CN115367099A - Lockpin linear driving device for aircraft wing folding system - Google Patents
Lockpin linear driving device for aircraft wing folding system Download PDFInfo
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- CN115367099A CN115367099A CN202210915042.2A CN202210915042A CN115367099A CN 115367099 A CN115367099 A CN 115367099A CN 202210915042 A CN202210915042 A CN 202210915042A CN 115367099 A CN115367099 A CN 115367099A
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- 230000037431 insertion Effects 0.000 claims description 3
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- 230000000694 effects Effects 0.000 abstract description 4
- 230000004308 accommodation Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
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- 230000009286 beneficial effect Effects 0.000 description 2
- 239000010720 hydraulic oil Substances 0.000 description 2
- 230000000670 limiting effect Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 229910000881 Cu alloy Inorganic materials 0.000 description 1
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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Abstract
The application discloses a lockpin linear driving device for an aircraft wing folding system, including the casing, be provided with the lockpin in the casing, lockpin one end is connected with actuating mechanism, and actuating mechanism is used for driving lockpin rectilinear movement, and the lockpin other end activity stretches out the casing, is provided with locking mechanical system on the casing, and locking mechanical system is used for locking lockpin extreme position, and this application has increased locking function, double insurance, improves the advantage of security down.
Description
Technical Field
The application relates to the technical field of aircraft wing folding systems, in particular to a lockpin linear driving device for an aircraft wing folding system.
Background
The occupied area of the airplane on the ground greatly depends on the size of the wings, the wings are designed to be foldable to form a conventional project for saving space, and the wing folding technology can effectively shorten the wingspan of the airplane and improve the storage and transportation performance of the airplane, so that the wing folding technology has important significance for the application of carrier-based airplanes and has potential value for the daily maintenance and storage of some civil airplanes. In the folding process of the airplane wing, the movable section and the fixed section of the wing are connected through a hinge and can rotate relatively, the connecting part of the wing not only needs to have enough strength, but also needs to fix the movable section and the fixed section of the wing through a lock pin mechanism when the airplane wing is in an open state, so that the whole wing is integrated, and the realization of various functions of the airplane wing in the flying process is ensured.
The lock pin linear driving device is a main component of a lock pin mechanism in an airplane wing folding system, and has the main function of driving the lock pin to extend and retract so as to realize position locking and unlocking movement between wing components. The existing lock pin linear driving device only locks the limit position of the lock pin by the driving mechanism, so that the load on the driving mechanism is large, if the driving mechanism breaks down, the locking function is easy to fail, the safety function is lacked, and potential safety hazards exist.
Disclosure of Invention
The application mainly aims to provide a lockpin linear driving device for an airplane wing folding system, and aims to solve the technical problems that when an existing lockpin linear driving device breaks down, a locking function is easy to fail, and safety is low.
In order to achieve the purpose, the application provides a lock pin linear driving device for an aircraft wing folding system, which comprises a shell, wherein a lock pin is arranged in the shell, one end of the lock pin is connected with a driving mechanism, the driving mechanism is used for driving the lock pin to move linearly, the other end of the lock pin movably extends out of the shell, and a locking mechanism is arranged on the shell and used for locking the limit position of the lock pin.
Optionally, the locking mechanism includes an extension shell disposed on an outer wall of the housing, a stop pin perpendicular to an axis of the lock pin is disposed in the extension shell, the outer wall of the lock pin is respectively provided with a positioning pin hole matched with the stop pin at two limit positions corresponding to the lock pin, and a control assembly is further disposed in the extension shell and used for controlling the stop pin to be inserted into or pulled out of the corresponding positioning pin hole.
Optionally, the control assembly comprises an electromagnet movably sleeved on the stop pin, one end of the stop pin, which is far away from the lock pin, is connected with an armature, the armature is used for generating magnetic adsorption with the electromagnet, the other end of the armature is connected with an extension spring, and the other end of the extension spring is connected to the inner wall of one side, which is far away from the lock pin, of the extension shell.
