CN100509561C - Assemblage for hanger bracket with engine - Google Patents
Assemblage for hanger bracket with engine Download PDFInfo
- Publication number
- CN100509561C CN100509561C CNB2006100834668A CN200610083466A CN100509561C CN 100509561 C CN100509561 C CN 100509561C CN B2006100834668 A CNB2006100834668 A CN B2006100834668A CN 200610083466 A CN200610083466 A CN 200610083466A CN 100509561 C CN100509561 C CN 100509561C
- Authority
- CN
- China
- Prior art keywords
- subelement
- hanger
- assy
- test
- engine
- 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.)
- Expired - Fee Related
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2211/00—Modular constructions of airplanes or helicopters
Abstract
The present invention is one embodiment of improved process for assembling and/or disassembling the engine unit to the wing of airplane. The engine unit including one pylon for engine is pre-assembled before being assembled to the wing.
Description
Technical field
The present invention relates to aircraft assembling field.Particularly, the present invention relates to method that the aero-engine unit is assembled on the aircraft wing and/or disassembles, described engine unit comprises driving engine and hanger.
Background technology
In current commercial aircraft industry, the short aircraft delivery time has become more and more important.Therefore the shorter delivery time requires production and fitting process in the airplane industry to have comformability and pipelining.But high quality in this industry and administrative standard require the product of producing and assemble is carried out full test.In order to consider the desired test duration, consider shorter lead time on the other hand on the one hand, therefore wish to have a kind of improved method that engine unit is assembled to wing.If require certain test duration, this requires the possibility that lead time shortens in common limit production and the fitting process.
Particularly, engine unit is assembled to aircraft wing and needs several installation step at present.At first the different parts with the aero-engine unit progressively are assembled on the aircraft wing.In the last assembling that engine unit is assembled to aircraft wing, earlier hanger is installed on the wing usually.This hanger is the driving engine Lift-on/Lift-off System that is used for aircraft wing.After hanger is installed on the wing, for this hanger provides common equipment, fire extinguisher tank etc. for example.Subsequently, with engine installation to the subelement that assembles of hanger and wing.In case after engine installation is to hanger, the installation system connecting device.Arrangement for connecting system comprises any such as supply arrangements such as pneumatic shuttle, hydraulic efficiency gear, fuel, electrical equipment, fire extinguishers.Certainly, after having set up these connecting devices, need full test to take place without any fault in all function normal operation and these connecting devices guaranteeing.In final aircraft fitting process, need carry out some days the assembling fully and the test of this connecting device.
After the test of finishing connecting device, other parts such as engine nacelle are assembled on this unit.Engine nacelle generally includes the fairing and the commutator of driving engine.After this step is finished, need further test the holonomic system that comprises driving engine, hanger, wing, connecting device and engine nacelle.
Because these installation step all directly carry out on the aircraft wing that is connected to fuselage, clearly, any problem that takes place during in these parts of assembling/test any production of aircraft of all may slowing down, so even prolong total lead time.
In to the test of engine unit or any maintenance work process, make a mistake or during fault, need fully any connecting device, engine nacelle, driving engine, hanger are disassembled from wing, with correction or maintenance failure and/or mistake.It will be apparent for a person skilled in the art that this process is time-consuming, and the production/maintenance of may slow down aircraft or driving engine.
Because said process must be followed, therefore need a kind of improved method that engine unit is assembled on the aircraft wing and disassembles in the production/fitting process of new aircraft and in each assembling of the engine unit that carries out in each maintenance process of engine unit.
Summary of the invention
The improved assembly method that the purpose of this invention is to provide the aero-engine unit.
Another object of the present invention provides the assembly method of engine unit, and this method can shorten lead time.
A further object of the present invention provides a kind of method of pre-assy subelement of the test engine unit that can carry out simultaneously with aircraft installation step early.
