CN105403362A - Helicopter blade static balance detection and calibration method - Google Patents
Helicopter blade static balance detection and calibration method Download PDFInfo
- Publication number
- CN105403362A CN105403362A CN201510939447.XA CN201510939447A CN105403362A CN 105403362 A CN105403362 A CN 105403362A CN 201510939447 A CN201510939447 A CN 201510939447A CN 105403362 A CN105403362 A CN 105403362A
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- blade
- standard
- static
- truss
- helicopter
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/12—Static balancing; Determining position of centre of gravity
Abstract
The invention discloses a helicopter blade static balance detection and calibration method. The method is completed by use of a helicopter blade static moment calibration device. The device comprises a support clamping assembly (2) in the middle, one side of the support clamping assembly (2) is provided with an adjustable counterweight assembly (1), the other side of the support clamping assembly (2) is provided with a blade support truss (3), and an electric scale (4) is arranged below the top end of the blade support truss (3). The method comprises the following steps: step one, placing a standard blade on the blade support truss (3) after the standard blade is clamped by use of the support clamping assembly (2); step two, adjusting the adjustable counterweight assembly (1), and enabling the electronic scale (4) to display a value P specified in advance; step three, locking the adjustable counterweight assembly (1) for no more contact, and replacing the standard blade with a blade to be detected; and step four, enabling reading of the electronic scale (4) to be the same as P by increasing and decreasing the number of counterweight blocks. According to the invention, the standard blade is introduced by use of a comparison measurement mode, and the static moment of the blade to be detected is calibrated to be consistent with that of the standard blade. Since static movement measurement of an auxiliary tool is unnecessary, system errors are reduced, and the static balance calibration precision of the blade is improved.
Description
Technical field
The present invention is a kind of helicopter blade static equilibrium detection and calibration steps, belongs to field of measuring technique.
Background technology
The static moment of blade refers to the quality of blade and the product of its barycenter distance blade rotation center distance.In actual production process, inevitably there is certain difference in the weight of blade, center of gravity and aerodynamic configuration, so generally all arranged the static equilibrium of blade to adjust in process of production, eliminates the difference of static moment between blade.
Traditional blade static moment calibration steps adopts the mode directly measured, and one end helicopter simulating propeller hub clamps rear placement in the plane to blade root, and the other end is placed on electronic scales after clamping wing tip.Utilizing the principle of two ends equalising torque, by measuring the static moment of blade root bare terminal end and wing tip bare terminal end, extrapolating the reading of electronic scales.But the method finds to there are some problems in practice process: wing tip bare terminal end neither one accurately locating surface or hole can use, and cause repeated clamping location difficulty, duplicate measurements precision is lower, and the blade static moment namely measured is inaccurate; Because classic method needs to clamp wing tip, may damage blade; Traditional equipment needs the visual adjustment of operator, and the personal error brought is larger; When measuring, supposition blade is rigid body, and in fact detected blade can produce slight deformation under self gravitation effect, increases systematic error.
Summary of the invention
The shortcoming that the present invention exists for above-mentioned prior art just and design and provide a kind of helicopter blade static equilibrium detection and calibration steps, the method adopts the mode of measurement of comparison, introduce standard blade, the static moment of detected blade is calibrated to consistent with standard blade.Owing to no longer needing the static moment of carrying out auxiliary mould to measure, reduce systematic error, promote the static equilibrium calibration accuracy of blade.
Technical scheme of the present invention is as follows:
This kind of helicopter blade static equilibrium detection and calibration steps, the method uses helicopter blade static moment correcting device, this equipment comprises middle support clamp assemblies (2), support clamp assemblies (2) side be adjustable counter balance assembly (1), opposite side is blade sub-truss (3), below the top of blade sub-truss (3), be provided with electronic scales (4), it is characterized in that: the step of the method is as follows:
Step one, with support clamp assemblies (2) will standard blade clamp after be placed on blade sub-truss (3);
Step 2, adjustment adjustable counter balance assembly (1), make electronic scales (4) be shown as a prespecified numerical value P;
Step 3, by adjustable counter balance assembly (1) lock, standard blade is replaced by blade to be detected;
Step 4, by increasing and decreasing balancing weight on blade to be detected, make the reading of electronic scales (4) identical with P.
Technical solution of the present invention proposes the mode adopting measurement of comparison, introduces standard blade, is all calibrated to consistent with standard blade by the static moment of detected blade.Utilize helicopter blade static moment correcting device, standard blade is placed on correcting device, the adjustable counter balance part of adjustment correcting device, the adjustable counter balance part of correcting device is locked after making the reading of electronic scales be shown as some predetermined value P, standard of replacement blade is blade to be detected, by increasing and decreasing balancing weight on blade to be detected, make the reading of electronic scales consistent with P or in certain margin tolerance.
