CN112623281B - Redundant-drive large-self-folding-angle support locking unfolding and folding device - Google Patents
Redundant-drive large-self-folding-angle support locking unfolding and folding device Download PDFInfo
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- CN112623281B CN112623281B CN202011437294.6A CN202011437294A CN112623281B CN 112623281 B CN112623281 B CN 112623281B CN 202011437294 A CN202011437294 A CN 202011437294A CN 112623281 B CN112623281 B CN 112623281B
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Abstract
The invention relates to a redundantly-driven large-self-folding-angle support locking unfolding and folding device, belonging to the technical field of take-off and landing systems of air vehicles to and fro from the sky and the earth; comprises a supporting locking unfolding and folding mechanism, a folding and unfolding driving actuator cylinder and a self-adaptive unlocking actuator cylinder; wherein, one axial end of the supporting, locking, unfolding and folding mechanism is arranged on the aircraft body structure, and the other axial end is connected with the middle section of the buffer; one end of the retraction driving actuator cylinder is connected with the support locking retraction mechanism, and the other end of the retraction driving actuator cylinder is arranged at the upper part of the buffer to provide a driving force for rotating between the support locking retraction mechanism and the buffer; the self-adaptive unlocking actuator cylinder is arranged at the middle joint position of the support locking unfolding and folding mechanism and provides locking supporting force when the support locking unfolding and folding mechanism is unfolded and unlocking driving force when the support locking unfolding and folding mechanism is folded; the invention provides a driving integrated design scheme of a large-self-folding-angle support locking unfolding and folding mechanism, a self-adaptive driving unlocking actuator cylinder and a double-channel redundant driving folding and unfolding actuator cylinder, and the driving integrated design scheme has the advantages of small overall accommodating space envelope, high unfolding driving reliability and the like.
Description
Technical Field
The invention belongs to the technical field of take-off and landing systems of air vehicles and ground shuttle vehicles, and relates to a redundantly-driven large-self-folding-angle support locking unfolding and folding device.
Background
With the deep fusion of aerospace technologies, as the highest point of future space technologies, the related technical fields such as repeatedly-usable space shuttle aircrafts, high-altitude high-speed unmanned aerial vehicles and the like become research hotspots in recent years.
The functions of the unfolding and folding locking and supporting mechanism are that under the condition of the overall spatial layout of the landing system of the horizontal take-off and landing aircraft, the reliable folding, unfolding, locking and unlocking functions of the landing gear buffer of the landing system are realized: when the landing buffer is folded, the landing buffer is arranged in an aircraft cabin to keep the aerodynamic appearance of the aircraft, and the landing buffer is put down in the working process of the landing system and provides stable lateral structural support for the buffer, so that the buffer structure is prevented from connecting, rotating, inclining or unstably deforming, and the structural strength and rigidity of the system are ensured. Since the landing system buffer is set down to determine the success or failure of the aircraft landing, ensuring that the buffer is set down, locked and provides sufficient support is a key link for landing the horizontal take-off and landing aircraft. The support locking unfolding and folding mechanism commonly used for the aircraft in the aviation industry at present comprises technical schemes of an actuator cylinder inner lock, a support type strut lock, a self-folding strut lock, a stop block type lower lock and the like, and the support locking schemes are low in force bearing capacity or require large motion envelope and storage space.
Compare relatively ripe aviation industry aircraft technique, hypersonic speed world comes and goes the aerodynamic appearance of aircraft more flatter, and overall layout is compacter, and interior space resources are more nervous, often can not provide more sufficient space like aviation industry aircraft and accomodate landing buffer system. Meanwhile, the higher landing speed of the hypersonic speed air-ground shuttle vehicle also puts higher requirements on the reliability of the landing buffer system.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the redundant-drive large-folding-angle-support locking and unfolding device is provided, and the driving integrated design scheme of the large-folding-angle-support locking and unfolding mechanism, the self-adaptive driving unlocking actuator cylinder and the dual-channel redundant-drive folding and unfolding actuator cylinder has the advantages of small envelope of the whole accommodating space, high reliability of unfolding driving and the like.
