CN206318013U - A kind of rope arrangement for aircraft leading edge flap control system - Google Patents
A kind of rope arrangement for aircraft leading edge flap control system Download PDFInfo
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- CN206318013U CN206318013U CN201621387345.8U CN201621387345U CN206318013U CN 206318013 U CN206318013 U CN 206318013U CN 201621387345 U CN201621387345 U CN 201621387345U CN 206318013 U CN206318013 U CN 206318013U
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- fixing hole
- leading edge
- pulley
- cable wire
- aircraft leading
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Abstract
The utility model is related to aircraft flap steerable system structure design, more particularly to a kind of rope arrangement for aircraft leading edge flap control system, at least to solve the problem of current rope arrangement reliability is low.Rope arrangement includes：Fan-shaped rocking arm, drives fan-shaped rocking arm to be rotated towards two opposite directions, to drive aircraft leading edge wing flap to carry out back rotation by its first fixing hole and the second fixing hole；Two first cable wires, are respectively fixedly connected with to the first fixing hole and the second fixing hole；Two second cable wires, are respectively fixedly connected with to the first fixing hole and the second fixing hole；Wherein two first cable wires are controlled by same first actuator, and two second cable wires are controlled by same second actuator.Rope arrangement of the present utility model for aircraft leading edge flap control system, the first cable wire and the second cable wire are two, and such pair of redundancy design can improve the reliability of manipulation, improve flight safety guarantee.
Description
Technical field
The utility model is related to aircraft flap steerable system structure design, more particularly to a kind of to be used for aircraft leading edge wing flap behaviour
The rope arrangement of vertical system.
Background technology
Using the transmission mechanism of mechanical rod-pulling type more than flight control system, there is system weight weight, occupy sky in this mechanism
Between shortcoming that is big and being difficult arrangement.To solve drawbacks described above, rope arrangement is occurred in that, aircraft leading edge flap control system is used in
In system, connection steering wheel and hydraulic pressure distributor gear, to replace the transmission mechanism of mechanical rod-pulling type.
But, in use, particularly under complicated environmental condition, cable wire therein is easily by salt for rope arrangement
The influence of the severe environmental conditions such as mist, temperature shock, in addition, cable wire is in the case of Reusability, cable tension value also easily by
Influence, easily produces cable wire failure, or even occur the extreme failure such as cables break.
The content of the invention
The purpose of this utility model there is provided a kind of rope arrangement for aircraft leading edge flap control system, with least
Solve the problem of current rope arrangement reliability is low.
The technical solution of the utility model is：
A kind of rope arrangement for aircraft leading edge flap control system, the deflection for controlling aircraft leading edge wing flap, bag
Include：
Fan-shaped rocking arm, is arranged on the aircraft leading edge wing flap rotational position, the fan-shaped rocking arm and offers two phases
To the first fixing hole and the second fixing hole, the fan-shaped rocking arm is driven towards two by first fixing hole and the second fixing hole
Individual opposite direction is rotated, to drive the aircraft leading edge wing flap to carry out back rotation；
Two first cable wires, wherein one end of first cable wire is fixedly attached to first fixing hole, it is another
One end of first cable wire described in root is fixedly attached to second fixing hole；
Two second cable wires, wherein one end of second cable wire is fixedly attached to first fixing hole, it is another
One end of second cable wire described in root is fixedly attached to second fixing hole；Wherein
The other end for first cable wire being connected with first fixing hole and it is connected with first fixing hole
The other end of second cable wire is controlled by same first actuator；
The other end for first cable wire being connected with second fixing hole and it is connected with second fixing hole
The other end of second cable wire is controlled by same second actuator.
It is preferred that, the described rope arrangement for aircraft leading edge flap control system also includes：
First bearing, is fixedly installed between the fan-shaped rocking arm and first actuator and the second actuator, described
First pulley and second pulley, the shaft axis of the first pulley and the shaft axis of second pulley are provided with first bearing
Parallel and misaligned, further, the first pulley is located above the level of second pulley, wherein, two first cable wires
Turned to through the first pulley, two second cable wires are turned to through the second pulley.
