CN106568583B - A kind of aircraft main landing gear can holding bar deflection metrology device and its method - Google Patents
A kind of aircraft main landing gear can holding bar deflection metrology device and its method Download PDFInfo
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- CN106568583B CN106568583B CN201510658887.8A CN201510658887A CN106568583B CN 106568583 B CN106568583 B CN 106568583B CN 201510658887 A CN201510658887 A CN 201510658887A CN 106568583 B CN106568583 B CN 106568583B
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Abstract
The invention belongs to aircraft manufacturing technology, being related to can holding bar deflection metrology device and measurement method in a kind of aircraft main landing gear installation.Measuring appliance of the invention includes the first nipple [01], flexible handle [02], gland [03], sunk screw [04], measurement main body [05], measurement connector [06], measurement column [07], wirerope [08], label, the second nipple [09]；When solving aircraft main landing gear mounting and adjusting using deflection metrology device can holding bar deflection value measurement, when being effectively ensured aircraft main landing gear mounting and adjusting can holding bar deflection value accuracy requirement, solves the major issue in undercarriage installation process, it is ensured that the installation of undercarriage.Measuring appliance is easy to use, securely and reliably, calculates simply, improves installation effectiveness.
Description
Technical field
The invention belongs to aircraft manufacturing technology, being related in a kind of aircraft main landing gear installation can the measurement of holding bar deflection value
Technological equipment and measurement method.
Background technique
Main landing gear is the main fulcrum of aircraft, and left and right landing gear structure is identical, certain each main landing gear of type machine is respectively mounted four
A brake machine wheel.Be made of following main member: retractable actuating cylinder, damper leg, it is locking can holding bar, wheel group, stablize it is slow
Rush device etc..Wherein, it is locking can holding bar be subject to the load-carrying member of load in aircraft landing and starting heats, by upper Universal connector
Head, strut, middle universal joint, triangle inclined strut, band tooth plate connector, band idler wheel tooth plate support arm, unlocking retractable actuating cylinder and bottom
The components such as latch mechanism composition.Downlock mechanism is made of spring pressurized strut, adjustable extension arm, spring, lock rocker arm etc..It is locking can holding
Bar is due to having upward 4.5+0.8 -0.5The amount of deflection of mm, the additional load that the adjustable extension arm in downlock mechanism can generate thus amount of deflection
It is transmitted on damper leg outer cylinder.It is locking can holding bar by two holes with bronze bushing of triangle inclined strut, be hinged on slow
Rush on the shaft shoulder of pillar outer cylinder center contact, thus make lateral load on main landing gear by it is locking can holding bar, be transmitted to
Fuselage gets on.It is locking can holding bar upward 4.5+0.8 -0.5The amount of deflection of mm is a critical data of main landing gear design, installation
Precision directly influence undercarriage using safe.
Summary of the invention
The object of the present invention is to provide it is a kind of can rapid survey aircraft main landing gear can holding bar deflection value technique dress
It is standby.
In addition, the present invention also provides a kind of aircraft main landing gear can holding bar deflection value measurement process.
Technical solution of the present invention: a kind of aircraft main landing gear can holding bar deflection metrology device；The measuring appliance includes the
One nipple [01], flexible handle [02], gland [03], sunk screw [04], measurement main body [05], measurement connector [06],
Measurement column [07], wirerope [08], label, the second nipple [09]；Wherein, first nipple [01] passes through gland
[03] and sunk screw [04] is mounted in measurement main body [05], and two flexible handles [02] are separately mounted to the first nipple
[01] and in the hole of the second nipple [09] end, the second nipple [09] is by the opening in measurement main body [05] and flies
Owner's undercarriage can the stud on holding lever lock rocker arm connect firmly.Label [] is riveted on main body by cup head aluminium rivet [11]
[05] on caliber outer surface.
The measurement main body [05] include fixed ear base [05-01], measurement supervisor [05-02], measurement ear mount [05-03],
Fixation fork ear [05-04] and two reference blocks [05-05]；The material of measurement main body [05] is 45# steel；The fixation
Ear mount [05-01] is welded on the left upper part of measurement supervisor [05-02], and fixation fork ear [05-04] is welded on measurement supervisor [05-
02] right end top, measurement ear mount [05-03] are welded at the position to the right of measurement supervisor [05-02] middle part, two reference blocks
[05-05] is respectively welded at measurement supervisor both ends lower part [05-02].For guaranteeing the essence of measurement main body upper installing hole and mounting surface
Degree.
The first nipple [01] being adjusted in place is fixed on measurement master by gland [03] by the sunk screw [04]
On body [05].
