CN201696394U - High-pressure hydraulic pulse test system for aircraft - Google Patents
High-pressure hydraulic pulse test system for aircraft Download PDFInfo
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- CN201696394U CN201696394U CN2010202147544U CN201020214754U CN201696394U CN 201696394 U CN201696394 U CN 201696394U CN 2010202147544 U CN2010202147544 U CN 2010202147544U CN 201020214754 U CN201020214754 U CN 201020214754U CN 201696394 U CN201696394 U CN 201696394U
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Abstract
The utility model provides a high-pressure hydraulic pulse test system for an aircraft. A high-pressure internal gear pump provides high-pressure fluid flow for the system under the dragging of a dragging motor; a computer outputs the control signal for a proportional flow servo valve and a proportional pressure servo valve to control the hydraulic system to generate stable and controlled high-pressure hydraulic incoming flow; and a piezoelectric ceramic driver controlled by the computer generates the exciting force to push a metal diaphragm to generate the accurate and controlled pressure pulse value in the stable high-pressure hydraulic incoming flow. The utility model has the advantages of high accuracy, simple and convenient operation, large flow rate and pressure adjusting range, wide controlled frequency range, quick response and simple structure; in addition, the interference on the controlled pressure pulse part is small.
Description
Technical field
The utility model relates to a kind of hydraulic pulsation test system, is applicable to aircraft high-pressure hydraulic pressure pulsation test.
Background technique
Along with aviation technical quick development, every technical order of aircraft hydraulic system all needs corresponding raising.Hydraulic system pressure improves constantly with the development of hydraulics always.With regard to driving force and acting, high pressure means the size that can reduce dynamical element, thereby can alleviate the structure weight of hydraulic system.It should be noted that the every minimizing of hydraulics weight 1kg, can make aircaft configuration weight saving 4kg, and the aircraft bearing capacity can increase 15kg.On the development trend of following aircraft, aircraft is just day by day to high speed and large scale development, and this just requires and must constantly increase system power, alleviates the dynamic response of structure weight and improvement system.Therefore, the aircraft hydraulic system must adopt higher pressure.The various countries particularly best approach that alleviates the aircraft hydraulic system weight and dwindle its volume that studies show that in a large number of USA in recent years are to improve the working pressure of aircraft hydraulic system; during high-pressure hydraulic work; because the unexpected switch of valve; reasons such as the inefficacy of pump and executive component stop; to produce the pressure pulse wave of propagating along pipeline in the pipeline; strong pressure collision can appear in voltage supply pipeline and return line; be pressure pulsation; on pressure duct; the pressure pulsation peak value might reach more than 1.5 times of system's rated pressure, then may reach more than 10 times of normal return pressure value on the return line.High-pressure hydraulic pressure pulsation may cause the fracture of system pipeline, link, pressurized strut etc., and system attachment is malfunctioning, can cause the generation of aircraft major accident when serious.Since the hydraulic system pressure height, factors such as the easy leakage of annex processing precise and fluid, failure ratio is more, and wherein most of fault is directly related with the pressure pulsation of hydraulic system.The pressure pulsation of aircraft hydraulic system is the fatal harm that influences aircraft security, so the pipeline of hydraulic system and annex must carry out the pressure pulsation test, to test the ability of its compressive resistance pulsatile impact, improve design thereby pinpoint the problems, improve the reliability of aircraft hydraulic system.
At present, with regard to the document of publishing, still do not introduce the testing apparatus of aircraft high-pressure and hydraulic impulse test, disclosed most hydraulic impulse testing apparatus all differs far away with aircraft high-pressure hydraulic real work situation, the patent No. for hydraulic impulse fatigue device in the pipeline of ZL 200920038289.0 by pneuamtic part, electric control equipment be immersed in air bag in the liquid and come to provide pulse hydraulic fatigue test in a kind of pipeline that can simulate hydraulic impulse for the stainless steel thin-wall bellows; The patent No. is that 95219594.1 hydraulic pulsation pressure generator is mainly used in various fatigue strength or the vibration test, for some equipment provide pulse signal, form by pulsation deceleration loading device, hydraulic station, driving mechanism and actuator, the special way deceleration loading device that is to pulse is the rotatable selector valve of spool, driving machine drives the changeover valve core rotation, the oil cylinder filler opening is alternately communicated into and out of hydraulic fluid port with selector valve, change oil cylinder working-pressure and promote piston in system, to produce pressure pulsation, its piston return relies on system pressure to realize that frequency response is lower.The hydraulic pressure of active service aircraft hydraulic system is generally in 21Mpa and 28Mpa and above level at present, the pressure pulsation frequency is higher, by relay control pressurize and pressure release time, by air compressor and various valve the state of air bag is controlled to produce the pilot system of hydraulic impulse, its hydraulic pressure level and pulse control accuracy are all lower, and it is lower by changing oil cylinder working-pressure promotion piston with its response frequency of hydraulic pulsation pressure generator that in system, produces pressure pulsation, the control accuracy deficiency, all can't satisfy the test requirements document of aircraft high-pressure hydraulic, must seek a kind of degree of precision that has, control easy, the hydraulic impulse pilot system that is fit to aircraft high-pressure hydraulic real work situation is improved design to pinpoint the problems.
Summary of the invention
In order to overcome the lower deficiency of prior art response frequency and control accuracy, the utility model proposes a kind of high-pressure and hydraulic pulsation test system of aircraft, structure is simple relatively, can raise the efficiency preferably, carries out aircraft and other system high pressure hydraulic pulsation system tests accurately.
The technological scheme that its technical problem that solves the utility model adopts is: comprise hydraulic part and observing and controlling part.Hydraulic part comprises high pressure crescent gear pump, thick oil purifier, accumulator, dragging motor, one-way valve, ratio pressure servovalve, ratio flow servovalve, smart oil purifier, pressure relay, cooler, throttle valve and pulsation generation device; Observing and controlling partly comprises computer, pressure transducer and the flow transducer that contains the D/A card.
Described hydraulic part is mainly device high-tension pulse hydrodynamic stream is provided, and observing and controlling partly guarantees to provide for device the control command of required a certain amount of high pressure liquid stream.Dragging motor is the system dynamic source in the hydraulic part; Liquid stream flows into the high pressure crescent gear pump by fuel tank after thick oil purifier filters, the high pressure crescent gear pump provides high pressure liquid stream for system under the dragging of dragging motor; The pressure relay that is installed in high pressure inside engaged gear pump discharge is monitored the pressure of described high pressure liquid stream, when the flow stream pressure of system reaches the setting threshold values for a certain reason, in time cuts off the dragging motor power supply, guarantees security of system; The outlet port that one-way valve is installed in the high pressure crescent gear pump guarantees that liquid flows to the outer one-way flow of high pressure crescent gear pump, and the realization system isolates; The one-way valve outlet connects smart oil purifier inlet, guarantees the cleaning of system liquid stream; Accumulator, ratio pressure servovalve and ratio flow servovalve all are connected with smart oil purifier outlet; Accumulator is used to stabilize high pressure inside engaged gear pump discharge fluid pulse; Ratio pressure servovalve and ratio flow servovalve are respectively under the control of computer, for liquid chunnel provides required force value and flow value; There is a flow transducer at liquid chunnel place between ratio flow servovalve and the pulsation generation device, is used for the real-time acquisition system flow value; The pulsation generation device comprises computer-controlled piezoelectric ceramic actuator and the metal diaphragm that is promoted by piezoelectric ceramic actuator, and metal diaphragm is welded on the liquid chunnel side, in order to produce the pressure pulsation composition in liquid stream; In the liquid chunnel of pulsation generation device both sides a pressure transducer is arranged respectively, be respectively applied for the system pressure value of real-time collection pulsation generation device both sides.Flow transducer and two pressure transducers are with the signal back computer that collects, and pressure and flow that the pulsation generation device is exported carry out calibration; The pulsation generation device connects test portion by liquid chunnel, applies high-voltage pulse to test portion; Liquid chunnel is flowed through and is connected cooler by throttle valve behind the test portion, and throttle valve is that liquid chunnel is set up required back pressure, and cooler is system's cooling, the long-time reliable operation of assurance system; Liquid stream is got back to system's fuel tank after being cooled off by cooler.
Described high pressure crescent gear pump is meant provides the crescent gear pump of pressure for 16-32Mpa liquid stream.
The smart oil purifier of described high pressure is meant that pressure is that 16-32Mpa, filter precision are 0.005 millimeter oil purifier.
Described metal diaphragm is welded on the liquid chunnel side, becomes the part of liquid chunnel, and its one side directly contacts with liquid stream, and another side links to each other with piezoelectric ceramic actuator, is promoted by piezoelectric ceramic actuator.
The beneficial effects of the utility model are: 1. control section is by computer control, and the precision height is easy and simple to handle; 2. provide the hydraulic part of high-tension pulse hydrodynamic stream, band flow feedback and pressure feedback, flow and the pressure regulation range is big, precision is high; 3. pressure pulsation is directly produced in the liquid stream by computer-controlled piezoelectric ceramic actuator promotion metal diaphragm, can realize the excitation of different wave different frequency, frequency range is wide, response is fast, simple in structure, its feedback is separate with the hydraulic part pressure feedback that high-tension pulse hydrodynamic stream is provided, the degree of regulation height; 4. the high pressure crescent gear pump combines with accumulator and can realize pressure output more stably, partly disturbs less to controlled pressure pulsation.
Below in conjunction with drawings and Examples the utility model is further specified.
Description of drawings
Figure is the utility model system architecture schematic representation.
Among the figure, 1-hydraulic oil container, the thick oil purifier of 2-, 3-high pressure crescent gear pump, 4-dragging motor, 5-pressure relay, the 6-one-way valve, the smart oil purifier of 7-, 8-accumulator, 9-ratio flow servovalve, 10-ratio pressure servovalve, 11-flutter generator (11-1-metal diaphragm, the 11-2-piezoelectric ceramic actuator), 12-test portion, 13-adjustable restrictive valve, the 14-cooler, 15-computer (containing the D/A card).
Embodiment
As shown be the utility model system architecture schematic representation, work fluid enters 3 superchargings of high pressure crescent gear pump by fuel tank 1 after thick oil purifier 2 filters, thick oil purifier 2 adopts simple in structure, the WU-63 that oil filling capacity is big * 80-J screen filter, with protection high pressure crescent gear pump, the high pressure crescent gear pump adopts duplex high pressure crescent gear pump QT43-31.5, maximum pressure 32Mpa, and flow is 42.2L/min when adopting 4 utmost point motors to drag; The pressure of high pressure liquid stream is by pressure relay 5 monitorings that are installed in high pressure inside engaged gear pump discharge, and the pressure relay model is JCS-02H, and maximum working (operation) pressure (MWP) is 40Mpa, and the pressure adjustment range is 0.6～40Mpa; 3 outlets of high pressure crescent gear pump link to each other with one-way valve 6 inlets, and one-way valve 6 goes into to adopt CRK2 type one-way valve, and maximum service pressure is 50Mpa, and maximum cracking pressure is 0.5Mpa, and peak rate of flow is 50L/min.One-way valve 6 outlets and smart oil purifier 7 inlets are connected, and smart oil purifier 7 adopts the good ZU-H63 * 5S high pressure paper type oil filter of filter precision, and its rated pressure is 31.5Mpa, and its reset pressure loss is not more than 0.1Mpa, Max pressure loss 0.35Mpa.Smart oil purifier 7 outlets are connected with accumulator 8, ratio flow servovalve 9 and ratio pressure servovalve 10 inlets, and accumulator 8 adopts the TBR50-2.5-E bag type accumulator, and its maximum service pressure is 34.5Mpa, and fluid displacement is 10L, and the leather bag material is that fluorine is as glue; Ratio flow servovalve 9 adopts KPG-03-63-31.5, and peak rate of flow is 63L/min, and pressure maximum is 31.5Mpa; Ratio pressure servovalve 10 adopts RZMO-TERS-PS-030/315, and latus rectum is 6mm, and peak rate of flow is 40L/min, and pressure maximum is 31.5Mpa.9 outlets of ratio flow servovalve have respectively one of turbine type flow sensor and high-tension resistive strain pressure transducer, and be connected with pulsation generation device 11 inlet by flow transducer, 11 outlets of pulsation generation device have one of high-tension resistive strain pressure transducer, test portion 12 is sent in liquid pulsation generation device 11 outlet of flowing through, test portion 12 outlets are connected with throttle valve 13 inlets, throttle valve 13 outlets connect cooler 14, cooler 14 adopts AH0608T-CA type forced air cooler, peak rate of flow is 60L/min, and working solution is flowed through and got back to fuel tank after cooler 14 cools off.Computer (containing the D/A card) 15 is by electrical signal control ratio flow servovalve 9, ratio pressure servovalve 10 and piezoelectric ceramic actuator 11-2, and two pressure transducers and a flow transducer constitute feedback loop with computer (containing the D/A card) 15 respectively.
After the system start-up, it is 10mm that the initial pressure of working solution stream can adopt latus rectum, pressure maximum is 32Mpa, peak rate of flow is that the throttle valve adjustment of 40L/min is set, computer (containing the D/A card) 15 outputs are given ratio flow servovalve and ratio pressure servovalve in order to the instruction electrical signal of control, feedback in conjunction with pressure transducer and flow transducer is implemented accurately control to the flow and the pressure of pulsation generation device inlet, and flow and force value are stabilized on the command value; Piezoelectric ceramic actuator in the pulsation generation device adopts lamination mechanical encapsulation formula high pressure piezoelectric ceramic actuator, it receives by computer (containing the D/A card) 15 command signals of sending, the designated displacement that produces under the controllable frequency promotes metal diaphragm 11-1, in system, produce the controllable pressure pulsation of size and frequency, this pressure pulsation value feeds back to computer by pulsation generation device 11 outlet pressure sensors and proofreaies and correct, main hydraulic channel feedback is separate with fluctuation pressure passage feedback, do not disturb mutually, to realize high control precision.
As mentioned above, by hydraulic pulsation test system design proposal of the present utility model, can when satisfying aircraft high-pressure hydraulic pulsation test requirements document, obtain high control precision, thereby improve test efficiency, lifting test performance.
Claims (4)
1. high-pressure and hydraulic pulsation test system of aircraft, comprise hydraulic part and observing and controlling part, hydraulic part comprises high pressure crescent gear pump, accumulator, dragging motor, one-way valve, ratio pressure servovalve, ratio flow servovalve, pressure relay, cooler, throttle valve and pulsation generation device; Observing and controlling partly comprises computer, pressure transducer and the flow transducer that contains the D/A card, it is characterized in that: described dragging motor is the system dynamic source; Liquid stream flows into the high pressure crescent gear pump by fuel tank after thick oil purifier filters, the high pressure crescent gear pump provides high pressure liquid stream for system under the dragging of dragging motor; The pressure relay that is installed in high pressure inside engaged gear pump discharge is monitored the pressure of described high pressure liquid stream; The outlet port that one-way valve is installed in the high pressure crescent gear pump guarantees that liquid flows to the outer one-way flow of high pressure crescent gear pump; The one-way valve outlet connects the smart oil purifier inlet of high pressure, and accumulator, ratio pressure servovalve and ratio flow servovalve all are connected with the smart oil purifier outlet of high pressure; Accumulator is used to stabilize high pressure inside engaged gear pump discharge fluid pulse; Under the control of computer, the control liquid chunnel provides required force value and flow value respectively for ratio pressure servovalve and ratio flow servovalve; There is one of flow transducer at liquid chunnel place between ratio flow servovalve and the pulsation generation device, is used for the real-time acquisition system flow value; The pulsation generation device comprises computer-controlled piezoelectric ceramic actuator and the metal diaphragm that is promoted by piezoelectric ceramic actuator, and metal diaphragm is welded on the liquid chunnel side, in order to produce the pressure pulsation composition in liquid stream; In the liquid chunnel of pulsation generation device both sides a pressure transducer is arranged respectively, be respectively applied for the system pressure value of real-time collection pulsation generation device both sides; Flow transducer and two pressure transducers carry out the signal back computer that collects flux modification and the pulsation generation device are carried out the pressure calibration the high pressure crescent gear pump respectively; The pulsation generation device connects test portion by liquid chunnel, applies high-pressure pulsating to test portion; Liquid chunnel is flowed through and is connected cooler by throttle valve behind the test portion, and throttle valve is that liquid chunnel is set up required back pressure, and cooler is system's cooling; Liquid stream is got back to system's fuel tank after being cooled off by cooler.
2. high-pressure and hydraulic pulsation test system of aircraft according to claim 1 is characterized in that: described high pressure crescent gear pump is meant the crescent gear pump that pressurised fluid stream between the 16-32Mpa is provided.
3. high-pressure and hydraulic pulsation test system of aircraft according to claim 1 is characterized in that: the smart oil purifier of described high pressure is meant that pressure is that 16-32Mpa, filter precision are 0.005 millimeter oil purifier.
4. high-pressure and hydraulic pulsation test system of aircraft according to claim 1 is characterized in that: described metal diaphragm one side directly contacts with liquid stream, and another side links to each other with piezoelectric ceramic actuator, is promoted by piezoelectric ceramic actuator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202147544U CN201696394U (en) | 2010-06-03 | 2010-06-03 | High-pressure hydraulic pulse test system for aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202147544U CN201696394U (en) | 2010-06-03 | 2010-06-03 | High-pressure hydraulic pulse test system for aircraft |
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| CN201696394U true CN201696394U (en) | 2011-01-05 |
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| CN2010202147544U Expired - Lifetime CN201696394U (en) | 2010-06-03 | 2010-06-03 | High-pressure hydraulic pulse test system for aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101881287A (en) * | 2010-06-03 | 2010-11-10 | 西北工业大学 | High-pressure and hydraulic pulsation test system of aircraft |
| CN102723432A (en) * | 2012-07-04 | 2012-10-10 | 陈�峰 | Piezoelectric driving device integrating resistor strain sheet-type sensor and manufacture method thereof |
| CN103644170A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Hydraulic low-pressure pulse experiment method of aircraft |
-
2010
- 2010-06-03 CN CN2010202147544U patent/CN201696394U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101881287A (en) * | 2010-06-03 | 2010-11-10 | 西北工业大学 | High-pressure and hydraulic pulsation test system of aircraft |
| CN101881287B (en) * | 2010-06-03 | 2012-09-05 | 西北工业大学 | High-pressure and hydraulic pulsation test system of aircraft |
| CN102723432A (en) * | 2012-07-04 | 2012-10-10 | 陈�峰 | Piezoelectric driving device integrating resistor strain sheet-type sensor and manufacture method thereof |
| CN102723432B (en) * | 2012-07-04 | 2013-12-25 | 陈�峰 | Piezoelectric driving device integrating resistor strain sheet-type sensor and manufacture method thereof |
| CN103644170A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Hydraulic low-pressure pulse experiment method of aircraft |
| CN103644170B (en) * | 2013-11-28 | 2016-05-11 | 江西洪都航空工业集团有限责任公司 | A kind of test method of airplane hydraulic pressure action of low-voltage pulse |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20110105 Effective date of abandoning: 20120905 |