Optionally, a first accommodating cavity and a second accommodating cavity are arranged in the extension shell, the first accommodating cavity is located between the lock pin and the second accommodating cavity, the electromagnet is located in the first accommodating cavity, the armature and the extension spring are both located in the second accommodating cavity, and the lock pin movably penetrates through the first accommodating cavity and the second accommodating cavity.
Optionally, a guide sliding sleeve is arranged on the inner wall of the shell, the guide sliding sleeve is movably sleeved on the lock pin, and a retainer ring is also movably sleeved on the lock pin and is attached to one end, close to the opening of the shell, of the guide sliding sleeve; wherein the opening of the housing is for the latch to protrude.
Optionally, the driving mechanism includes a driving motor disposed on the housing, the driving motor is connected to a worm and worm gear assembly located in the housing, the worm and worm gear assembly is connected to a conversion assembly, the other end of the conversion assembly is connected to the lock pin, and the conversion assembly is configured to convert a rotational motion of the worm and worm gear assembly into a linear motion of the lock pin.
Optionally, the conversion assembly includes a screw rod capable of moving linearly in the housing, a connecting pin penetrates through between one end of the screw rod and one end of the lock pin, a guide linear groove matched with the connecting pin is formed in the inner wall of the housing, the length direction of the guide linear groove is the same as that of the screw rod, a nut is threaded on the other side of the screw rod, and the nut is connected with the worm and worm gear assembly.
Optionally, the worm and worm wheel assembly comprises a worm shaft, one end of the worm shaft is connected with an output shaft of the driving motor through a coupler, the worm shaft is connected with a worm wheel in a meshed mode, the worm wheel is movably connected to the inner wall of the shell, and the worm wheel is fixedly sleeved on the nut.
Optionally, the worm shaft is connected with an extension rod, and the extension rod movably extends out of the machine shell.
Optionally, the extension rod is polygonal in cross-section.
The beneficial effect that this application can realize as follows:
this application is through having add locking mechanical system, can lock the extreme position of lockpin, and the spacing locking function that cooperation actuating mechanism itself possessed, the reliability of locking structure has been improved, even actuating mechanism breaks down and loses self-locking function, also can rely on locking mechanical system to continue to keep the locking function to the lockpin, thereby have dual fail-safe's effect, the security has been improved, also can only rely on locking mechanical system to play the locking effect to the lockpin here simultaneously, during the locking, actuating mechanism can be for the outage state, thereby reduce the burden that produces when actuating mechanism needs to keep the circular telegram when realizing the auto-lock, thereby reduce actuating mechanism fault rate, also can improve system security.
Drawings
In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings that are needed in the detailed description of the present application or the technical solutions in the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a schematic structural diagram of a latch linear actuator for an aircraft wing folding system according to an embodiment of the present application;
FIG. 2 is a structural schematic view of another cross-sectional orientation of a latch linear actuator for an aircraft wing folding system according to an embodiment of the present application.
Reference numerals:
110-shell, 111-guide linear groove, 120-lock pin, 121-positioning pin hole, 130-locking mechanism, 131-extension shell, 132-stop pin, 133-control component, 1331-electromagnet, 1332-armature, 1333-extension spring, 140-guide sliding sleeve, 150-retainer ring, 160-driving motor, 170-worm and worm wheel component, 171-worm shaft, 172-worm wheel, 173-extension rod, 180-conversion component, 181-screw rod, 182-connecting pin, 183-nut, 190-coupler, 210-flat key, 220-upper bearing, 230-lower bearing, 240-bearing end cap, 250-front bearing, 260-rear bearing, 270-rear cap and 280-sealing ring.
The implementation, functional features and advantages of the objectives of the present application will be further explained with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present application will be described clearly and completely with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It should be noted that all the directional indicators (such as upper, lower, left, right, front, and rear … …) in the present embodiment are only used to explain the relative position relationship between the components, the movement situation, and the like in a specific posture, and if the specific posture is changed, the directional indicator is changed accordingly.
In this application, unless expressly stated or limited otherwise, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
In addition, if there is a description relating to "first", "second", etc. in the embodiments of the present application, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" appearing throughout includes three juxtapositions, exemplified by "A and/or B", including either A or B or both A and B. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present application.
