CN104142227B - Supporting device and method for aircraft maintenance - Google Patents
Supporting device and method for aircraft maintenance Download PDFInfo
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- CN104142227B CN104142227B CN201310169714.0A CN201310169714A CN104142227B CN 104142227 B CN104142227 B CN 104142227B CN 201310169714 A CN201310169714 A CN 201310169714A CN 104142227 B CN104142227 B CN 104142227B
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- load
- support meanss
- maintenance
- pressurized strut
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Abstract
The invention belongs to the technology of aircraft maintenance supporting, and relates to a supporting device and method for aircraft maintenance in a structural test. The supporting device for aircraft maintenance comprises an upper fixing clamp, a lower fixing clamp, connecting screw rods and fixing nuts, wherein the upper fixing clamp is installed on the upper end face or the lower end face of an actuator cylinder sensor, the lower fixing clamp is installed on a covering cap at the front end of an actuator cylinder, the connecting screw rods are connected between the upper fixing clamp and the lower fixing clamp, and the upper fixing clamp and the lower fixing clamp are locked through the fixing nuts. According to the supporting device for aircraft maintenance, external force is applied by means of the hydraulic actuator cylinder, the external force is transferred to the supporting device to be applied by adjusting the connecting screw rods and the fixing nuts between the upper fixing clamp and the lower fixing clamp, and the external force is transmitted to a strength bearing base through the fixing clamps and the connecting screw rods; in the examination and maintenance process, an aircraft is supported by the supporting device, and the phenomenon that no effective supporting can be provided when the hydraulic actuator cylinder conducts accidental unloading due to the fact that a test loading system suddenly fails is avoided.
Description
Technical field
The invention belongs to aircraft maintenance support technology, be related to a kind of support meanss for aircraft maintenance in structural test and
Method.
Background technology
In the full machine fatigue test of structure of aircraft, generally carry out static determinacy constraint using gripping clamping apparatus, by Theoretical Calculation and
In-site measurement obtains constraining point load, according to constraint point load, can be to aircaft configuration critical piece stressing conditions, stress level
It is analyzed and monitors, guarantees testing machine safety.
When fatigue stage life test is completed or housing construction important fatigue damage occurs, need to examine testing machine
Look into, damage location is keeped in repair.Some load-carrying construction or part are generally dismounted in inspection, maintenance process, was being dismounted
Dismounting position is kept to be carried as 0 or minimum in journey.In addition, removing after these load-carrying construction or part, partial structurtes are destroyed
Integrity, change Path of Force Transfer, reduce structural strength.And body own wt, on machine maintenance overhaul personnel set
Under standby weight, can produce compared with big load and stress concentration in these positions, form structural danger position.
Prior art is adopted simply to hang or pave mode and supported when aircraft maintenance work is carried out, generally, it is impossible to real
Apply monitoring and assess the stress level of dangerous position, it is difficult to maintenance work is effectively ensured and is normally carried out and testing machine safety.
The content of the invention
The purpose of the present invention is：There is provided one kind can apply corresponding external force in aircraft correct position, and be carried according to obligatory point
The size of lotus real-time adjustment power, effectively guarantees the support meanss of aircraft safety.
In addition, the present invention also provides a kind of method for supporting for aircraft maintenance in structural test.
The technical scheme is that：A kind of support meanss for aircraft maintenance, it includes fixing hoop, lower fixation
Clip, connecting screw rod, fixing nut, wherein, upper fixing hoop is arranged on the upper surface or lower surface of start cylinder sensor, lower solid
Clip is determined on pressurized strut front port lid, and connected by connecting screw rod between upper fixing hoop and lower fixing hoop, and
Locked by fixing nut.
Up and down fixing hoop is into a single integrated structure by bolt connection by 2 pieces of clamps and 2 pieces of connector compositions.
The connecting screw rod is a pair, and relative pressurized strut is symmetrical.
A kind of method for supporting for aircraft maintenance, it comprises the steps：
Step 1：External force size and distribution are determined according to aircraft dangerous position and maintenance program；
Step 2：According to external force size and distribution, pressurized strut load(ing) point is set in aircraft relevant position, and loading is installed and make
Dynamic cylinder, support meanss are fixed in pressurized strut；
Step 3：Loading Control System control pressurized strut applies respective loads, it is ensured that constraint point load is within safety limit；
Step 4：Adjustment support meanss, and pressurized strut load is reduced to into 0, external force is transferred to into support meanss and is applied；
Step 5：By adjusting fixing nut, support meanss load is adjusted so that constrain point load within safety limit, such as
Fruit then 3～step 5 of repeat step when transfiniting and cannot be adjusted by fixing nut；
Step 6：Pressurized strut unloading, release, close oil circuit, close oil pump.
