CN104122034A - Helicopter main blade dynamic balancing test bed hydraulic drive system - Google Patents
Helicopter main blade dynamic balancing test bed hydraulic drive system Download PDFInfo
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- CN104122034A CN104122034A CN201310145257.1A CN201310145257A CN104122034A CN 104122034 A CN104122034 A CN 104122034A CN 201310145257 A CN201310145257 A CN 201310145257A CN 104122034 A CN104122034 A CN 104122034A
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- hydraulic
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- servo
- main blade
- test bed
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Abstract
The invention belongs to the technical field of rotary speed control of a helicopter main blade dynamic balancing test bed, and relates to a helicopter main blade dynamic balancing test bed hydraulic drive system. The helicopter main blade dynamic balancing test bed hydraulic drive system includes a hydraulic pump, a hydraulic pipeline, a hydraulic motor, a servo control system and a motor; the motor is connected to the hydraulic pump; the hydraulic pump is connected to the hydraulic motor via the hydraulic pipeline; the hydraulic motor is connected to a balancing test bed spindle through a gearbox; the servo control system includes a servo valve, a spindle speed measuring device, a control computer and a comparator; the servo valve is connected to the hydraulic pump; the spindle speed measuring device is connected to the control computer via a wire; the comparator is connected to the control computer via a wire; and the comparator is connected to the servo valve via a wire. The helicopter main blade dynamic balancing test bed hydraulic drive system has the characteristics of high reliability, easy maintenance and relatively low cost.
Description
Technical field
The invention belongs to Helicopter Main blade dynamic balance test stand rotating speed control technology field, relate to a kind of Helicopter Main blade dynamic balance test stand fluid power system.
Background technology
Original system is made up of high voltage converter, AC/DC motor, by high voltage converter, 6000V high pressure is carried out to frequency control motor is carried out to speed governing.The rotation of motor direct-drive rotor head main shaft.This kind of type of drive is high especially to operating personnel's professional requirement, once the bad maintenance of breaking down, high voltage converter needs external import, and expensive.
Summary of the invention
Technical matters to be solved by this invention is: the Helicopter Main blade dynamic balance test stand that a kind of maintainability is good, cost is low fluid power system is provided.
Technical conceive of the present invention is: the alternating current generator of constant speed rotation is connected with hydraulic pump, because the rotation of motor makes to produce in hydraulic pump pressure differential, hydraulic oil has been produced to flow, and flow is controlled with servo control mechanism, again by fluid motor-driven dynamic balance test stand main shaft, make rotor head rotation, with flow, rotor head rotating speed is controlled.
Based on above design, technical scheme of the present invention is: a kind of Helicopter Main blade dynamic balance test stand fluid power system, is characterized by: described fluid power system comprises hydraulic pump, fluid pressure line, oil motor, servo-control system and motor; Motor is connected with hydraulic pump; Hydraulic pump is by fluid pressure line connecting fluid pressure motor; Oil motor connects dynamic balance test stand main shaft by wheel box; Servo-control system comprises servo-valve, main shaft speed measuring device, controls computing machine, comparer; Servo-valve is connected with hydraulic pump; Main shaft speed measuring device is connected by wire with control computing machine; Comparer is connected with control computing machine by wire, and comparer is connected with servo-valve by wire.
The invention has the beneficial effects as follows: Helicopter Main blade dynamic balance test stand fluid power system of the present invention, adopt hydraulic system, power is delivered to dynamic balance test stand main shaft by power source, drive shaft rotation, simultaneously, servo-control system is applied in this hydraulic system, the speed of mainshaft can be regulated the control of flow by servo-drive system, regulate accurately fast; What the present invention adopted is all proven technique, and reliability is high, easy to maintenance, and cost is relatively cheap.
Brief description of the drawings
Fig. 1 is the structured flowchart of Helicopter Main blade dynamic balance test stand fluid power system of the present invention.
Embodiment
A kind of Helicopter Main blade of the present invention dynamic balance test stand fluid power system is a set of enclosed drive system, by four hydraulic pumps, hydraulic plumbing system, four oil motors, control the parts such as computing machine, comparer and form.By dragging hydraulic system with quadruplet hydraulic closed circuit pump, the working pressure of hydraulic system is 21～30Mpa.
Hydraulic pump is made up of four inclined disc type hydraulic servo Variable plunger pumps (closed circuit pump), and four hydraulic pumps drive (rotating speed 1470rpm) by 4 constant speed alternating current generators, drive respectively four oil motors, drive shaft rotation.
Due to this system requirements fine adjustment motor output speed, and the rotating speed rising or falling speed of output shaft is controlled, thereby requires hydraulic servo variable output pump, and should drive and regulate swash plate angle by servo-valve, and with swash plate positions feedback signal.
Hydraulic plumbing system adopts stainless steel hard tube to lay, and high-voltage tube is the stainless-steel tube of eight 60mm latus rectums (external diameter is 76mm), and drain mast is the stainless-steel tube of a 60mm latus rectum (external diameter is 76mm), and the length of every steel pipe is estimated as 30 meters of left and right.
The rated operating pressure of oil motor is 28MPa, and specified equivalent output torque is 2.98Nm/bar, turn/min of rated speed 1700.
Four oil motors are by the consideration of maximum leakage amount, and leakage flow is less than 200L/min, so system has adopted a pipeline that negotiability is 200L/min, is enough to ensure that draining is unimpeded.
