CN106568583A - Foldable strut flexibility measurement device and method for airplane main undercarriage - Google Patents
Foldable strut flexibility measurement device and method for airplane main undercarriage Download PDFInfo
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- CN106568583A CN106568583A CN201510658887.8A CN201510658887A CN106568583A CN 106568583 A CN106568583 A CN 106568583A CN 201510658887 A CN201510658887 A CN 201510658887A CN 106568583 A CN106568583 A CN 106568583A
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- measurement
- landing gear
- holding bar
- nipple
- main landing
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Abstract
The invention belongs to the airplane manufacturing technology and relates to a foldable strut flexibility measurement device and method during airplane main undercarriage mounting. The measurement device comprises a first thread connector [1], a moving handle [02], a gland [03], a countersink screw [04], a main measurement body [05], a measurement connector [06], a measurement column [07], a steel rope [08], a label and a second thread connector [09]. Foldable strut flexibility measurement during airplane main undercarriage mounting and adjustment can be realized through employing the flexibility measurement device, precision requirements of a foldable strut flexibility value during airplane main undercarriage mounting and adjustment can be effectively guaranteed, a crucial problem in an airplane undercarriage mounting process is solved, and undercarriage mounting is guaranteed; the measurement device is convenient to use and is safe and reliable, calculation is simple, and mounting efficiency is improved.
Description
Technical field
The invention belongs to aircraft manufacturing technology, be related to during a kind of aircraft main landing gear is installed can the measurement of holding bar deflection value technique dress
Standby and measuring method.
Background technology
Main landing gear is the main fulcrum of aircraft, and left and right landing gear structure is identical, and certain type machine each main landing gear is respectively mounted four braking machines
Wheel.It is made up of following main member：Retractable actuating cylinder, damper leg, it is locking can holding bar, wheel group, stabilizing bumper etc..
Wherein, it is locking can holding bar be subject to the load-carrying member of load in aircraft landing and starting heats, its by upper universal joint, pole,
The structures such as middle universal joint, triangle inclined strut, band tooth plate joint, band roller tooth plate support arm, unlocking retractable actuating cylinder and downlock mechanism
Part is constituted.Downlock mechanism is made up of spring pressurized strut, adjustable extension arm, spring, lock rocking arm etc..It is locking can holding bar due to oriented
Upper 4.5+0.8 -0.5Thus the additional load that amount of deflection is produced can be delivered to damper leg by the amount of deflection of mm, the adjustable extension arm in downlock mechanism
On outer tube.It is locking can holding bar by two holes with bronze bushing of triangle inclined strut, be hinged on damper leg outer tube center contact
The shaft shoulder on so that the lateral load on main landing gear by it is locking can holding bar, be delivered to fuselage up.It is locking can holding bar
Upwards 4.5+0.8 -0.5The amount of deflection of mm is a critical data of main landing gear design, and its installation accuracy directly influences the use of undercarriage
Safety.
The content of the invention
The purpose of the present invention is：There is provided a kind of quick survey aircraft main landing gear of energy can holding bar deflection value technological equipment.
In addition, the present invention also provide a kind of aircraft main landing gear can holding bar deflection value measurement process.
Technical scheme：A kind of aircraft main landing gear can holding bar deflection metrology device；The measuring device connects including the first screw thread
Head [01], flexible handle [02], gland [03], sunk screw [04], measurement main body [05], measurement joint [06], measurement column [07],
Steel wire rope [08], label, the second nipple [09]；Wherein, first nipple [01] is by gland [03] and countersunk head spiral shell
In measurement main body [05], two flexible handles [02] are separately mounted to the first nipple [01] and the second screw thread connects for nail [04]
In the hole of head [09] termination, the second nipple [09] can holding lever lock by the opening and aircraft main landing gear measured in main body [05]
Stud on rocking arm is connected firmly.Label [] is riveted on the caliber outer surface of main body [05] by cup head aluminium rivet [11].
