CN205228762U - Automatic adjusting device of wind tunnel test model aircraft rudder face angle - Google Patents
Automatic adjusting device of wind tunnel test model aircraft rudder face angle Download PDFInfo
- Publication number
- CN205228762U CN205228762U CN201520902414.3U CN201520902414U CN205228762U CN 205228762 U CN205228762 U CN 205228762U CN 201520902414 U CN201520902414 U CN 201520902414U CN 205228762 U CN205228762 U CN 205228762U
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- rudder face
- rocking arm
- pedestal
- wind tunnel
- face angle
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Abstract
The utility model discloses an automatic adjusting device of wind tunnel test model aircraft rudder face angle, including base and rocking arm, one side on the base is provided with the slidable push rod on being provided with slide mechanism slide mechanism, and the one end of push rod is connected to the rudder face and connects, be provided with the clamping part on the base with on slide mechanism opposite one side, centre gripping actuating mechanism is fixed to the clamping part, a rhizoid thick stick is connected to actuating mechanism's power take off end, and the lead screw passes the connecting block, passes through the thread engagement between lead screw and the connecting block, the connecting block is fixed in the clamping part of rocking arm one end, and the rocking arm other end is provided with two tie points, and on a tie point passed through the slide mechanism of hinge setting on the base, another tie point was connected to on the base through the compensation rocking arm. The utility model discloses an one set of transmission of motor drive to drive rudder face angle is in good time to be changed automatically consecutively, not only can improve test efficiency by a wide margin, reduce intensity of labour, can also reduce the human error simultaneously, reduce the energy consumption.
Description
Technical field
The present invention relates to wind tunnel test field, be specifically related to a kind of wind tunnel test model aircraft rudder face angle automatic regulating device.
Background technology
Scale down is the basic skills of aircraft wind tunnel test.Aircraft its inner space of scale smaller is that cube declines.Therefore, when carrying out aerospace flight vehicle model test, due to narrow space, the control surface deflection of its model, be all generally adopt the artificial mode changing angle block gauge or rotating shaft latch, rudder face drift angle can not deflect continuously, and test efficiency is low, and labour intensity is large.If automatically adjust rudder face angle in process of the test in good time, then not only significantly can improve test efficiency, reduce labour intensity, human error can also be reduced simultaneously, reduce energy consumption.
Number of patent application be 201410333094.4 patent discloses a kind of low-speed wind tunnel dynamometer check model automatic steering gear, this invention drives slide block along lead screw straight-line by drive motor, via lever, connecting rod, displacement is driven to driving stem, the straight-line displacement that drive motor drives slide block to produce is converted into angle displacement on driving stem, and drive axis of rotation by driving stem, finally realize the automatic deflection of elevating rudder rudder face angle.
Summary of the invention
The object of the invention is on the basis of existing technology, set up a kind of rudder face angular adjustment apparatus, adjust rudder face angle automatically and continuously in good time.
For achieving the above object, the present invention adopts following technical scheme:
A kind of wind tunnel test model aircraft rudder face angle automatic regulating device, comprising: pedestal and rocking arm,
Side on described pedestal is provided with on slide mechanism slide mechanism and is provided with slidably push rod, and one end of push rod is connected to rudder face joint, and the side that described pedestal opposes with slide mechanism is provided with clamping part, clamping part fixed clamp driving mechanism;
The clutch end of described driving mechanism connects a rhizoid thick stick, and leading screw, through contiguous block, passes through screw-threaded engagement between leading screw and contiguous block;
Described contiguous block is fixed in the clamping part of one end, and the rocking arm other end is provided with two tie points, and a tie point is arranged on the slide mechanism on pedestal by hinge, and another tie point is connected on pedestal by compensating rocking arm.
In technique scheme, one end pedestal of described compensation rocking arm connects, and the other end compensating rocking arm is connected with rocking arm by straight pin, can mutually rotate between rocking arm and compensation rocking arm.
In technique scheme, described compensation rocking arm is connected with adopting straight pin between pedestal, compensates between rocking arm and pedestal and can mutually rotate.
In technique scheme, described push rod is connected by straight pin with rudder face joint, can mutually rotate between rudder face joint and push rod.
In technique scheme, between rudder face joint and pedestal, be provided with linear movement pick-up.
In technique scheme, described linear movement pick-up two ends are provided with link, and link is connected on rudder face joint and pedestal each via straight pin.
In technique scheme, comprise controller, the signal output part of linear movement pick-up is connected to controller, and the output terminal of controller is connected to the control end on driving mechanism.
In technique scheme, the clamping part on described pedestal protrudes into outside pedestal, is fixedly connected with between clamping part with pedestal.