The technical scheme of the invention is as follows:
a redundantly driven large-self-folding-angle support locking unfolding and folding device comprises a support locking unfolding and folding mechanism, a folding and folding driving actuator cylinder and a self-adaptive unlocking actuator cylinder; wherein, one axial end of the supporting, locking, unfolding and folding mechanism is arranged on the aircraft body structure, and the other axial end is connected with the middle section of the buffer; one end of the retraction driving actuator cylinder is connected with the support locking retraction mechanism, and the other end of the retraction driving actuator cylinder is arranged at the upper part of the buffer to provide a driving force for rotating between the support locking retraction mechanism and the buffer; the self-adaptive unlocking actuator cylinder is arranged at the middle joint position of the support locking unfolding and folding mechanism and provides locking supporting force when the support locking unfolding and folding mechanism is unfolded and unlocking driving force when the support locking unfolding and folding mechanism is folded.
In the above redundantly driven large self-folding angle support locking unfolding and folding device, the working process of the support locking unfolding and folding device is as follows:
when the buffer is in a put-down state, the support locking unfolding and folding mechanism is in a linear unfolding state, and the self-adaptive unlocking actuating cylinder is in the longest expenditure state under the action of the spring, so that the support locking unfolding and folding mechanism is locked; the retractable driving actuating cylinder is in an extension state;
when the buffer needs to be folded, the self-adaptive unlocking actuating cylinder acts and shortens, the supporting locking unfolding and folding mechanism is unlocked, meanwhile, the folding and folding driving actuating cylinder starts to be shortened, the supporting locking unfolding and folding mechanism is driven to fold and fold the buffer until the buffer is folded in place, and the supporting locking unfolding and folding mechanism is unlocked and is in a large-folding-angle bending state.
In the redundantly-driven large-self-folding-angle support locking unfolding and folding device, the support locking unfolding and folding mechanism comprises a lower support rod, an upper support rod, a lubricating nozzle, an upper support rod supporting seat, an in-place sensor, a long rocker arm, a short rocker arm and a deflector rod;
one end of the upper stay bar is hinged with the lower stay bar, and the other end of the upper stay bar is hinged with the upper stay bar supporting seat and is arranged on the aircraft body structure; the other end of the lower stay bar is hinged on the buffer; the lower support rod, the upper support rod, the buffer and the aircraft body form a four-bar linkage mechanism, the buffer is lifted and put down by driving the retractable actuating cylinder through dual-channel redundancy driving, and the support is formed by the stop surfaces on the lower support rod and the upper support rod; one end of the long rocker arm is hinged to the lower stay bar, the other end of the upper stay bar is hinged to one end of the short rocker arm, and the other end of the short rocker arm is fixedly connected with the shift lever and hinged to the upper stay bar; one end of the self-adaptive unlocking actuating cylinder is hinged with the shifting rod, and the other end of the self-adaptive unlocking actuating cylinder is hinged on the upper support rod; the in-place sensor is arranged on the lower support rod and used for judging the in-place unfolding state of the support locking unfolding and folding mechanism; the lubricating nozzle is arranged at the positions of the upper support rod and the rotating shaft at the end part of the upper support rod, so that the lubricating agent is injected to ensure smooth rotation.
In the above redundantly driven large self-folding angle support locking unfolding and folding device, the working process of the support locking unfolding and folding mechanism is as follows:
the lower stay bar, the upper stay bar, the long rocker arm and the short rocker arm form a four-bar linkage mechanism to realize unfolding and folding linkage; when the support locking unfolding and folding mechanism is unfolded in place, the stop surfaces of the lower support rod and the upper support rod are butted and bear the load of the buffer, the long rocker arm is positioned above the dead point of the connecting rod mechanism, and the locking state is ensured under the spring force action of the self-adaptive unlocking actuating cylinder; the in-place sensor is propped by the deflector rod to output an in-place locking state signal; when the support locking unfolding and folding mechanism needs to be folded, the self-adaptive unlocking actuating cylinder overcomes the spring force to actuate and contract, the deflector rod is pulled to link the long rocker arm to swing through a dead point, then unlocking is carried out, the support locking unfolding and folding mechanism is driven by the folding and folding driving actuating cylinder to fold in place, and finally large self-folding angle bending is realized; the lubricating nozzle is used for injecting a lubricating agent to ensure that each rotary joint rotates smoothly.
In the redundantly driven large-self-folding-angle support locking unfolding and folding device, the folding and folding driving actuator cylinder comprises a joint, an end cover, an outer cylinder, an outer piston rod, an inner piston rod and a nozzle adapter; wherein, the outer cylinder is axially and horizontally arranged; the end cover is arranged at the axial opening end of the outer barrel to realize sealing; one end of the outer cylinder is hinged with the buffer; the joint is connected with the upper stay bar and is fixedly connected with the outer piston rod in a threaded manner; the oil nozzle joint is screwed on the outer cylinder and sequentially forms three hydraulic oil inlets a, b and c along the axial direction; the outer piston rod and the inner piston rod are arranged in the outer cylinder in series and are not fixedly connected with each other to form a high-pressure oil cavity with two extending actuating cylinders.