Measurement main body [05] includes 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；Described fixed ear base [05-01] is welded on survey
The left upper part of amount supervisor [05-02], fixation fork ear [05-04] is welded on the right-hand member top of measurement supervisor [05-02], measures ear mount
[05-03] is welded at the position to the right of measurement supervisor [05-02] middle part, and two reference blocks [05-05] are respectively welded at measurement supervisor
[05-02] two ends bottom.For ensureing the precision of measurement main body upper installing hole and mounting surface.
The sunk screw [04] is fixed on the first nipple [01] being adjusted in place in measurement main body [05] by gland [03].
Second nipple [09] can be on holding lever lock rocking arm with aircraft main landing gear by measuring opening on main body [05]
Stud connect firmly, facilitate its with aircraft main landing gear can holding bar connect firmly.
Measurement joint [06] can be arranged on aircraft main landing gear can be on the stud of holding bar triangle inclined strut, and measurement column [7] can
In being inserted into the through hole of measurement ear mount [05-03].Measurement column [07] can use cooperatively to carry out deflection value with measurement joint [06]
Measurement.
The label cup head aluminium rivet [11] is riveted on the caliber outer surface of measurement supervisor [05-02], and label is surveyed to deflection value
Amount method carries out schematically illustrate.
The measurement column [07] and the second nipple [09] fasten knot in measurement supervisor [05-02], with anti-lost with steel wire rope [08] respectively.
A kind of survey aircraft main landing gear can holding bar deflection value method, it is winged using the one kind as described in one of claim 1-5
Owner's undercarriage can holding bar deflection metrology device, it is characterised in that comprise the steps：
Step 1：By can the measurement joint [06] of holding bar deflection metrology device can holding bar triangle inclined strut installed in aircraft main landing gear
On stud；
Step 2：By main landing gear can holding bar deflection metrology device the first nipple [01] and the end face point of the second nipple [09]
The faying face of universal joint and lock rocking arm can not fit on holding bar with aircraft main landing gear；
Step 3：By the first nipple [01] and undercarriage can the stud of upper universal joint of holding bar be attached, by second
Nipple [09] can be on holding lever lock rocking arm with aircraft main landing gear at the opening of fixation fork ear [05-04] in measurement main body [05]
Stud connect firmly；
Step 4：Measurement column [07] is inserted in the through hole of measurement ear mount [05-03] in place, measurement measures joint [06] and measurement column [07]
Between extend out size, extend out dimensional units for millimeter；
Step 5：By Deflection Formula and described contour dimension obtain can holding bar deflection value, described Deflection Formula
For：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 deflection value survey
Amount, when being effectively ensured aircraft main landing gear mounting and adjusting can holding bar deflection value accuracy requirement, solve undercarriage installation
During major issue, it is ensured that the installation of undercarriage.Measuring device is easy to use, safe and reliable, calculates simple, improves installation
Efficiency.
Description of the drawings
Fig. 1 can holding bar deflection metrology working state schematic representation for aircraft left main；
Fig. 2 is measurement part-structure schematic diagram；
Fig. 3 is measurement agent structure top view；
Fig. 4 is measurement agent structure side view；
Wherein：The nipples of 01- first, 02- flexible handles, 03- glands, 04- sunk screws, 05- measurement main bodys, 06-
Measurement joint, 07- measurement columns, 08- steel wire ropes, the nipples of 09- second, 05-01- fixed ear bases, 05-02- measurement supervisor,
05-03- measurement ear mounts, 05-04- fixation fork ears, 05-05- reference blocks.
Specific embodiment
Below in conjunction with accompanying drawing the present invention is described in further detail with instantiation：
Aircraft main landing gear of the present invention can holding bar deflection value measurement technological equipment with certain model transporter as platform, it is by the first spiral shell
Stricture of vagina joint [01], flexible handle [02], gland [03], sunk screw [04], measurement main body [05], measurement joint [06], measurement
Post [07], steel wire rope [08], label, the second nipple [09] and cup head aluminium rivet.
