CN100393578C - Aircraft wing rotation or folding actuator - Google Patents

Abstract

An aircraft wing rotation or folding actuator, including an oil cylinder and a wing rotation or folding mechanism, is characterized in that: the wing rotation or folding mechanism is alternately arranged by rolling spline pairs and rolling straight rotation pairs, or the same or different lift angles The rolling spline pair is composed of a rolling straight-spin pair; among them, the rolling spline pair includes a spline sleeve, a spline groove section of the central shaft, a steel ball in the spline groove and its synchronizing ring; a rolling straight-spin pair includes a spiral sleeve, a spiral groove section of the central shaft , the steel balls and their synchronous rings located in the grooves; the center shaft of the rolling spline pair and the center shaft of the direct-rotation pair or the direct-rotation pair with different lift angles have the same median diameter, which is an integral shaft; one end of the center shaft or Both ends are connected with the piston rod in the oil cylinder body. The present invention uses the oil cylinder piston to drive the rolling screw mechanism to convert the movement into a rotary motion to complete the rotation or folding of the wing. It has the advantages of simple structure, large output torque, small diameter, high transmission efficiency, high reliability, easy manufacture and low cost.

Description

Aircraft wing rotation or folding actuator

technical field

The invention belongs to aircraft components in the aircraft field, in particular to an aircraft wing rotation or folding actuator.

Background technique

The aircraft uses the rotation of each wing such as the rotation of the elevator, leading edge flap, and rudder to control the flight state. Sometimes, such as a carrier-based aircraft, it is necessary to use a rotating mechanism to fold the main wing to reduce the space it occupies. The actuators that turn these wings are called rotary actuators. Typical actuators currently used include: 1. crank mechanism, such as the Su-27 fighter, which has the disadvantage of forming a convex hull on the wing; 2. planetary gear train, such as the F16, which has the disadvantage of complex structure and parts There are many; 3. The screw actuator was first proposed by the United States. The patent is called the ball screw rotary actuator, and the patent number is USB4945779, 1990; this kind of actuator has a small diameter and a large torque, but the patent only proposes A concept has been developed, and many structural problems have not yet been resolved.

Contents of the invention

The purpose of the present invention is to provide a general-purpose wing rotary actuator for aircraft, which can be used for civil large, medium and small passenger and cargo aircraft, as well as military fighters, carrier-based aircraft and space shuttles. This actuator has the advantages of simple structure, small diameter, large output torque, easy manufacture and low cost.

The technical content of the present invention is: an aircraft wing rotation or folding actuator, including an oil cylinder and a wing rotation or folding mechanism, characterized in that: the wing rotation or folding mechanism is alternately arranged by rolling spline pairs and rolling straight rotation pairs , or the arrangement of rolling straight-spin pairs with the same or different lift angles; wherein, the rolling spline pair includes a spline sleeve, a central shaft spline groove segment, steel balls in the spline groove and its synchronizing ring; the rolling straight-spin pair includes a helical The sleeve, the spiral groove section of the central shaft, the steel ball in the groove and its synchronous ring; the central shaft of the rolling spline pair and the direct-rotation pair or the center shafts of the direct-rotation pair with different elevation angles have the same middle diameter, which is an integral shaft; One or both ends of the central shaft are connected with the piston rod in the oil cylinder body.

The wing rotation or folding mechanism of the present invention converts the axial movement of the oil cylinder piston into rotational motion output; the input oil quantity is used to control the rotation angle, and the oil quantity input per unit time is used to control the rotational speed. Use the helix angle to control the torque magnification. Among them, the axial movement speed of the steel ball center is twice as slow as the shaft movement speed, creating a small steel ball moving mechanism, which saves the complicated ball returning mechanism; using the synchronous ring to guide the steel balls to move synchronously, solving the problem of batches of steel balls The synchronous action of the spline pair and the direct rotation pair are treated with equal diameters to create a structure where each pair can enter each other; the three-way thrust bearings in the radial direction, the axial direction to the left, and the axial direction to the right eliminate the need for stop The number of push bearings; the use of multi-screw mechanism can double the output rotation angle.

Description of drawings

Figure 1 is a schematic diagram of the working method of the actuator.

Figure 2 is a schematic diagram of the structure of the actuator.

Fig. 3 is a schematic diagram of an actuator capable of outputting a double rotation angle.

concrete way

The present invention will be specifically described below in conjunction with the accompanying drawings.