In the above redundantly-driven large-self-folding-angle support locking unfolding and folding device, the working process of the folding and folding driving actuator cylinder is as follows:
when the dual-channel redundancy drive retractable actuating cylinder is shortened, high-pressure oil is injected into the cavity of the outer cylinder from the port c of the oil nozzle joint, and the high-pressure oil pushes the outer piston rod and the inner piston rod to move towards one end of the port b of the oil nozzle joint until the structure is in the shortest state; when the dual-channel redundancy drive retractable actuating cylinder extends, high-pressure oil is injected from any one of the ports a and b of the oil nozzle joint to realize the extension action of the actuating cylinder; meanwhile, when any one path of hydraulic oil has faults such as leakage and the like, the other path of hydraulic oil can not be influenced to actuate, the isolation of driving faults is realized, and the putting-down reliability of the buffer is improved.
In the redundantly-driven large-self-folding-angle support locking unfolding and folding device, the self-adaptive unlocking actuating cylinder comprises an outer cylinder, a piston, an end cover, a pressure spring, a connecting rod sleeve and a joint; one end of the outer cylinder joint is hinged with the upper support rod, one end of the piston is installed in the outer cylinder, and the other end of the piston is fixedly connected with the connecting rod; the end cover is arranged at the axial opening section of the outer barrel to realize sealing; one end of the connecting rod sleeve is sleeved on the connecting rod and can slide relatively, and the other end of the connecting rod sleeve is fixedly connected with the joint; the pressure spring is arranged between the connecting rod sleeve and the end cover and is in a compressed state.
In the above redundantly driven large-folding-angle support locking unfolding and folding device, the working process of the adaptive unlocking actuator cylinder is as follows:
in a free state, the self-adaptive unlocking actuating cylinder is in the longest structure state under the action of the pressure spring; when the lock is unlocked, high-pressure oil is injected into the inner cavity of the outer cylinder, the piston moves towards one side of the joint of the outer cylinder under the pressure of the oil, and the joint is driven to contract through the connecting rod and the connecting rod sleeve; after the piston moves to the right position and is unlocked, the joint and the connecting rod sleeve compress the compression spring under the driving of the movement of the integral mechanism to continue to perform self-adaptive contraction in the movement process of the mechanism until the whole mechanism finishes the action.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the large-self-folding-angle supporting, locking and unfolding device provided by the invention, the integrated design of the supporting, locking and unfolding mechanism and the unlocking actuating cylinder can realize the length linkage of the unlocking actuating cylinder, further realize the large-angle folding of the upper and lower support rods of the buffer from 180 degrees to 15 degrees, reduce the required storage space of a landing system, and realize the layout, unfolding and folding and locking of the landing system in narrow space envelopes such as a shuttle vehicle and the like;
(2) the double-channel redundancy driving retractable actuating cylinder provided by the invention is used as a driving of the strut locking and unfolding device, can realize double-channel redundancy driving in the buffer putting-down process, simultaneously isolates any driving oil circuit fault, realizes the buffer putting-down action through the driving of another oil circuit under the condition of ensuring one oil circuit fault, greatly improves the buffer putting-down reliability, and finally realizes the improvement of the working reliability of a landing system in narrow space envelope by integrating a large-folding-angle support locking and unfolding device.
Drawings
FIG. 1 is a schematic view of a foldable self-folding support device for locking and unfolding the device according to the present invention;
FIG. 2 is a schematic view of the self-folding support locking and unfolding apparatus of the present invention;
FIG. 3 is a schematic view of the support locking deployment mechanism of the present invention;
FIG. 4 is a schematic view of the support lock deployment mechanism of the present invention;
FIG. 5 is a schematic view of the folding of the support locking deployment mechanism of the present invention;
FIG. 6 is a schematic view of the retractable drive ram of the present invention;
fig. 7 is a schematic view of the adaptive unlocking actuator of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
The invention provides a driving integrated design scheme of a large-self-folding-angle support locking unfolding and folding mechanism, a self-adaptive unlocking actuating cylinder and a double-channel redundant driving unfolding and folding actuating cylinder, and the driving integrated design scheme has the advantages of small overall containing space envelope, high unfolding driving reliability and the like, thereby completing the invention. The landing and taking-off system can be used for storing and arranging limited or atypical aerodynamic-shape aircrafts such as a sky-ground shuttle aircraft, an aerial high-speed unmanned aerial vehicle and the like.