In technique scheme, concrete adjustment process is as follows:
Rudder face joint be fixed on model rudder face, driving mechanism Power output is on leading screw, screw turns drives contiguous block to do rectilinear motion along leading screw, contiguous block drives rocker motion; the tie point that between rocking arm and compensation rocking arm, mutual rotating band shakes arm does rectilinear motion on the sliding mechanism and promotes push rod; push rod acting force makes to rotate between rudder face connector and pedestal by straight pin;; controller controls stopping and the operation of driving mechanism by the signal of gathering line displacement transducer, realizes the automatic adjustment of rudder face angle.
In sum, owing to have employed technique scheme, the invention has the beneficial effects as follows: this technology belongs in large-sized low-speed wind tunnel test at home and uses first, greatly reduces the labour intensity of model post personnel;
Adopt this device can change the method for original rudder effectiveness test, directly can realize the simulation to steerage, and then reach the object improving rudder effectiveness test precision;
This apparatus structure is simple, and volume is little, compares the result of use with existing various device with protrusion;
The test findings utilizing this system to obtain and the test findings utilizing angle block gauge to obtain match, and therefore this programme has exploitativeness.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is Facad structure schematic diagram of the present invention;
Fig. 2 is structure schematic diagram of the present invention;
Wherein: 1 is driving mechanism, 2 is leading screws, and 3 is contiguous blocks, and 4 is rocking arms, and 5 is linear movement pick-ups, and 6 is pedestals, and 7 is compensate rocking arm, and 8 is rudder face joints, and 9 is slide mechanisms, and 10 is push rods.
Embodiment
As shown in Figure 1 and Figure 2, apparatus of the present invention comprise a pedestal, the side on basis is provided with slide mechanism, can be slided on the sliding mechanism by the form of hinge, slide mechanism connecting a push rod, can mutually slide when being subject to external force between push rod and slide mechanism; One end of push rod is connected on rudder face joint, adopts straight pin to be connected between push rod with rudder face joint, and under the acting force of push rod, rudder face joint is by can mutually rotate between straight pin and push rod.
Another side of pedestal, namely side that slide mechanism opposes is provided with an outstanding clamping part with being provided with, clamping part is used for fixed clamp driving mechanism, driving mechanism comprises linear electric motors and speed reduction unit, the clutch end of driving mechanism is connected on a rhizoid thick stick, and under Power output, leading screw starts rotation.Driving mechanism and leading screw remain on same level direction, and the dead in line of leading screw and driving mechanism.Leading screw is connected with rocking arm by contiguous block, contiguous block is provided with a through hole, is provided with internal thread in through hole, and leading screw is through the through hole of contiguous block, and the external thread of leading screw engages with the internal thread of contiguous block.When leading screw is while rotation, rectilinear motion can be done along leading screw by the block that is connected with a joggle of screw thread.
Contiguous block is fixedly installed in the clamping part of rocking arm; the similar triangle of global shape of rocking arm; clamping part is on a leg-of-mutton angle; be separately two angles be two tie points; one of them tie point is hinged on the slide mechanism on pedestal, makes this point of rocking arm can do rectilinear motion along slide mechanism; Another tie point of rocking arm is connected on pedestal by compensating rocking arm.Here supplementary rocking arm adopts the connected mode of two straight pins, and the one end namely supplementing rocking arm is connected with pedestal by straight pin, and the other end supplementing rocking arm is connected with rocking arm by another straight pin.The reason adopting two straight pins to connect is, when rocking arm is while rotation, supplements and also mutually rotate between rocking arm and pedestal, supplement an angle to rocking arm, to make on rocking arm point on the sliding mechanism can preserve rectilinear motion all the time.If adopt a straight pin, when rocking arm rotates, the rocking arm tie point be connected with slide mechanism will do movement in a curve, on the sliding mechanism will be stuck, can not realize the effect promoting push rod.
In order to realize the control to rudder face angular setting, need between pedestal and rudder face joint, arrange a linear movement pick-up, the angle being converted to rudder face by the straight-line displacement of being rotated by pedestal realizes adjustment automatically.But because linear movement pick-up is straight line device in rotation process; if do not carry out protection will damage linear movement pick-up; therefore be respectively arranged with link at the two ends of linear movement pick-up, link is connected on pedestal and rudder face joint each via a straight pin.Make rudder face joint in the process of rotating, linear movement pick-up also can follow rotation, can not damage linear movement pick-up.
Also control system is needed in the present invention, control system is by the positional precision of gathering line displacement transducer, and corresponding rudder face angle will be converted to, control the Power output of driving mechanism cathetus motor by preset value in compared with control system, make whole device can realize the automatic adjustment of angle under control system.
The present invention is not limited to aforesaid embodiment.The present invention expands to any new feature of disclosing in this manual or any combination newly, and the step of the arbitrary new method disclosed or process or any combination newly.
