CN117585156A - Folding and locking integrated aviation actuator - Google Patents
Folding and locking integrated aviation actuator Download PDFInfo
- Publication number
- CN117585156A CN117585156A CN202311506135.0A CN202311506135A CN117585156A CN 117585156 A CN117585156 A CN 117585156A CN 202311506135 A CN202311506135 A CN 202311506135A CN 117585156 A CN117585156 A CN 117585156A
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- Prior art keywords
- locking
- lock pin
- gear ring
- lock
- shell
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- 230000005540 biological transmission Effects 0.000 claims abstract description 16
- 230000033001 locomotion Effects 0.000 claims description 5
- 229910000831 Steel Inorganic materials 0.000 description 10
- 239000010959 steel Substances 0.000 description 10
- 230000000903 blocking effect Effects 0.000 description 6
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/50—Blades foldable to facilitate stowage of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Retarders (AREA)
Abstract
The invention discloses a folding and locking integrated aviation actuator which comprises a planetary gear mechanism and shells on two sides, wherein a motor arranged in the shells drives a gear ring and a planet carrier shaft to rotate, the gear ring drives paddles to rotate to realize folding and unfolding, the planet carrier shaft drives a lock pin frame to slide through a transmission assembly, and a first locking piece and a second locking piece are used for locking the gear ring and the lock pin frame respectively to limit and lock the folding and unfolding of the paddles. Because the actuator can be locked when the folding and unfolding of the actuator are finished, the external force load is prevented from reversely driving the gear ring, the transmission system and the motor are prevented from being damaged, the actuator adopts a single motor, folding and unfolding, locking and unlocking can be realized through mechanical time sequence, and the actuator has the advantages of small size, light weight and simplicity in control.
Description
Technical Field
The invention relates to the technical field of actuators, in particular to a folding and locking integrated aviation actuator.
Background
The helicopter is one of the creation of the very special features of the aviation technology in the 20 th century, and greatly expands the application range of the aircraft. However, helicopters require a large storage space due to the size of their rotors, and especially medium and heavy helicopters have larger rotor sizes as their takeoff weight increases. The helicopter adopting the rotor wing folding mechanism can greatly reduce the occupied space for parking, and particularly has a remarkable effect on the carrier-borne aircraft.
The helicopter rotor wing folding can adopt modes such as manual folding, hydraulic automatic folding, electric automatic folding and the like, and most of helicopters in China adopt a hydraulic folding mode at present, and the hydraulic folding mode has the advantages of more accessories, complex pipelines, high maintenance difficulty, easy oil leakage and high failure rate. The electric folding mode has compact structure, high reliability, light weight and convenient maintenance, and is a development trend of helicopter folding technology.
In the prior art, the electric folding blade has the following defects: the paddle can only be locked when the paddle is unfolded, no special locking pin mechanism is used for locking the paddle when the paddle is folded, and the mechanical holding of the transmission chain is completely relied on.
At present, two implementations exist, one is to finish two movements by two actuators respectively, two motors and two transmission systems are needed, the other is to realize two actions by one actuator, the input of the two actions can be realized by a single motor or a double motor driving mode, and the two actions are finished by respective motors; with a single motor drive, a transfer mechanism must be provided due to the two different outputs. The adoption of a double-motor driving mode can cause overlarge volume and weight of the actuator, and the control system is also complicated; if a single motor is adopted, a transfer device is required to be arranged, power is switched by means of electromagnet attraction, a transmission part is required to be additionally added, and the size and the weight are overlarge.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides an aviation actuator integrated with folding and locking.