The present invention relates to the aero-engine unit is assembled to method on the aircraft wing, this engine unit comprises driving engine and hanger, and wherein said method may further comprise the steps: driving engine and hanger are pre-assembled on the pre-assy subelement; With the pre-assy subelement is installed on the wing.
Although the present invention relates to the assembling of engine unit, it should be apparent to those skilled in the art that the present invention also can be diverted to any assembly method in the industry, it can allow pre-assembled unit is carried out pre-assy and/or test.
Term used herein " engine unit " is meant the pre-assembled unit that comprises driving engine and hanger, further comprises engine nacelle alternatively and/or is used for the connecting device of various supplies.Engine unit also can be called " hanger of band driving engine ".
Engine nacelle may further include commutator, back and/or outer commutator fairing, air intlet, nozzle and/or is used for the fairing of driving engine.
Used term " driving engine " is meant any combination of parts such as fairing, commutator, nozzle, air intlet or driving engine itself among the present invention.
Term used herein " hanger of band driving engine " is meant the pre-assembled unit of hanger and driving engine, and it is also referred to as preassembled subelement.
The method according to this invention can shorten total lead time of Aircraft Production.
Particularly, owing to can handle aircraft assembling carrying out parallel work flow well known in the prior art and/or work package, the present invention can make lead time shorten.
In exemplary of the present invention, in the last production phase of aircraft, be installed to each subelement on the wing before, the pre-assy subelement of hanger of band driving engine is tested.
In exemplary of the present invention, described hanger is equipped with common device, for example fire extinguisher tank." be equipped with " hanger and be connected with driving engine then, form " hanger of band driving engine ".In another exemplary of the present invention, the hanger of band driving engine may further include fairing.
In another exemplary, the hanger of band driving engine can further include engine nacelle and/or commutator.
The pre-assy hanger of band driving engine can be equipped with necessary connecting device, for example be connected to pneumatics, hydraulic efficiency gear, fuel, blowdown apparatus (bleed), ladder and gap (steps and gaps), power supply and/or fire extinguisher, so that carry out the test of pre-assy subelement.
In an exemplary of the present invention, gap and ladder are only regulated once at the hanger place, therefore can omit other treatment step, for example application of A-framework (model (a dummy for prejustment) that for example, is used for preset adjustment).
In an exemplary of the present invention, the test of hanger of band driving engine is carried out in independent assembly unit, this independent assembly unit can also comprise independent test desk.Therefore, can under situation about not being installed on the aircraft wing, carry out function test by the hanger to the band driving engine.
Testing in independent assembly unit can be so that tests the pre-assy hanger of band driving engine with other production and processing step of aircraft concurrently, according to the known method of prior art, other production and processing step of described aircraft must be finished before the aircraft unit is installed on the wing of aircraft at last, and can test the driving engine that is installed to fully on the wing.In other words, the present invention allows test is moved on to early stage and/or parallel with the installation step of aircraft.
Therefore concurrent testing itself can shorten the lead time of aircraft.
In addition, in in test process in the parts of hanger of band driving engine any or in connecting device, make a mistake or the situation of fault under, the present invention allows shorter repairing/maintenance time, because do not need to pull down from aircraft wing before repairing as the hanger of the band driving engine of pre-assy subelement.In addition, for example do not needing to disconnect from the connecting device between the fuel supply of wing etc., this can further add quick-detach/assembling again.
In exemplary embodiment, test to the pre-assy subelement, preferably to the test of hanger of band driving engine, allow really to trail run (dry runs), commencement of commercial operation (wet runs) and/or not other early stage installation step of test and the aircraft of run with load (destorage runs) walk abreast.
In case completed successfully after the test of pre-assy subelement, this pre-assy subelement be installed on the wing of aircraft.
By any method known to those skilled in the art, transport trolley for example can will be tested and preassembled subelement is transported to position with the wing assembling.