Second nipple [09] can holding with aircraft main landing gear by the opening in measurement main body [05]
Stud on lever lock rocker arm connects firmly, facilitate its with aircraft main landing gear can holding bar connect firmly.
Measurement connector [06] can be mounted on aircraft main landing gear can be on the stud of holding bar triangle inclined strut, measurement
Column [7] is inserted into the through-hole of measurement ear mount [05-03].Measurement column [07] can cooperate with measurement connector [06] and make
To carry out the measurement of deflection value.
The label is riveted on the caliber outer surface of measurement supervisor [05-02] with cup head aluminium rivet [11], label pair
Amount of deflection value measurement method is illustrated.
The measurement column [07] and the second nipple [09] fasten knot with wirerope [08] respectively and are responsible for [05-02] in measurement
On, with anti-lost.
A kind of survey aircraft main landing gear can holding bar deflection value method, using as described in one of claim 1-5
A kind of aircraft main landing gear can holding bar deflection metrology device, it is characterised in that includes the following steps:
Step 1: by can holding bar deflection metrology device measurement connector [06] be mounted on aircraft main landing gear can holding bar three
On the stud of angle inclined strut；
Step 2: by main landing gear can holding bar deflection metrology device the first nipple [01] and the second nipple
[09] end face universal joint and can lock the faying face of rocker arm and be bonded on holding bar with aircraft main landing gear respectively；
Step 3: by the first nipple [01] and undercarriage can the stud of upper universal joint of holding bar connect
It connects, by the second nipple [09], the opening of fixation fork ear [05-04] and aircraft main landing gear can in measurement main body [05]
Stud on holding lever lock rocker arm connects firmly；
Step 4: measurement ear mount [05-03] through-hole in insertion measurement column [07] in place, measurement measurement connector [06] with
Size is extended out between measurement column [07], extending out dimensional units is millimeter；
Step 5: by Deflection Formula and the contour dimension obtain can holding bar deflection value, the amount of deflection
Calculation formula are as follows: deflection value=extend out size -50mm.
Beneficial effects of the present invention: when solving aircraft main landing gear mounting and adjusting using deflection metrology device can holding bar scratch
The measurement of angle value, when being effectively ensured aircraft main landing gear mounting and adjusting can holding bar deflection value accuracy requirement, solve winged
Major issue in machine undercarriage installation process, it is ensured that the installation of undercarriage.Measuring appliance is easy to use, securely and reliably, calculates letter
It is single, improve installation effectiveness.
Detailed description of the invention
Fig. 1 is that the left main landing gear of aircraft can holding bar deflection metrology working state schematic representation；
Fig. 2 is measurement partial structure diagram；
Fig. 3 is measurement main structure top view；
Fig. 4 is measurement main structure side view；
Wherein: the first nipple of 01-, 02- flexible handle, 03- gland, 04- sunk screw, 05- measure main body, 06-
Measure connector, 07- measurement column, 08- wirerope, the second nipple of 09-, 05-01- fixed ear base, 05-02- measurement supervisor,
05-03- measures ear mount, 05-04- fixation fork ear, 05-05- reference block.
Specific embodiment
Below in conjunction with attached drawing, present invention is further described in detail with specific example:
Aircraft main landing gear of the present invention can holding bar deflection value measurement technological equipment using certain model transporter as platform,
By the first nipple [01], flexible handle [02], gland [03], sunk screw [04], measurement main body [05], measurement connector
[06], measurement column [07], wirerope [08], label, the second nipple [09] and cup head aluminium rivet.
Referring to Fig. 1, its be the left main landing gear of aircraft can holding bar deflection metrology working state schematic representation, starboard main landing gear
Can holding bar deflection metrology working condition corresponding thereto.The measurement connector of the deflection metrology device is mounted on aircraft main landing gear can
On the stud of holding bar triangle inclined strut, the first nipple is mounted in measurement main body by gland with sunk screw, and
Aircraft main landing gear the stud of universal joint can connect firmly on holding bar；Second nipple by measurement main body on opening and
Aircraft main landing gear can the stud on holding lever lock rocker arm connect firmly.Measuring appliance and main landing gear can be after holding bar install, survey
It measures in column insertion measurement main body, measurement column and measurement connector are with the use of the measurement for carrying out deflection value.
Referring to Fig. 2, it is measurement partial structure diagram.The part reflects the structure size of measurement part, measurement
Column and measurement connector with the use of carry out can holding bar amount of deflection measurement.