The aim of the invention is realized by the following technical scheme:
the utility model provides a folding locking integrative aviation actuator, includes planetary gear mechanism, planetary gear mechanism includes ring gear, sun gear, planet carrier shaft and a plurality of planet wheel, the both sides of ring gear are provided with first casing, second casing respectively, circumference is provided with a plurality of first slides in the first casing, correspond in the second casing and be provided with a plurality of second slides, still be provided with the motor in the second casing, the motor connect in the sun gear, the ring gear can first casing with rotate between the second casing, just be provided with a plurality of locked groove along circumference on the ring gear, first casing sliding is provided with the lockpin frame, be provided with a plurality of first lockpins on the lockpin frame, first lockpin stretches into in the first slide, the bullet is provided with the second in the second slide, be provided with the steel ball in the locked groove, the planet carrier shaft with the lockpin frame passes through drive assembly transmission and is connected with on the second casing and is used for restricting the first locking piece that the ring gear carrier axially moves, be provided with on the first casing and be used for locking piece to rotate.
Further, a first boss and a second boss are arranged on the side wall of the gear ring, the second locking piece comprises a stop pin, and the stop pin is used for blocking the first boss and the second boss and limiting circumferential rotation of the gear ring.
Further, the first locking piece comprises a locking barrel, the locking barrel is sleeved outside the lock pin frame, a first stop block and a second stop block are arranged on the inner wall of the locking barrel in a radial extending mode, the first stop block and the second stop block are axially distributed, a third stop block and a fourth stop block are arranged on the lock pin frame, and the third stop block and the fourth stop block are axially distributed and circumferentially spaced.
Further, a spring is arranged on the second lock pin, one end of the spring is abutted against the second lock pin, and the other end of the spring is abutted against the inner wall of the second shell.
Further, a through hole is further formed in the lock pin frame, a nut is arranged in the through hole, the transmission assembly comprises a screw rod arranged on the planet carrier shaft, and the lock pin frame is driven to move through transmission connection of the screw rod and the nut.
Further, the motor is in transmission connection with the sun gear through a speed reducing device.
The invention achieves the following beneficial effects: when the folding and unfolding of the actuator are finished, the actuator can be locked, the external force load is prevented from reversely driving the gear ring, the transmission system and the motor are damaged, the actuator adopts a single motor, folding and unfolding and locking and unlocking can be realized through mechanical time sequence, and the actuator has the advantages of small size, light weight and simplicity in control.
Drawings
FIG. 1 is a cross-sectional view of an embodiment;
FIG. 2 is a schematic diagram of a planetary gear mechanism;
FIG. 3 is a schematic structural view of a ring gear;
FIG. 4 is a schematic structural view of a planet carrier shaft;
FIG. 5 is a schematic view of the structure of the first housing;
FIG. 6 is a schematic structural view of the second housing;
FIG. 7 is a schematic structural view of a lockpin rack;
FIG. 8 is a schematic view of the structure of the first locking member;
FIG. 9 is a schematic view of the structure when the lock is deployed;
fig. 10 is a schematic view of the structure in the folding lock.
Reference numerals: 1. a planetary gear mechanism; 2. a gear ring; 3. a sun gear; 4. a planet carrier shaft; 5. a planet wheel; 6. a first housing; 7. a second housing; 8. a first slideway; 9. a second slideway; 10. a motor; 11. a locking groove; 12. a lockpin rack; 13. a first lock pin; 14. a second lock pin; 15. a steel ball; 16. a transmission assembly; 17. a first locking member; 18. a second locking member; 19. a first boss; 20. a second boss; 21. a stop pin; 22. a locking cylinder; 23. a first stopper; 24. a second stopper; 25. a third stopper; 26. a fourth stopper; 27. a spring; 28. a through hole; 29. a nut; 30. a screw rod; 31. a speed reducing device; 32. a mounting hole; 33. a first mounting boss; 34. a second mounting boss; 35. clamping strips; 36. a clamping groove.
Detailed Description
The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments, and it is apparent that the described embodiments are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by a person skilled in the art without any inventive effort, are intended to be within the scope of the present invention, based on the embodiments of the present invention.