Accompanying drawing explanation
Fig. 1 is the structural representation of the helicopter blade static moment correcting device that the inventive method uses
Embodiment
Below with reference to drawings and Examples, technical solution of the present invention is further described:
Shown in accompanying drawing 1, this kind of helicopter blade static equilibrium detection and calibration steps, the method uses helicopter blade static moment correcting device, this equipment comprises middle support clamp assemblies 2, support clamp assemblies 2 side be adjustable counter balance assembly 1, opposite side is blade sub-truss 3, is provided with electronic scales 4, it is characterized in that below the top of blade sub-truss 3: the step of the method is as follows:
Step one, with support clamp assemblies 2 will standard blade clamp after be placed on blade sub-truss 3;
Step 2, adjustment adjustable counter balance assembly 1, make electronic scales 4 be shown as a prespecified numerical value P;
Step 3, adjustable counter balance assembly 1 to be locked, must not touch again, standard blade is replaced by blade to be detected;
Step 4, by increasing and decreasing balancing weight on blade to be detected, make the reading of electronic scales 4 identical with P.
The main blade static-balance that the method for the invention is applicable to certain type now detects and calibration, measuring accuracy can reach 1g, duplicate measurements precision reaches ± 1g, compared with the duplicate measurements precision ± 4g of former static equilibrium detection and calibration steps, substantially increases measuring accuracy.
Claims (1)
1. a helicopter blade static equilibrium detection and calibration steps, the method uses helicopter blade static moment correcting device, this equipment comprises middle support clamp assemblies (2), support clamp assemblies (2) side be adjustable counter balance assembly (1), opposite side is blade sub-truss (3), below the top of blade sub-truss (3), be provided with electronic scales (4), it is characterized in that: the step of the method is as follows:
Step one, with support clamp assemblies (2) will standard blade clamp after be placed on blade sub-truss (3);
Step 2, adjustment adjustable counter balance assembly (1), make electronic scales (4) be shown as a prespecified numerical value P;
Step 3, by adjustable counter balance assembly (1) lock, standard blade is replaced by blade to be detected;
Step 4, by increasing and decreasing balancing weight on blade to be detected, make the reading of electronic scales (4) identical with P.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510939447.XA CN105403362A (en) | 2015-12-11 | 2015-12-11 | Helicopter blade static balance detection and calibration method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510939447.XA CN105403362A (en) | 2015-12-11 | 2015-12-11 | Helicopter blade static balance detection and calibration method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105403362A true CN105403362A (en) | 2016-03-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510939447.XA Pending CN105403362A (en) | 2015-12-11 | 2015-12-11 | Helicopter blade static balance detection and calibration method |
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| CN (1) | CN105403362A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108072345A (en) * | 2016-11-14 | 2018-05-25 | 江西昌河航空工业有限公司 | A kind of paddle size composite measurement platform |
| CN110657918A (en) * | 2019-09-19 | 2020-01-07 | 哈尔滨飞机工业集团有限责任公司 | Tail rotor blade static balance detection tool |
| CN112525423A (en) * | 2020-11-20 | 2021-03-19 | 昌河飞机工业（集团）有限责任公司 | Lifting and rotating device and method for adjusting balance |
| CN113291486A (en) * | 2021-01-06 | 2021-08-24 | 合肥联合飞机科技有限公司 | Balancing method for static balance of helicopter blades |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5824897A (en) * | 1996-08-15 | 1998-10-20 | Avion, Inc. | Blade static balancing fixture |
| CN102359848A (en) * | 2011-09-06 | 2012-02-22 | 上海福伊特水电设备有限公司 | Water turbine rotating wheel three-fulcrum weighing static balance device and static balance technology thereof |
| CN202195872U (en) * | 2011-08-31 | 2012-04-18 | 南京工业大学 | Batch automatic matching device for vane of small wind-driven generator |
| CN202453149U (en) * | 2012-02-24 | 2012-09-26 | 南通东泰新能源设备有限公司 | Megawatt-level vane balancing device |
| CN204479242U (en) * | 2015-02-13 | 2015-07-15 | 镇江中船瓦锡兰螺旋桨有限公司 | A kind of adjustable propeller static balance testing device |
-
2015
- 2015-12-11 CN CN201510939447.XA patent/CN105403362A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5824897A (en) * | 1996-08-15 | 1998-10-20 | Avion, Inc. | Blade static balancing fixture |
| CN202195872U (en) * | 2011-08-31 | 2012-04-18 | 南京工业大学 | Batch automatic matching device for vane of small wind-driven generator |
| CN102359848A (en) * | 2011-09-06 | 2012-02-22 | 上海福伊特水电设备有限公司 | Water turbine rotating wheel three-fulcrum weighing static balance device and static balance technology thereof |
| CN202453149U (en) * | 2012-02-24 | 2012-09-26 | 南通东泰新能源设备有限公司 | Megawatt-level vane balancing device |
| CN204479242U (en) * | 2015-02-13 | 2015-07-15 | 镇江中船瓦锡兰螺旋桨有限公司 | A kind of adjustable propeller static balance testing device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108072345A (en) * | 2016-11-14 | 2018-05-25 | 江西昌河航空工业有限公司 | A kind of paddle size composite measurement platform |
| CN110657918A (en) * | 2019-09-19 | 2020-01-07 | 哈尔滨飞机工业集团有限责任公司 | Tail rotor blade static balance detection tool |
| CN112525423A (en) * | 2020-11-20 | 2021-03-19 | 昌河飞机工业（集团）有限责任公司 | Lifting and rotating device and method for adjusting balance |
| CN113291486A (en) * | 2021-01-06 | 2021-08-24 | 合肥联合飞机科技有限公司 | Balancing method for static balance of helicopter blades |
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Application publication date: 20160316 |
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