During maintenance and inspection, each load(ing) point of real-time monitoring, obligatory point feedback simultaneously circulate a notice of in time scene, if transfiniting
Stop maintenance and inspection work, by adjusting connecting screw rod and fixing nut between upper and lower fixing hoop, readjust external force load
Lotus be distributed so that constraint point load safety limit within, when transfiniting and cannot be adjusted by fixing nut if repeat step 3
～step 6.
The solution have the advantages that：
Using the support meanss and method, apply corresponding external force at testing machine intensity, the larger position of rigidity, according to obligatory point
The size of load real-time adjustment power, it is ensured that dismounting is working properly to be carried out, and makes that dangerous position load is as far as possible little, and stress level is tried one's best
It is low, and have the advantage that：
A) solve in fatigue test, a support difficult problem for testing machine maintenance overhaul；
B) strong adaptability, can be used for Multiple Type aircraft fatigue, slow test；
C) point load is constrained by real-time monitoring, adjusts support meanss load, it is ensured that maintenance work is normally carried out and tests
Machine safety；
D) support meanss convenient and flexible installation, it is cheap for manufacturing cost, it is easy to production.
Description of the drawings
Fig. 1 is support meanss assembling figure, and Fig. 2 is support meanss exploded view, and Fig. 3 uses the installation diagram, Fig. 4 to be to press to carrying
Pull to carrying and use installation diagram.
Wherein, 1 be fixing hoop, 2 be clip clamp, 3 be clamp connection part, 4 be clamp bolt, 5 be connecting bolt, 6
For connecting screw rod, 7 be fixing nut, 8 be pressurized strut front end-plate, 9 be pressurized strut piston rod, 10 be sensor.
Specific embodiment
Below in conjunction with the accompanying drawings the present invention is described further：
Fig. 1 and 2 is referred to, the present invention includes upper fixing hoop, lower fixing hoop, company for the support meanss of aircraft maintenance
Connect screw rod, fixing nut.Wherein, upper fixing hoop is arranged on the lower surface of start cylinder sensor, and for providing carrying is pressed to.Under
Fixing hoop is arranged on pressurized strut front port lid, and is connected with connecting screw rod between upper fixing hoop and lower fixing hoop, and
Locked by fixing nut.
Wherein, above-mentioned each part concrete structure and function are as follows：
Upper fixing hoop 1 and lower fixing hoop 1 are constituted by 2 pieces of clip clamps, 2,2 pieces of clamp connection parts 3, by 8 cards
Hoop bolt 4 is connected as a single entity, and is easy to in-site installation.
Connecting bolt 5 is fixed on lower fixing hoop on hydraulic actuator front port lid, and this is the load base of support meanss
Plinth.
Connecting screw rod 6 is a pair, and opposing hydraulic pressurized strut is symmetrical, connects upper and lower fixing hoop, according to hydraulic actuation
Cylinder piston rod elongation, spiro rod length between two clips of adjustment, is positioned and is fixed, when upper solid by 4 fixing nuts 7
Determine clip installed in force transducer lower end, i.e., near hydraulic actuator, when can provide and press to load, when upper fixing hoop is installed
In force transducer upper end, i.e., near testpieces, when can provide and pull to load.
The present invention is used for the support meanss force path of aircraft maintenance：Sensor end face → upper fixing hoop → fixation spiral shell
Female, connecting screw rod → lower fixing hoop → hydraulic actuator front end lid → hydraulic actuator load base.
The present invention applies external force for the support meanss of aircraft maintenance first with hydraulic actuator, then is arranged by adjusting
Connecting screw rod and fixing nut between upper and lower fixing hoop, is transferred to external force support meanss and applies, support meanss power transmission
Approach is as described above.All the time by support device aircraft during maintenance and inspection, it is to avoid because of plate test loading system accident
The hydraulic actuator that failure causes surprisingly is unloaded and cannot provide effective situation about supporting.
