CN107082114A - A kind of airplane operation system control wheel rotating shaft - Google Patents
A kind of airplane operation system control wheel rotating shaft Download PDFInfo
- Publication number
- CN107082114A CN107082114A CN201710200428.4A CN201710200428A CN107082114A CN 107082114 A CN107082114 A CN 107082114A CN 201710200428 A CN201710200428 A CN 201710200428A CN 107082114 A CN107082114 A CN 107082114A
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- CN
- China
- Prior art keywords
- control wheel
- rotating shaft
- wheel rotating
- axis
- connecting hole
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of flight control system control wheel rotating shaft, control wheel rotating shaft one end is control wheel end and is connected with control wheel, the other end is chain end and is connected with operating system, there is survey to turn round region in the middle part of control wheel rotating shaft, surveying to turn round stress section is posted on region, surveyed from control wheel rotating shaft and turn round region to chain end provided with two inclined holes, axisymmetrical of two inclined holes along control wheel rotating shaft, and the intersection point of two inclined hole axis is located on the axis of control wheel rotating shaft, connecting hole is provided with from the end face at control wheel rotating shaft chain end to control wheel end, the axis of connecting hole and the axis collinear of control wheel rotating shaft, and the axis of connecting hole meets at intersection point；The cable of foil gauge is passed after passing through inclined hole from connecting hole.The airplane operation system control wheel rotating shaft of the present invention solves the problem of cable can wind control wheel rotating shaft in process of the test, realizes the measurement for the power that control wheel applies to control wheel rotating shaft, so that the optimization to control wheel rotating shaft provides foundation.
Description
Technical field
The invention belongs to technical field of aircraft structure design, more particularly to a kind of airplane operation system control wheel rotating shaft.
Background technology
Flight control system is complicated, and current aircraft is not monitored to the power that control wheel applies, therefore can not
The accurate size for obtaining active force on control wheel, influences the flight safety of aircraft.In order to ensure that the use safety of steerable system can
Lean on, it is desirable to which the static strength and fatigue behaviour of rotating shaft are on the premise of existing aircraft mounting means are not less than, and countershaft is optimized
Design.When testing existing control wheel rotating shaft, after strain gauge adhesion is in relevant position, the cable being connected with foil gauge
Placement Problems will highlight, i.e., when experiment, cable can enwind control wheel rotating shaft, cause experiment can not continue or influence
The accuracy of experiment.
The content of the invention
It is an object of the invention to provide a kind of airplane operation system control wheel rotating shaft, solve current control wheel rotating shaft and carry out
The problem of cable meeting twisting shaft being connected during experiment with foil gauge.
To reach above-mentioned purpose, the technical solution adopted by the present invention is：A kind of flight control system control wheel rotating shaft, drives
Disk rotating shaft one end is control wheel end and is connected with control wheel that the other end is chain end and is connected with operating system, is being driven
There is survey to turn round region in the middle part of disk rotating shaft, post stress section in described survey on torsion region, surveyed from the control wheel rotating shaft and turn round region to institute
Chain end is stated provided with two inclined holes, axisymmetrical of two inclined holes along the control wheel rotating shaft, and two inclined hole axis
Intersection point is located on the axis of the control wheel rotating shaft, and connecting hole is provided with from the end face at control wheel rotating shaft chain end to control wheel end,
The axis of the connecting hole and the axis collinear of the control wheel rotating shaft, and the axis of the connecting hole meets at the intersection point；Institute
State foil gauge cable pass through inclined hole after passed from the connecting hole.
Further, the angle of the axis of the inclined hole and the axis of the control wheel rotating shaft is 45 °.
Further, the diameter of the connecting hole is more than the diameter of the inclined hole.
A kind of airplane operation system control wheel rotating shaft of the present invention is turned round by being provided with inclined hole and connecting hole on body surveying
After the arrangement stress section of region, cable can be passed from inclined hole and connecting hole, and control wheel can be wound by solving cable in process of the test
The problem of rotating shaft, the measurement for the power that control wheel applies to control wheel rotating shaft is realized, so that the optimization to control wheel rotating shaft is provided
Foundation.
Brief description of the drawings
Accompanying drawing herein is merged in specification and constitutes the part of this specification, shows the implementation for meeting the present invention
Example, and for explaining principle of the invention together with specification.