Examples
Referring to fig. 1 to 2, the embodiment provides a lock pin linear driving device for an aircraft wing folding system, including a housing 110, a lock pin 120 is disposed in the housing 110, one end of the lock pin 120 is connected to a driving mechanism, the driving mechanism is used for driving the lock pin 120 to move linearly, the other end of the lock pin 120 movably extends out of the housing 110, a locking mechanism 130 is disposed on the housing 110, and the locking mechanism 130 is used for locking the limit position of the lock pin 120.
Because the locking of the lock pin 120 is kept still by adopting the self-locking function of the driving mechanism in the prior art, the driving mechanism is required to keep the electrified state continuously, the load on the driving mechanism is large, the failure rate of the driving mechanism is increased, and once the driving mechanism fails, the locking function of the lock pin 120 fails, and the safety problem during the operation of the aircraft wing folding system is easily caused. Therefore, in this embodiment, by additionally providing the locking mechanism 130, the limit position of the lock pin 120 can be locked, and the lock mechanism is matched with the limit locking function of the driving mechanism itself, so as to improve the reliability of the locking structure, and even if the driving mechanism fails and loses the self-locking function, the locking mechanism 130 can be used to continue to maintain the locking function of the lock pin 120, thereby having the function of double insurance and improving the safety, and meanwhile, the locking mechanism 130 can be used to play a role in locking the lock pin 120, and during locking, the driving mechanism can be in a power-off state, thereby reducing the burden generated when the driving mechanism needs to be kept powered on when realizing self-locking, thereby reducing the failure rate of the driving mechanism, and also improving the system safety.
It should be noted that the end of the locking pin 120 extending out of the housing 110 is provided with a tapered surface which guides when inserted into the locking hole of the wing folding mechanism.
As an alternative embodiment, the locking mechanism 130 includes an extension shell 131 disposed on an outer wall of the housing 110, a stop pin 132 perpendicular to an axis of the lock pin 120 is disposed in the extension shell 131, two limit positions of the outer wall of the lock pin 120 corresponding to the lock pin 120 are respectively provided with a positioning pin hole 121 engaged with the stop pin 132, and a control assembly 133 is further disposed in the extension shell 131, and the control assembly 133 is configured to control the insertion or extraction of the stop pin 132 into or out of the corresponding positioning pin hole 121.
In the embodiment, the stop pins 132 can be respectively inserted into the positioning pin holes 121 of the two lock pins 120 at the corresponding limit positions, so that the lock pins 120 are locked when being extended to the limit positions or retracted to the limit positions, and the control assembly 133 controls the stop pins 132 to be inserted or pulled out, so that the operation is efficient, the operation is convenient, and the functions of locking and unlocking the positions of the lock pins 120 are realized.
As an alternative embodiment, the control assembly 133 includes an electromagnet 1331 movably sleeved on the stopper pin 132, one end of the stopper pin 132 away from the lock pin 120 is connected with an armature 1332, the armature 1332 is used for generating magnetic attraction with the electromagnet 1331, the other end of the armature 1332 is connected with an extension spring 1333, and the other end of the extension spring 1333 is connected to the inner wall of the extension shell 131 at the side away from the lock pin 120.
