CN106553768A - A kind of main oar steering wheel benchmark method of adjustment - Google Patents
A kind of main oar steering wheel benchmark method of adjustment Download PDFInfo
- Publication number
- CN106553768A CN106553768A CN201611090943.3A CN201611090943A CN106553768A CN 106553768 A CN106553768 A CN 106553768A CN 201611090943 A CN201611090943 A CN 201611090943A CN 106553768 A CN106553768 A CN 106553768A
- Authority
- CN
- China
- Prior art keywords
- steering wheel
- main oar
- adjustment
- oar steering
- blade
- 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.)
- Granted
Links
Landscapes
- Steering Control In Accordance With Driving Conditions (AREA)
- Catching Or Destruction (AREA)
Abstract
The invention discloses a kind of main oar steering wheel benchmark method of adjustment, belongs to helicopter technical field of measurement and test；Including：Step one：The adjustment of passenger cabin manipulation device completes and each passage is fixed on reference position, and in the case where system power supply is for pressure condition, adjustment helicopter makes mast vertical；Step 2：Adjust main oar steering wheel, make auto-bank unit vertical with mast, Jing adjust for many times and using closed loop control make baseline blade four orientation change elongation in the range of setting；After the completion of step 3, baseline blade zeroing, the pitch-change-link of other blades is adjusted, completes pre- to beat cone process.The present invention is the main oar steering wheel adjusting zero method that need not be modified to spare part on machine and finished product, the setting and storage of the location bias amount of steering wheel is write in flight control computer by ground experiment device, flight control computer sends command signal to main oar steering wheel, control the switch of its servo rotation driving valve, drive steering wheel motion, corresponding propeller pitch angle is produced, the adjustment of main oar steering wheel reference position is realized.
Description
Technical field
The invention belongs to helicopter technical field of measurement and test, and in particular to a kind of main oar steering wheel benchmark method of adjustment.
Background technology
The adjustment of Helicopter Main oar steering wheel reference position is one of key link of fly-by-wire adjustment, realizes manipulating
Blade during device diverse location to should determine that becomes elongation.Traditional steerable system adopts mechanical linkage by passenger cabin manipulation device and three
The main booster connection of platform, generally two kinds adjustment modes.
Mode one：The flexible of main booster is controlled by adjusting main booster input pull bar length, auto-bank unit is made
It is vertical with mast, then adjust the length of certain specified pitch-change-link.
Mode two：Change the length of main booster by adjusting the length for being input into pull bar, and then be directly realized by benchmark shape
State lower-pilot device is corresponding with the position of control surface.
The connection of the passenger cabin manipulation device of fly-by-wire and main oar steering wheel realizes there is no input and draw by cable
Bar, so needing a kind of method to adjust the length of three main oar steering wheels, realizes the determination of main oar steering wheel reference position.
The content of the invention
The purpose of the present invention：In order to solve the above problems, the present invention proposes a kind of main oar steering wheel benchmark method of adjustment, adopts
With the main oar steering wheel adjusting zero method for being not required to be modified spare part on machine and finished product, with convenient and swift, time saving and energy saving etc. excellent
Point.
Technical scheme：A kind of main oar steering wheel benchmark method of adjustment, it is adaptable to fax helicopter, including following step
Suddenly：
Step one：The adjustment of passenger cabin manipulation device completes and each passage is fixed on reference position, in system power supply voltage supply shape
Under state, adjustment helicopter makes mast vertical；
Step 2：Main oar steering wheel is adjusted, makes auto-bank unit vertical with mast；
A) fixed reference blade flapping direction；
B) oar in any two orientation is checked in the propeller pitch angle Ф k in four orientation with differential quarter position instrument measuring basiss blade
Whether the measured value of elongation meets angle change less than 6 '；
If being unsatisfactory for, the respective location bias amount of the main oar steering wheel of calculating three
δ1=A Δ Ф1+B·ΔФ2+C·ΔФ3+D·ΔФ4
Wherein：A, B, C, D are correction factor；Δ Ф k (k=1,2,3,4) is the angle measurement value and four in each orientation
The difference of individual orientation propeller pitch angle average；
If meet requiring, step d is carried out；
C) measuring basiss blade checks whether satisfaction in the propeller pitch angle Ф k in four orientation | Фk-Ф0|≤6 ', wherein Ф0
For theoretical value；
If being unsatisfactory for, the common location bias amount of three main oar steering wheels is calculated；
δ2=i × | Фk-Ф0|
Wherein, i is gear ratio always away from the main oar steering wheel of passage to blade；
If meeting, final main oar steering wheel location bias amount is stored in flight control computer by ground experiment device；
After the completion of step 3, baseline blade zeroing, the pitch-change-link of other blades is adjusted, completes pre- to beat cone process.
