CN105460234A - Aircraft command sensor driving device for testing - Google Patents
Aircraft command sensor driving device for testing Download PDFInfo
- Publication number
- CN105460234A CN105460234A CN201510852691.2A CN201510852691A CN105460234A CN 105460234 A CN105460234 A CN 105460234A CN 201510852691 A CN201510852691 A CN 201510852691A CN 105460234 A CN105460234 A CN 105460234A
- Authority
- CN
- China
- Prior art keywords
- instruction sensor
- testing
- aeroplane
- actuating device
- aircraft
- 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
Links
Landscapes
- Mechanical Control Devices (AREA)
Abstract
The invention discloses an aircraft command sensor driving device for testing. The aircraft command sensor driving device for testing comprises a transition plate (2), a driving assembly and a scaleplate (4), wherein the transition plate (2) is used for placing an aircraft command sensor (1); the driving assembly comprises a driving sliding block (3), and the stretching and retracting end (11) of the aircraft command sensor (1) can be driven by the driving sliding block (3) to move; a vernier (41) is arranged on the scaleplate (4) and is in linkage with the driving sliding block (3) of the driving assembly, so that the movement distance of the driving sliding block is displayed. According to the aircraft command sensor driving device for testing, the aircraft command sensor is arranged on the transition plate, and thus the driving device can be adapted to aircraft command sensors of different types by replacing the transition plate; in addition, in the way that the scaleplate, the driving assembly is in linkage with the aircraft command sensor, the displacement of the aircraft command sensor is displayed on the scaleplate in real time, and thus the displacement of the aircraft command sensor can be known accurately.
Description
Technical field
The present invention relates to aircraft testing technical field, be specifically related to a kind of testing aeroplane instruction sensor actuating device and testing aeroplane instruction sensor actuating device using method.
Background technology
Instruction sensor is the important component part of airplane brake system, aviator produces displacement output electric signal by trampling brake pedal driving instruction sensor telescopic mast, then by series of electrical signals conversion, output, hydraulic control servovalve aperture produces hydraulic pressure, and then forms brake weight.The displacement that the size and instruction sensor telescopic end of brake weight produces is closely related, need in the test before instruction sensor installation the checking displacement of instruction sensor and the corresponding relation of brake weight and design value whether consistent.
Instruction sensor displacement stroke due to current each model is shorter (about 20mm ~ 30mm), and required actuating force comparatively large (minimum actuating force is about 150N), existing instruction sensor actuating device cannot realize the fine adjustment of displacement, and reliable and stable for instruction sensor cannot be remained on a certain fixing displaced position, this to instruction sensor installation before accurately verification experimental verification bring difficulty.
Simultaneously existing instruction sensor actuating device cannot compatible polytypic instruction sensor, and this sets up the rising bringing time and financial cost to experimental enviroment.
Therefore, wish a kind of technical scheme to overcome or at least alleviate at least one the problems referred to above of prior art.
Summary of the invention
A kind of testing aeroplane instruction sensor actuating device is the object of the present invention is to provide to overcome or at least alleviate at least one the problems referred to above of the prior art.
For achieving the above object, the invention provides a kind of testing aeroplane instruction sensor actuating device, described testing aeroplane instruction sensor actuating device is for driving aircraft instruction sensor, described aircraft instruction sensor comprises fixed end and can the flexible telescopic end of relatively described fixed end, described testing aeroplane instruction sensor actuating device comprises: rebound, and described rebound is for placing aircraft instruction sensor; Driven unit, described driven unit comprises one and drives slide block, and described driving slide block can drive the telescopic end of described aircraft instruction sensor to move; Scale, described scale is provided with vernier, and the driving slide block of described vernier and described driven unit links, thus shows the miles of relative movement of described drive end.
Preferably, described driven unit comprises further: leading screw, and described driving slide block is arranged on described leading screw; Clamp handle, described clamp handle is arranged on one end of described leading screw, for locking leading screw, thus prevents described leading screw from rotating.
Preferably, described driven unit comprises further: handwheel, and described handwheel is arranged on one end away from described clamp handle of leading screw.
Preferably, described driven unit comprises further: brace table, and described brace table is for supporting described leading screw.
Preferably, described scale is digital display scale, and described vernier is numerical monitor vernier.
Preferably, described testing aeroplane instruction sensor actuating device comprises base plate further, and described rebound, driven unit and scale are all arranged on described base plate.
Preferably, described vernier and described driving slide block are rigidly connected.