Refer to Fig. 1, its be aircraft left main can holding bar deflection metrology working state schematic representation, starboard main landing gear can holding bar
Deflection metrology working condition is corresponding thereto.The measurement joint of the deflection metrology device can holding bar triangular aslant installed in aircraft main landing gear
On the stud of pillar, the first nipple is arranged in measurement main body by gland with sunk screw, and itself and aircraft main landing gear can be rolled over
The stud of universal joint is connected firmly on strut；Second nipple can holding bar by the opening and aircraft main landing gear in measurement main body
Stud on lock rocking arm is connected firmly.Measuring device and main landing gear can be after holding bar install, in measurement column insertion measurement main body, measurement
Post and measurement joint are with the use of the measurement for carrying out deflection value.
Fig. 2 is referred to, it is measurement part-structure schematic diagram.The part reflects the physical dimension of measurement part, measurement column and measurement
Joint with the use of carry out can holding bar amount of deflection measurement.
Refer to Fig. 3,4, its be measurement agent structure schematic diagram, the measurement main body by fixed ear base, measurement supervisor, measurement ear mount,
Fixation fork ear and the part group weldering of reference block five are formed, and the annealed stress that eliminates of its postwelding roughing carries out again polish.Reflect phase in figure
Close physical dimension and positional precision.It is main using benchmark B faces, C faces, D faces position each other and the depth of parallelism, at three connecting hole and
The perpendicularity of 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, its process is as follows：
Step 1：By can holding bar deflection metrology device measurement joint [06] installed in aircraft main landing gear can holding bar triangle inclined strut stud
On.
Step 2：By main landing gear can holding bar deflection metrology device the first nipple [01], the second nipple [09] end face respectively and and
Aircraft main landing gear can faying face laminating at universal joint, lock rocking arm on holding bar.
Step 3：With the first nipple [01] and undercarriage can the upper universal joint stud of holding bar be attached, use the second screw thread
Joint [09] is by measuring the spiral shell that the opening and aircraft main landing gear of fixation fork ear [05-04] on main body [05] can be on holding lever lock rocking arms
Post is connected firmly.
Step 4：Measurement column [07] is inserted in measurement ear mount [05-03] hole, it is with connect firmly can holding bar triangular aslant in aircraft main landing gear
Measurement joint [06] on the stud of post is with the use of the measurement for carrying out deflection value.
Step 5：Deducted according to measurement result calculate by 50 can holding bar existing deflection value.
Step 6：If not meeting upwards 4.5+0.8 -0.5The deflection value of mm, need to adjust and be adjusted with roller tooth plate support arm with the tooth on tooth plate joint
Length, so as to ensure the technical requirements that undercarriage is installed.
The present invention using measurement frock carry out aircraft main landing gear can holding bar deflection value measurement when, first the measurement of deflection metrology device
Post is arranged on aircraft main landing gear and then the nipple of deflection metrology device and master can be risen and fallen on the stud of holding bar triangle inclined strut
Frame can holding bar connect firmly, then can be carried out survey calculation.After the present invention puts into production use, undercarriage is significantly reduced
The difficulty of installation, it is easy to use and reliable, installation effectiveness is improve, undercarriage installation specification is effectively ensured, with larger
Actual application value.
Claims (5)
1. a kind of aircraft main landing gear can holding bar deflection metrology measuring device；The measuring device includes the first nipple [01], lives
Fixed handle [02], gland [03], sunk screw [04], measurement main body [05], measurement joint [06], measurement column [07], steel wire rope
[08], label, the second nipple [09]；Wherein, first nipple [01] is by gland [03] and sunk screw [04]
In measurement main body [05], two flexible handles [02] are separately mounted to the first nipple [01] and the second nipple [09]
In the hole of termination, the second nipple [09] can be on holding lever lock rocking arm by measuring opening and aircraft main landing gear on main body [05]
Stud connect firmly.Label [] is riveted on the caliber outer surface of main body [05] by cup head aluminium rivet [11].