Can be by any method known to those skilled in the art with the installation of the hanger of driving engine.In exemplary, the installation of the pre-assy hanger of band driving engine is undertaken by hoist cable one lifting gear.With the installation of hoist cable-lifting gear since its free-running operation feature can accurately locate the hanger of band driving engine.
In another exemplary, the installation of preassembled subelement particularly with the installation of the hanger of driving engine, can be carried out under the help of steady arm.In another exemplary, steady arm can be the driving engine steady arm, and it can be positioned on the assembly support.
In exemplary of the present invention, steady arm can move on all six spatial axes, and moving direction and centre of gration can be determined arbitrarily.In another exemplary of the present invention, steady arm has the accuracy of positioning within required tolerance.In addition, in another exemplary of the present invention, steady arm is automatically and can be at diagonal line and side travel.Steady arm can also be equipped with general purpose interface, is used for moving and transmitting framework.
In another embodiment of the invention, steady arm is equipped with sensor, is used to measure with respect to the current load of wing and the position of load, so that can control this load and steady arm.
In another exemplary of the present invention, steady arm is a programmable, with the motion of carrying out pre-programmed on all three dimensions.This can treat, and the pre-assy subelement that is installed on the aircraft wing carries out very accurately, " shock-free " and soft motion.
In another exemplary of the present invention, steady arm can be followed the tracks of and/or Digital Photogrammetric System by optical measuring system such as laser, further determines the parts to be installed and to be connected and/or the accurate position and the angle of subelement.
Those skilled in the art understand easily, be used for will the band driving engine the hanger moving method that is installed to the steady arm on the wing may be embodied as computer program, promptly implement by software, perhaps can use one or more specific electronic optimization circuits, be that hardware is implemented, perhaps this method can be implemented by mixed form, promptly utilizes the software and hardware assembly to implement.
Program element according to exemplary of the present invention can preferably be loaded in the working storage of data handler.Therefore this data memory can be equipped with the exemplary with the method for the hanger of carrying out the mounting strap driving engine.Computer program can be write with any suitable programming language, C++ for example, and can be stored on any computer-readable medium, as CD-ROM.And computer program can for example obtain on the WWW from network, can download to graphics processing unit or the treater from this network, or in any suitable computing machine.
Hanger and being connected of wing are that the engaging lug by wing socket (spigot) and wing proparea and back zone provides, and described wing socket is sent to the thrust of driving engine in the aircaft configuration, and described engaging lug is supported hanger.
Described socket is installed with the definite angle perpendicular to wingpiston almost, if therefore hanger with the angle of mistake near socket, the installation of hanger may be difficult.This may cause the obstruction of hanger, and the installation of hanger may be complicated or before restarting new installation, hanger need be shifted out from socket.In some cases, described obstruction may cause the damage of socket (so wing) or hanger, and perhaps the two all is damaged.
Have above-mentioned features location device by use, " socket problem ", promptly the obstruction in the hanger installation process can be prevented from.
In exemplary, the invention provides a kind of method, wherein locate preassembled subelement by steady arm, the obstruction of socket and bearing sleeve is minimized.
Another benefit of the present invention can be, the test in assembly unit and/or independent test platform separately can be satisfied legal requiremnt, and this may become more and more important in the future.Because can comprise " closed (closed) " space that the test desk needs are big of complete stack-mounted airframe and wing, provide the suitable test equipment of hanger subelement that can closed calibration tape driving engine may be easier.Therefore, the test easily that will not be installed to the hanger of driving engine on the wing of aircraft can also be that employee and/or environment reduce noise and/or disagreeable smell.In addition, method of the present invention also is suitable for reducing polluting by more effective and experiment more efficiently.
The elaboration of the embodiment described of vide infra, these and other aspect of the present invention will become apparent.
Description of drawings
Only the present invention is described referring now to accompanying drawing in the mode of example, wherein:
Fig. 1 shows the scheme drawing of different parts of the typical aero-engine of exemplary of the present invention.