It is preferred that, the described rope arrangement for aircraft leading edge flap control system also includes：
Second bearing, is fixedly installed between first bearing and first actuator and the second actuator, described
The 3rd pulley is provided with second bearing, and the shaft axis of the 3rd pulley are parallel with the shaft axis of first pulley, its
In, two first cable wires and two second cable wires both pass through the 3rd pulley and are oriented to.
It is preferred that, the 3rd pulley includes four, and the axis of four the 3rd pulleys is overlapped, every described first
Cable wire and second cable wire are each passed through the 3rd pulley and are oriented to.
It is preferred that, the fan-shaped rocking arm has rotation axis, the rotation axis and the aircraft leading edge wing flap rotary shaft
Line is overlapped, and first fixing hole and the second fixing hole are symmetrically distributed in the both sides of the rotation axis.
The utility model has the advantage of：
Rope arrangement of the present utility model for aircraft leading edge flap control system, position signalling is used as by the use of cable wire
Transfer Medium, can substantially reduce the weight of system, and cable wire can easily adjust direction of transfer using turning support；Enter
One step, the first cable wire and the second cable wire are two, and such pair of redundancy design can improve the reliability of manipulation, improve winged
Row safety guarantee.
Brief description of the drawings
Fig. 1 is the structural representation for the rope arrangement that the utility model is used for aircraft leading edge flap control system；
Fig. 2 is that the utility model is used for the structural representation of fan-shaped rocking arm in the rope arrangement of aircraft leading edge flap control system
Figure；
Fig. 3 is that the utility model is used for the structural representation of the first bearing in the rope arrangement of aircraft leading edge flap control system
Figure；
Fig. 4 is that the utility model is used for the structural representation of the second bearing in the rope arrangement of aircraft leading edge flap control system
Figure.
Embodiment
To make the purpose, technical scheme and advantage of the utility model implementation clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the utility model embodiment is further described in more detail.In the accompanying drawings, from beginning
Same or similar element or element with same or like function are represented to same or similar label eventually.Described reality
It is a part of embodiment of the utility model to apply example, rather than whole embodiments.The embodiment described below with reference to accompanying drawing
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belongs to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of description the utility model and simplifies description, rather than indicate or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
1 to Fig. 4 the utility model is described in further details below in conjunction with the accompanying drawings.
The utility model provides a kind of rope arrangement for aircraft leading edge flap control system, for controlling before aircraft
The deflection of edge wing flap, also, rope arrangement is the aircraft leading edge wing flap that may be respectively used for controlling the left and right sides, the present embodiment
In, illustrated by taking side as an example；Rope arrangement for aircraft leading edge flap control system can include fan-shaped rocking arm 1, the
One cable wire 21 and the second cable wire 22.
Fan-shaped rocking arm 1 can be using known a variety of suitable structure types, and it is arranged on aircraft leading edge wing flap and rotates position
Put and two relative the first fixing holes 11 and the second fixing hole 12 are offered on place, fan-shaped rocking arm 1, pass through the He of the first fixing hole 11
Second fixing hole 12 drives fan-shaped rocking arm 1 to be rotated towards two opposite directions, to drive aircraft leading edge wing flap to carry out back rotation.
The quantity of first cable wire 21 is two, wherein one end (left end in Fig. 1) of first cable wire 21 is fixedly connected
To the first fixing hole 11, one end (left end in Fig. 1) of another first cable wire 21 is fixedly attached to the second fixing hole 12.
The quantity of second cable wire 22 is two, wherein one end (left end in Fig. 1) of second cable wire 22 is fixedly connected
To the first fixing hole 11, one end (left end in Fig. 1) of another second cable wire 22 is fixedly attached to the second fixing hole 12.