Present invention also offers a kind of testing aeroplane instruction sensor actuating device using method, described testing aeroplane instruction sensor actuating device using method adopts testing aeroplane instruction sensor actuating device as above, described testing aeroplane instruction sensor actuating device using method comprises: carry out scale clearing, and to reset the zero point of position as the telescopic end of aircraft instruction sensor; Make the telescopic end motion preset distance of aircraft instruction sensor described in the driving slider-actuated in driven unit, and drive the cursor movement on scale, thus the distance that the vernier on scale is moved equals described preset distance.
Preferably, described testing aeroplane instruction sensor actuating device using method comprises further: after making the telescopic end motion preset distance of aircraft instruction sensor described in the driving slider-actuated in driven unit, locked by clamp handle, thus prevent leading screw from rotating.
Preferably, described preset distance is the distance of the telescopic end motion of the required aircraft instruction sensor of test.
Aircraft instruction sensor is arranged on rebound by testing aeroplane instruction sensor actuating device of the present invention, by changing rebound, the aircraft instruction sensor of different model can be adapted to, and in invention, by the mode that scale and driven unit and aircraft instruction sensor link, the displacement of aircraft instruction sensor is presented on scale in real time, thus can the displacement of accurate perception aircraft instruction sensor.
Accompanying drawing explanation
Fig. 1 is the structural representation of testing aeroplane instruction sensor actuating device according to a first embodiment of the present invention.
Reference numeral:
| 1 | Aircraft instruction sensor | 5 | Leading screw |
| 11 | Telescopic end | 6 | Clamp handle |
| 2 | Rebound | 7 | Handwheel |
| 3 | Drive slide block | 8 | Brace table |
| 4 | Scale | 9 | Base plate |
| 41 | Vernier |
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention; it will be appreciated that; term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limiting the scope of the invention.
Fig. 1 is the structural representation of testing aeroplane instruction sensor actuating device according to a first embodiment of the present invention.
Testing aeroplane instruction sensor actuating device of the present invention is for driving aircraft instruction sensor 1, and aircraft instruction sensor 1 comprises fixed end and can fixed end is flexible relatively telescopic end 11.
Testing aeroplane instruction sensor actuating device as shown in Figure 1 comprises rebound 2, base plate 9, driven unit and scale.In the present embodiment, rebound, driven unit and scale are all arranged on base plate.Like this, under above-mentioned rebound, driven unit and scale can being made to be positioned at sustained height.
Be understandable that, in an alternative embodiment, this aircraft instruction sensor actuating device does not comprise base plate.
In the present embodiment, rebound 2, for placing aircraft instruction sensor 1, like this, when needing the aircraft instruction sensor 1 using different size, can be changed by the mode changing rebound 2.
See Fig. 1, in the present embodiment, driven unit comprises driving slide block 3, leading screw 5, handwheel 7, brace table 8 and a clamp handle 6.In the present embodiment, drive slide block 3 to be arranged on leading screw 5, drive slide block 3 that the telescopic end 11 of aircraft instruction sensor 1 can be driven to move.
In the present embodiment, clamp handle 6 is arranged on one end of leading screw 5, for locking leading screw 5, thus prevents leading screw 5 from rotating.Like this, when needs make aircraft instruction sensor be fixed on a certain position, can be locked by the mode of locking leading screw.
In the present embodiment, handwheel 7 is arranged on one end away from clamp handle 6 of leading screw 5.Control leading screw by handwheel to rotate, comparatively laborsaving.
In the present embodiment, brace table 8 is for supporting leading screw 5.Like this, by regulating the height (in Fig. 1 above-below direction) of brace table thus making the height of leading screw parallel with aircraft instruction sensor, thus datum error can be prevented.
See Fig. 1, in the present embodiment, scale 4 is provided with vernier 41, vernier 41 links with the driving slide block 3 of driven unit, thus the miles of relative movement of display driver slide block.Particularly, the driving slide block 3 of vernier 41 and driven unit, for being rigidly connected, adopting rigidly connected mode, can prevent the error because elasticity or distortion cause.
In the present embodiment, scale 4 is digital display scale, and vernier 41 is numerical monitor vernier.By digitized equipment, data more accurately can be provided.
Be understandable that, scale also can be mechanical scale or other scales.