Fig. 1 is the control wheel pivot structure schematic diagram of one embodiment of the invention.
Wherein, 1- control wheels rotating shaft, 2-, which is surveyed, turns round region, 3- stress sections, 4- inclined holes, 5- connecting holes.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than whole embodiments.The embodiment described below with reference to accompanying drawing is exemplary type, it is intended to used
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of the work of creation type is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, 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 the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
It is as shown in Figure 1 the airplane operation system control wheel rotating shaft of the present invention, its one end is connected with control wheel, another
End is connected with operating system (i.e. next stage component), when it should be understood that when static strength to control wheel rotating shaft and fatigue behaviour, just
When testing it.The power applied during experiment on control wheel, is delivered to down by the control wheel rotating shaft being connected with control wheel
One-level component.In order to ensure the flight safety of aircraft, influence of the power acted on control wheel to control wheel rotating shaft need to be monitored, it is right
Moment of torsion in rotating shaft is measured in real time.The survey that stress section is pasted on control wheel rotating shaft is turned round region by prime minister, afterwards will be with stress
The cable of piece connection is through the inclined hole in control wheel rotating shaft, and a plurality of cable is passed after collecting from connecting hole.It is to be appreciated that
The quantity for surveying the stress section for turning round region stickup according to actual needs can be with unrestricted choice, after multiple stress sections are pasted, a plurality of line
Cable is just divided into two groups, is passed respectively from two inclined holes, cable group forming criterion is defined by close inclined hole, can be with uneven distribution.
In addition, two inclined holes are made a call in relevant position in control wheel rotating shaft and a connecting hole does not destroy the structure of control wheel rotating shaft,
Result of the test will not be impacted during experiment.
The airplane operation system control wheel rotating shaft of the present invention has the following advantages that：
(1) arbitrary section is carried out to inclined hole or connecting hole, the loss of Torsion Section coefficient is very small, and tapping shear stress depends on
In diameter of section；
(2) because rotating shaft itself is in enclosed environment, the lead channels of foil gauge are designed inside rotating shaft, it is to avoid axle
While rotating, wire is wound on axle with the rotation of axle.
It is described above, it is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in,
It should all be included within the scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Enclose and be defined.
Claims (3)
1. a kind of flight control system control wheel rotating shaft, control wheel rotating shaft (1) one end is control wheel end and connected with control wheel
Connect, the other end is chain end and is connected with operating system, it is characterised in that have survey to turn round region (2) in the middle part of control wheel rotating shaft,
Described survey on torsion region posts stress section (3), is surveyed from the control wheel rotating shaft and turns round region to the chain end provided with two inclined holes
(4), axisymmetrical of two inclined holes along the control wheel rotating shaft, and the intersection point of two inclined hole axis is located at the control wheel
On the axis of rotating shaft, connecting hole (5), the axis of the connecting hole are provided with from the end face at control wheel rotating shaft chain end to control wheel end
The intersection point is met at the axis of the axis collinear of the control wheel rotating shaft, and the connecting hole；The cable of the foil gauge is worn
Cross after inclined hole and to be passed from the connecting hole.
2. flight control system control wheel rotating shaft according to claim 1, it is characterised in that the axis of the inclined hole (4)
Angle with the axis of the control wheel rotating shaft is 45 °.
3. flight control system control wheel rotating shaft according to claim 1, it is characterised in that the connecting hole (5) it is straight
Footpath is more than the diameter of the inclined hole (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710200428.4A CN107082114A (en) | 2017-03-30 | 2017-03-30 | A kind of airplane operation system control wheel rotating shaft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710200428.4A CN107082114A (en) | 2017-03-30 | 2017-03-30 | A kind of airplane operation system control wheel rotating shaft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107082114A true CN107082114A (en) | 2017-08-22 |
Family
ID=59614644
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710200428.4A Pending CN107082114A (en) | 2017-03-30 | 2017-03-30 | A kind of airplane operation system control wheel rotating shaft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107082114A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108151928A (en) * | 2017-12-22 | 2018-06-12 | 中航电测仪器股份有限公司 | A kind of aircraft control force sensor |
-
2017
- 2017-03-30 CN CN201710200428.4A patent/CN107082114A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108151928A (en) * | 2017-12-22 | 2018-06-12 | 中航电测仪器股份有限公司 | A kind of aircraft control force sensor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170822 |