In this embodiment, the electromagnet 1331 is a device that generates electromagnetism when being powered on, and a conductive winding matched with the power of the electromagnet is wound outside the iron core, and the coil that is powered on has magnetism like a magnet, and by using the principle of the electromagnet 1331, when the electromagnet 1331 is powered on, magnetic attraction is generated on the armature 1332, so that the armature 1332 is close to the electromagnet 1331, and the stop pin 132 is driven to move towards the direction close to the lock pin 120 until the stop pin 132 is inserted into the positioning pin hole 121 of the lock pin 120, so as to realize automatic locking of the lock pin 120, when unlocking is required, the electromagnet 1331 is powered off, magnetic force is lost, the armature 1332 and the stop pin 132 are reset under the pulling force of the extension spring 1333, so that the positioning pin hole 121 of the lock pin 120 is drawn out, so as to realize automatic unlocking of the lock pin 120, so that the lock pin 120 can freely extend or contract on the housing 110, and the operation is convenient and fast. The extension spring 1333 (also called a tension spring, simply referred to as a tension spring) is a coil spring that is under axial tension, the extension spring 1333 is generally made of a material with a circular cross section, and when the extension spring 1333 is not under load, the coils of the extension spring 1333 are generally parallel and have no gap. In addition, here, the electromagnet 1331 is a circular sleeve structure, and when the stopper pin 132 is movably sleeved with the electromagnet, the movement of the stopper pin 132 is not affected, and meanwhile, a certain guiding function is provided for the movement of the stopper pin 132, so that the stopper pin 132 can stably perform linear motion, thereby achieving two purposes. The stop pin 132 should be of a material that does not magnetically attract the electromagnet 1331 to ensure proper operation.
It should be noted that, here, the electromagnet 1331 and the driving mechanism can be separately powered by a power supply system on the aircraft, when the driving mechanism fails, the locking and unlocking of the lock pin 120 can be controlled by switching on and off the electromagnet 1331, so the control assembly 133 adopts the electromagnet 1331 structure instead of adopting a common telescopic cylinder or other telescopic parts to drive the linear movement of the lock pin 132, because the common telescopic parts need to reserve the stroke space when the moving parts move, the device volume is increased, the assembly with the aircraft wing is inconvenient, the assembly difficulty is large, therefore, the control assembly 133 adopting the electromagnet 1331 structure with a compact structure has a short moving stroke, a small overall volume, and is more beneficial to the adaptability of the aircraft wing system; meanwhile, when power failure occurs, the electromagnet 1331 is automatically powered off to unlock the lock pin 120, so that locking is prevented, and when a common telescopic component fails, locking is directly caused, so that normal operation is affected, and therefore the control assembly 133 adopting the electromagnet 1331 structure is better in adaptability.
As an alternative embodiment, a first receiving cavity and a second receiving cavity are arranged in the extension housing 131, the first receiving cavity is located between the lock pin 120 and the second receiving cavity, the electromagnet 1331 is located in the first receiving cavity, the armature 1332 and the extension spring 1333 are both located in the second receiving cavity, and the stop pin 132 movably penetrates through the first receiving cavity and the second receiving cavity.
In this embodiment, by disposing the electromagnet 1331 in the first accommodation cavity, the armature 1332 and the tension spring 1333 in the second accommodation cavity, and the first accommodation cavity and the second accommodation cavity are independent of each other, the armature 1332 can slide in the second accommodation cavity, which corresponds to a piston movement, thereby improving a guiding effect on the stopper pin 132.
It should be noted that, here, the extension shell 131 can be a detachable assembly mechanism, that is, the extension shell 131 includes a first shell integrally connected with the housing, the other end of the first shell is detachably connected with a second shell through a bolt, the first accommodating cavity is in the first shell, and the second accommodating cavity is in the second shell, so that the assembly and the disassembly are convenient, and the manufacturing difficulty is reduced.
As an optional embodiment, the inner wall of the casing 110 is provided with a guide sleeve 140, the guide sleeve 140 is movably sleeved on the lock pin 120, the lock pin 120 is also movably sleeved with a retainer ring 150, and the retainer ring 150 is attached to one end of the guide sleeve 140 close to the opening of the casing 110; wherein the opening of the housing 110 is for the latch 120 to protrude.
In the present embodiment, when the locking pin 120 performs a linear motion, it can stably slide under the guiding action of the sliding guide sleeve 140, so as to ensure stable and reliable motion and accurate positioning. It should be noted that, here, the guide sliding sleeve 140 is made of copper alloy or other wear-resistant materials, the guide sliding sleeve 140 can be installed in a through hole in the front of the housing 110 through its outer circle, there is a through hole in the middle of the guide sliding sleeve 140, the outer circle diameter of the lock pin 120 is the same as the diameter of the through hole in the guide sliding sleeve 140, the lock pin 120 passes through the hole and forms clearance fit, the lock pin 120 can move back and forth in the through hole in the middle of the guide sliding sleeve 140 during operation, the front end of the hole has an annular groove, a sealing ring 280 is built in to prevent the lubricant in the housing 110 from leaking, the inner wall of the housing 110 has steps to limit the displacement of the guide sliding sleeve 140, and the front end of the guide sliding sleeve 140 is installed with a retaining ring 150 for limiting, the structure is compact, and the operation is stable.