As shown in fig. 1-10, a folding and locking integrated aviation actuator is provided at the folding joint between the hub arm and the blade for folding and unfolding the blade. For example, the actuator includes a housing and a planetary gear mechanism 1 disposed in the housing, the planetary gear mechanism 1 is in the prior art, and the specific principle and connection relationship thereof are not described in the present embodiment. In brief, the planetary gear mechanism 1 includes a gear ring 2, a sun gear 3, and a plurality of planetary gears 5, where the planetary gears 5 are connected to the same planet carrier shaft 4, and the sun gear 3 is powered by a motor 10 in the housing and a connected speed reducer 31, so that the sun gear 3 can drive the gear ring 2 to rotate and drive the blades connected to the gear ring 2 to rotate.
In detail, the housing includes a first housing 6 and a second housing 7, and the first housing 6 and the second housing 7 are disposed on both sides of the ring gear 2, respectively, so that the ring gear 2 is rotatable between the first housing 6 and the second housing 7. In more detail, the first casing 6 and the second casing 7 are respectively provided with a first slideway 8 and a second slideway 9, the first slideway 8 and the second slideway 9 are uniformly distributed with a plurality of locking grooves 11 along the circumferential direction, and the gear ring 2 is uniformly provided with a plurality of locking grooves 11 along the circumferential direction, and the first slideway 8, the second slideway 9 and the locking grooves 11 are in one-to-one correspondence. The first shell 6 is internally provided with a lock pin frame 12, the lock pin frame 12 is provided with a through hole 28, the through hole 28 is internally provided with a nut 29, the nut 29 is connected with the transmission assembly 16 on the planet carrier shaft 4, the transmission assembly 16 comprises a screw rod 30, and the screw rod 30 converts the rotation motion of the planet carrier shaft 4 into linear motion, so that the nut 29 drives the lock pin frame 12 to slide along the linear motion. In addition, a plurality of first lock pins 13 are arranged on the lock pin frame 12, the first lock pins 13 are inserted into the first slide ways 8, and when the lock pin frame 12 moves, the first lock pins 13 are driven to slide in the first slide ways 8. The second slideway 9 is internally provided with a second lock pin 14, the second lock pin 14 is provided with a spring 27, one end of the spring 27 is abutted against the second lock pin 14, the other end is abutted against the inner wall of the second shell 7, the locking groove 11 is internally provided with a steel ball 15, and two sides of the steel ball 15 are respectively abutted against the first lock pin 13 and the second lock pin 14.
For example, a first locking member 17 is disposed in the first housing 6, the first locking member 17 includes a locking cylinder 22, the locking cylinder 22 is sleeved outside the lock pin frame 12, a first stop 23 and a second stop 24 are disposed on an inner wall of the locking sleeve in a radial extending manner, the first stop 23 and the second stop 24 are axially distributed, and a third stop 25 and a fourth stop 26 are disposed on the lock pin frame 12 in an axial distribution and circumferentially spaced. The lock cylinder 22 is provided with a locking bar 35, and the locking bar 35 can be inserted into a locking groove 36 provided in the ring gear 2, so that the lock cylinder 22 and the ring gear 2 can be rotated and stopped simultaneously.
In detail, the outer wall of the first housing 6 is provided with a mounting hole 32, the mounting hole 32 is internally provided with a second locking piece 18, the second locking piece 18 comprises a blocking pin 21, the blocking pin 21 is abutted against the outer wall of the gear ring 2, the outer wall of the gear ring 2 is provided with a first boss 19 and a second boss 20, when the gear ring 2 rotates, due to the existence of the blocking pin 21, the rotation angle of the gear ring 2 can be limited to the interval angle between the first boss 19 and the second boss 20, the rotation of the gear ring 2 drives the folding and unfolding of the blade, and the blocking pin 21 can limit the folding and unfolding range of the blade.