The large-self-folding-angle support locking and unfolding device with redundant drive, as shown in fig. 1, comprises a support locking and unfolding mechanism 10, a folding and unfolding drive actuator cylinder 20 and a self-adaptive unlocking actuator cylinder 30; wherein, one axial end of the supporting, locking, unfolding and folding mechanism 10 is arranged on the aircraft body structure, and the other axial end is connected with the middle section of the buffer; one end of the retraction driving actuator cylinder 20 is connected with the support locking retraction mechanism 10, and the other end is arranged at the upper part of the buffer to provide a driving force for rotating between the two; the adaptive unlocking actuator 30 is installed at the middle joint position of the support lock deployment and retraction mechanism 10, and provides a locking support force when the support lock deployment and retraction mechanism 10 is deployed and an unlocking driving force when retracted.
As shown in fig. 1 and 2, the working process of the supporting, locking and unfolding device is as follows:
when the buffer is in a put-down state, the support locking unfolding and folding mechanism 10 is in a linear unfolding state, and the self-adaptive unlocking actuating cylinder 30 is in the longest expenditure state under the action of the spring, so that the support locking unfolding and folding mechanism 10 is locked; the retractable drive ram 20 is in an extended state;
when the buffer needs to be folded, the adaptive unlocking actuating cylinder 30 acts and shortens, the supporting locking unfolding and folding mechanism 10 is unlocked, meanwhile, the folding and unfolding driving actuating cylinder 20 starts to be shortened, the supporting locking unfolding and folding mechanism is driven to fold and fold the buffer until the buffer is folded in place, and the supporting locking unfolding and folding mechanism 10 is unlocked and is in a large-folding-angle bending state.
As shown in fig. 3, the support lock folding and unfolding mechanism 10 includes a lower stay 101, an upper stay 102, a lubricating nipple 103, an upper stay support 104, a position sensor 108, a long rocker 110, a short rocker 111, and a shift lever 114;
one end of an upper stay bar 102 is hinged with a lower stay bar 101, and the other end of the upper stay bar 102 is hinged with an upper stay bar supporting seat 104 and is installed on an aircraft body structure; the other end of the lower stay bar 101 is hinged on the buffer; the lower stay bar 101, the upper stay bar 102, the buffer and the aircraft body form a four-bar linkage mechanism, the buffer is lifted and put down by driving the retractable actuating cylinder 20 through dual-channel redundancy driving, and the support is formed through stop surfaces on the lower stay bar 101 and the upper stay bar 102; one end of a long rocker arm 110 is hinged to the lower stay bar 101, the other end of an upper stay bar 102 is hinged to one end of a short rocker arm 111, and the other end of the short rocker arm 111 is fixedly connected with a shifting lever 114 and is hinged to the upper stay bar 102; one end of the self-adaptive unlocking actuating cylinder 30 is hinged with the shifting rod 114, and the other end is hinged on the upper support rod 102; the in-place sensor 108 is mounted on the lower stay 101 and used for judging the in-place state of the support locking unfolding and folding mechanism 10; the lubricating nozzle 103 is arranged at the rotating shaft positions of the end parts of the upper stay bar 102 and the upper stay bar 102, and lubricant is injected to ensure smooth rotation.
As shown in fig. 4 and 5, the working process of the support locking unfolding and folding mechanism 10 is as follows:
the lower stay bar 101, the upper stay bar 102, the long rocker arm 110 and the short rocker arm 111 form a four-bar linkage mechanism to realize unfolding and folding linkage; when the support locking unfolding and folding mechanism 10 is unfolded in place, the stop surfaces of the structures of the lower support rod 101 and the upper support rod 102 are butted and bear the load of the buffer, the long rocker arm 110 is positioned above the dead point of the connecting rod mechanism, and the locking state is ensured under the spring force action of the self-adaptive unlocking actuating cylinder 30; the in-position sensor 108 outputs an in-position locking state signal by being held by the shift lever 114; when the supporting locking unfolding and folding mechanism 10 needs to be folded, the self-adaptive unlocking actuating cylinder 30 overcomes the spring force to actuate and contract, the shifting rod 114 is pulled to be linked with the long rocker arm 110 to swing through a dead point to unlock, then the long rocker arm is driven by the folding and unfolding driving actuating cylinder 20 to fold in place, and finally the large self-folding angle bending is realized; the lubrication nozzle 103 is used for injecting lubricant to ensure that each rotary joint rotates smoothly.