Further, the other end (right-hand member in Fig. 1) for the first cable wire 21 being connected with the first fixing hole 11 and with first
The other end (right-hand member in Fig. 1) for the second cable wire 22 that fixing hole 11 is connected is controlled by same first actuator；
Equally, the other end (right-hand member in Fig. 1) for first cable wire 21 being connected with the second fixing hole 12 and with
The other end (right-hand member in Fig. 1) of second cable wire 22 of two fixing holes 12 connection is controlled by same second actuator；Need
Bright, the first actuator and the second actuator are not shown, and it can use known a variety of suitable drive devices,
To pull the first cable wire 21 and the second cable wire 22, here is omitted.
Further, in the rope arrangement of the present utility model for aircraft leading edge flap control system, especially such as Fig. 2 institutes
Show, fan-shaped rocking arm 1 has rotation axis, rotation axis 13 is overlapped with aircraft leading edge wing flap pivot center, the He of the first fixing hole 11
Second fixing hole 12 is symmetrically distributed in the both sides of rotation axis 13.
In rope arrangement of the present utility model for aircraft leading edge flap control system, cable wire will pass through aircaft configuration,
And have the requirement of steering, and hence it is also possible to including the first bearing 3 and the second bearing 4.
Especially as shown in figure 3, the first bearing 3 be fixedly installed on the fan-shaped actuator of rocking arm 1 and first and the second actuator it
Between, first pulley 31 and second pulley 32, shaft axis and the second pulley 32 of first pulley 31 are provided with the first bearing 3
Shaft axis are parallel and misaligned；Further, first pulley is located above the level of second pulley；Also, two first cable wires
21 are turned to (steering angle is relevant with the relative position of fan-shaped rocking arm 1) through first pulley 31, and two second cable wires 22 are worn
Second pulley 32 is crossed to be turned to (while also functioning to fixation).In addition, in other preferred embodiments, can also be by first
Pulley 31 and second pulley 32 are respectively set to two, and ratio setting, so that every first cable wire 21 is through one the
One pulley 31, every second cable wire 22 reduces interference each other through a second pulley 32, improves stability.
Especially as shown in figure 4, the second bearing 4 be fixedly installed on the first bearing 3 and the first actuator and the second actuator it
Between, the 3rd pulley 41 is provided with the second bearing 4, and the shaft axis of the 3rd pulley 41 are put down with the shaft axis of first pulley 31
OK, wherein, two first cable wires 21 and two second cable wires 22 both pass through the 3rd pulley 41 and are oriented to (while also functioning to fixation
Effect).In addition, in other preferred embodiments, the 3rd pulley 41 can include four, and the axis weight of four the 3rd pulleys 41
Close, every first cable wire 21 and the second cable wire 22 are each passed through the 3rd pulley 41 and are oriented to, can equally be reduced
Interference each other, improves stability.
The droope snoot rudder face of aircraft belongs to the high-lift system of aircraft, and deflection is synchronized according to control instruction, and this is just needed
Wanting the uniformity of control instruction will get well；It is double in the rope arrangement of the present utility model for aircraft leading edge flap control system
Remaining position signalling transmission system one has four cable wires, and every two cable wires constitute the position signalling transmission system of a closure,
Four cable wires just constitute the position signalling transmission system of a double remainings；In any one point plus a force of this system
Point, it is possible to which control signal is injected into cable wire special delivery system；Also, after one of which cables break, another group of cable wire is still
It can work on, stability is strong.
The above, embodiment only of the present utility model, but protection domain of the present utility model do not limit to
In this, any one skilled in the art is in the technical scope that the utility model is disclosed, the change that can be readily occurred in
Change or replace, should all cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with described
Scope of the claims is defined.
