CN105277314A - Helicopter blade dynamic balance experiment platform hinge moment parameter correction method - Google Patents
Helicopter blade dynamic balance experiment platform hinge moment parameter correction method Download PDFInfo
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Abstract
The invention belongs to the helicopter blade dynamic balance experiment platform measurement technology field and provides a helicopter blade dynamic balance experiment platform hinge moment parameter correction method. The method comprises the following steps of acquiring a moment difference value of a second propeller hub and a first propeller hub and a moment difference value of a third propeller hub and the first propeller hub; using (L-H) and (R-H) to replace a counterweight system of a helicopter blade dynamic balance rotor head to correct a hinge moment of batch production blades.
Description
Technical field
The invention belongs to Helicopter Blade Dynamic Balance Test platform field of measuring technique, relate to a kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method.
Background technology
In Helicopter Blade Dynamic Balance Test, the linear actuator that rotor head is installed, force cell are for measuring the fundamental characteristics of helicopter blade, and the linear actuator of installation, force cell and herringbone fork etc. are followed the measurement of centrifugal force to hinge moment self produced when rotor head rotates and had a great impact.In the past, Weighting system was adopted to revise the eccentric force that linear actuator, force cell and herringbone fork etc. produce.By adjusting the height of Weighting system and angle effectively balances out extra additional hinge moment in displacement cascade system, from but hinge moment reaches higher measuring accuracy.But the centrifugal force that large counterweight produces makes the serious wear of herringbone fork bearing, regularly (about 100 hours) bearing must be changed, and the height of Weighting system and angle need periodic calibration, affect dynamic balance test stand service efficiency.
Summary of the invention
The technical problem to be solved in the present invention: a kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method is provided, thorough solution installs the centrifugal force of generation when the tooling devices such as linear actuator, force cell and herringbone fork rotate to the impact on hinge moment measuring system due to rotor head, the maintenance cost of reduction equipment, shorten the maintenance period of measuring system, improve test efficiency.
Technical scheme of the present invention: a kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method, comprising:
First blade is arranged on the first propeller hub, second blade is arranged on the second propeller hub, 3rd blade is arranged on the 3rd propeller hub, measure the second blade to be arranged on the second propeller hub and to be arranged on the moment difference on the first propeller hub relative to the first blade, formula is: L2=(L-H)+(J2-J1), wherein L2 is that the second blade is arranged on the second propeller hub and is arranged on the moment difference on the first propeller hub relative to the first blade, H is the first hub moment, L is the second hub moment, J2 is the second blade moment, and J1 is the first blade moment; Measure the 3rd blade and be arranged on the moment difference the 3rd propeller hub is arranged on relative to the first blade on the first propeller hub, formula is: H3=(R-H)+(J3-J1), wherein H3 is the moment that the 3rd blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J3 is the 3rd blade moment, and J1 is the first blade moment;
Second blade is arranged on the first propeller hub, 3rd blade is arranged on the second propeller hub, first blade is arranged on the 3rd propeller hub, measure the 3rd blade to be arranged on the second propeller hub and to be arranged on the moment difference on the first propeller hub relative to the second blade, formula is L3=(L-H)+(J3-J2), wherein L3 is that the 3rd blade is arranged on the second propeller hub and is arranged on the moment difference on the first propeller hub relative to the second blade, H is the first hub moment, L is the second hub moment, J2 is the second blade moment, and J3 is the 3rd blade moment; Measure the first blade and be arranged on the moment difference the 3rd propeller hub is arranged on relative to the second blade on the first propeller hub, formula is: H1=(R-H)+(J1-J2), wherein H1 is the moment that the first blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J2 is the second blade moment, and J1 is the first blade moment;
3rd blade is arranged on the first propeller hub, first blade is arranged on the second propeller hub, second blade is arranged on the 3rd propeller hub, measure the first blade and be arranged on the moment difference the second propeller hub is arranged on relative to the 3rd blade on the first propeller hub, formula is: L1=(L-H)+(J1-J3), wherein L1 is that the first blade is arranged on the moment difference the second propeller hub is arranged on relative to the 3rd blade on the first propeller hub, H is the first hub moment, L is the second hub moment, J3 is the 3rd blade moment, and J1 is the first blade moment; And second blade be arranged on the moment difference the 3rd propeller hub is arranged on relative to the 3rd blade on the first propeller hub, formula is: H2=(R-H)+(J2-J3), wherein H2 is the moment that the second blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J3 is the 3rd blade moment, and J2 is the second blade moment;
(L1+L2+L3) ÷ 3 is obtained the moment difference (L-H) of the second propeller hub and the first propeller hub; (R1+R2+R3) ÷ 3 is obtained the moment difference (R-H) of the 3rd propeller hub and the first propeller hub;
The Weighting system of helicopter blade transient equilibrium rotor head is replaced to revise batch hinge moment of production blade with (L-H) and (R-H).