Main hydraulic system start-up course and requirement are as follows:
Press oil sources start button, main hydraulic system automatic decision self is carried out and is started after preparation, can start successively four main pump sources, now wants strict guarantee oil motor without rotation, otherwise wants indication fault speed-regulating function is locked.To establish special null setting for this reason;
When oil sources starts, need and before termination of pumping, keep this signal to connection signal of master control system; Computing machine to be controlled is ready to after signal feedback, just can carry out speed governing operation, otherwise should speed-regulating function is locked;
After system is ready to, can presses speed-adjusting start key and carry out speed governing operation;
After speed-adjusting start key is pressed, answer solenoidoperated cluthes adhesive, ensure after normal adhesive, then carry out speed setting according to default governing time and desired value, be better than ± 1rpm of adjusting speed accuracy;
After off-test, the normal shut down procedure of available test stops;
In process of the test, lose system as unexpected and be ready to signal, also can stop with the normal shut down procedure of test;
In process of the test, if rotating speed exceedes preset rotation speed limit, carry out hypervelocity parking procedure;
If intervention button was manually pressed or controlled computing machine and sends emergent stop signal in testing, carry out the anxious program of stopping.
Claims (1)
1. a Helicopter Main blade dynamic balance test stand fluid power system, is characterized by: described fluid power system comprises hydraulic pump, fluid pressure line, oil motor, servo-control system and motor; Motor is connected with hydraulic pump; Hydraulic pump is by fluid pressure line connecting fluid pressure motor; Oil motor connects dynamic balance test stand main shaft by wheel box; Servo-control system comprises servo-valve, main shaft speed measuring device, controls computing machine, comparer; Servo-valve is connected with hydraulic pump; Main shaft speed measuring device is connected by wire with control computing machine; Comparer is connected with control computing machine by wire, and comparer is connected with servo-valve by wire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145257.1A CN104122034A (en) | 2013-04-24 | 2013-04-24 | Helicopter main blade dynamic balancing test bed hydraulic drive system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145257.1A CN104122034A (en) | 2013-04-24 | 2013-04-24 | Helicopter main blade dynamic balancing test bed hydraulic drive system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104122034A true CN104122034A (en) | 2014-10-29 |
Family
ID=51767538
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310145257.1A Pending CN104122034A (en) | 2013-04-24 | 2013-04-24 | Helicopter main blade dynamic balancing test bed hydraulic drive system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104122034A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006060638A2 (en) * | 2004-12-01 | 2006-06-08 | Haldex Hydraulics Corporation | Hydraulic drive system |
| WO2008001657A1 (en) * | 2006-06-30 | 2008-01-03 | Daikin Industries, Ltd. | Fluid pressure drive device |
| CN101695816A (en) * | 2009-10-19 | 2010-04-21 | 路文忠 | Low-speed high-torque high-thrust digital electro-hydraulic servo drive device |
| CN101698283A (en) * | 2009-10-19 | 2010-04-28 | 路文忠 | Big-torque big-thrust big-power digital type electrohydraulic servo drive device |
| CN201818591U (en) * | 2010-10-08 | 2011-05-04 | 三一重工股份有限公司 | Hydraulic driving device for engineering machine |
| CN201836145U (en) * | 2010-10-09 | 2011-05-18 | 三一重工股份有限公司 | Self-adaptive hydraulic driving device for engineering machinery |
| CN201865881U (en) * | 2010-08-02 | 2011-06-15 | 昆明中铁大型养路机械集团有限公司 | Hydraulic driving device of air compressor |
| CN202220656U (en) * | 2011-09-01 | 2012-05-16 | 何东海 | Hydraulically driven electric generating set |
| CN102814244A (en) * | 2012-07-31 | 2012-12-12 | 天圣环保工程（成都）有限公司 | Full hydraulic drive differential horizontal screw centrifuge |
-
2013
- 2013-04-24 CN CN201310145257.1A patent/CN104122034A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006060638A2 (en) * | 2004-12-01 | 2006-06-08 | Haldex Hydraulics Corporation | Hydraulic drive system |
| WO2008001657A1 (en) * | 2006-06-30 | 2008-01-03 | Daikin Industries, Ltd. | Fluid pressure drive device |
| CN101695816A (en) * | 2009-10-19 | 2010-04-21 | 路文忠 | Low-speed high-torque high-thrust digital electro-hydraulic servo drive device |
| CN101698283A (en) * | 2009-10-19 | 2010-04-28 | 路文忠 | Big-torque big-thrust big-power digital type electrohydraulic servo drive device |
| CN201865881U (en) * | 2010-08-02 | 2011-06-15 | 昆明中铁大型养路机械集团有限公司 | Hydraulic driving device of air compressor |
| CN201818591U (en) * | 2010-10-08 | 2011-05-04 | 三一重工股份有限公司 | Hydraulic driving device for engineering machine |
| CN201836145U (en) * | 2010-10-09 | 2011-05-18 | 三一重工股份有限公司 | Self-adaptive hydraulic driving device for engineering machinery |
| CN202220656U (en) * | 2011-09-01 | 2012-05-16 | 何东海 | Hydraulically driven electric generating set |
| CN102814244A (en) * | 2012-07-31 | 2012-12-12 | 天圣环保工程（成都）有限公司 | Full hydraulic drive differential horizontal screw centrifuge |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20141029 |