As shown in fig. 6, the retractable drive ram 20 includes a joint 201, an end cap 202, an outer cylinder 203, an outer piston rod 204, an inner piston rod 205, and a nozzle joint 214; wherein, the outer cylinder 203 is axially and horizontally arranged; the end cover 202 is arranged at the axial opening end of the outer cylinder 203 to realize sealing; one end of the outer cylinder 203 is hinged with the buffer; the joint 201 is connected with the upper support rod 102 and is fixedly connected with the outer piston rod 204 in a threaded manner; the oil nozzle joint 214 is screwed on the outer cylinder 203 and sequentially forms three hydraulic oil inlets a, b and c along the axial direction; the outer piston rod 204 and the inner piston rod 205 are arranged in series in the outer cylinder 203, and are not fixedly connected with each other, so that two extended high-pressure oil chambers of the actuating cylinders are formed.
The working process of the retractable driving actuator cylinder 20 is as follows:
when the dual-channel redundancy drive retractable actuating cylinder 20 is retracted, high-pressure oil is injected into the cavity of the outer cylinder 203 from the port c of the oil nozzle joint 214, and the high-pressure oil pushes the outer piston rod 204 and the inner piston rod 205 to move towards one end of the port b of the oil nozzle joint 214 until the structure is in the shortest state; when the dual-channel redundancy drive retractable actuator cylinder 20 extends, high-pressure oil is injected from any one of an opening a or an opening b of the oil nozzle joint 214 to realize the extension action of the actuator cylinder; meanwhile, when any one path of hydraulic oil has faults such as leakage and the like, the other path of hydraulic oil can not be influenced to actuate, the isolation of driving faults is realized, and the putting-down reliability of the buffer is improved.
As shown in fig. 7, adaptive unlocking ram 30 includes outer cylinder 301, piston 302, end cap 303, compression spring 304, connecting rod 305, connecting rod sleeve 306, and joint 307; one end of a joint of the outer cylinder 301 is hinged with the upper support rod 102, one end of a piston 302 is installed in the outer cylinder 301, and the other end of the piston is fixedly connected with a connecting rod 305; the end cover 303 is arranged at the axial opening section of the outer barrel 301 to realize sealing; one end of the connecting rod sleeve 306 is sleeved on the connecting rod 305 and can slide relatively, and the other end is fixedly connected with the joint 307; a compression spring 304 is mounted between the link sleeve 306 and the end cap 303 and is in a compressed state.
The working process of the self-adaptive unlocking actuator cylinder 30 is as follows:
in a free state, the self-adaptive unlocking actuating cylinder 30 is in the longest structure state under the action of the pressure spring 304; when the lock is unlocked, high-pressure oil is injected into the inner cavity of the outer cylinder 301, the piston 302 moves towards one side of the joint of the outer cylinder 301 under the pressure of the oil, and the joint 307 is driven to contract through the connecting rod 305 and the connecting rod sleeve 306; after the piston 302 moves to the right position and is unlocked, the joint 307 and the connecting rod sleeve 306 compress the pressure spring 304 under the driving of the movement of the whole mechanism and continue to perform self-adaptive contraction in the mechanism movement process until the whole mechanism finishes the action.
The present invention provides a support locking deployment mechanism 10, shown schematically in fig. 3, 4, 5. The mechanism comprises a lower stay bar 101, an upper stay bar 102, a lubricating nozzle 103, an upper stay bar supporting seat 104, an in-position sensor 108, a long rocker arm 110, a short rocker arm 111 and a deflector rod 114. One end of an upper stay bar 102 is hinged with a lower stay bar 101, the other end of the upper stay bar 102 is hinged with an upper stay bar supporting seat 104 and is installed on an aircraft body structure, the other end of the lower stay bar 101 is hinged on a buffer, the lower stay bar 101, the upper stay bar 102, the buffer and the aircraft body form a four-link mechanism, the buffer is lifted and put down through the driving of a dual-channel redundancy driving retractable actuating cylinder 20, and the support is formed through the stop surfaces on the lower stay bar 101 and the upper stay bar 102. One end of a long rocker arm 110 is hinged to the lower support rod 101, the other end of the long rocker arm 110 is hinged to one end of a short rocker arm 111, the other end of the short rocker arm 111 is fixedly connected with a shifting rod 114 and is hinged to the upper support rod 102, one end of the self-adaptive unlocking actuator cylinder 30 is hinged to the shifting rod 114, and the other end of the self-adaptive unlocking actuator cylinder is hinged to the upper support rod 102. The lower stay bar 101, the upper stay bar 102, the long rocker arm 110 and the short rocker arm 111 form a four-bar linkage mechanism to realize unfolding and folding linkage, the buffer is folded to realize large self-folding angle folding and folding, and when the buffer is put down to the place, the self-adaptive unlocking actuating cylinder 30 is locked by the structural stop surfaces of the lower stay bar 101 and the upper stay bar 102 and the structural fixed length of the long rocker arm 110 after swinging over a dead point.