Present invention also offers a kind of testing aeroplane instruction sensor actuating device using method, the method adopt as weigh upper as described in testing aeroplane instruction sensor actuating device, described testing aeroplane instruction sensor actuating device using method comprises: carry out scale 4 and reset, and to reset the zero point of position as the telescopic end 11 of aircraft instruction sensor; Make the driving slide block 3 in driven unit drive the telescopic end 11 motion preset distance of aircraft instruction sensor, and drive the cursor movement on scale 4, thus the distance that the vernier on scale 4 is moved equals preset distance.
In the present embodiment, testing aeroplane instruction sensor actuating device using method comprises further: after making the driving slide block 3 in driven unit drive the telescopic end 11 motion preset distance of aircraft instruction sensor, locked by clamp handle 6, thus prevent the telescopic end 11 of driven unit countermeasure aircraft instruction sensor 1.
In the present embodiment, preset distance is the distance of telescopic end 11 motion of the required aircraft instruction sensor of test.
Finally it is to be noted: above embodiment only in order to technical scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (10)
1. a testing aeroplane instruction sensor actuating device, for driving aircraft instruction sensor (1), described aircraft instruction sensor (1) comprises fixed end and can the flexible telescopic end (11) of relatively described fixed end, it is characterized in that, described testing aeroplane instruction sensor actuating device comprises:
Rebound (2), described rebound (2) is for placing described aircraft instruction sensor (1);
Driven unit, described driven unit comprises one and drives slide block (3), and described driving slide block (3) can drive the telescopic end (11) of described aircraft instruction sensor (1) to move;
Scale (4), described scale (4) is provided with vernier (41), and described vernier (41) links with the driving slide block (3) of described driven unit, thus shows the miles of relative movement of described driving slide block.
2. testing aeroplane instruction sensor actuating device as claimed in claim 1, it is characterized in that, described driven unit comprises further:
Leading screw (5), described driving slide block (3) is arranged on described leading screw (5);
Clamp handle (6), described clamp handle (6) is arranged on one end of described leading screw (5), for locking leading screw (5), thus prevents described leading screw (5) from rotating.
3. testing aeroplane instruction sensor actuating device as claimed in claim 2, it is characterized in that, described driven unit comprises further:
Handwheel (7), described handwheel (7) is arranged on one end away from described clamp handle (6) of leading screw (5).
4. testing aeroplane instruction sensor actuating device as claimed in claim 3, it is characterized in that, described driven unit comprises further: brace table (8), and described brace table (8) is for supporting described leading screw (5).
5. testing aeroplane instruction sensor actuating device as claimed in claim 4, it is characterized in that, described scale (4) is digital display scale, and described vernier (41) is numerical monitor vernier.
6. testing aeroplane instruction sensor actuating device as claimed in claim 1, it is characterized in that, described testing aeroplane instruction sensor actuating device comprises base plate (9) further, and described rebound (2), driven unit and scale (4) are all arranged on described base plate (9).
7. testing aeroplane instruction sensor actuating device as claimed in claim 1, is characterized in that, described vernier (41) and described driving slide block (3) are rigidly connected.
8. a testing aeroplane instruction sensor actuating device using method, it is characterized in that, described testing aeroplane instruction sensor actuating device using method adopts testing aeroplane instruction sensor actuating device as claimed in any of claims 1 to 7 in one of claims, and described testing aeroplane instruction sensor actuating device using method comprises:
Carry out scale (4) to reset, and to reset the zero point of position as the telescopic end (11) of aircraft instruction sensor;
The driving slide block (3) in driven unit is made to drive telescopic end (11) the motion preset distance of described aircraft instruction sensor, and drive the cursor movement on scale (4), thus the distance that the vernier on scale (4) is moved equals described preset distance.
9. testing aeroplane instruction sensor actuating device using method as claimed in claim 8, it is characterized in that, described testing aeroplane instruction sensor actuating device using method comprises further:
After making the driving slide block (3) in driven unit drive telescopic end (11) the motion preset distance of described aircraft instruction sensor, by clamp handle (6) locking, thus prevent driven unit from disturbing the telescopic end (11) of described aircraft instruction sensor (1).
