CN105277314B - A kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method - Google Patents
A kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method Download PDFInfo
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- CN105277314B CN105277314B CN201410323079.1A CN201410323079A CN105277314B CN 105277314 B CN105277314 B CN 105277314B CN 201410323079 A CN201410323079 A CN 201410323079A CN 105277314 B CN105277314 B CN 105277314B
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Abstract
The invention belongs to Helicopter Blade Dynamic Balance Test platform field of measuring technique, there is provided a kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method, including：Obtain the moment difference of the second propeller hub and the first propeller hub, and the moment difference of the 3rd propeller hub and the first propeller hub；The Weighting system for replacing helicopter blade dynamic balancing rotor head with (L H) and (R H) is modified to batch hinge moment of production blade.
Description
Technical field
The invention belongs to Helicopter Blade Dynamic Balance Test platform field of measuring technique, is related to a kind of helicopter blade dynamic balancing
Testing stand hinge moment parameter correction method.
Background technology
In Helicopter Blade Dynamic Balance Test, linear actuator, the force cell installed on rotor head are used to measure
When the fundamental characteristics of helicopter blade, the linear actuator of installation, force cell and herringbone fork etc. follows the rotor head to rotate from
Measurement of the centrifugal force caused by body to hinge moment has a great impact.In the past, using Weighting system to linear actuator, dynamometry
Eccentric force caused by sensor and herringbone fork etc. is modified.Effectively balanced out by the height and angle that adjust Weighting system
The hinge moment of additional in displacement train, so as to be that hinge moment reaches higher measurement accuracy.But big counterweight
Caused centrifugal force makes the serious wear of herringbone fork bearing, it is necessary to periodically (about 100 hours) replacing bearings, and Weighting system
Height and angle need periodic calibration, influence dynamic balance test stand service efficiency.
The content of the invention
The technical problem to be solved in the present invention：A kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameters revision is provided
Method, thoroughly solve due to being produced during the tooling device rotations such as rotor head installation linear actuator, force cell and herringbone fork
Centrifugal force to the influence to hinge moment measuring system, reduce the maintenance cost of equipment, shorten the maintenance period of measuring system,
Improve test efficiency.
Technical scheme：A kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method, including：
First blade is arranged on the first propeller hub, the second blade is arranged on the second propeller hub, the 3rd blade is installed
On the 3rd propeller hub, the second blade of measurement is arranged on the second propeller hub and is arranged on the torque on the first propeller hub relative to the first blade
Difference, formula are：L2=(L-H)+(J2-J1), wherein L2 are that the second blade is arranged on the second propeller hub relative to the first blade
Moment difference on the first propeller hub, H are the first hub moment, and L is the second hub moment, and J2 is the second blade torque,
J1 is the first blade torque；The 3rd blade is measured to be arranged on the first propeller hub relative to the first blade on the 3rd propeller hub
Moment difference, formula are：H3=(R-H)+(J3-J1), wherein H3 are the torque that the 3rd blade is arranged on the 3rd propeller hub, and R is
3rd hub moment, H are the first hub moment, and J3 is the 3rd blade torque, and J1 is the first blade torque；
Second blade is arranged on the first propeller hub, the 3rd blade is arranged on the second propeller hub, the first blade is installed
On the 3rd propeller hub, the 3rd blade of measurement is arranged on the second propeller hub and is arranged on the torque on the first propeller hub relative to the second blade
Difference, formula are L3=(L-H)+(J3-J2), and wherein L3 is that the 3rd blade is arranged on the second propeller hub relative to the second blade peace
Moment difference on the first propeller hub, H are the first hub moment, and L is the second hub moment, and J2 is the second blade torque, J3
For the 3rd blade torque；Measure the first blade and be arranged on the power on the first propeller hub relative to the second blade on the 3rd propeller hub
Square difference, formula are：H1=(R-H)+(J1-J2), wherein H1 are the torque that the first blade is arranged on the 3rd propeller hub, R the
Three hub moments, H are the first hub moment, and J2 is the second blade torque, and J1 is the first blade torque；
3rd blade is arranged on the first propeller hub, the first blade is arranged on the second propeller hub, the second blade is installed
On the 3rd propeller hub, the first blade of measurement is arranged on the second propeller hub and is arranged on the torque on the first propeller hub relative to the 3rd blade
Difference, formula are：L1=(L-H)+(J1-J3), wherein L1 are that the first blade is arranged on the second propeller hub relative to the 3rd blade
Moment difference on the first propeller hub, H are the first hub moment, and L is the second hub moment, and J3 is the 3rd blade torque,
J1 is the first blade torque；And second blade be arranged on the 3rd propeller hub on relative to the 3rd blade be arranged on the first propeller hub on
Moment difference, formula are：H2=(R-H)+(J2-J3), wherein H2 are the torque that the second blade is arranged on the 3rd propeller hub, and R is
3rd hub moment, H are the first hub moment, and J3 is the 3rd blade torque, and J2 is the second blade torque；
(L1+L2+L3) ÷ 3 is obtained into the moment difference (L-H) of the second propeller hub and the first propeller hub；By (H1+H2+H3) ÷ 3
Obtain the moment difference (R-H) of the 3rd propeller hub and the first propeller hub；
The Weighting system of helicopter blade dynamic balancing rotor head is replaced to batch hinge of production blade with (L-H) and (R-H)
Torque is modified.