It should be noted that the guide sleeve 140 can be a ball guide sleeve, and has low friction, small resistance, stable operation and good guidance.
As the driving part in the lock pin linear driving device in the prior art adopts the hydraulic oil cylinder technology, hydraulic pipelines and valves are required to be arranged on the wings, and the system is complex to install and maintain; and because the characteristics on the hydraulic cylinder structure, the strength of piston return stroke is less, therefore the thrust and the pulling force that drive lockpin 120 and stretch out and withdraw are inconsistent, the phenomenon that lockpin 120 can't withdraw appears easily in the operation.
Therefore, as an alternative embodiment, the driving mechanism includes a driving motor 160 disposed on the housing 110, the driving motor 160 is connected with a worm and worm gear assembly 170 located in the housing 110, the worm and worm gear assembly 170 is connected with a conversion assembly 180, the other end of the conversion assembly 180 is connected with the lock pin 120, and the conversion assembly 180 is used for converting the rotational motion of the worm and worm gear assembly 170 into the linear motion of the lock pin 120. The conversion assembly 180 comprises a screw 181 which can move linearly in the housing 110, a connecting pin 182 is connected between one end of the screw 181 and one end of the lock pin 120 in a penetrating manner, a guide linear groove 111 which is matched with the connecting pin 182 is formed in the inner wall of the housing 110, the length direction of the guide linear groove 111 is the same as that of the screw 181, a nut 183 is sleeved on the other side of the screw 181 in a threaded manner, and the nut 183 is connected with the worm and gear assembly 170. The worm and worm gear assembly 170 includes a worm shaft 171, one end of the worm shaft 171 is connected to an output shaft of the driving motor 160 through a coupling 190, the worm shaft 171 is connected with a worm gear 172 in a meshing manner, the worm gear 172 is movably connected to an inner wall of the housing 110, and the worm gear 172 is fixedly sleeved on a nut 183.
In this embodiment, during operation, when the output shaft of the driving motor 160 rotates, the coupling 190 drives the worm shaft 171 to rotate, the worm shaft 171 drives the worm wheel 172 to rotate through gear meshing transmission, so as to drive the nut 183 fixedly connected with the worm wheel 172 to rotate, when the nut 183 rotates, the screw 181 cannot rotate along with the screw under the limiting action of the connecting pin 182, so that the rotation motion of the nut 183 is converted into the linear motion of the screw 181, and at this time, the connecting pin 182 slides along with the screw in the guide linear groove 111, so as to drive the lock pin 120 to perform the linear motion. The worm and worm gear transmission has the advantages of compact structure and large transmission ratio, can improve the rotating speed of the motor and simultaneously reduce the volume of the device; meanwhile, the worm and worm gear transmission has a self-locking characteristic, and the lock pin 120 cannot move due to external force factors such as vibration and the like after moving in place, so that the working reliability of the lock pin 120 can be improved; compared with a hydraulic cylinder, the extension and retraction power of the lock pin 120 is the same, so that the lock pin 120 is guaranteed to have reliable retraction driving force, meanwhile, the worm gear 172 is in worm transmission, self-locking can be achieved, and the system reliability is high.