Claims (8)
1. a wind tunnel test model aircraft rudder face angle automatic regulating device, is characterized in that comprising: pedestal and rocking arm,
Side on described pedestal is provided with on slide mechanism slide mechanism and is provided with slidably push rod, and one end of push rod is connected to rudder face joint, and the side that described pedestal opposes with slide mechanism is provided with clamping part, clamping part fixed clamp driving mechanism;
The clutch end of described driving mechanism connects a rhizoid thick stick, and leading screw, through contiguous block, passes through screw-threaded engagement between leading screw and contiguous block;
Described contiguous block is fixed in the clamping part of one end, and the rocking arm other end is provided with two tie points, and a tie point is arranged on the slide mechanism on pedestal by hinge, and another tie point is connected on pedestal by compensating rocking arm.
2. a kind of wind tunnel test model aircraft rudder face angle automatic regulating device according to claim 1, it is characterized in that one end pedestal of described compensation rocking arm connects, the other end compensating rocking arm is connected with rocking arm by straight pin, can mutually rotate between rocking arm and compensation rocking arm.
3. a kind of wind tunnel test model aircraft rudder face angle automatic regulating device according to claim 2, is characterized in that described compensation rocking arm is connected with adopting straight pin between pedestal, compensates between rocking arm and pedestal and can mutually rotate.
4. a kind of wind tunnel test model aircraft rudder face angle automatic regulating device according to claim 1, is characterized in that described push rod is connected by straight pin with rudder face joint, can mutually rotate between rudder face joint and push rod.
5. a kind of wind tunnel test model aircraft rudder face angle automatic regulating device according to claim 4, is characterized in that being provided with linear movement pick-up between rudder face joint and pedestal.
6. a kind of wind tunnel test model aircraft rudder face angle automatic regulating device according to claim 5, it is characterized in that described linear movement pick-up two ends are provided with link, link is connected on rudder face joint and pedestal each via straight pin.
7. a kind of wind tunnel test model aircraft rudder face angle automatic regulating device according to claim 6, it is characterized in that comprising controller, the signal output part of linear movement pick-up is connected to controller, and the output terminal of controller is connected to the control end on driving mechanism.
8. a kind of wind tunnel test model aircraft rudder face angle automatic regulating device according to claim 1, is characterized in that the clamping part on described pedestal protrudes into outside pedestal, is fixedly connected with between clamping part with pedestal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520902414.3U CN205228762U (en) | 2015-11-13 | 2015-11-13 | Automatic adjusting device of wind tunnel test model aircraft rudder face angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520902414.3U CN205228762U (en) | 2015-11-13 | 2015-11-13 | Automatic adjusting device of wind tunnel test model aircraft rudder face angle |
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| Publication Number | Publication Date |
|---|---|
| CN205228762U true CN205228762U (en) | 2016-05-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520902414.3U Withdrawn - After Issue CN205228762U (en) | 2015-11-13 | 2015-11-13 | Automatic adjusting device of wind tunnel test model aircraft rudder face angle |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105258910A (en) * | 2015-11-13 | 2016-01-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Automatic adjusting device for control surface angle of wind tunnel test airplane model |
| CN107091724A (en) * | 2017-06-26 | 2017-08-25 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wind tunnel model gravity adjusting device |
| CN111337219A (en) * | 2020-02-21 | 2020-06-26 | 北理伺服(珠海)科技有限公司 | Pneumatic test is with taking automatic variable rudder face reduction gears of feedback |
| CN113071706A (en) * | 2021-03-31 | 2021-07-06 | 成都飞机工业（集团）有限责任公司 | Aircraft control surface clearance measuring device |
| CN113237629A (en) * | 2021-07-08 | 2021-08-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring control plane angle of low-speed wind tunnel free flight model |
-
2015
- 2015-11-13 CN CN201520902414.3U patent/CN205228762U/en not_active Withdrawn - After Issue
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105258910A (en) * | 2015-11-13 | 2016-01-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Automatic adjusting device for control surface angle of wind tunnel test airplane model |
| CN105258910B (en) * | 2015-11-13 | 2017-09-26 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of wind tunnel test model aircraft rudder face angle automatic regulating device |
| CN107091724A (en) * | 2017-06-26 | 2017-08-25 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wind tunnel model gravity adjusting device |
| CN107091724B (en) * | 2017-06-26 | 2019-10-15 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wind tunnel model gravity adjusting device |
| CN111337219A (en) * | 2020-02-21 | 2020-06-26 | 北理伺服(珠海)科技有限公司 | Pneumatic test is with taking automatic variable rudder face reduction gears of feedback |
| CN113071706A (en) * | 2021-03-31 | 2021-07-06 | 成都飞机工业（集团）有限责任公司 | Aircraft control surface clearance measuring device |
| CN113237629A (en) * | 2021-07-08 | 2021-08-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring control plane angle of low-speed wind tunnel free flight model |
| CN113237629B (en) * | 2021-07-08 | 2021-09-21 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring control plane angle of low-speed wind tunnel free flight model |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160511 Effective date of abandoning: 20170926 |