Beneficial effect of the present invention: use method of the present invention to cancel Weighting system, decrease the wear extent of bearing, like this without the need to regularly replacing bearing, reduces the maintenance cost of equipment, shortens the maintenance period of measuring system, improves test efficiency.
Accompanying drawing explanation
Fig. 1 is the blade mounting means of embodiment of the present invention step 1.
Fig. 2 is the blade mounting means of embodiment of the present invention step 2.
Fig. 3 is the blade mounting means of embodiment of the present invention step 3.
Embodiment
Embodiment
A kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method provided by the invention, comprising:
Step 1, as shown in Figure 1, first blade is arranged on the first propeller hub, second blade is arranged on the second propeller hub, 3rd blade is arranged on the 3rd propeller hub, the initial settling angle of the corresponding each blade of adjustment propeller hub support arm initial settling angle, running-up test Delta is to the test speed of blade, total pitch is adjusted to zero lift state, the initial settling angle adjusting the second propeller hub and the 3rd propeller hub in this case makes three same taperings of blade, measure the second blade to be arranged on the second propeller hub and to be arranged on the moment difference on the first propeller hub relative to the first blade, formula is: L2=(L-H)+(J2-J1), wherein L2 is that the second blade is arranged on the second propeller hub and is arranged on the moment difference on the first propeller hub relative to the first blade, H is the first hub moment, L is the second hub moment, J2 is the second blade moment, J1 is the first blade moment, measure the 3rd blade and be arranged on the moment difference the 3rd propeller hub is arranged on relative to the first blade on the first propeller hub, formula is: H3=(R-H)+(J3-J1), wherein H3 is the moment that the 3rd blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J3 is the 3rd blade moment, and J1 is the first blade moment.
Step 2, as shown in Figure 2, second blade is arranged on the first propeller hub, 3rd blade is arranged on the second propeller hub, first blade is arranged on the 3rd propeller hub, measure the 3rd blade to be arranged on the second propeller hub and to be arranged on the moment difference on the first propeller hub relative to the second blade, formula is L3=(L-H)+(J3-J2), wherein L3 is that the 3rd blade is arranged on the second propeller hub and is arranged on the moment difference on the first propeller hub relative to the second blade, H is the first hub moment, L is the second hub moment, J2 is the second blade moment, and J3 is the 3rd blade moment; Measure the first blade and be arranged on the moment difference the 3rd propeller hub is arranged on relative to the second blade on the first propeller hub, formula is: H1=(R-H)+(J1-J2), wherein H1 is the moment that the first blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J2 is the second blade moment, and J1 is the first blade moment.
Step 3, as shown in Figure 3, 3rd blade is arranged on the first propeller hub, first blade is arranged on the second propeller hub, second blade is arranged on the 3rd propeller hub, measure the first blade and be arranged on the moment difference the second propeller hub is arranged on relative to the 3rd blade on the first propeller hub, formula is: L1=(L-H)+(J1-J3), wherein L1 is that the first blade is arranged on the moment difference the second propeller hub is arranged on relative to the 3rd blade on the first propeller hub, H is the first hub moment, L is the second hub moment, J3 is the 3rd blade moment, J1 is the first blade moment, and second blade be arranged on the moment difference the 3rd propeller hub is arranged on relative to the 3rd blade on the first propeller hub, formula is: H2=(R-H)+(J2-J3), wherein H2 is the moment that the second blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J3 is the 3rd blade moment, and J2 is the second blade moment.
Step 4, (L1+L2+L3) ÷ 3 is obtained the moment difference (L-H) of the second propeller hub and the first propeller hub; (R1+R2+R3) ÷ 3 is obtained the moment difference (R-H) of the 3rd propeller hub and the first propeller hub.
Step 5, use (L-H) and (R-H) replace the Weighting system of helicopter blade transient equilibrium rotor head to revise batch hinge moment of production blade.