The aviation actuator has two states, namely an unfolding locking state and a folding locking state. When the locking state is unfolded, the lock pin frame 12 is positioned between the first locking piece 17 and the gear ring 2, the first lock pin 13 completely stretches into the locking groove 11 to lock the gear ring 2, meanwhile, the steel ball 15 is extruded into the second slideway 9, the second lock pin 14 is extruded to enable the spring 27 to be in a force storage state, the second boss 20 on the gear ring 2 is in contact with the blocking pin 21, and the third stop block 25 on the lock pin frame 12 is axially opposite to the first stop block 23 on the locking cylinder 22. In the folded and locked state, the lock pin frame 12 is positioned between the locking cylinder 22 and the inner wall of the first shell 6, the second lock pin 14 completely stretches into the locking groove 11 to lock the gear ring 2, meanwhile, the steel balls 15 are extruded into the first slide way 8, the first boss 19 on the gear ring 2 is abutted against the stop pin 21, and the fourth stop block 26 on the lock pin frame 12 is axially opposite to the second stop block 24 on the locking cylinder 22.
In some embodiments, the gear ring 2 is provided with a first mounting boss 33, and the outer walls of the first casing 6 and the second casing 7 are provided with two second mounting bosses 34, and the aero actuator can be mounted at the folding joint of the hub support arm and the blade through the first mounting boss 33 and the second mounting boss 34.
Folding locking working principle: when the initial state of the aviation actuator is at the unfolding locking position, the motor 10 drives the sun wheel 3 to rotate anticlockwise, the gear ring 2 rotates clockwise, the first lock pin 13 stretches into the locking groove 11, the gear ring 2 is in a locking state, the planet carrier shaft 4 rotates anticlockwise through the planet wheel 5, so that the screw rod 30 is driven to rotate, the screw rod 30 rotates, the nut 29 is driven to slide along the side far from the gear ring 2, and the lock pin frame 12 is driven to move; when the lock pin frame 12 moves along the side far away from the gear ring 2, the first lock pin 13 on the lock pin frame 12 will withdraw from the locking groove 11, and as the extrusion force disappears, the spring 27 on the second lock pin 14 extrudes the steel ball 15 by the rebound force to push the second lock pin 14 to approach the locking groove 11, and when the steel ball 15 completely enters the locking groove 11, the third stop block 25 on the lock pin frame 12 abuts against the first stop block 23 on the locking cylinder 22 to limit the lock pin frame 12 to continue sliding; at this time, the gear ring 2 is in an unlocking state, the gear ring 2 rotates to drive the paddles to rotate, the paddles are folded, when the folding is completed, the first boss 19 on the gear ring 2 is abutted against the stop pin 21, the gear ring 2 is limited to rotate continuously through the stop pin 21, the locking cylinder 22 is driven to rotate when the gear ring 2 rotates, the first stop block 23 and the third stop block 25 are dislocated, the locking cylinder 22 is in limited contact with the lock pin frame 12, at this time, the second stop block 24 is positioned below the fourth stop block 26, the lock pin frame 12 is kept away from the gear ring 2 to slide, at this time, the second lock pin 14 slides in the second slide under the resilience force of the spring 27 and stretches into the locking groove 11 to lock the gear ring 2.
The working principle of unfolding locking: when the lock pin frame 12 moves close to the gear ring 2, the first lock pin 13 on the lock pin frame 12 pushes the steel ball 15 to the locking groove 11, when the steel ball 15 completely enters the locking groove 11, the fourth stop block 26 on the lock pin frame 12 is abutted with the second stop block 24 on the locking cylinder 22 to limit the lock pin frame 12 to slide continuously, and when the gear ring 2 is locked, the fourth stop block 26 is in contact with the lock pin frame 12, and the lock pin frame 12 is locked with the first stop block 25, and the lock pin frame 12 is locked continuously, so that the lock pin frame 12 is locked continuously.
The foregoing is merely a preferred embodiment of the invention, and it is to be understood that the invention is not limited to the form disclosed herein but is not to be construed as excluding other embodiments, but is capable of numerous other combinations, modifications and environments and is capable of modifications within the scope of the inventive concept, either as taught or as a matter of routine skill or knowledge in the relevant art. And that modifications and variations which do not depart from the spirit and scope of the invention are intended to be within the scope of the appended claims.
Claims (6)
1. An aviation actuator integrated with folding and locking is characterized in that: the planetary gear mechanism (1) comprises a gear ring (2), a sun gear (3), a planet carrier shaft (4) and a plurality of planet gears (5), wherein a first shell (6) and a second shell (7) are respectively arranged on two sides of the gear ring (2), a plurality of first sliding ways (8) are circumferentially arranged in the first shell (6), a plurality of second sliding ways (9) are correspondingly arranged in the second shell (7), a motor (10) is further arranged in the second shell (7), the motor (10) is connected with the sun gear (3), the gear ring (2) can rotate between the first shell (6) and the second shell (7), a plurality of locking grooves (11) are circumferentially arranged on the gear ring (2), a lock pin carrier (12) is arranged in the first shell (6), a plurality of first lock pins (13) are arranged on the lock pin carrier (12), the first lock pins (13) extend into the first sliding ways (8), a lock pin assembly (16) is arranged in the second sliding ways (9), and the lock pin assembly (16) is connected with the lock pin assembly (14) through the second sliding ways (11), the gear ring (2) is connected with a first locking piece (17) used for limiting the axial movement of the lock pin frame (12), and the first shell (6) is provided with a second locking piece (18) used for limiting the circumferential rotation of the gear ring (2).
2. The fold-lock integrated aircraft actuator of claim 1, wherein: the side wall of the gear ring (2) is provided with a first boss (19) and a second boss (20), the second locking piece (18) comprises a stop pin (21), and the first boss (19) and the second boss (20) are blocked by the stop pin (21) to limit circumferential rotation of the gear ring (2).
3. The fold-lock integrated aircraft actuator of claim 1, wherein: the first locking piece (17) comprises a locking barrel (22), the locking barrel (22) is sleeved outside the locking pin frame (12), a first stop block (23) and a second stop block (24) are arranged on the inner wall of the locking barrel (22) in a radial extending mode, the first stop block (23) and the second stop block (24) are axially distributed, a third stop block (25) and a fourth stop block (26) are arranged on the locking pin frame (12), and the third stop block (25) and the fourth stop block (26) are axially distributed and circumferentially spaced.
4. The fold-lock integrated aircraft actuator of claim 1, wherein: the second lock pin (14) is provided with a spring (27), one end of the spring (27) is abutted against the second lock pin (14), and the other end is abutted against the inner wall of the second shell (7).
5. The fold-lock integrated aircraft actuator of claim 1, wherein: the novel planetary gear is characterized in that a through hole (28) is further formed in the lock pin frame (12), a nut (29) is arranged in the through hole (28), the transmission assembly (16) comprises a screw rod (30) arranged on the planet carrier shaft (4), and the lock pin frame (12) is driven to move through transmission connection of the screw rod (30) and the nut (29).
6. The fold-lock integrated aircraft actuator of claim 1, wherein: the motor (10) is in transmission connection with the sun gear (3) through a speed reduction device (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311506135.0A CN117585156A (en) | 2023-11-13 | 2023-11-13 | Folding and locking integrated aviation actuator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311506135.0A CN117585156A (en) | 2023-11-13 | 2023-11-13 | Folding and locking integrated aviation actuator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117585156A true CN117585156A (en) | 2024-02-23 |
Family
ID=89909143
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311506135.0A Pending CN117585156A (en) | 2023-11-13 | 2023-11-13 | Folding and locking integrated aviation actuator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117585156A (en) |
-
2023
- 2023-11-13 CN CN202311506135.0A patent/CN117585156A/en active Pending
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