The invention provides a dual-channel redundancy drive retractable actuator cylinder 20, which is shown in a structural schematic diagram of fig. 6. The structure comprises a joint 201, an end cover 202, an outer cylinder 203, an outer piston rod 204, an inner piston rod 205 and a nozzle joint 214. Wherein the outer cylinder 203 is hinged with the buffer, and the joint 201 is connected with the upper support rod 102 and is screwed with the outer piston rod 204. The nozzle adapter 214 is screwed to the outer cylinder 203 to form three hydraulic oil inlets a, b, and c. The outer piston rod 204 and the inner piston rod 205 are arranged in the outer cylinder 203 in series and are not fixedly connected with each other to form a high-pressure oil cavity with two extending actuating cylinders, so that the extending action of the actuating cylinders can be realized by any one path of hydraulic oil at the port a and the port b, meanwhile, when any one path of hydraulic oil has faults such as leakage and the like, the other path of hydraulic oil cannot be influenced, the driving fault isolation is realized, and the buffer laying-down reliability is improved.
The present invention provides an adaptive unlocking actuator cylinder 30, the structural schematic of which is shown in fig. 7. The structure comprises an outer cylinder 301, a piston 302, an end cover 303, a spring 304, a connecting rod 305, a connecting rod sleeve 306 and a joint 307. The piston 302 and the connecting rod 305 are fixedly connected, the connecting rod sleeve 306 is sleeved on the connecting rod 305 and can slide relatively, the connecting rod sleeve 306 is pressed against one end of the connecting rod sleeve 306 through the pressure spring 304, the actuating cylinder is guaranteed to have a fixed structural length and used for locking the expanding and contracting mechanism, and meanwhile self-adaptive compression can be performed between the piston and the actuating cylinder joint 307 in the mechanism movement process.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (6)
1. The utility model provides a redundant driven is from dog-ear support locking exhibition receipts device greatly which characterized in that: comprises a supporting locking unfolding and folding mechanism (10), a folding and unfolding driving actuator cylinder (20) and a self-adaptive unlocking actuator cylinder (30); wherein, one axial end of the supporting, locking, unfolding and folding mechanism (10) is arranged on the aircraft body structure, and the other axial end is connected with the middle section of the buffer; one end of a retraction driving actuator cylinder (20) is connected with the support locking retraction mechanism (10), and the other end is arranged at the upper part of the buffer to provide a driving force for rotating between the two; the self-adaptive unlocking actuator cylinder (30) is arranged at the middle joint position of the supporting, locking and unfolding mechanism (10) and provides locking supporting force when the supporting, locking and unfolding mechanism (10) is unfolded and unlocking driving force when the supporting, locking and unfolding mechanism is folded;
the working process of the supporting, locking, unfolding and folding device is as follows:
when the buffer is in a put-down state, the support locking unfolding and folding mechanism (10) is in a linear unfolding state, and the self-adaptive unlocking actuating cylinder (30) is in the longest expenditure state under the action of the spring, so that the support locking unfolding and folding mechanism (10) is locked; the retractable drive ram (20) is in an extended state;
when the buffer needs to be folded, the self-adaptive unlocking actuating cylinder (30) acts and shortens, the supporting locking unfolding and folding mechanism (10) unlocks, meanwhile, the folding and unfolding driving actuating cylinder (20) starts to be shortened, the supporting locking unfolding and folding mechanism is driven to fold and fold the buffer until the buffer is folded in place, and the supporting locking unfolding and folding mechanism (10) unlocks to be in a large-folding-angle folding state;
the supporting, locking, unfolding and folding mechanism (10) comprises a lower support rod (101), an upper support rod (102), a lubricating nozzle (103), an upper support rod supporting seat (104), an in-place sensor (108), a long rocker arm (110), a short rocker arm (111) and a shifting rod (114);
one end of an upper stay bar (102) is hinged with a lower stay bar (101), and the other end of the upper stay bar (102) is hinged with an upper stay bar supporting seat (104) and is installed on an aircraft body structure; the other end of the lower stay bar (101) is hinged on the buffer; the lower support rod (101), the upper support rod (102), the buffer and the aircraft body form a four-bar linkage mechanism, the buffer is lifted and put down by driving the retractable driving actuator cylinder (20) through dual-channel redundancy driving, and the support is formed through the stop surfaces on the lower support rod (101) and the upper support rod (102); one end of the long rocker arm (110) is hinged to the lower stay bar (101), the other end of the upper stay bar (102) is hinged to one end of the short rocker arm (111), and the other end of the short rocker arm (111) is fixedly connected with the shifting rod (114) and is hinged to the upper stay bar (102); one end of the self-adaptive unlocking actuating cylinder (30) is hinged with the shifting rod (114), and the other end is hinged on the upper support rod (102); the in-place sensor (108) is arranged on the lower support rod (101) and used for judging the unfolding in-place state of the support locking unfolding and folding mechanism (10); the lubricating nozzle (103) is arranged at the rotating shaft positions of the end parts of the upper stay bar (102) and the upper stay bar (102), so that the lubricating nozzle can be injected with lubricant to ensure smooth rotation.
