CN100393578C

CN100393578C - Actuator for rotating or folding aerofoil of airplane

Info

Publication number: CN100393578C
Application number: CNB2004100221049A
Authority: CN
Inventors: 梁锡昌
Original assignee: Chongqing University
Current assignee: Chongqing University
Priority date: 2004-03-23
Filing date: 2004-03-23
Publication date: 2008-06-11
Anticipated expiration: 2024-03-23
Also published as: CN1562704A

Abstract

The present invention relates to an actuator for the rotation or the folding of the wings of a plane, which comprises an oil cylinder and a wing rotation or folding mechanism. The actuator is characterized in that the wing rotation or folding mechanism is formed by alternately providing spline pairs with rolling contact and rolling straight rotation pairs or by arranging rolling straight rotation pairs with identical or different ascent angles, wherein the spline pairs with rolling contact comprise spline sleeves, center shaft spline slotted sections, steel balls in spline slots and synchronous rings thereof; the rolling straight rotation pairs comprise helical casings, center shaft helical slotted sections, steel balls in slots and synchronous rings thereof; the pitch diameters of center shafts of the spline pairs with rolling contact and the straight rotation pairs or center shafts of the straight rotation pairs with different rise angles are equal, and the center shafts are an integral shaft; and one end or both ends of each of the center shafts are connected with a piston rod in the oil cylinder. The actuator utilizes a piston in the oil cylinder to drive a rolling screw mechanism to convert translation to rotation, and thus, the actuator can rotate or fold wings. The actuator has the advantages of simple structure, large output force moment, small diameter, high transmission efficiency, high reliability, easy production and low cost.

Description

Aircraft wing rotation or fold actuator

Technical field

The invention belongs to the aircraft components in the aircraft field, specifically be the rotation of a kind of aircraft wing or fold actuator.

Background technology

Aircraft is to utilize each wing rotation to control state of flight as the rotation of elevating plane, droope snoot, yaw rudder, sometimes, also need utilize rotating mechanism to fold main wing as ship-board aircraft, is taken up space to dwindle self.Rotate the actuating unit of these wings, be called rotary actuator.The present typical actuator of using has: 1, and crank mechanism, as 27 fighter planes of reviving, its shortcoming is to form convex closure on wing; 2, planet circular system, as F16, its shortcoming is a complex structure, the part number is a lot; 3, the spiral actuator is proposed the earliest by the U.S., and patent is called the ball screw rotary actuator, and the patent No. is USB4945779, and 1990; This actuator diameter is little, and it is big to produce moment, but this patent has only proposed a conception of species, and a lot of structure problems are still unresolved.

Summary of the invention

The purpose of this invention is to provide a kind of aircraft general-duty wing rotary actuator, both can be used for large-scale, medium-sized, the small-sized Passenger Cum Freighter of coml, also can be used for military fighter plane, ship-board aircraft, space shuttle.This actuator has simple in structure, and diameter is little, and output torque is big, is convenient to make low cost and other advantages.

Technology contents of the present invention is: a kind of aircraft wing rotation or the folding actuator of using, comprise rotation of the oil cylinder and the wing or fold mechanism, it is characterized in that: wing rotation or fold mechanism are by rolling spline pair and the secondary alternately arrangement of rolling direct rotary, 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.

Wing rotation of the present invention or fold mechanism are converted to the output that rotatablely moves with moving axially of oil cylinder piston; Utilize the fuel-flow control corner of input, utilize the fuel-flow control rotating speed of unit time input.Utilize lead angle control torque magnification factor.Wherein, the steel ball center shaft than axle moving velocity doppio lunghezza di tempo, creates the little travel mechanism of steel ball to moving velocity, has saved complicated go back to pearl mechanism; Utilize baulk ring, the guiding steel ball is synchronized with the movement, and has solved the synchronization action of steel ball in batch; Spline pair, direct rotary pair are carried out equal diameter handle, created the structure that each pair can enter mutually; Utilize radially, axially left, axial three axial thrust bearings to the right, saved the quantity of thrust bearing; Adopt many screw mechanisms, increase output corner that can be at double.

Description of drawings

Fig. 1 is the method for work scheme drawing of actuator.

Fig. 2 is the structural representation of actuator.

Fig. 3 is the actuator scheme drawing that can export double corner.

Concrete real mode

Below in conjunction with accompanying drawing the present invention is made specific description.

Fig. 1 is the method for work scheme drawing of actuator.Actuator is made up of following parts: the 1-oil cylinder; The 2-piston; The 3-piston rod; The 4-spline housing; The 5-steel ball; 6-left side baulk ring; The 15-axis, it is by forming for three sections with the left side axle of straight spline, band spiral fluted axis and with the right axle of straight spline, and the three constitutes a bearing; 4,5,6,15 form rolling spline pair; Its function is only to allow the piston rod axial motion, and bears the moment of reaction of load; Screw shaft by screw-casing 8, steel ball, middle baulk ring 9 and axis 15 stage casings is formed the direct rotary pair, and its function is that the axial straight line with axis moves and is converted to rotatablely moving of screw-casing 8; Between spline housing 4 and screw-casing 8, have left thrust pair, constitute by the interior raceway of outer raceway, steel ball 7 and screw-casing 8 left ends of spline housing 4 right-hand members; Its function is only to allow spline housing 4 and screw-casing 8 to rotate mutually, limits both moving axially mutually; Baulk ring among the 9-; Rotatablely moving by screw-casing 8 of actuator through hangers 10 outputs; The right thrust pair steel ball of 11-; The right spline housing of 12-; The right baulk ring of 13-; The castellated shaft of right spline housing 12, steel ball, right baulk ring 13, axis 15 right sections is formed right spline pair; Actuator and the body fixedly hangers 14 of usefulness are connected on left and right two spline pairs, can balancedly bear antagonistic force and moment that rotor transmits.

The working process of actuator is as follows: when flight control computer instructs hydraulic efficiency servo-valve to oil cylinder 1 input oil, promote piston rods 3 by piston 2 and move; Drive axis 15 and move axially, the plug helix promotion steel ball rolling by axis 15 stage casings drives screw-casing 8 and rotates, and drives the rotor rotation by the hangers on the screw-casing 8 10 again.Rotor, is passed to about it and is held through axis 15 diametral load of actuator and the moment of reaction, through the left and right spline housing of left and right spline pair transmission, passes to body through hangers 14 more again.

Fig. 2 is the structural representation of actuator.All piece numbers are corresponding one by one with Fig. 1 among the figure.The main body of actuator is an axis and three covers.The output torque amplification ratio of actuator is regulated by lead angle α.The spline pair of actuator is designed to identical value with the middle footpath of direct rotary pair, and like this, the splined shaft portion of axis and screw shaft part can enter mutually, thereby has significantly shortened the axial dimension of actuator.

Fig. 3 is the actuator that can export bigger corner, and the difference of it and Fig. 1 is, except original axis stage casing is dextrorotation direct rotary pair, again with left and right spline pair also as left-handed direct rotary pair.Its lift angle is respectively α ₁And α ₂Like this, when moving axially except original axis 15, screw-casing 8 will be exported rotation (α ₁Effect); And, the left side also be a direct rotary pair because its overcoat 4 is fixing with oil cylinder 1, can not move and rotate, therefore, when piston rod 3 moved, axis left side section also can be promoted to rotate (α by steel ball 5 ₂Effect), thereby make both rotations of screw-casing 8 output.At this moment, because piston rod 3 can not transfer axis 15 and will change, so both also need through thrust bearing 16 connections.

Claims

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.