Claims (1)
1. a Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method, is characterized in that, comprising:
First blade is arranged on the first propeller hub, second blade is arranged on the second propeller hub, 3rd blade is arranged on the 3rd propeller hub, measure the second blade to be arranged on the second propeller hub and to be arranged on the moment difference on the first propeller hub relative to the first blade, formula is: L2=(L-H)+(J2-J1), wherein L2 is that the second blade is arranged on the second propeller hub and is arranged on the moment difference on the first propeller hub relative to the first blade, H is the first hub moment, L is the second hub moment, J2 is the second blade moment, and J1 is the first blade moment; Measure the 3rd blade and be arranged on the moment difference the 3rd propeller hub is arranged on relative to the first blade on the first propeller hub, formula is: H3=(R-H)+(J3-J1), wherein H3 is the moment that the 3rd blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J3 is the 3rd blade moment, and J1 is the first blade moment;
Second blade is arranged on the first propeller hub, 3rd blade is arranged on the second propeller hub, first blade is arranged on the 3rd propeller hub, measure the 3rd blade to be arranged on the second propeller hub and to be arranged on the moment difference on the first propeller hub relative to the second blade, formula is L3=(L-H)+(J3-J2), wherein L3 is that the 3rd blade is arranged on the second propeller hub and is arranged on the moment difference on the first propeller hub relative to the second blade, H is the first hub moment, L is the second hub moment, J2 is the second blade moment, and J3 is the 3rd blade moment; Measure the first blade and be arranged on the moment difference the 3rd propeller hub is arranged on relative to the second blade on the first propeller hub, formula is: H1=(R-H)+(J1-J2), wherein H1 is the moment that the first blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J2 is the second blade moment, and J1 is the first blade moment;
3rd blade is arranged on the first propeller hub, first blade is arranged on the second propeller hub, second blade is arranged on the 3rd propeller hub, measure the first blade and be arranged on the moment difference the second propeller hub is arranged on relative to the 3rd blade on the first propeller hub, formula is: L1=(L-H)+(J1-J3), wherein L1 is that the first blade is arranged on the moment difference the second propeller hub is arranged on relative to the 3rd blade on the first propeller hub, H is the first hub moment, L is the second hub moment, J3 is the 3rd blade moment, and J1 is the first blade moment; And second blade be arranged on the moment difference the 3rd propeller hub is arranged on relative to the 3rd blade on the first propeller hub, formula is: H2=(R-H)+(J2-J3), wherein H2 is the moment that the second blade is arranged on the 3rd propeller hub, R is the 3rd hub moment, H is the first hub moment, J3 is the 3rd blade moment, and J2 is the second blade moment;
(L1+L2+L3) ÷ 3 is obtained the moment difference (L-H) of the second propeller hub and the first propeller hub; (R1+R2+R3) ÷ 3 is obtained the moment difference (R-H) of the 3rd propeller hub and the first propeller hub;
The Weighting system of helicopter blade transient equilibrium rotor head is replaced to revise batch hinge moment of production blade with (L-H) and (R-H).
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| CN201410323079.1A CN105277314B (en) | 2014-07-08 | 2014-07-08 | A kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106121907A (en) * | 2016-06-28 | 2016-11-16 | 三重型能源装备有限公司 | Blade balancing method, blade and wind-driven generator |
| CN108007644A (en) * | 2017-11-17 | 2018-05-08 | 哈尔滨飞机工业集团有限责任公司 | A kind of calibration method of helicopter blade dynamic balance bench propeller hub initial settling angle |
| CN110789711A (en) * | 2019-10-12 | 2020-02-14 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting internal vibration of rotating surface of hub of helicopter rotor |
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| RU101185U1 (en) * | 2010-08-13 | 2011-01-10 | Павел Юрьевич Борисов | DEVICE FOR DYNAMIC BALANCING OF A HELICOPTER SCREW |
| CN202522377U (en) * | 2011-12-22 | 2012-11-07 | 中国直升机设计研究所 | Helicopter blade static/moving balance adjusting device |
| CN103822741A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Wireless dynamic balance test bench hinge torque measurement method |
| CN203688147U (en) * | 2013-12-26 | 2014-07-02 | 哈尔滨工业大学 | Helicopter rotor blade dynamic hinge moment calibration device |
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2014
- 2014-07-08 CN CN201410323079.1A patent/CN105277314B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| RU101185U1 (en) * | 2010-08-13 | 2011-01-10 | Павел Юрьевич Борисов | DEVICE FOR DYNAMIC BALANCING OF A HELICOPTER SCREW |
| CN202522377U (en) * | 2011-12-22 | 2012-11-07 | 中国直升机设计研究所 | Helicopter blade static/moving balance adjusting device |
| CN103822741A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Wireless dynamic balance test bench hinge torque measurement method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106121907A (en) * | 2016-06-28 | 2016-11-16 | 三重型能源装备有限公司 | Blade balancing method, blade and wind-driven generator |
| CN108007644A (en) * | 2017-11-17 | 2018-05-08 | 哈尔滨飞机工业集团有限责任公司 | A kind of calibration method of helicopter blade dynamic balance bench propeller hub initial settling angle |
| CN110789711A (en) * | 2019-10-12 | 2020-02-14 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting internal vibration of rotating surface of hub of helicopter rotor |
| CN110789711B (en) * | 2019-10-12 | 2023-03-14 | 哈尔滨飞机工业集团有限责任公司 | Method for adjusting internal vibration of rotating surface of rotor hub of helicopter |
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| CN105277314B (en) | 2018-03-02 |
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