The present invention is as follows for the detailed process of the method for supporting of aircraft maintenance：
Step 1：External force size and distribution are determined according to aircraft dangerous position and maintenance program；
Step 2：According to external force size and distribution, determine pressurized strut load(ing) point in aircraft relevant position, and loading is installed and make
Dynamic cylinder, support meanss are fixed in pressurized strut；
Step 3：Loading Control System control pressurized strut applies respective loads, it is ensured that constraint point load is within safety limit；
Step 4：Adjustment support meanss, and pressurized strut load is reduced to into 0, external force is transferred to into support meanss and is applied；
Step 5：By adjusting fixing nut, support meanss load is adjusted so that constrain point load within safety limit, such as
Fruit then 3～step 5 of repeat step when transfiniting and cannot be adjusted by fixing nut；
Step 6：Pressurized strut unloading, release, close oil circuit, close oil pump.
In addition, the upper fixing hoop of support meanss of the present invention can also be arranged on start cylinder sensor lower surface, there is provided pressure
To carrying.
Below the present invention is carried out specifically by taking the 2500 backward maintenance and inspection of full machine fatigue test of certain type civil aircraft as an example
It is bright, in the aircraft maintenance, need to remove central wing wainscot, in order to smoothly dismount central wing wainscot, it is ensured that remove central authorities
The integrity of structure, safety after wing wainscot, need to apply the weight that external force offsets aircraft, maintenance overhaul personnel and equipment,
Make after dismounting central wing wainscot that big opening region moment of flexure is as far as possible little, stress level is as far as possible low, in maintenance overhaul, take this
Invention support meanss and method, for testing machine support is provided.
It is embodied as that three steps can be divided into.
A) before maintenance and inspection work starts
1) according to testing machine and maintenance overhaul personnel, the distribution of weight of equipment, according to dangerous position load, stress level with
Constraint point load corresponding relation, it is determined that constraining point load and needing to apply the size of external force, distribution；
2) according to external force size and distribution, 28 pressurized strut loadings are set at positions such as fuselage, wing, horizontal tail, electromotors
Point；
3) loading pressurized strut is installed, and support meanss (pull to, press to) is fixed in pressurized strut；
4) Loading Control System control pressurized strut applies respective loads, it is ensured that constraint point load is within safety limit；
5) support meanss are adjusted, and pressurized strut load is reduced to into 0, external force is transferred to into support meanss and is applied；
6) by adjusting fixing nut, support meanss load is adjusted so that constraint point load is within safety limit, if surpassed
Limit and when cannot be adjusted by fixing nut then repeatedly 4)～6)；
7) pressurized strut unloading, release, close oil circuit, close oil pump.
B) maintenance and inspection work starts
1) central wing wainscot is removed；
2) keeped in repair by maintenance and inspection scheme；
3) reasonable arrangement maintenance and inspection personnel, equipment go on or off the plane order, position and quantity；
4) during maintenance and inspection, each load(ing) point of real-time monitoring, obligatory point feedback simultaneously circulate a notice of in time scene.If transfinited
Then stop maintenance and inspection work, by adjusting connecting screw rod and fixing nut between upper and lower fixing hoop, readjust external force
Load be distributed so that constraint point load safety limit within, when transfiniting and cannot be adjusted by fixing nut if hold again
In row a) 4)～7).
C) after maintenance and inspection end-of-job
1) central wing wainscot is installed；
2) oil pump is driven, each load(ing) point oil pipe line is opened；
3) Loading Control System control pressurized strut applies respective loads, it is ensured that constraint point load is within safety limit；
4) Divisional, one by one remove pressurized strut on support meanss；
5) remove after terminating, pressurized strut unloading, release are closed oil circuit, close oil pump.
Claims (5)
1. a kind of support meanss for aircraft maintenance, it is characterised in that：Including upper fixing hoop, lower fixing hoop, connection spiral shell
Bar, fixing nut, wherein, upper fixing hoop is arranged on the upper surface or lower surface of start cylinder sensor, and lower fixing hoop is installed
On pressurized strut front port lid, and connecting screw rod is connected between upper fixing hoop and lower fixing hoop, and is locked by fixing nut
It is fixed.
2. support meanss for aircraft maintenance according to claim 1, it is characterised in that：Up and down fixing hoop is by 2
Block clamp and 2 pieces of connector compositions, it is into a single integrated structure by bolt connection.
3. support meanss for aircraft maintenance according to claim 1, it is characterised in that：The connecting screw rod is one
It is right, and relative pressurized strut is symmetrical.