Fig. 3,4 are please referred to, is measurement agent structure schematic diagram, the measurement main body is by fixed ear base, measurement supervisor, measurement
Ear mount, fixation fork ear and five part group of reference block are welded, and the annealed elimination stress of postwelding roughing is finished again.Figure
Middle reflection dependency structure size and location precision.The main position and the depth of parallelism mutual using the face benchmark B, the face C, the face D, three
Locate the verticality of connecting hole and datum level, the concentricity of connecting hole axis of symmetry is all important technical parameter at three.
Be given below aircraft main landing gear of the present invention can the measurement of holding bar deflection value method, process is as follows:
Step 1: by can holding bar deflection metrology device measurement connector [06] be mounted on aircraft main landing gear can holding bar three
On the stud of angle inclined strut.
Step 2: by main landing gear can holding bar deflection metrology device the first nipple [01], the second nipple [09]
End face is respectively and can universal joint on holding bar, faying face fitting at lock rocker arm with aircraft main landing gear.
Step 3: with the first nipple [01] and undercarriage can the upper universal joint stud of holding bar connected
It connects, it can by the opening and aircraft main landing gear of fixation fork ear [05-04] in measurement main body [05] with the second nipple [09]
Stud on holding lever lock rocker arm connects firmly.
Step 4: being inserted into measurement column [07] in measurement hole ear mount [05-03], can be rolled over connecting firmly in aircraft main landing gear
Measurement connector [06] on the stud of strut triangle inclined strut is with the use of the measurement for carrying out deflection value.
Step 5: according to measurement result subtract 50 can calculate can holding bar existing deflection value.
Step 6: if not meeting upward 4.5+0.8 -0.5The deflection value of mm need to be adjusted with the tooth adjustment band rolling on tooth plate connector
The length of tooth plate support arm is taken turns, to guarantee the technical requirements of undercarriage installation.
The present invention using measurement tooling carry out aircraft main landing gear can holding bar deflection value measurement when, first deflection metrology
The measurement column of device is mounted on aircraft main landing gear can be on the stud of holding bar triangle inclined strut, then the screw thread of deflection metrology device
Connector and main landing gear can holding bar connect firmly, then can be carried out survey calculation.After the present invention puts into production use, substantially drop
The difficulty of low undercarriage installation, it is easy to use and reliable, installation effectiveness is improved, undercarriage mounting technique has been effectively ensured
It is required that having biggish practical application value.
Claims (5)
1. a kind of aircraft main landing gear can holding bar deflection metrology device, the measuring appliance include the first nipple (01), activity
Handle (02), gland (03), sunk screw (04), measurement main body (05), measurement connector (06), measurement column (07), wirerope
(08), label, the second nipple (09)；Wherein, first nipple (01) passes through gland (03) and sunk screw
(04) it is mounted in measurement main body (05), two flexible handles (02) are separately mounted to the first nipple (01) and the second screw thread
In the hole of connector (09) end, the second nipple (09) by measurement main body (05) on opening and aircraft main landing gear can roll over
Stud on strut lock rocker arm connects firmly；Label is riveted on the caliber outer surface of main body (05) by cup head aluminium rivet (11)；
The measurement main body (05) includes fixed ear base (05-01), measurement supervisor (05-02), measurement ear mount (05-03), fixes
Pitch ear (05-04) and two reference blocks (05-05)；The fixed ear base (05-01) is welded on measurement supervisor's (05-02)
Left upper part, fixation fork ear (05-04) are welded on the right end top of measurement supervisor (05-02), and measurement ear mount (05-03) is welded on
At the position to the right of measurement supervisor (05-02) middle part, two reference blocks (05-05) are respectively welded at measurement supervisor both ends (05-02)
Lower part, for guaranteeing the precision of measurement main body upper installing hole and mounting surface；
The first nipple (01) being adjusted in place is fixed on measurement main body by gland (03) by the sunk screw (04)
(05) on；
Second nipple (09) can holding lever lock with aircraft main landing gear by the opening in measurement main body (05)
Stud on rocker arm connects firmly, facilitate its with aircraft main landing gear can holding bar connect firmly；
Measurement connector (06) can be mounted on aircraft main landing gear can be on the stud of holding bar triangle inclined strut, measurement column
(07) it is mountable in the through-hole of measurement ear mount (05-03).
2. aircraft main landing gear according to claim 1 can holding bar deflection metrology device, it is characterised in that: the measurement master
Body (05) is 45# steel weldment.
3. aircraft main landing gear according to claim 1 can holding bar deflection metrology device, it is characterised in that: the label is used
Cup head aluminium rivet (11) is riveted on the caliber outer surface of measurement supervisor (05-02).