Figure 1 is a schematic diagram of the working method of the actuator. The actuator is composed of the following parts: 1-oil cylinder; 2-piston; 3-piston rod; 4-spline sleeve; 5-steel ball; 6-left synchronous ring; The left shaft, the middle shaft with spiral groove and the right shaft with straight spline groove are composed of three sections, and the three constitute a whole shaft; 4, 5, 6, 15 form a rolling spline pair; its function is to only allow the piston to The rod moves axially and bears the reaction moment of the load; the straight rotation pair is composed of the spiral sleeve 8, the steel ball, the middle synchronous ring 9 and the screw shaft in the middle section of the central shaft 15, and its function is to convert the axial linear movement of the central shaft It is the rotational motion of the helical sleeve 8; there is a left thrust pair between the spline sleeve 4 and the helical sleeve 8, which is composed of the outer raceway at the right end of the spline sleeve 4, the steel ball 7 and the inner raceway at the left end of the helical sleeve 8; Its function is to only allow the spline sleeve 4 and the spiral sleeve 8 to rotate mutually, and limit the mutual axial movement of the two; 9- the synchronous ring; the rotary motion of the actuator is output by the spiral sleeve 8 through the hanging ear 10; 11- Right thrust pair steel ball; 12-right spline sleeve; 13-right synchronous ring; right spline sleeve 12, steel ball, right synchronous ring 13, the spline shaft of central shaft 15 right section form right spline pair; The mounting lug 14 used for fixing the actuator and the body is connected on the left and right spline pairs, which can bear the reaction force and moment from the rotor in a balanced manner.

The working process of the actuator is as follows: when the flight control computer instructs the hydraulic servo valve to input oil to the oil cylinder 1, the piston rod 3 is pushed by the piston 2 to move; the central shaft 15 is driven to move axially, and the spiral groove in the middle of the central shaft 15 pushes the steel The ball rolls to drive the helical sleeve 8 to rotate, and the hanging lug 10 on the helical sleeve 8 drives the rotor to rotate. The radial force and the reaction moment of the rotating wing to the actuator are passed to the left and right ends through the central shaft 15, and then passed to the body through the left and right spline auxiliary transmission left and right spline sleeves, and then passed to the body through the hanging lug 14.

Figure 2 is a schematic diagram of the structure of the actuator. All part numbers in the figure correspond to those in figure 1 one by one. The main body of the actuator is a central shaft and three sleeves. The output torque amplification ratio of the actuator is adjusted by the helix angle α. The pitch diameter of the spline pair of the actuator and the direct rotation pair are designed to be the same value, so that the spline shaft part and the screw shaft part of the central shaft can enter each other, thus significantly shortening the axial dimension of the actuator.

Figure 3 is an actuator capable of outputting a larger rotation angle. The difference between it and Figure 1 is that, in addition to the right-handed straight-rotation pair in the middle of the original central shaft, the left and right spline pairs are also used as left-handed straight-rotation pairs. vice. The lift angles are α ₁ and α ₂ respectively. Like this, except that when the original central axis 15 moves axially, the helical sleeve 8 will output the rotation (the effect of α ₁ ); Therefore, when the piston rod 3 moves, the left section of the central axis will also be pushed to rotate by the steel ball 5 (the effect of α ₂ ), so that the screw sleeve 8 can output both rotations. At this time, since the piston rod 3 cannot turn and the center shaft 15 will turn, the two need to be connected through the thrust bearing 16.

Claims (4)

1. an aircraft wing rotates or folds and uses actuator, comprises rotation of the oil cylinder and the wing or fold mechanism, it is characterized in that: wing rotation or fold mechanism replace arrangement by rolling spline pair and rolling direct rotary pair, or the rolling direct rotary pair of identical or different lift angle rearranges; Wherein, rolling spline pair comprises spline housing, axis spline section, the steel ball that is positioned at spline and baulk ring thereof; Rolling direct rotary pair comprises screw-casing, axis plug helix section, the steel ball that is positioned at groove and baulk ring thereof; The rolling spline pair axis equates with the middle footpath of the axis of the direct rotary pair of direct rotary pair or different lift angles, is an integral shaft; Piston rod in the one or both ends of described axis and the cylinder body is connected.

2. aircraft wing rotation according to claim 1 and the folding actuator of using, it is characterized in that: between spline housing and screw-casing, or have left thrust pair between the screw-casing of different lift angles, constitute by the interior raceway of outer raceway, steel ball 7 and adjacent screw-casing one end of spline housing or screw-casing one end.

3. aircraft wing rotation according to claim 1 reaches to fold uses actuator, and it is characterized in that: the screw-casing of rolling direct rotary pair has the hangers that connects wing.

4. aircraft wing rotation according to claim 1 reaches to fold uses actuator, and it is characterized in that: the screw-casing of the spline housing of rolling spline pair or rolling direct rotary pair has the hangers that connects body.

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