Beneficial effects of the present invention：Method using the present invention can cancel Weighting system, reduce the wear extent of bearing,
Bearing need not be so regularly replaced, reduces the maintenance cost of equipment, shortens the maintenance period of measuring system, improves experiment effect
Rate.
Brief description of the drawings
Fig. 1 is the blade mounting means of step 1 of the embodiment of the present invention.
Fig. 2 is the blade mounting means of step 2 of the embodiment of the present invention.
Fig. 3 is the blade mounting means of step 3 of the embodiment of the present invention.
Embodiment
Embodiment
A kind of Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method provided by the invention, including：
Step 1, as shown in figure 1, by the first blade be arranged on the first propeller hub on, the second blade is arranged on the second propeller hub
On, the 3rd blade is arranged on the 3rd propeller hub, adjustment propeller hub support arm initial settling angle corresponds to the initial settling angle of each blade, rises
Total pitch is adjusted to zero lift state to the test speed of blade by dynamic test Delta, adjust in this case the second propeller hub and
The initial settling angle of 3rd propeller hub makes three same tapers of blade, and the second blade of measurement is arranged on the second propeller hub relative to the first oar
Leaf is arranged on the moment difference on the first propeller hub, and formula is：L2=(L-H)+(J2-J1), wherein L2 are that the second blade is arranged on
The moment difference on the first propeller hub is arranged on relative to the first blade on second propeller hub, H is the first hub moment, and L is the second oar
Hub torque, J2 are the second blade torque, and J1 is the first blade torque；The 3rd blade is measured on the 3rd propeller hub relative to the
One blade is arranged on the moment difference on the first propeller hub, and formula is：H3=(R-H)+(J3-J1), wherein H3 pacify for the 3rd blade
Torque on the 3rd propeller hub, R are the 3rd hub moment, and H is the first hub moment, and J3 is the 3rd blade torque, J1
One blade torque.
Step 2, as shown in Fig. 2 by the second blade be arranged on the first propeller hub on, the 3rd blade is arranged on the second propeller hub
On, the first blade is arranged on the 3rd propeller hub, the 3rd blade of measurement is arranged on the second propeller hub and installed relative to the second blade
Moment difference on the first propeller hub, formula are L3=(L-H)+(J3-J2), and wherein L3 is that the 3rd blade is arranged on the second propeller hub
On moment difference on the first propeller hub is arranged on relative to the second blade, H is the first hub moment, and L is the second hub moment, J2
For the second blade torque, J3 is the 3rd blade torque；The first blade is measured on the 3rd propeller hub relative to the second blade to pacify
Moment difference on the first propeller hub, formula are：H1=(R-H)+(J1-J2), wherein H1 are that the first blade is arranged on the 3rd
Torque on propeller hub, R are the 3rd hub moment, and H is the first hub moment, and J2 is the second blade torque, and J1 is the first blade power
Square.
Step 3, as shown in figure 3, by the 3rd blade be arranged on the first propeller hub on, the first blade is arranged on the second propeller hub
On, the second blade is arranged on the 3rd propeller hub, the first blade of measurement is arranged on the second propeller hub and installed relative to the 3rd blade
Moment difference on the first propeller hub, formula are：L1=(L-H)+(J1-J3), wherein L1 are that the first blade is arranged on the second oar
The moment difference on the first propeller hub is arranged on relative to the 3rd blade on hub, H is the first hub moment, and L is the second hub moment,
J3 is the 3rd blade torque, and J1 is the first blade torque；And second blade be arranged on the 3rd propeller hub on relative to the 3rd blade
Moment difference on the first propeller hub, formula are：H2=(R-H)+(J2-J3), wherein H2 are that the second blade is arranged on the
Torque on three propeller hubs, R are the 3rd hub moment, and H is the first hub moment, and J3 is the 3rd blade torque, and J2 is the second blade
Torque.