Fig. 2 shows the scheme drawing of the hanger that has driving engine, and this hanger comprises the engine nacelle and the wing of aircraft.
Fig. 3 shows the scheme drawing of the method according to this invention (bottom) that compares with known method (top).
The specific embodiment
Diagram in the accompanying drawing is schematic.In different accompanying drawings, similar or components identical has identical Reference numeral.
In Fig. 1, schematically show the different parts of the representative engine of aircraft.Air intlet 101 is positioned at the front portion of driving engine.Commutator 102 and nozzle 103 are positioned at the rear portion of driving engine.Surround in the middle of driving engine 104 is positioned at self and by fairing 105.
Fig. 2 schematically shows the scheme drawing that preassembled engine unit 200 is installed to wing 203, and wherein this preassembled engine unit the method according to this invention is assembled and tested.Engine unit 200 comprises hanger 201, and it is connected engine unit with the wing 203 of aircraft.The exemplary of engine unit 200 also shows has engine nacelle.
Fig. 3 shows the benefit of the inventive method 300 of comparing with known method 301.Art methods is illustrated in the top of Fig. 3, and it schematically shows the different installation step of aircraft.Represented to be assemblied in the exemplary cell in the independent assembly unit 302.And in the known method of prior art, for example hanger 201 and electric wire 304 must tested on the wing that was installed to aircraft before 305.In the known method of prior art, after the test of successfully having carried out hanger 201 and electric wire 304, driving engine 306, fairing 105 and commutator 102 are installed on the hanger 201 that has been installed on the aircraft wing successively.After installation driving engine 306, commutator 102 and fairing 105, carry out next one test 309.The method according to this invention, driving engine 306, fairing 105 and commutator 102 also are pre-assembled in the independent pre-assembled unit 302, and finish be pre-assembled to hanger 201 after, test.Therefore, in the method according to the invention, all these parts 201,304,306,307 and 308 are pre-assembled in the independent pre-assembled unit 302, and can be used as preassembled subelement 310 and test in this pre-assembled unit 302.In the method for prior art, must after being installed to wing, carry out each test phase 305,309,311, for example carry out test at hanger 201, electric wire 304, driving engine 306, cowling 105 or commutator 102.The method according to this invention before being installed to wing, has just assembled and the preassembled subelement 310 of calibration tape engine unit randomly.Therefore, the method according to this invention can walk abreast and early stage test to the pre-assy hanger of band engine unit, and therefore can obtain shorter lead time, and this is shown by the time difference that the method according to this invention obtains.
It should be apparent to those skilled in the art that benefit of the present invention is not limited to the production of aircraft, and can obtain benefit aspect the time of the repair and maintenance of various aircrafts.
Should be noted that term " comprises " does not get rid of other element and step, and " one " does not get rid of a plurality of situations.The element of describing among the different embodiment can make up.
Should be noted that the Reference numeral in the claim not should be understood to limitation of the scope of the invention.
Claims (10)
1. one kind is assembled to method on the aircraft wing (203) with aero-engine unit (200), and this engine unit comprises:
Driving engine (104); With
Hanger (201);
Wherein, said method comprising the steps of:
Driving engine and hanger prepackage are made into the pre-assy subelement; With
Described pre-assy subelement is installed on the wing.
2. according to the process of claim 1 wherein, described method is further comprising the steps of:
The pre-assy subelement of the hanger of this band driving engine of test before being installed on the wing.
3. according to the method for claim 2, wherein, described test comprises trail run, commencement of commercial operation and/or not run with load test.
4. according to each method in claim 2 or 3, wherein, the test of pre-assy subelement is included in the test in the independent assembly unit.
5. according to each method in claim 2 or 3, wherein, described test comprises the test to pneumatics, hydraulic efficiency gear, fuel, blowdown, ladder and gap, electrical equipment and/or fire extinguisher.