It should be noted that the driving motor 160 is a dc motor, the power of the dc motor is 250 w, the rotating speed is 3000 rpm, and the dc motor is driven by the power supply of the aircraft through the controller to rotate to output power;
the output shaft of the direct current motor is connected with a worm shaft 171 below by two flat keys 210 through a coupler 190 into a whole, the axes of the two shafts are collinear, the two shafts rotate synchronously when in use, an upper bearing 220 and a lower bearing 230 are respectively arranged above and below the worm shaft 171, the two bearings are supported on a vertical bearing hole of the shell 110 through bearing outer rings, the lower end of the bearing hole is provided with an opening, a bearing end cover 240 is arranged at the opening, the bearing end cover 240 is fixed at the opening position of the lower end of the shell 110 through a spring washer and a bolt, a boss is arranged in the middle of the bearing end cover 240, the outer ring of the lower bearing 230 is contacted with the upper surface of the boss of the bearing end cover 240, the structure is compact, and the operation is reliable;
two ends of a nut 183 are respectively supported on a horizontal bearing hole of the shell 110 through a front bearing 250 and a rear bearing 260, the rear end of the bearing hole is provided with an opening, a rear cover 270 is arranged at the opening, the rear cover 270 is arranged at the opening position of the rear end of the bearing hole through a bolt and a spring washer, a through hole is formed in the center of the nut 183, a section of internal thread is arranged at the front part of the through hole, a hole is formed in the middle of a worm wheel, the through hole is arranged on the outer circular surface of the middle part of the nut 183 through a flat key 210, the axis of the worm wheel is vertical to the axis of a worm shaft 171, and the gear teeth of the worm wheel are meshed with a worm to transmit motion and drive the nut 183 to rotate;
the surface of the screw 181 is provided with external threads, the external threads are screwed into the internal thread holes on the nut 183 to form a spiral kinematic pair, the lock pin 120 is cylindrical, the axis of the lock pin 120 is coincided with the axis of the screw 181, one end of the lock pin 120 positioned in the shell 110 is provided with a counter bore, the front end of the screw 181 is provided with a cylinder, the cylinder is inserted into the counter bore of the lock pin 120, the cylinder at the front end of the screw 181 and the counter bore at the rear end of the lock pin 120 are both provided with a radial hole perpendicular to the central line, the axes of the two holes are coincided, the connecting pin 182 is inserted into the radial hole and penetrates through the screw 181 and the lock pin 120, the lower end surface of the connecting pin 182 is flush with the outer circumferential surface of the lock pin 120, the upper part of the connecting pin 182 protrudes out of the outer circumferential surface of the lock pin 120 and extends into the guide linear groove 111, and the width of the guide linear groove 111 is equal to the diameter of the connecting pin 182.
As the manual operation of plugging and unplugging the lock pin 120 is difficult to achieve by adopting the hydraulic oil cylinder scheme under the condition of system failure, so that the wing cannot be folded or unfolded, and the folding mechanism must be integrally disassembled, as an alternative embodiment, the worm shaft 171 is connected with the extension rod 173, and the extension rod 173 movably extends out of the casing.
In the present embodiment, in case of system failure, the extension rod 173 can be rotated from the outside to rotate the worm shaft 171, so that the manual insertion and extraction operation of the lock pin 120 can be realized to improve the safety of the system.
As an alternative embodiment, the cross section of the extension rod 173 is polygonal, generally hexagonal, so as to be convenient for matching with a tool such as a wrench, etc. for convenient operation.
The above description is only a preferred embodiment of the present application, and not intended to limit the scope of the present application, and all the equivalent structures or equivalent processes that can be directly or indirectly applied to other related technical fields by using the contents of the specification and the drawings of the present application are also included in the scope of the present application.
Claims (10)
1. The lockpin linear driving device for the aircraft wing folding system is characterized by comprising a shell, wherein a lockpin is arranged in the shell, one end of the lockpin is connected with a driving mechanism, the driving mechanism is used for driving the lockpin to move linearly, the other end of the lockpin movably extends out of the shell, a locking mechanism is arranged on the shell, and the locking mechanism is used for locking the limit position of the lockpin.
2. The locking pin linear driving device for an aircraft wing folding system according to claim 1, wherein the locking mechanism includes an extension shell disposed on an outer wall of the housing, a stop pin is disposed in the extension shell and perpendicular to an axis of the locking pin, the outer wall of the locking pin is respectively provided with a positioning pin hole corresponding to two extreme positions of the locking pin, the extension shell is further provided with a control assembly, and the control assembly is configured to control the insertion or extraction of the stop pin into or out of the corresponding positioning pin hole.