2. A redundantly driven large dog-ear support locking deployment device as claimed in claim 1, wherein: the working process of the supporting, locking, unfolding and folding mechanism (10) is as follows:
the lower stay bar (101), the upper stay bar (102), the long rocker arm (110) and the short rocker arm (111) form a four-bar linkage mechanism to realize unfolding and folding linkage; when the support locking unfolding and folding mechanism (10) is unfolded in place, the structure stop surfaces of the lower support rod (101) and the upper support rod (102) are butted and bear the load of the buffer, the long rocker arm (110) is positioned above the dead point of the connecting rod mechanism, and the locking state is ensured under the spring force action of the self-adaptive unlocking actuating cylinder (30); the in-place sensor (108) is propped by the deflector rod (114) to output an in-place locking state signal; when the supporting locking unfolding and folding mechanism (10) needs to be folded, the self-adaptive unlocking actuating cylinder (30) overcomes the spring force to actuate and contract, pulls the deflector rod (114) to link the long rocker arm (110) to swing through a dead point and then unlock, and then folds in place under the driving of the folding and unfolding driving actuating cylinder (20), and finally large-self-folding-angle bending is achieved; the lubricating nozzle (103) is used for injecting lubricant to ensure that each rotary joint rotates smoothly.
3. A redundantly driven large dog-ear support locking deployment device as claimed in claim 2, wherein: the retractable driving actuator cylinder (20) comprises a retractable driving actuator cylinder joint (201), a retractable driving actuator cylinder end cover (202), a retractable driving actuator cylinder outer cylinder (203), an outer piston rod (204), an inner piston rod (205) and a nozzle adapter (214); wherein, the outer cylinder (203) of the retractable driving actuator cylinder is horizontally arranged in the axial direction; the end cover (202) of the retractable driving actuator cylinder is arranged at the axial opening end of the outer cylinder (203) of the retractable driving actuator cylinder to realize sealing; one end of an outer cylinder (203) of the retractable driving actuator cylinder is hinged with the buffer; the retractable driving actuator cylinder joint (201) is connected with the upper support rod (102) and is fixedly connected with the outer piston rod (204) in a threaded manner; the oil nozzle joint (214) is in threaded connection with the retractable driving actuator cylinder outer cylinder (203) and sequentially forms three hydraulic oil inlets a, b and c along the axial direction; the outer piston rod (204) and the inner piston rod (205) are arranged in series in the retractable driving actuator cylinder outer cylinder (203) and are not fixedly connected with each other to form two extended high-pressure oil cavities of the actuator cylinders.
4. A redundantly driven large self-folding angle support locking deployment and retraction device as claimed in claim 3, wherein: the working process of the retractable driving actuating cylinder (20) is as follows:
when the dual-channel redundancy drive retractable driving actuating cylinder (20) is retracted, high-pressure oil is injected into a cavity of an outer cylinder (203) of the retractable driving actuating cylinder from a port c of the oil nozzle joint (214), and the high-pressure oil pushes an outer piston rod (204) and an inner piston rod (205) to move towards one end of a port b of the oil nozzle joint (214) until the structure is in the shortest state; when the dual-channel redundancy drive retractable driving actuating cylinder (20) extends, high-pressure oil is injected from any one of an opening a or an opening b of the oil nozzle joint (214) to realize the extension action of the actuating cylinder; meanwhile, when any one path of hydraulic oil has faults such as leakage and the like, the other path of hydraulic oil can not be influenced to actuate, the isolation of driving faults is realized, and the putting-down reliability of the buffer is improved.