6. according to each method in the claim 1 to 3, wherein, the pre-assy subelement also comprises engine nacelle and/or commutator.
7. according to each method in the claim 1 to 3, wherein,
By hoist cable one lifting gear this pre-assy subelement is installed.
8. according to each method among the claim 1-3, wherein,
By steady arm this pre-assy subelement is installed.
9. method according to Claim 8, wherein, follow the trail of and/or the photogrammetric automatic guidance that carries out by optical measuring system such as laser the location of pre-assy subelement.
10. method according to Claim 8, wherein, by prevent the obstruction of socket and bearing sleeve with steady arm location pre-assy subelement.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100834668A CN100509561C (en) | 2006-05-30 | 2006-05-30 | Assemblage for hanger bracket with engine |
| PCT/EP2007/004731 WO2007137812A1 (en) | 2006-05-30 | 2007-05-29 | Pylon with engine assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2006100834668A CN100509561C (en) | 2006-05-30 | 2006-05-30 | Assemblage for hanger bracket with engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101081641A CN101081641A (en) | 2007-12-05 |
| CN100509561C true CN100509561C (en) | 2009-07-08 |
Family
ID=38432935
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2006100834668A Expired - Fee Related CN100509561C (en) | 2006-05-30 | 2006-05-30 | Assemblage for hanger bracket with engine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN100509561C (en) |
| WO (1) | WO2007137812A1 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2935954B1 (en) * | 2008-09-18 | 2011-06-03 | Airbus France | REAR AIRCRAFT PART COMPRISING A SUPPORT STRUCTURE OF ENGINES CROSSING THE FUSELAGE AND CONNECTED THERETO TO IT BY AT LEAST ONE ROD. |
| CN102030110B (en) * | 2010-10-25 | 2013-03-20 | 北京航空航天大学 | Clamp device for involutory processing of anti-interference airplane fuselage and wings intersection point |
| FR2975669B1 (en) * | 2011-05-24 | 2013-07-05 | Airbus Operations Sas | METHOD FOR POINTING A PLURALITY OF PREDETERMINAL LOCATIONS WITHIN A STRUCTURE, AND CORRESPONDING SCORING SYSTEM |
| WO2015010315A1 (en) | 2013-07-26 | 2015-01-29 | Mra Systems, Inc. | Aircraft engine pylon |
| US10295970B2 (en) | 2013-07-29 | 2019-05-21 | C Series Aircraft Limited Partnership | Method for attachment of a pre-assembled powerplant and pylon assembly to an aircraft |
| DE102014017596A1 (en) * | 2014-05-16 | 2015-11-19 | Liebherr-Aerospace Lindenberg Gmbh | Flash FAL Track II |
| FR3040043B1 (en) * | 2015-08-12 | 2019-04-12 | Sogeclair Sa | AIRCRAFT ENGINE MAST WITH INTEGRATED MULTIFUNCTIONAL FRAME |
| JP7003278B2 (en) * | 2018-08-31 | 2022-01-20 | 川崎重工業株式会社 | Aircraft parts assembly jig and aircraft parts inspection jig |
| US11479363B2 (en) | 2019-05-17 | 2022-10-25 | Rohr, Inc. | Total underwing nacelle and engine installation |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2069427B (en) * | 1981-02-12 | 1983-09-01 | British Aerospace | Aircraft powerplant housings |
| GB9119853D0 (en) * | 1991-09-17 | 1991-10-30 | Rolls Royce Plc | Method of and apparatus for removing and replacing a part or parts of a gas turbine engine powerplant |
-
2006
- 2006-05-30 CN CNB2006100834668A patent/CN100509561C/en not_active Expired - Fee Related
-
2007
- 2007-05-29 WO PCT/EP2007/004731 patent/WO2007137812A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| CN101081641A (en) | 2007-12-05 |
| WO2007137812A1 (en) | 2007-12-06 |
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