Preferably, in the step 2, the main oar steering wheel each location bias amount repeatedly adjustment and closed loop control.
Preferably, in the step one, angle of flap fixture is arranged on the corresponding propeller hub root of baseline blade so that blade is waved
Dance angle is 0 ° ± 6 '.
The technology of the present invention effect：
1st, realize the adjustment of main oar steering wheel reference position；
2nd, directly control the length change of main oar steering wheel by command signal, it is accurate quick, easy to operate；
3rd, it is not required to mechanically actuated is carried out on machine, efficiency is improved, and saves labour cost.
Description of the drawings
Fig. 1 is a kind of blade azimuth angle schematic diagram of a preferred embodiment of main oar steering wheel benchmark method of adjustment of the present invention；
Measurement apparatus scheme of installations of the Fig. 2 for a kind of fax Helicopter Main oar steering wheel of embodiment illustrated in fig. 1；
Fig. 3 is a kind of schematic flow sheet of a preferred embodiment of main oar steering wheel benchmark method of adjustment of the present invention；
Wherein, 1- auto-bank units, 2- masts, 3- baseline blades, 4- ground experiment devices, the main oar steering wheels of 5-, 6- become
Away from pull bar.
Specific embodiment
To make purpose, technical scheme and the advantage of present invention enforcement 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 start to finish 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 the embodiment of whole.It is exemplary below with reference to the embodiment of Description of Drawings, it is intended to use
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 obtained under the premise of creative work is not made by member, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " is based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than indicate or imply the dress of indication
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The restriction of scope.
Below in conjunction with the accompanying drawings embodiments of the invention are described in detail, Fig. 1 to Fig. 3 is referred to；
A kind of main oar steering wheel benchmark method of adjustment of the present invention, there is provided it is a kind of it is convenient and swift, time saving and energy saving, be not required to on machine zero
The main oar steering wheel adjusting zero method that component and finished product are modified；The setting and storage of the wherein location bias amount of steering wheel is by ground
In the exerciser write flight control computer of face, flight control computer sends command signal to main oar steering wheel, controls its servo rotation driving
The switch of valve, drives steering wheel motion, produces corresponding propeller pitch angle.
Comprise the following steps：
Step one, the adjustment of passenger cabin manipulation device are completed and by each passage pin solid in reference position, in system power supply voltage supply shape
Under state west, adjustment helicopter makes mast vertical.
Step 2, the adjustment of main oar steering wheel, make auto-bank unit 1 vertical with mast 2；
1) fixed reference blade flapping direction, is to reduce the shimmy impact to main oar displacement of blade flapping, using angle of flap
Fixture is arranged on the corresponding propeller hub root of baseline blade so that blade flapping angle is controlled in the range of 0 ° of ± 6', the present embodiment
Cushion block of the angle of flap fixture using adjustable thickness.
2) with the differential propeller pitch angle for carving displacement measurement baseline blade 3 in four orientation,
If whether the range of error between the measured value of the propeller pitch angle in any two orientation is met less than 6 '；
If being unsatisfactory for, the respective location bias amount of the main oar steering wheel (5) of calculating three, that is, the change that steering wheel needs are flexible
Change amount；
δ1=A Δ Ф1+B·ΔФ2+C·ΔФ3+D·ΔФ4
Wherein, in formula, A, B, C, D are correction factor；Δ Ф k (k=1,2,3,4) is the angle measurement in certain orientation
It is worth the difference with four orientation propeller pitch angle averages, and location bias amount is input to by flight control computer by ground experiment device 4 and changes
Become the length of steering wheel, this step is repeatedly adjusted and using closed loop control between the measured value to the propeller pitch angle for meeting two orientation
Range of error requirement.