4. a kind of method for supporting for aircraft maintenance of the support meanss for aircraft maintenance based on described in claim 2,
It is characterized in that：
Step 1：External force size and distribution are determined according to aircraft dangerous position and maintenance program；
Step 2：According to external force size and distribution, pressurized strut load(ing) point is set in aircraft relevant position, and loading pressurized strut is installed,
Support meanss are fixed in pressurized strut；
Step 3：Loading Control System control pressurized strut applies respective loads, it is ensured that constraint point load is within safety limit；
Step 4：Adjustment support meanss, and pressurized strut load is reduced to into 0, external force is transferred to into support meanss and is applied；
Step 5：By adjusting fixing nut, support meanss load is adjusted so that constraint point load is within safety limit, if surpassed
Limit and then 3～step 5 of repeat step when cannot be adjusted by fixing nut；
Step 6：Pressurized strut unloading, release, close oil circuit, close oil pump.
5. the method for supporting for aircraft maintenance according to claim 4, it is characterised in that during maintenance and inspection,
The each load(ing) point of Real Time Observation, obligatory point feedback simultaneously circulate a notice of in time scene, maintenance and inspection work are stopped if transfiniting, by adjusting
Up and down the connecting screw rod and fixing nut between fixing hoop, readjusts the distribution of external force load so that constraint point load is in peace
Within full limit, when transfiniting and cannot be adjusted by fixing nut if 3～step 6 of repeat step.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310169714.0A CN104142227B (en) | 2013-05-10 | 2013-05-10 | Supporting device and method for aircraft maintenance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310169714.0A CN104142227B (en) | 2013-05-10 | 2013-05-10 | Supporting device and method for aircraft maintenance |
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| Publication Number | Publication Date |
|---|---|
| CN104142227A CN104142227A (en) | 2014-11-12 |
| CN104142227B true CN104142227B (en) | 2017-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310169714.0A Active CN104142227B (en) | 2013-05-10 | 2013-05-10 | Supporting device and method for aircraft maintenance |
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| CN (1) | CN104142227B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109878759B (en) * | 2019-03-29 | 2022-07-15 | 中国飞机强度研究所 | Airplane test device, restraining and loading method and weight deducting and loading method |
| CN110294144B (en) * | 2019-06-26 | 2023-08-22 | 中国飞机强度研究所 | Actuator cylinder support and actuator loading device with same |
| CN111811631A (en) * | 2020-07-10 | 2020-10-23 | 苏州振湖电炉有限公司 | High-precision suspension frame weighing device for electroslag furnace |
| CN112611550B (en) * | 2020-11-13 | 2022-07-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Fatigue test loading device for control system |
Citations (5)
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|---|---|---|---|---|
| EP0107348A1 (en) * | 1982-10-22 | 1984-05-02 | East/West Industries, Inc. | Mobile maintenance stand for servicing and transporting ejection seats |
| CN101344455A (en) * | 2007-07-10 | 2009-01-14 | 陈镜图 | Rolling wheel test device |
| CN102980750A (en) * | 2012-11-09 | 2013-03-20 | 上海交通大学 | Aircraft wing long purlin assembling process and automatic simulation experiment set of clamp force |
| CN102991727A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Constraint system of airplane structure test |
| CN103010484A (en) * | 2012-12-10 | 2013-04-03 | 中国飞机强度研究所 | Follow-up support device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2977992B1 (en) * | 2011-07-13 | 2014-04-04 | Eads Europ Aeronautic Defence | INTERMEDIATE STRUCTURE FOR MAINTAINING AIRCRAFT SYSTEMS ON BOARD AN AIRCRAFT |
-
2013
- 2013-05-10 CN CN201310169714.0A patent/CN104142227B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0107348A1 (en) * | 1982-10-22 | 1984-05-02 | East/West Industries, Inc. | Mobile maintenance stand for servicing and transporting ejection seats |
| CN101344455A (en) * | 2007-07-10 | 2009-01-14 | 陈镜图 | Rolling wheel test device |
| CN102980750A (en) * | 2012-11-09 | 2013-03-20 | 上海交通大学 | Aircraft wing long purlin assembling process and automatic simulation experiment set of clamp force |
| CN102991727A (en) * | 2012-12-10 | 2013-03-27 | 中国飞机强度研究所 | Constraint system of airplane structure test |
| CN103010484A (en) * | 2012-12-10 | 2013-04-03 | 中国飞机强度研究所 | Follow-up support device |
Non-Patent Citations (1)
| Title |
|---|
| 飞机结构静强度试验支持方案的确定;刘权良 等;《航空科学技术》;20121015(第5期);第32-35页 * |
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| CN104142227A (en) | 2014-11-12 |
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