10. testing aeroplane instruction sensor actuating device using method as claimed in claim 8, is characterized in that, described preset distance is the distance that the telescopic end (11) of the required aircraft instruction sensor of test moves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510852691.2A CN105460234A (en) | 2015-11-27 | 2015-11-27 | Aircraft command sensor driving device for testing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510852691.2A CN105460234A (en) | 2015-11-27 | 2015-11-27 | Aircraft command sensor driving device for testing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105460234A true CN105460234A (en) | 2016-04-06 |
Family
ID=55598489
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510852691.2A Pending CN105460234A (en) | 2015-11-27 | 2015-11-27 | Aircraft command sensor driving device for testing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105460234A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107054687A (en) * | 2017-06-19 | 2017-08-18 | 沈阳飞机工业（集团）有限公司 | A kind of big stroke aircraft bracket of low clearance |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201411045Y (en) * | 2009-06-10 | 2010-02-24 | 哈尔滨飞机工业集团有限责任公司 | Transportable type workbench |
| CN102809490A (en) * | 2012-07-28 | 2012-12-05 | 奇瑞汽车股份有限公司 | Test detecting device with safety belt height adjuster and detecting method for test detecting device |
| CN203217863U (en) * | 2013-03-25 | 2013-09-25 | 中国航空工业集团公司沈阳飞机设计研究所 | A brake system instruction transmission mechanism for united simulation |
| CN103673900A (en) * | 2013-12-13 | 2014-03-26 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Field calibration device of linear displacement measuring system |
| CN103852028A (en) * | 2012-11-30 | 2014-06-11 | 昆山允可精密工业技术有限公司 | Manual two-dimensional cutter measurement auxiliary device |
-
2015
- 2015-11-27 CN CN201510852691.2A patent/CN105460234A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201411045Y (en) * | 2009-06-10 | 2010-02-24 | 哈尔滨飞机工业集团有限责任公司 | Transportable type workbench |
| CN102809490A (en) * | 2012-07-28 | 2012-12-05 | 奇瑞汽车股份有限公司 | Test detecting device with safety belt height adjuster and detecting method for test detecting device |
| CN103852028A (en) * | 2012-11-30 | 2014-06-11 | 昆山允可精密工业技术有限公司 | Manual two-dimensional cutter measurement auxiliary device |
| CN203217863U (en) * | 2013-03-25 | 2013-09-25 | 中国航空工业集团公司沈阳飞机设计研究所 | A brake system instruction transmission mechanism for united simulation |
| CN103673900A (en) * | 2013-12-13 | 2014-03-26 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Field calibration device of linear displacement measuring system |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107054687A (en) * | 2017-06-19 | 2017-08-18 | 沈阳飞机工业（集团）有限公司 | A kind of big stroke aircraft bracket of low clearance |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109573097B (en) | Vehicle-mounted test method and system for aerodynamic parameters of low-speed aircraft | |
| US9216829B2 (en) | System and method for rigging a control surface of an aircraft | |
| CN202267466U (en) | Displacement sensor performance detection apparatus | |
| CN107192549B (en) | Aircraft steering column static characteristic measuring device | |
| CN103207064A (en) | In-situ testing system for flight control system loading mechanism | |
| CN105328911A (en) | 3D printer platform leveling device | |
| CN110307975A (en) | Flight control system control stick measuring device | |
| CN104925270A (en) | Method, torsion load testing system, pressure load testing system and adjustment assembly | |
| CN105424344A (en) | Debugging device used for airplane calibration test deformation structure loading actuator | |
| CN109506919A (en) | A kind of aircraft takeoffs and landings rack loading device and loading method | |
| CN203908423U (en) | Two-dimensional translation frame applied to detection and tracking of moving target | |
| CN105460234A (en) | Aircraft command sensor driving device for testing | |
| CN107655438A (en) | A kind of measurement apparatus and its measuring method at aircraft rudder surface angle | |
| CN209037879U (en) | One kind being used for auxiliary tank of aircraft flight environment of vehicle and attitude-simulating experimental rig | |
| CN102589783B (en) | Universal testing system for intelligent airplane loading mechanism | |
| CN105651527A (en) | Portable rigidity test bench | |
| CN202748225U (en) | Electrodynamic force acting load and load analog device | |
| CN210243187U (en) | Measuring equipment for steering column of airplane control system | |
| CN205209733U (en) | Torgue measurement balance | |
| CN104216401A (en) | Multi-degree-of-freedom side rod operating force and corresponding displacement testing device | |
| CN208568218U (en) | The torsional rigidity test of vehicular platform of passenger car torsion beam | |
| CN106595495A (en) | Optical displacement measurement system | |
| US9499254B2 (en) | Trim adjustment device, aircraft, and method of performing trim adjustment | |
| CN109556843A (en) | Rotor system Calibrating experimental bench | |
| CN103424063A (en) | Non-metallic product stiffness measurement device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160406 |
|
| RJ01 | Rejection of invention patent application after publication |