If meet requiring, next step is carried out；
3) measuring basiss blade, in the propeller pitch angle Ф k in four orientation, checks whether satisfaction again | Фk-Ф0|≤6 ', wherein
Ф0For theoretical value；
If being unsatisfactory for, the common location bias amount of three main oar steering wheels is calculated；
δ2=i × | Фk-Ф0|
Wherein, i is gear ratio always away from the main oar steering wheel of passage to blade, and common location is inclined by ground experiment device 4
The amount of putting is input to flight control computer, makes three main oar steering wheel simultaneous retractable certain lengths；Repeat step 3, Jing are adjusted and are adopted for many times
With closed loop control make baseline blade four orientation change elongation in the range of setting.
If meeting, final main oar steering wheel location bias amount is stored in flight control computer by ground experiment device 4；
After the completion of step 3, baseline blade zeroing, the pitch-change-link 6 of other blades is adjusted, completes pre- to beat cone process.
A kind of main oar steering wheel benchmark method of adjustment of the present invention, it is adaptable to fax helicopter, realizes main oar steering wheel benchmark position
The adjustment put, directly controls the length change of main oar steering wheel by command signal, accurate quick, easy to operate；It is not required on machine
Mechanically actuated is carried out, efficiency is improved, and saves labour cost.
It is last it is to be noted that：Above example only to illustrate technical scheme, rather than a limitation.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：Which is still
Technical scheme described in foregoing embodiments can be modified, or equivalent is carried out to which part technical characteristic and replace
Change；And these modifications or replacement, do not make the essence of appropriate technical solution depart from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (3)
1. a kind of main oar steering wheel benchmark method of adjustment, it is adaptable to fax helicopter, it is characterised in that：Comprise the following steps：
Step one：The adjustment of passenger cabin manipulation device completes and each passage is fixed on reference position, in the case where system power supply is for pressure condition,
Adjustment helicopter makes mast vertical；
Step 2：Main oar steering wheel (5) is adjusted, makes auto-bank unit (1) vertical with mast (2)；
A) fixed reference blade (3) waves direction；
B) pitch in any two orientation is checked in the propeller pitch angle Ф k in four orientation with differential quarter position instrument measuring basiss blade (3)
Whether the measured value at angle meets angle change less than 6 '；
If being unsatisfactory for, the respective location bias amount of the main oar steering wheel (5) of calculating three
δ1=A Δ Ф1+B·ΔФ2+C·ΔФ3+D·ΔФ4
Wherein：A, B, C, D are correction factor；Δ Ф k (k=1,2,3,4) is the angle measurement value in each orientation and four sides
The difference of position propeller pitch angle average；
If meet requiring, step c is carried out；
C) measuring basiss blade checks whether satisfaction in the propeller pitch angle Ф k in four orientation | Фk-Ф0|≤6 ', wherein Ф0For reason
By value；
If being unsatisfactory for, the common location bias amount of three main oar steering wheels is calculated；
δ2=i × | Фk-Ф0|
Wherein, i is gear ratio always away from the main oar steering wheel of passage to blade；
If meeting, final main oar steering wheel location bias amount is stored in flight control computer by ground experiment device (4)；
After the completion of step 3, baseline blade zeroing, the pitch-change-link (6) of other blades is adjusted, completes pre- to beat cone process.
2. fax Helicopter Main oar steering wheel benchmark method of adjustment according to claim 1, it is characterised in that：The step 2
In, the main oar steering wheel each location bias amount repeatedly adjustment and closed loop control.