Claims (5)
1. a kind of rope arrangement for aircraft leading edge flap control system, the deflection for controlling aircraft leading edge wing flap, it is special
Levy and be, including：
Fan-shaped rocking arm (1), is arranged on the aircraft leading edge wing flap rotational position, the fan-shaped rocking arm (1) and offers two
Relative the first fixing hole (11) and the second fixing hole (12), is driven by first fixing hole (11) and the second fixing hole (12)
Move the fan-shaped rocking arm (1) to rotate towards two opposite directions, to drive the aircraft leading edge wing flap to carry out back rotation；
Two first cable wires (21), wherein one end of first cable wire (21) is fixedly attached to first fixing hole
(11), one end of another first cable wire (21) is fixedly attached to second fixing hole (12)；
Two second cable wires (22), wherein one end of second cable wire (22) is fixedly attached to first fixing hole
(11), one end of another second cable wire (22) is fixedly attached to second fixing hole (12)；Wherein
The other end for first cable wire (21) being connected with first fixing hole (11) and with first fixing hole
(11) other end of second cable wire (22) of connection is controlled by same first actuator；
The other end for first cable wire (21) being connected with second fixing hole (12) and with second fixing hole
(12) other end of second cable wire (22) of connection is controlled by same second actuator.
2. the rope arrangement according to claim 1 for aircraft leading edge flap control system, it is characterised in that also wrap
Include：
First bearing (3), is fixedly installed between the fan-shaped rocking arm (1) and first actuator and the second actuator, institute
State and first pulley (31) and second pulley (32) be provided with the first bearing (3), the shaft axis of the first pulley (31) with
The shaft axis of second pulley (32) are parallel and misaligned, wherein, two first cable wires (21) pass through the first pulley
(31) turned to, two second cable wires (22) are turned to through the second pulley (32).
3. the rope arrangement according to claim 2 for aircraft leading edge flap control system, it is characterised in that also wrap
Include：
Second bearing (4), is fixedly installed between first bearing (3) and first actuator and the second actuator, institute
State and the 3rd pulley (41) is provided with the second bearing (4), and the shaft axis and first pulley (31) of the 3rd pulley (41)
Shaft axis it is parallel, wherein, two first cable wires (21) and two second cable wires (22) both pass through the described 3rd
Pulley (41) is oriented to.
4. the rope arrangement according to claim 3 for aircraft leading edge flap control system, it is characterised in that described
Three pulleys (41) include four, and the axis of four the 3rd pulleys (41) is overlapped, every first cable wire (21) and institute
State the second cable wire (22) and be each passed through the 3rd pulley (41) and be oriented to.
5. the rope arrangement according to claim 1 for aircraft leading edge flap control system, it is characterised in that the fan
Shape rocking arm (1) has rotation axis, and the rotation axis (13) overlaps with the aircraft leading edge wing flap pivot center, and described first
Fixing hole (11) and the second fixing hole (12) are symmetrically distributed in the both sides of the rotation axis (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621387345.8U CN206318013U (en) | 2016-12-16 | 2016-12-16 | A kind of rope arrangement for aircraft leading edge flap control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621387345.8U CN206318013U (en) | 2016-12-16 | 2016-12-16 | A kind of rope arrangement for aircraft leading edge flap control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206318013U true CN206318013U (en) | 2017-07-11 |
Family
ID=59267224
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621387345.8U Active CN206318013U (en) | 2016-12-16 | 2016-12-16 | A kind of rope arrangement for aircraft leading edge flap control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206318013U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920868A (en) * | 2019-11-19 | 2020-03-27 | 哈尔滨飞机工业集团有限责任公司 | Steering engine mounting device of automatic pilot |
-
2016
- 2016-12-16 CN CN201621387345.8U patent/CN206318013U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920868A (en) * | 2019-11-19 | 2020-03-27 | 哈尔滨飞机工业集团有限责任公司 | Steering engine mounting device of automatic pilot |
| CN110920868B (en) * | 2019-11-19 | 2024-01-12 | 哈尔滨飞机工业集团有限责任公司 | Steering engine mounting device of automatic pilot |
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| GR01 | Patent grant |