direction is the upper direction and the negative direction is the lower direction.
According to the link mechanism, the landing gear and the aircraft comprising the link mechanism, when the link mechanism (landing gear) is in a contraction state, motion locking is achieved through the locking device, and when the link mechanism (landing gear) is in an extension state (namely a put-down state), motion locking is achieved through the motion relation of the three link mechanisms, the first limiting structure and the second limiting structure. The whole landing gear system can realize the driving and the control of the whole mechanism only by the simple torque output of one power assembly, and the inertia force of the landing gear system in the contraction state and the loaded torque of the landing gear system in the extension state can not be transmitted to the power assembly, thereby improving the safety performance of the power assembly. In addition, the link mechanism can meet the functional requirements of most aircrafts on the retraction and extension of the landing gear, and only one power assembly is input, so the landing gear is simple in structure, small in size, light in weight and capable of being adapted to small aircrafts with limited space and load. Meanwhile, the invention has high locking reliability, can effectively avoid the conditions of accidental extension of the undercarriage during overload flight and accidental contraction of the undercarriage during landing, and ensures the flight safety. Therefore, the invention effectively overcomes some practical problems in the prior art, thereby having high utilization value and use significance.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (10)
1. A linkage mechanism having an extended state and a retracted state, comprising:
the base is fixedly installed;
the first connecting rod is rotatably connected with a first position of the base; a first limiting structure used for limiting in an extending state is arranged between the first connecting rod and the base;
the second connecting rod is rotatably connected with the first connecting rod;
the third connecting rod is respectively and rotatably connected with the second connecting rod and the second position of the base; a second limiting structure used for limiting in an extending state is arranged between the third connecting rod and the second connecting rod;
the driving shaft drives the third connecting rod to drive the connecting rod mechanism to switch between an extension state and a contraction state when rotating;
A locker driven by the drive shaft to lock the base and the third link in the collapsed state and unlock the base and the third link in a state other than the collapsed state.
2. The linkage mechanism according to claim 1, wherein a clutch drive structure is provided between the drive shaft and the third link, the clutch drive structure enabling the drive shaft to continue to rotate after the linkage mechanism is locked to provide unlocking or locking power to the locker.
3. The link mechanism according to claim 2, wherein the clutch drive structure includes a first drive body and a second drive body provided on the drive shaft and the third link, respectively, and a gap for the drive shaft to drive the locker to unlock or lock is provided in a circumferential direction between the first drive body and the second drive body.
4. The linkage mechanism according to claim 3, wherein the base is provided with a first pivot hole, and the third link is provided with a hinge pivot rotatably mounted in the first pivot hole.
5. The link mechanism of claim 4, wherein the third link is provided with a second rotating shaft hole, and the second rotating shaft hole is coaxially arranged with the first rotating shaft hole; the second driving body is arranged on the second rotating shaft hole, the first driving body is arranged on the driving shaft, the driving shaft is inserted into the second rotating shaft hole, and the first driving body correspondingly extends to the position of the second driving body.
6. The linkage mechanism according to claim 1, wherein the first limiting structure comprises at least one stop body provided on the base and/or the first link and limiting the first link from continuing its extension action when the linkage mechanism reaches the extended state.
7. The linkage mechanism according to claim 1, wherein the second limiting structure comprises at least one stop body disposed on the second link and/or the third link and limiting continued extension action between the second link and the third link when the linkage mechanism reaches the extended state.
8. The link mechanism as claimed in claim 1, wherein the locker includes a locker driving body, a telescopic member provided at one of the third link and the base, and a locking hole correspondingly provided at the other of the third link and the base, the locker driving body being actuated by a driving shaft and driving the telescopic member to be inserted into or withdrawn from the locking hole to correspondingly lock or unlock the third link and the base.
9. A landing gear, comprising a linkage according to any of claims 1 to 8.
10. An aircraft comprising a fuselage, wings, a power system and landing gear, wherein the landing gear comprises a linkage according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210321027.5A CN114408165B (en) | 2022-03-30 | 2022-03-30 | Link mechanism and undercarriage and aircraft comprising same |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210321027.5A CN114408165B (en) | 2022-03-30 | 2022-03-30 | Link mechanism and undercarriage and aircraft comprising same |
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| CN114408165A CN114408165A (en) | 2022-04-29 |
| CN114408165B true CN114408165B (en) | 2022-06-14 |
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| CN202210321027.5A Active CN114408165B (en) | 2022-03-30 | 2022-03-30 | Link mechanism and undercarriage and aircraft comprising same |
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Effective date of registration: 20230530 Address after: 6/F, Block A, Building 4, No. 200, Tianfu Fifth Street, Chengdu Hi-tech Zone, China (Sichuan) Pilot Free Trade Zone, Chengdu, Sichuan, 610095 Patentee after: Chengdu wofeitianyu Technology Co.,Ltd. Patentee after: ZHEJIANG GEELY HOLDING GROUP Co.,Ltd. Address before: 610000 China (Sichuan) pilot Free Trade Zone, Chengdu Patentee before: Wofei Changkong Technology (Chengdu) Co.,Ltd. Patentee before: ZHEJIANG GEELY HOLDING GROUP Co.,Ltd. |