3. fax Helicopter Main oar steering wheel benchmark method of adjustment according to claim 1, it is characterised in that：The step 2
In, angle of flap fixture is arranged on the corresponding propeller hub root of baseline blade so that blade flapping angle is 0 ° ± 6 '.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611090943.3A CN106553768B (en) | 2016-11-30 | 2016-11-30 | A kind of main paddle steering engine benchmark method of adjustment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611090943.3A CN106553768B (en) | 2016-11-30 | 2016-11-30 | A kind of main paddle steering engine benchmark method of adjustment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106553768A true CN106553768A (en) | 2017-04-05 |
| CN106553768B CN106553768B (en) | 2018-10-02 |
Family
ID=58445540
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611090943.3A Active CN106553768B (en) | 2016-11-30 | 2016-11-30 | A kind of main paddle steering engine benchmark method of adjustment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106553768B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100234A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter tail rotor servo actuator benchmark method of adjustment |
| CN109100125A (en) * | 2018-06-28 | 2018-12-28 | 中国直升机设计研究所 | A kind of rotating amplifier output signal modification method |
| CN110562479A (en) * | 2019-07-29 | 2019-12-13 | 北京中航智科技有限公司 | pneumatic performance adjusting device for paddle |
| CN112373721A (en) * | 2020-11-03 | 2021-02-19 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting reference of main-rotor steering engine of helicopter in ground state |
| CN112478193A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Real-time online measuring device and method for helicopter rotor cone |
| CN112758315A (en) * | 2019-10-21 | 2021-05-07 | 北京京东乾石科技有限公司 | Propeller blade angle adjusting method and device |
| CN113401313A (en) * | 2021-07-30 | 2021-09-17 | 广船国际有限公司 | Installation method of rudder propeller device |
| CN115285373A (en) * | 2022-07-22 | 2022-11-04 | 哈尔滨工业大学 | Electromagnetic variable-pitch rotor blade variable-pitch characteristic measuring device |
| CN116605416A (en) * | 2023-07-17 | 2023-08-18 | 四川腾盾科技有限公司 | Automatic inclinator calibration equipment and calibration method |
| CN117734963A (en) * | 2024-02-19 | 2024-03-22 | 成都以太航空保障工程技术有限责任公司 | Helicopter rotor wing common taper detection method and device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4958786A (en) * | 1987-02-03 | 1990-09-25 | Sumitomo Precision Products Co., Ltd. | Active control mechanism for a helicopter |
| US5042965A (en) * | 1989-06-16 | 1991-08-27 | United Technologies Corporation | Propeller synchrophaser control with trajectory logic |
| CN203921189U (en) * | 2014-06-07 | 2014-11-05 | 珠海羽人飞行器有限公司 | Agricultural unmanned plane blade pitch control mechanism |
| CN105314128A (en) * | 2015-11-04 | 2016-02-10 | 中国直升机设计研究所 | Hydraulic control system for helicopter ground integrated test bench |
| CN205707301U (en) * | 2016-04-20 | 2016-11-23 | 程靖 | A kind of pulp distance varying mechanism |
-
2016
- 2016-11-30 CN CN201611090943.3A patent/CN106553768B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4958786A (en) * | 1987-02-03 | 1990-09-25 | Sumitomo Precision Products Co., Ltd. | Active control mechanism for a helicopter |
| US5042965A (en) * | 1989-06-16 | 1991-08-27 | United Technologies Corporation | Propeller synchrophaser control with trajectory logic |
| CN203921189U (en) * | 2014-06-07 | 2014-11-05 | 珠海羽人飞行器有限公司 | Agricultural unmanned plane blade pitch control mechanism |
| CN105314128A (en) * | 2015-11-04 | 2016-02-10 | 中国直升机设计研究所 | Hydraulic control system for helicopter ground integrated test bench |
| CN205707301U (en) * | 2016-04-20 | 2016-11-23 | 程靖 | A kind of pulp distance varying mechanism |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100234A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter tail rotor servo actuator benchmark method of adjustment |