3. The lock pin linear driving device for the airplane wing folding system according to claim 2, wherein the control assembly comprises an electromagnet movably sleeved on the stop pin, one end of the stop pin far away from the lock pin is connected with an armature, the armature is used for generating magnetic adsorption with the electromagnet, the other end of the armature is connected with an extension spring, and the other end of the extension spring is connected with the inner wall of the extension shell far away from the lock pin.
4. The lock pin linear actuator for an aircraft wing folding system of claim 3, wherein a first receiving chamber and a second receiving chamber are provided in the extension housing, the first receiving chamber is located between the lock pin and the second receiving chamber, the electromagnet is located in the first receiving chamber, the armature and the tension spring are both located in the second receiving chamber, and the lock pin movably penetrates through the first receiving chamber and the second receiving chamber.
5. The lockpin linear driving device for the aircraft wing folding system as claimed in any one of claims 1 to 4, wherein the inner wall of the housing is provided with a guide sliding sleeve, the guide sliding sleeve is movably sleeved on the lockpin, the lockpin is further movably sleeved with a retaining ring, and the retaining ring is attached to one end of the guide sliding sleeve, which is close to the opening of the housing; wherein the opening of the housing is for the latch pin to protrude.
6. A lock-pin linear drive arrangement for an aircraft wing folding system according to any one of claims 1 to 4, wherein the drive mechanism includes a drive motor disposed on the housing, the drive motor having a worm and gear assembly connected thereto, the worm and gear assembly having a conversion assembly connected thereto, the conversion assembly being connected at another end to the lock pin, the conversion assembly being adapted to convert rotational movement of the worm and gear assembly into linear movement of the lock pin.
7. The lock-pin linear driving device for the aircraft wing folding system according to claim 6, wherein the conversion assembly comprises a screw rod capable of linearly moving in the housing, a connecting pin is connected between one end of the screw rod and one end of the lock pin in a penetrating manner, a guide linear groove matched with the connecting pin is formed in the inner wall of the housing, the length direction of the guide linear groove is the same as that of the screw rod, a nut is threaded on the other side of the screw rod, and the nut is connected with the worm and gear assembly.
8. The lock-pin linear drive device for an aircraft wing folding system as claimed in claim 7, wherein the worm-and-worm gear assembly comprises a worm shaft, one end of the worm shaft is connected with an output shaft of the driving motor through a coupling, the worm shaft is engaged with a worm gear, the worm gear is movably connected to the inner wall of the housing, and the worm gear is fixedly sleeved on the nut.
9. The lock-pin linear drive assembly for an aircraft wing-folding system of claim 8, wherein an extension rod is coupled to the worm shaft, the extension rod being movably extendable from the housing.
10. An aircraft wing folding system latch linear actuator as defined in claim 8 in which said extension rod is polygonal in cross section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210915042.2A CN115367099A (en) | 2022-07-29 | 2022-07-29 | Lockpin linear driving device for aircraft wing folding system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210915042.2A CN115367099A (en) | 2022-07-29 | 2022-07-29 | Lockpin linear driving device for aircraft wing folding system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115367099A true CN115367099A (en) | 2022-11-22 |
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| CN202210915042.2A Pending CN115367099A (en) | 2022-07-29 | 2022-07-29 | Lockpin linear driving device for aircraft wing folding system |
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| CN111703570A (en) * | 2020-06-16 | 2020-09-25 | 贵州航天林泉电机有限公司 | Electric mechanism for locking helicopter universal tail wheel |
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| CN111114754A (en) * | 2019-12-31 | 2020-05-08 | 北京机电工程研究所 | Locking mechanism and folding airfoil with same |
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| CN111703570A (en) * | 2020-06-16 | 2020-09-25 | 贵州航天林泉电机有限公司 | Electric mechanism for locking helicopter universal tail wheel |
| CN216805133U (en) * | 2022-03-08 | 2022-06-24 | 湖北航宇精工科技有限公司 | Self-locking device after charging and locking of new energy automobile |
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