Measurement main body [05] includes 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]；Described fixed ear base [05-01] is welded on the left upper part of measurement supervisor [05-02],
Fixation fork ear [05-04] is welded on the right-hand member top of measurement supervisor [05-02], and measurement ear mount [05-03] is welded on measurement supervisor
At the position to the right of [05-02] middle part, two reference blocks [05-05] are respectively welded at measurement supervisor [05-02] two ends bottom.For protecting
The precision of card measurement main body upper installing hole and mounting surface.
The sunk screw [04] is fixed on the first nipple [01] being adjusted in place in measurement main body [05] by gland [03].
Second nipple [09] can holding lever lock rocking arm with aircraft main landing gear by measuring opening on main body [05]
On stud connect firmly, facilitate its with aircraft main landing gear can holding bar connect firmly.
Measurement joint [06] can be arranged on aircraft main landing gear can be on the stud of holding bar triangle inclined strut, measurement column [07] energy
In being enough installed to 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 main body
[05] it is 45# steel weldments.
3. aircraft main landing gear according to claim 1 can holding bar deflection metrology device, it is characterised in that：The label is with partly
Round end 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 state
Under, the measurement column [07] and the second nipple [09] fasten knot in measurement supervisor [05-02] with steel wire rope [08] respectively.
5. a kind of survey aircraft main landing gear can holding bar deflection value method, it is winged using the one kind as described in one of claim 1-4
Owner's undercarriage can holding bar deflection metrology device, it is characterised in that comprise the steps：
Step 1：By can the measurement joint [06] of holding bar deflection metrology device can holding bar triangle inclined strut installed in aircraft main landing gear
Stud on；
Step 2：By main landing gear can holding bar deflection metrology device the first nipple [01] and the end face of the second nipple [09]
The faying face of universal joint and lock rocking arm can fit 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, by
Two nipples [09] can holding lever lock rocking arm with aircraft main landing gear at the opening of fixation fork ear [05-04] on main body [05] is measured
On stud connect firmly；
Step 4：Measurement column [07] is inserted in the through hole of measurement ear mount [05-03] in place, measurement measures joint [06] and measurement column [07]
Between extend out size, extend out dimensional units for millimeter；
Step 5：By Deflection Formula and described contour dimension obtain can holding bar deflection value, described amount of deflection calculates public
Formula is：Deflection value=extend out size -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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106568583A true CN106568583A (en) | 2017-04-19 |
| CN106568583B CN106568583B (en) | 2019-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107356405A (en) * | 2017-07-25 | 2017-11-17 | 厦门大学 | A kind of combined type positioning installation apparatus of wind tunnel test model aircraft |
| CN109374243A (en) * | 2018-11-18 | 2019-02-22 | 中航天水飞机工业有限责任公司 | Mechanism deflection value measuring appliance |
| CN111272049A (en) * | 2020-03-31 | 2020-06-12 | 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 |
| CN113405748A (en) * | 2021-05-14 | 2021-09-17 | 陕西飞机工业有限责任公司 | Device and method for measuring airplane cabin door deflection |
| CN114184340A (en) * | 2021-12-10 | 2022-03-15 | 凌云科技集团有限责任公司 | Method and platform for measuring deflection of strut of landing gear of airplane |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107356405A (en) * | 2017-07-25 | 2017-11-17 | 厦门大学 | A kind of combined type positioning installation apparatus of wind tunnel test model aircraft |
| 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 |
| CN109374243A (en) * | 2018-11-18 | 2019-02-22 | 中航天水飞机工业有限责任公司 | Mechanism deflection value measuring appliance |
| 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 |
| CN111272049A (en) * | 2020-03-31 | 2020-06-12 | 成都飞机工业（集团）有限责任公司 | Method for measuring eccentricity of stay bar |
| 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 |
| CN113405748A (en) * | 2021-05-14 | 2021-09-17 | 陕西飞机工业有限责任公司 | Device and method for measuring airplane cabin door deflection |
| 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 |
| CN114184340A (en) * | 2021-12-10 | 2022-03-15 | 凌云科技集团有限责任公司 | Method and platform for measuring deflection of strut of landing gear 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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| Publication number | Publication date |
|---|---|
| CN106568583B (en) | 2019-01-25 |
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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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