4. aircraft main landing gear according to claim 1 can holding bar deflection metrology device, it is characterised in that: in non-measured shape
Under state, the measurement column (07) and the second nipple (09) fasten knot on measurement supervisor (05-02) with wirerope (08) respectively.
5. a kind of survey aircraft main landing gear can holding bar deflection value method, use one as described in one of claim 1-4
Kind of aircraft main landing gear can holding bar deflection metrology device, it is characterised in that includes the following steps:
Step 1: by can holding bar deflection metrology device measurement connector (06) be mounted on aircraft main landing gear can holding bar triangular aslant
On the stud of pillar；
Step 2: by main landing gear can holding bar deflection metrology device the first nipple (01) and the second nipple (09)
End face universal joint and can lock the faying face of rocker arm and be bonded on holding bar with aircraft main landing gear respectively；
Step 3: by the first nipple (01) and undercarriage can the stud of upper universal joint of holding bar be attached, will
The opening of fixation fork ear (05-04) and aircraft main landing gear can holding bars in measurement main body (05) for second nipple (09)
Stud on lock rocker arm connects firmly；
Step 4: in place, measurement measures connector (06) and measurement for insertion measurement column (07) in the through-hole of measurement ear mount (05-03)
Contour dimension between column (07), contour dimension unit are millimeter；
Step 5: by Deflection Formula and the contour dimension obtain can holding bar deflection value, the amount of deflection calculates
Formula are as follows: deflection value=contour dimension -50mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510658887.8A CN106568583B (en) | 2015-10-10 | 2015-10-10 | A kind of aircraft main landing gear can holding bar deflection metrology device and its method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510658887.8A CN106568583B (en) | 2015-10-10 | 2015-10-10 | A kind of aircraft main landing gear can holding bar deflection metrology device and its method |
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| Publication Number | Publication Date |
|---|---|
| CN106568583A CN106568583A (en) | 2017-04-19 |
| CN106568583B true CN106568583B (en) | 2019-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510658887.8A Active CN106568583B (en) | 2015-10-10 | 2015-10-10 | A kind of aircraft main landing gear can holding bar deflection metrology device and its method |
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| CN107356405B (en) * | 2017-07-25 | 2019-02-15 | 厦门大学 | A kind of combined type positioning installation apparatus of wind tunnel test model aircraft |
| CN109374243B (en) * | 2018-11-18 | 2024-02-02 | 中航天水飞机工业有限责任公司 | Mechanism deflection value measurer |
| CN111272049B (en) * | 2020-03-31 | 2021-04-27 | 成都飞机工业（集团）有限责任公司 | Method for measuring eccentricity of stay bar |
| CN113071660A (en) * | 2021-04-08 | 2021-07-06 | 北京北摩高科摩擦材料股份有限公司 | Main landing gear of airplane |
| CN113405748B (en) * | 2021-05-14 | 2023-11-21 | 陕西飞机工业有限责任公司 | Device and method for measuring deflection of cabin door of airplane |
| CN114184340B (en) * | 2021-12-10 | 2024-07-16 | 凌云科技集团有限责任公司 | Method and platform for measuring deflection of strut of undercarriage |
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|---|---|---|---|---|
| FR2800704A1 (en) * | 1999-11-10 | 2001-05-11 | Messier Dowty Sa | Aircraft landing gear for underwing use has stiffening actuator to allow flexibility except in deployment phase |
| CN102183364B (en) * | 2011-03-02 | 2012-06-27 | 北京工研精机股份有限公司 | Platform for testing performance of main shaft of machine tool |
| CN202661264U (en) * | 2012-07-13 | 2013-01-09 | 中钢集团郑州金属制品研究院有限公司 | Portable coal mine narrow-gauge vehicle connector measuring device |
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2015
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2800704A1 (en) * | 1999-11-10 | 2001-05-11 | Messier Dowty Sa | Aircraft landing gear for underwing use has stiffening actuator to allow flexibility except in deployment phase |
| CN102183364B (en) * | 2011-03-02 | 2012-06-27 | 北京工研精机股份有限公司 | Platform for testing performance of main shaft of machine tool |
| CN202661264U (en) * | 2012-07-13 | 2013-01-09 | 中钢集团郑州金属制品研究院有限公司 | Portable coal mine narrow-gauge vehicle connector measuring device |
Non-Patent Citations (1)
| Title |
|---|
| 直升机主起落架疲劳试验技术研究;刘明等;《直升机技术》;20131231(第1期);全文 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
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