CN109612524A - A kind of undercarriage oil-gas type buffer filling quantity monitoring method - Google Patents
A kind of undercarriage oil-gas type buffer filling quantity monitoring method Download PDFInfo
- Publication number
- CN109612524A CN109612524A CN201811500591.3A CN201811500591A CN109612524A CN 109612524 A CN109612524 A CN 109612524A CN 201811500591 A CN201811500591 A CN 201811500591A CN 109612524 A CN109612524 A CN 109612524A
- Authority
- CN
- China
- Prior art keywords
- buffer
- undercarriage
- oil
- temperature
- monitoring method
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
A kind of undercarriage oil-gas type buffer filling quantity monitoring method, temperature and pressure transmitter (2) are installed on undercarriage buffer (1), temperature and pressure transmitter (2) inner cavity and undercarriage buffer (1) inner cavity connection, and it is sealed in isolation, measure undercarriage buffer (1) inner cavity temperature and pressure, and undercarriage buffer (1) decrement, acquisition need makeup oil liquid measure.Buffer oil liquid supplement precision can be improved in the present invention, reduces landing gear maintenance workload, improves takeoff and landing safety.
Description
Technical field
The invention belongs to aircraft landing gears to monitor field, and in particular to a kind of undercarriage oil-gas type buffer fills
Fill out quantity monitoring method.
Background technique
Undercarriage oil gas bumper is aircraft in the dedicated dress of absorption road face impact energy during race that takes off, lands, slides
It sets.Buffer works under big load, harsh environmental conditions for a long time, oil and gas leakage such as occurs, will make undercarriage cushion performance
Decline, or even failure, cause a hidden trouble to aircraft safety.
To prevent trouble before it happens, flight-line service personnel need to periodically measure the operations such as supplement air pressure, supplement oil liquid.Currently,
It measures air pressure and uses mechanical compression table, which need to open buffer inner cavity and draw inner chamber gas, unavoidably generate pressure
Table damage, influences measurement accuracy；Buffer inner cavity oil liquid amount is then unable to measure, and is needed according to experience is made, periodically quantitative supplement.
Summary of the invention
Goal of the invention
It proposes a kind of oil-gas type buffer filling quantity monitoring method, solves the problems, such as measurement pressure gauge damage, improve measurement accuracy；
Solve the problems, such as that buffer inner cavity oil liquid is unable to measure, to realize real-time monitoring, maintenance on demand.
Technical solution
A kind of undercarriage oil-gas type buffer filling quantity monitoring method, installs temperature pressure on undercarriage buffer 1
Force snesor 2,2 inner cavity of temperature and pressure transmitter and 1 inner cavity connection of undercarriage buffer, and sealed in isolation, it measures
1 inner cavity temperature and pressure of frame buffer and 1 decrement of undercarriage buffer are fallen, acquisition needs makeup oil liquid measure.
A kind of undercarriage oil-gas type buffer fills quantity monitoring method, first survey aircraft tire liftoff shape
1 chamber pressure P1 of undercarriage buffer, temperature T1 and 1 decrement S1 of undercarriage buffer when state.
A kind of undercarriage oil-gas type buffer fills quantity monitoring method, it is also necessary to survey aircraft shutdown status
When 1 chamber pressure P2 of undercarriage buffer, temperature T2 and 1 decrement S2. of undercarriage buffer
A kind of undercarriage oil-gas type buffer fills quantity monitoring method:
It measures after numerical value according to formula (1)~(4)
Δ V=V1-V2………………………………(2)
Δ V=(S1-S2)·A……………………………(3)
Voil=V1-V0………………………………(4)
It pushes over and obtains formula (5)
Wherein: A is buffering piston rod area；
△ V is that buffer compression causes cavity volume variable quantity；
V0 is buffer factory air cavity volume；
Voil is to need makeup oil liquid measure；
Beneficial effect
It improves buffer oil liquid and supplements precision, reduce landing gear maintenance workload, improve takeoff and landing safety.
Detailed description of the invention
Fig. 1: state that aero tyre is liftoff；
Fig. 2: aircraft shutdown status.
Specific embodiment
Temperature and pressure transmitter (2) are installed on undercarriage buffer (1), temperature and pressure transmitter (2) inner cavity and buffering
Device (1) inner cavity connection, and sealed in isolation.
Buffer chamber pressure P1, temperature T1 are measured by temperature and pressure transmitter in aero tyre liftoff state, with card
Ruler measures S1 (measuring basis can be selected according to specific structure).It is measured and is buffered by temperature and pressure transmitter in aircraft shutdown status
Device chamber pressure P2, temperature T2, with calliper to measure S2, (measuring basis can be selected according to specific structure, but should keep one in S1
It causes).
The pressure value that buffer chamber pressure P1 as needs to monitor, can be calculated according to formula (5) needs makeup oil
Liquid measure Voil。
According to formula (1)~(4)
Δ V=V1-V2………………………………(2)
Δ V=(S1-S2)·A………………………………(3)
Voil=V1-V0………………………………(4)
Note: A is buffering piston rod area；
△ V is that buffer compression causes cavity volume variable quantity；
V0 is buffer factory air cavity volume；
Voil is to need makeup oil liquid measure；
Buffer chamber pressure P1, P2, temperature T1, T2 are measurement value sensor；
Decrement S1, S2 can be externally measured from buffer by ruler.
It can obtain formula (5)
Claims (4)
1. a kind of undercarriage oil-gas type buffer fills quantity monitoring method, which is characterized in that on undercarriage buffer (1)
It installs temperature and pressure transmitter (2), temperature and pressure transmitter (2) inner cavity and undercarriage buffer (1) inner cavity connection, and in the external world
Isolation sealing, measures undercarriage buffer (1) inner cavity temperature and pressure and undercarriage buffer (1) decrement, and acquisition needs to mend
Oil-filled liquid measure.
2. a kind of undercarriage oil-gas type buffer according to claim 1 fills quantity monitoring method, which is characterized in that
First survey aircraft tire liftoff state when undercarriage buffer (1) chamber pressure P1, temperature T1 and undercarriage buffer
(1) decrement S1.
3. a kind of undercarriage oil-gas type buffer according to claim 2 fills quantity monitoring method, which is characterized in that
Also need undercarriage buffer (1) chamber pressure P2, temperature T2 and the undercarriage buffer when survey aircraft shutdown status
(1) decrement S2.
4. a kind of undercarriage oil-gas type buffer according to claim 3 fills quantity monitoring method, it is characterised in that:
It measures after numerical value according to formula (1)~(4)
Δ V=V1-V2………………………………(2)
Δ V=(S1-S2)·A……………………………(3)
Voil=V1-V0………………………………(4)
It pushes over and obtains formula (5)
Wherein: A is buffering piston rod area；
△ V is that buffer compression causes cavity volume variable quantity；
V0 is buffer factory air cavity volume；
Voil is to need makeup oil liquid measure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811500591.3A CN109612524A (en) | 2018-12-07 | 2018-12-07 | A kind of undercarriage oil-gas type buffer filling quantity monitoring method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811500591.3A CN109612524A (en) | 2018-12-07 | 2018-12-07 | A kind of undercarriage oil-gas type buffer filling quantity monitoring method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109612524A true CN109612524A (en) | 2019-04-12 |
Family
ID=66007949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811500591.3A Pending CN109612524A (en) | 2018-12-07 | 2018-12-07 | A kind of undercarriage oil-gas type buffer filling quantity monitoring method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109612524A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111257163A (en) * | 2020-02-28 | 2020-06-09 | 南京航空航天大学 | Aircraft landing gear buffer oil liquid gas solubility test device and test method thereof |
| CN112683516A (en) * | 2021-01-13 | 2021-04-20 | 中国商用飞机有限责任公司 | Method and device for monitoring fluid content of shock absorption strut of undercarriage |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120053783A1 (en) * | 2010-08-31 | 2012-03-01 | Nance C Kirk | Automated inspection of aircraft landing gear internal fluid levels |
| CN102494073A (en) * | 2011-11-16 | 2012-06-13 | 南京航空航天大学 | Undercarriage buffer |
| CN104239608A (en) * | 2014-08-26 | 2014-12-24 | 中国直升机设计研究所 | Non-linear dynamics modeling method for undercarriage buffer |
| CN108216589A (en) * | 2017-12-15 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of undercarriage leg contracting mechanism |
| CN108254121A (en) * | 2017-12-14 | 2018-07-06 | 中国航空工业集团公司成都飞机设计研究所 | Inflation valve with temperature and pressure detection function |
| CN108444573A (en) * | 2018-05-29 | 2018-08-24 | 大连民族大学 | Vehicle fuel the measurement and calibration system |
-
2018
- 2018-12-07 CN CN201811500591.3A patent/CN109612524A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120053783A1 (en) * | 2010-08-31 | 2012-03-01 | Nance C Kirk | Automated inspection of aircraft landing gear internal fluid levels |
| CN102494073A (en) * | 2011-11-16 | 2012-06-13 | 南京航空航天大学 | Undercarriage buffer |
| CN104239608A (en) * | 2014-08-26 | 2014-12-24 | 中国直升机设计研究所 | Non-linear dynamics modeling method for undercarriage buffer |
| CN108254121A (en) * | 2017-12-14 | 2018-07-06 | 中国航空工业集团公司成都飞机设计研究所 | Inflation valve with temperature and pressure detection function |
| CN108216589A (en) * | 2017-12-15 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of undercarriage leg contracting mechanism |
| CN108444573A (en) * | 2018-05-29 | 2018-08-24 | 大连民族大学 | Vehicle fuel the measurement and calibration system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111257163A (en) * | 2020-02-28 | 2020-06-09 | 南京航空航天大学 | Aircraft landing gear buffer oil liquid gas solubility test device and test method thereof |
| CN112683516A (en) * | 2021-01-13 | 2021-04-20 | 中国商用飞机有限责任公司 | Method and device for monitoring fluid content of shock absorption strut of undercarriage |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9285007B2 (en) | Servicing monitoring system for mixed fluid-gas shock struts | |
| US9045237B2 (en) | Automated inspection of aircraft landing gear internal fluid levels | |
| EP3428475B1 (en) | Dual-stage, stroke-activated, mixed fluid gas shock strut servicing monitoring system | |
| EP2921404B1 (en) | Aircraft landing gear shock strut performance monitoring | |
| CN109612524A (en) | A kind of undercarriage oil-gas type buffer filling quantity monitoring method | |
| EP3424816B1 (en) | Dual-stage, separated gas/fluid shock strut servicing monitoring system using two pressure/temperature sensors | |
| CN104535243A (en) | Reciprocating seal experiment table for measuring friction feature of single seal ring | |
| EP4209769A1 (en) | Shock strut service monitoring using gas pressure and temperature sensors, combined with physical strut measurement and taking into account gas absorption/desorption in a fluid | |
| EP3379227A1 (en) | Dual-stage, pressure-activated, mixed fluid gas shock strut servicing monitoring system | |
| EP3693717A1 (en) | Shock strut service monitoring using sensors and physical strut measurement | |
| CN204214583U (en) | Brake torque measurement mechanism in aircraft taxi wheels-locked testing | |
| CN106353043A (en) | Seal performance test device of airplane landing gear buffer | |
| CN109580120B (en) | Monitoring method for aircraft landing gear buffer | |
| EP3722775A2 (en) | Dual stage stroke activated shock strut service monitoring using sensors and physical strut measurement | |
| CN201177541Y (en) | Force-measuring device | |
| CN103471504B (en) | The measuring method of a kind of hole of hydraulic torque converter fitted position and device | |
| CN205209454U (en) | Experimental device for detect hydro -cylinder sensor performance | |
| CN104237019B (en) | Coal mine dynamic disaster Multi-parameter coupling determinator | |
| CN207621006U (en) | Metering adjusts novel hydraulic oil rig | |
| CN212513449U (en) | Pressure monitoring valve for coal mine paste filling | |
| CN204008318U (en) | Colliery dynamic disaster Multi-parameter coupling determinator | |
| CN202250928U (en) | Axial force test instrument for pump | |
| CN105444658A (en) | Hydro-generator coupling bolt elongation value measurement technique | |
| CN104155040B (en) | A kind of airplane Hydraulic Tube dynamic stress rest decision method | |
| CN104482105B (en) | Undercarriage damper leg high low pressure chamber charger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190412 |