CN108216599B

CN108216599B - Front wheel turning mechanism with double linkage and large operation angle

Info

Publication number: CN108216599B
Application number: CN201711340073.5A
Authority: CN
Inventors: 雷驰; 刘远平; 许杰; 安涛; 方勇; 范哲
Original assignee: AVIC Chengdu Aircraft Design and Research Institute
Current assignee: AVIC Chengdu Aircraft Design and Research Institute
Priority date: 2017-12-14
Filing date: 2017-12-14
Publication date: 2021-04-20
Anticipated expiration: 2037-12-14
Also published as: CN108216599A

Abstract

The invention belongs to the field of aviation, and particularly relates to a double-linkage large-operating-angle front wheel turning mechanism. The mechanism is characterized in that: two push-pull type actuating cylinders are overlapped in a relay installation mode, so that the rotation angle is greatly increased. The actuator cylinder (5) is adopted to integrally push an upper sleeve (3) and a lower sleeve (7) which are provided with a secondary actuator cylinder (2) to realize the rotation of a first stage, and after the primary actuator cylinder (5) reaches an extreme position, the secondary actuator cylinder (2) can continuously push an output sleeve (4) to move to realize the movement of a second stage. The primary actuator cylinder (5) and the secondary actuator cylinder (2) can move respectively, wherein the immovable actuator cylinder realizes the stopping and the load transmission through a hydraulic oil lock, a mechanism self-locking device or an electric phase locking device. Meanwhile, the double actuating cylinders can provide redundancy and improve reliability. The mechanism can realize front turning with high power and can meet the requirements of carrier-borne airplanes and civil airplanes on front wheel power large turning angles.

Description

Front wheel turning mechanism with double linkage and large operation angle

Technical Field

The invention belongs to the field of aviation, and particularly relates to a double-linkage large-operating-angle front wheel turning mechanism.

Background

The push-pull type front wheel steering driving mode is widely applied to driving of front wheel steering systems of various models with the advantages of large force arm, high efficiency, simple and reliable mechanism and the like. However, the conventional single-acting force arm driving mode is limited by the structural form, and the turning angle of the conventional single-acting force arm driving mode cannot be too large, otherwise, the force arm of the actuating cylinder driving force is too small or structural collision interference is caused. The structure form of the angle amplification by the special mechanism has the limitation of the mechanism characteristic, the power turning angle cannot be too large, and the reliability is not high because of the multiple mechanisms, difficult adjustment and difficult maintenance. And the power control angle of the front wheel is required to be more than +/-90 degrees in the fields of carrier-based aircrafts, civil aircrafts and the like, and the required angle is more difficult to achieve by using a single-action driving mode. The double-linkage large-operating-angle front wheel turning mechanism has the advantages of simple structure, convenient maintenance, easy realization of large-angle power operation, mutual backup of the primary actuating cylinders and the secondary actuating cylinders of the double linkage, realization of double redundancy of the operating mechanism and good reliability.

Disclosure of Invention

A double-linkage large-angle front wheel steering mechanism is basically characterized in that an upper sleeve (3) and a lower sleeve (7) provided with a secondary actuating cylinder (2) are integrally pushed by an actuating cylinder (5) to realize rotation in a first stage, and after a primary actuating cylinder (5) reaches a limit position, the secondary actuating cylinder (2) can continuously push an output sleeve (4) to move to realize movement in a second stage. The primary actuator cylinder (5) and the secondary actuator cylinder (2) can move respectively, wherein the immovable actuator cylinder realizes the stopping and the load transmission through a hydraulic oil lock, a mechanism self-locking device or an electric phase locking device. The primary ram (5) and the secondary ram (2) are also simultaneously movable to achieve twice the rate of steering action. Meanwhile, the primary actuator cylinder (5) and the secondary actuator cylinder (2) move independently and are linked to realize large and small gain control of a front wheel steering system, and the secondary actuator cylinder (2) moves independently during small gain, so that the steering speed is low, and the steering angle is small. When the gain is large, the secondary actuator cylinder (2) and the primary actuator cylinder (5) are linked, the steering speed is high, and the steering angle is large.

The technical scheme is as follows:

a double-linkage large-operating-angle front wheel turning mechanism comprises a strut (1), a secondary actuating cylinder (2), an upper sleeve (3), a driving sleeve (4), a primary actuating cylinder (5), a connecting shaft (6), a lower sleeve (7), a torsion arm (8), a piston rod (9) and a tire (10).

The mechanism is formed by overlapping three sleeves, and the power steering movement is completed by a secondary actuating cylinder (2) and a primary actuating cylinder (5). The three rotating sleeves are an upper sleeve (3), a driving sleeve (4) and a lower sleeve (7) which are sleeved on the support column (1) in sequence, wherein the upper sleeve (3) and the lower sleeve (7) are connected together through a connecting shaft (6). The drive sleeve (4) is a force output sleeve which is connected to the torsion arm (8) in order to transmit a rotational torque to the wheel tire (10). The secondary actuating cylinder (2) is arranged between the upper sleeve (3) and the lower sleeve (7) through a trunnion and is linked with the upper sleeve (3) and the lower sleeve (7). The primary ram (5) is mounted on the arm of the strut (1). A piston rod of the primary actuating cylinder (5) is connected with the upper sleeve (3) and the lower sleeve (7) through a connecting shaft (6) and drives the upper sleeve (3), the lower sleeve (7), the connecting shaft (6) and the secondary actuating cylinder (2) to be in rotary linkage together. At the same time, the piston rod of the secondary actuator cylinder (2) is connected with the drive sleeve (4) and directly forces the drive sleeve (4) to rotate.

The invention has the advantages and beneficial effects that: (a) the invention can realize the power front wheel turning of more than +/-90 degrees (namely the total deflection angle is more than 180 degrees). (b) The invention adopts the conventional push-pull actuating cylinder, has large force arm and high efficiency. (c) The invention has double redundancy, when one actuator is blocked, the other actuator can continue to move to ensure the direction control capability of the airplane.

Drawings

FIG. 1 is a block diagram of the present invention

Wherein: 1-pillar, 2-secondary actuator cylinder, 3-upper sleeve, 4-driving sleeve, 5-primary actuator cylinder, 6-connecting shaft, 7-lower sleeve, 8-torsion arm, 9-piston rod and 10-tyre

FIG. 2 is a theoretical view of the structure neutral position of the present invention

FIG. 3 is a right deflection limit diagram of the mechanism of the present invention

FIG. 4 is a left deflection limit diagram of the mechanism of the present invention

Detailed Description

A double-linkage large-operating-angle front wheel turning mechanism comprises a strut (1), a secondary actuating cylinder (2), an upper sleeve (3), a driving sleeve (4), a primary actuating cylinder (5), a connecting shaft (6), a lower sleeve (7), a torsion arm (8), a piston rod (9) and a tire (10)

Fig. 2 is a neutral position theoretical diagram. Point 0 in the figure is the sleeve rotation center; the rod AD represents a connecting rod consisting of the upper sleeve (3) and the lower sleeve (7); the point C is a connecting point of the actuating cylinder (5) and the support arm; the rod BO is a drive sleeve (4) and is connected to a torque arm (8) to transmit the turning drive force to the tire. And the point D is a connecting point of the actuating cylinder (2) and the upper sleeve (3) and the lower sleeve (7). When the actuating cylinder (5) extends, the rod AD is pushed to rotate around the point O, the rod AD drives the actuating cylinder (2) to move to the rightmost position, meanwhile, the actuating cylinder (2) contracts, and the driving sleeve (4) is further pulled rightmost, namely, the point B is driven to move to the rightmost position. When the actuating cylinder (5) is shortened, the rod AD is pulled to rotate around the point O, the rod AD drives the actuating cylinder (2) to move to the leftmost position, meanwhile, the actuating cylinder (2) is extended, and the driving sleeve (4) is further pulled towards the left side, namely, the point B is driven to move to the leftmost position.

When the aircraft needs to turn at a large power angle, the actuating cylinder (2) and the actuating cylinder (5) are linked simultaneously, wherein when the actuating cylinder (2) contracts and the actuating cylinder (5) extends, the driving sleeve (4) drives the front wheel to deflect to the right at a large angle, which corresponds to the state shown in fig. 3.

When the actuating cylinder (2) is extended and the actuating cylinder (5) is retracted, the driving sleeve (4) drives the front wheel to deflect to the left by a large angle, which corresponds to the state of fig. 4.

Claims

1. A double-linkage large-operating-angle front wheel turning mechanism comprises a strut (1), a secondary actuating cylinder (2), an upper sleeve (3), a driving sleeve (4), a primary actuating cylinder (5), a connecting shaft (6), a lower sleeve (7), a torsion arm (8), a piston rod (9) and a tire (10); the method is characterized in that: the front wheel turning mechanism is formed by overlapping three rotating sleeves, and the power steering motion is completed by a secondary actuating cylinder (2) and a primary actuating cylinder (5); the three rotating sleeves, namely an upper sleeve (3), a driving sleeve (4) and a lower sleeve (7), are sequentially sleeved on the strut (1), wherein the upper sleeve (3) and the lower sleeve (7) are connected together through a connecting shaft (6); the driving sleeve (4) is a force output sleeve which is connected with the torque arm (8) so as to transmit the rotation torque to the tire (10); the secondary actuating cylinder (2) is arranged between the upper sleeve (3) and the lower sleeve (7) through a trunnion and is linked with the upper sleeve (3) and the lower sleeve (7) together; the primary actuating cylinder (5) is arranged on the support arm of the strut (1); a piston rod of the primary actuating cylinder (5) is connected with the upper sleeve (3) and the lower sleeve (7) through a connecting shaft (6) and drives the upper sleeve (3), the lower sleeve (7), the connecting shaft (6) and the secondary actuating cylinder (2) to be in rotary linkage; at the same time, the piston rod of the secondary actuator cylinder (2) is connected with the drive sleeve (4) and directly forces the drive sleeve (4) to rotate.