| CN109100125A (en) * | 2018-06-28 | 2018-12-28 | 中国直升机设计研究所 | A kind of rotating amplifier output signal modification method |
| CN110562479A (en) * | 2019-07-29 | 2019-12-13 | 北京中航智科技有限公司 | pneumatic performance adjusting device for paddle |
| CN112758315A (en) * | 2019-10-21 | 2021-05-07 | 北京京东乾石科技有限公司 | Propeller blade angle adjusting method and device |
| CN112758315B (en) * | 2019-10-21 | 2023-12-05 | 北京京东乾石科技有限公司 | Propeller blade angle adjusting method and device |
| CN112478193A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Real-time online measuring device and method for helicopter rotor cone |
| CN112373721B (en) * | 2020-11-03 | 2023-02-10 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting reference of main-rotor steering engine of helicopter in ground state |
| CN112373721A (en) * | 2020-11-03 | 2021-02-19 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting reference of main-rotor steering engine of helicopter in ground state |
| CN113401313A (en) * | 2021-07-30 | 2021-09-17 | 广船国际有限公司 | Installation method of rudder propeller device |
| CN115285373A (en) * | 2022-07-22 | 2022-11-04 | 哈尔滨工业大学 | Electromagnetic variable-pitch rotor blade variable-pitch characteristic measuring device |
| CN116605416A (en) * | 2023-07-17 | 2023-08-18 | 四川腾盾科技有限公司 | Automatic inclinator calibration equipment and calibration method |
| CN116605416B (en) * | 2023-07-17 | 2023-10-24 | 四川腾盾科技有限公司 | Automatic inclinator calibration equipment and calibration method |
| CN117734963A (en) * | 2024-02-19 | 2024-03-22 | 成都以太航空保障工程技术有限责任公司 | Helicopter rotor wing common taper detection method and device |
| CN117734963B (en) * | 2024-02-19 | 2024-04-26 | 成都以太航空保障工程技术有限责任公司 | Helicopter rotor wing common taper detection method and device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106553768B (en) | 2018-10-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106553768A (en) | A kind of main oar steering wheel benchmark method of adjustment | |
| CN104960666B (en) | Tilting vector control auxiliary system of flight vehicle provided with longitudinal double ducts | |
| CN102791578B (en) | Air vehicle flight mechanism and control method | |
| US7963485B2 (en) | Trimmable horizontal stabilizer | |
| CN100509557C (en) | Method and device for improving braking efficient of air vehicle running on the ground | |
| US9725164B2 (en) | Method for controlling rotorcraft airfoil to minimize auxiliary rotor noise and enhance rotorcraft performance | |
| US1917428A (en) | Aircraft | |
| EP1442976B2 (en) | Airfoil member comprising an inflatable geometric morphing device with embedded fiber matrix | |
| CN104881035B (en) | Aircraft control compensating for coupling method, attitude motion control method and system | |
| CN103241370B (en) | To aircraft landing gear can the method that is managed of the steering order of knuckle section | |
| US1753252A (en) | Turbine-wheel propeller and motor | |
| CN105247206A (en) | Submersible power plant having multiple turbines | |
| CN105259904B (en) | More control surface unmanned plane longitudinal direction decoupling control methods based on Model Predictive Control | |
| US20220355923A1 (en) | High-speed, vertical take-off and landing aircraft | |
| RU2007126817A (en) | METHOD FOR IMPROVED AIRCRAFT CONTROL FOR ROLLING AND AIRCRAFT | |
| CN110654530A (en) | Variable camber wing structure with deformation feedback | |
| US2960285A (en) | Aircraft wing with control elements at wing tips | |
| US1274986A (en) | Airplane. | |
| US1145013A (en) | Aeroplane. | |
| CN101723085B (en) | Airbag type aileron | |
| CN103407444A (en) | Hover take-off and landing technology based fixed-wing aircraft | |
| CN105691594A (en) | Novel control method and device for flying wing aircraft | |
| CN106628244A (en) | Ground flight control test device and method | |
| CN201647121U (en) | Inflatable flexible ailerons | |
| CN108284941A (en) | A kind of scale bridging type covering |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |