CN-117585156-B - Folding and locking integrated aviation actuator

CN117585156BCN 117585156 BCN117585156 BCN 117585156BCN-117585156-B

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.

Inventors

ZHANG WEI
FENG HAOYUAN
CHUN JIN
CUI JIANKUN

Assignees

成都飞亚航空设备应用研究所有限公司

Dates

Publication Date: 20260505
Application Date: 20231113

Claims (4)

1. The folding and locking integrated aviation actuator is characterized by comprising a planetary gear mechanism (1), wherein 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), 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 formed in the gear ring (2) along the circumferential direction, a lock pin frame (12) is arranged in the first shell (6), a plurality of first lock pins (13) are arranged on the lock pin frame (12) in a sliding way, the first lock pins (13) extend into the first sliding ways (8) and are provided with lock pins (15), the planet carrier shaft (4) is in transmission connection with the lock pin frame (12) through a transmission assembly (16), a first locking piece (17) for limiting the axial movement of the lock pin frame (12) is connected to the gear ring (2), and a second locking piece (18) for limiting the circumferential rotation of the gear ring (2) is arranged on the first shell (6); The lock pin frame (12) is further provided with a through hole (28), 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); 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.
2. The folding and locking integrated aviation actuator according to claim 1, wherein a first boss (19) and a second boss (20) are arranged on the side wall of the gear ring (2), the second locking piece (18) comprises a blocking pin (21), and the blocking pin (21) blocks the first boss (19) and the second boss (20) to limit circumferential rotation of the gear ring (2).
3. The folding and locking integrated aviation actuator according to claim 1, wherein a spring (27) is arranged on the second lock pin (14), one end of the spring (27) is abutted against the second lock pin (14), and the other end of the spring is abutted against the inner wall of the second shell (7).
4. The folding and locking integrated aviation actuator according to claim 1, wherein the motor (10) is in transmission connection with the sun wheel (3) through a speed reducing device (31).

Description

Folding and locking integrated aviation actuator 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 that the blade can be locked only when the blade is unfolded, no special locking pin mechanism is used for locking the blade when the blade is folded, and the blade is completely held by the mechanical gripping of a transmission chain. At present, two implementations are available, one of which is to use two actuators to complete two movements respectively, two motors and two transmission systems are needed, the other is to use one actuator to achieve two actions, the input of the two actions can be achieved by using a single motor or a double motor driving mode, the two actions are completed by using respective motors, and a transfer mechanism is needed to be arranged due to the fact that the two different outputs are adopted by using single motor driving. The adoption of a double-motor driving mode can lead to overlarge volume and weight of the actuator and is more complicated for a control system, if a single motor is adopted, a transfer device is required to be arranged, power is switched by means of attraction of an electromagnet, and a transmission part is required to be additionally added, so that the volume 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