Step 4, (L1+L2+L3) ÷ 3 is obtained to the moment difference (L-H) of the second propeller hub and the first propeller hub；By (R1+R2+
R3) ÷ 3 obtains the moment difference (R-H) of the 3rd propeller hub and the first propeller hub.
Step 5, the Weighting system of helicopter blade dynamic balancing rotor head is replaced with (L-H) and (R-H) to batch production blade
Hinge moment be modified.
Claims (1)
- A kind of 1. Helicopter Blade Dynamic Balance Test platform hinge moment parameter correction method, it is characterised in that including：First blade is arranged on the first propeller hub, the second blade is arranged on the second propeller hub, the 3rd blade is arranged on the On three propeller hubs, the second blade of measurement is arranged on the second propeller hub and is arranged on the torque difference on the first propeller hub relative to the first blade Value, formula are：L2=(L-H)+(J2-J1), wherein L2 are that the second blade is arranged on the second propeller hub relative to the first blade peace Moment difference on the first propeller hub, H are the first hub moment, and L is the second hub moment, and J2 is the second blade torque, J1 For the first blade torque；Measure the 3rd blade and be arranged on the power on the first propeller hub relative to the first blade on the 3rd propeller hub Square difference, formula are：H3=(R-H)+(J3-J1), wherein H3 are the torque that the 3rd blade is arranged on the 3rd propeller hub, R the Three hub moments, H are the first hub moment, and J3 is the 3rd blade torque, and J1 is the first blade torque；Second blade is arranged on the first propeller hub, the 3rd blade is arranged on the second propeller hub, the first blade is arranged on the On three propeller hubs, the 3rd blade of measurement is arranged on the second propeller hub and is arranged on the torque difference on the first propeller hub relative to the second blade Value, formula are L3=(L-H)+(J3-J2), and wherein L3 is that the 3rd blade is arranged on the second propeller hub relative to the installation of the second blade Moment difference on the first propeller hub, H are the first hub moment, and L is the second hub moment, and J2 is the second blade torque, and J3 is 3rd blade torque；Measure the first blade and be arranged on the torque on the first propeller hub relative to the second blade on the 3rd propeller hub Difference, formula are：H1=(R-H)+(J1-J2), wherein H1 are the torque that the first blade is arranged on the 3rd propeller hub, and R is the 3rd Hub moment, H are the first hub moment, and J2 is the second blade torque, and J1 is the first blade torque；3rd blade is arranged on the first propeller hub, the first blade is arranged on the second propeller hub, the second blade is arranged on the On three propeller hubs, the first blade of measurement is arranged on the second propeller hub and is arranged on the torque difference on the first propeller hub relative to the 3rd blade Value, formula are：L1=(L-H)+(J1-J3), wherein L1 are that the first blade is arranged on the second propeller hub relative to the 3rd blade peace Moment difference on the first propeller hub, H are the first hub moment, and L is the second hub moment, and J3 is the 3rd blade torque, J1 For the first blade torque；And second blade be arranged on the 3rd propeller hub on relative to the 3rd blade be arranged on the first propeller hub on power Square difference, formula are：H2=(R-H)+(J2-J3), wherein H2 are the torque that the second blade is arranged on the 3rd propeller hub, R the Three hub moments, H are the first hub moment, and J3 is the 3rd blade torque, and J2 is the second blade torque；(L1+L2+L3) ÷ 3 is obtained into the moment difference (L-H) of the second propeller hub and the first propeller hub；(H1+H2+H3) ÷ 3 is obtained The moment difference (R-H) of 3rd propeller hub and the first propeller hub；The Weighting system of helicopter blade dynamic balancing rotor head is replaced to batch hinge moment of production blade with (L-H) and (R-H) It is modified.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| 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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| CN105277314A CN105277314A (en) | 2016-01-27 |
| CN105277314B true CN105277314B (en) | 2018-03-02 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106121907B (en) * | 2016-06-28 | 2018-07-13 | 三一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 |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
|---|---|---|---|---|
| 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 |
Non-Patent Citations (1)
| Title |
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| 小型共轴式直升机旋翼桨叶铰链力矩研究;徐冠峰 等;《航空动力学报》;20100831;第25卷(第8期);第1805-1810页 * |
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