5. A redundantly driven large dog-ear support locking deployment device as claimed in claim 4, wherein: the self-adaptive unlocking actuator cylinder (30) comprises a self-adaptive unlocking actuator cylinder outer cylinder (301), a piston (302), a self-adaptive unlocking actuator cylinder end cover (303), a pressure spring (304), a connecting rod (305), a connecting rod sleeve (306) and a self-adaptive unlocking actuator cylinder joint (307); one end of a joint of the outer cylinder (301) of the self-adaptive unlocking actuator cylinder is hinged with the upper support rod (102), one end of a piston (302) is installed in the outer cylinder (301) of the self-adaptive unlocking actuator cylinder, and the other end of the piston is fixedly connected with a connecting rod (305); the end cover (303) of the self-adaptive unlocking actuator cylinder is arranged at the axial opening section of the outer cylinder (301) of the self-adaptive unlocking actuator cylinder to realize sealing; one end of a connecting rod sleeve (306) is sleeved on the connecting rod (305) and can slide relatively, and the other end of the connecting rod sleeve is fixedly connected with a self-adaptive unlocking actuating cylinder joint (307); a compression spring (304) is mounted between the link sleeve (306) and the adaptive unlocking actuator end cap (303) and is in a compressed state.
6. A redundantly driven large dog-ear support locking deployment device as claimed in claim 5, wherein: the working process of the self-adaptive unlocking actuator cylinder (30) is as follows:
in a free state, the self-adaptive unlocking actuator cylinder (30) is in the longest structure state under the action of the pressure spring (304); high-pressure oil is injected into the inner cavity of the outer cylinder (301) of the self-adaptive unlocking actuator cylinder during unlocking, the piston (302) moves towards one side of the joint of the outer cylinder (301) of the self-adaptive unlocking actuator cylinder under the pressure of the oil, and the joint (307) of the self-adaptive unlocking actuator cylinder is driven to contract through the connecting rod (305) and the connecting rod sleeve (306); after the piston (302) moves to the right position for unlocking, the self-adaptive unlocking actuator cylinder joint (307) and the connecting rod sleeve (306) compress the pressure spring (304) under the driving of the movement of the whole mechanism to continue to perform self-adaptive contraction in the mechanism movement process until the whole mechanism finishes the action.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011437294.6A CN112623281B (en) | 2020-12-07 | 2020-12-07 | Redundant-drive large-self-folding-angle support locking unfolding and folding device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011437294.6A CN112623281B (en) | 2020-12-07 | 2020-12-07 | Redundant-drive large-self-folding-angle support locking unfolding and folding device |
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| Publication Number | Publication Date |
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| CN112623281A CN112623281A (en) | 2021-04-09 |
| CN112623281B true CN112623281B (en) | 2022-07-05 |
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| CN202011437294.6A Active CN112623281B (en) | 2020-12-07 | 2020-12-07 | Redundant-drive large-self-folding-angle support locking unfolding and folding device |
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| CN114084377B (en) * | 2021-11-18 | 2022-06-07 | 中国科学院空间应用工程与技术中心 | Unfolding and folding movement device with cable arranging function and load test device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CH190590A (en) * | 1935-03-22 | 1937-04-30 | Aeroplanes Morane Saulnier Soc | Retractable landing gear for aircraft. |
| GB2428650B (en) * | 2005-08-04 | 2011-01-12 | Messier Dowty Ltd | Landing gear |
| CN201745745U (en) * | 2010-07-20 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Strut lock mechanism in landing position of airplane landing gear |
| US8752785B2 (en) * | 2012-06-25 | 2014-06-17 | Bell Helicopter Textron Inc. | Semi-levered articulated landing gear system |
| EP3069991B1 (en) * | 2015-03-20 | 2017-10-25 | Safran Landing Systems UK Limited | Aircraft landing gear assembly |
| EP3632794B1 (en) * | 2018-09-26 | 2020-10-28 | Safran Landing Systems UK Limited | Aircraft landing gear assembly |
| GB2578582A (en) * | 2018-10-30 | 2020-05-20 | Airbus Operations Ltd | Landing gear |
| CN111891340B (en) * | 2020-06-17 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Undercarriage receive and releases actuator based on four-bar linkage operation |
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