CN104724300B - Aircraft engine installing vehicle alignment system and localization method thereof - Google Patents
Aircraft engine installing vehicle alignment system and localization method thereof Download PDFInfo
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- CN104724300B CN104724300B CN201510137599.8A CN201510137599A CN104724300B CN 104724300 B CN104724300 B CN 104724300B CN 201510137599 A CN201510137599 A CN 201510137599A CN 104724300 B CN104724300 B CN 104724300B
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Abstract
The present invention provides a kind of aircraft engine installing vehicle alignment system, it includes two set Multi-section telescopic support arms, one clamp, one clamp base and a pair measurement arm, owing to alignment system of the present invention uses the design of Multi-section telescopic support arm, therefore the operating distance of alignment system it is effectively improved, it is made just to play positioning action in larger distance, and be all always maintained at effectively working installing during garage enters final operating position, therefore the present invention is actually a kind of lasting alignment system, and the precision of system improves along with installing car and reducing of aircraft engine nacelle distance.Alignment system based on the present invention and localization method that research design goes out, then can subsystem degree deviation and lateral displacement deviation carry out accurately and effectively measuring and controlling, lateral displacement deviation uses the mode that coarse positioning and fine positioning combine so that the localization method that the present invention provides is accurately, quickly, efficiently.
Description
Technical field
The present invention relates to a kind of aircraft engine installing vehicle alignment system and localization method thereof, belong to aircraft engine peace
Packing technique field.
Background technology
Aircraft engine installing vehicle is a kind of important airplane synthetic guarantee equipment, for the installation of electromotor, dismounting and
Oil sealing etc., also have the short time deposit and short distance transhipment electromotor function.
Modern air-jet engine weight and size are big, fixing connection complexity aboard, need to be accurately positioned, the most slightly
Waist uses electromotor to install this special equipment of car.
At present, jet engine installs car owner's visual fix to be used and the mode of auxiliary locator location.The most fixed
Position subject matter be: location inaccuracy, fully rely on experience and the object of reference of operator, it usually needs be repeated several times operation and
Adjust, therefore waste time and energy, and can not effectively ensure efficiency, time and the prescription that electromotor is installed.Auxiliary positioning fills
The subject matter putting location is: this type of positioner is mostly fixed on installation car, and operating distance is little, needs to install car close to
Competence exertion effect during whole operating position, and if positioning inaccurate, then after needing to retreat relatively at a distance installation car further along
Propelling is reorientated.And install car leave aircaft configuration relatively remote after, visual fix can only be leaned on again, so major part location work
Also it is dependent on visually；Need and in aircraft (enging cabin) structure additionally, available engine installs the positioner on car
Positioning datum or the positioner drawn from it with the use of, modular design is to make two alignment pins on car and enging cabin
Two datum holes in structure align, and are actually intended to carry out the accurate control of angles and positions deviation, it is achieved get up non-simultaneously
Often difficulty.
Summary of the invention
For above not enough, the present invention provides a kind of aircraft engine installing vehicle alignment system and localization method thereof.
Technical scheme: aircraft engine installing vehicle alignment system, this alignment system includes that two set multistages are stretched
Arm is measured in contracting support arm, a clamp, a clamp base and a pair, and wherein two set telescopic boom are placed in parallel and are separately mounted to
Installing the outside of two longitudinal rails of Herba Plantaginis end, described telescopic boom uses multi-joint telescoping structure, is positioned at the final section of rear end
Support arm is connected as canned paragraph and longitudinal rail are fixing, and the some joints being positioned at front end can freely stretch as active segment or shorten,
It is carved with size scale line on first segment support arm the most foremost；Described clamp base is put together by three sections of slots, described card
Plate is plugged on clamp base by slot, and clamp short transverse position is adjustable, and clamp base is transversely mounted on foremost first
Linking into an integrated entity on the end of joint support arm and by two set telescopic boom, the plate face of described clamp is vertical with the axis of telescopic boom,
The interior profile of described clamp is consistent with enging cabin profile (having the skew of about 100-200mm)；The pair of measurement arm level phase
To placement, each measurement arm is separately mounted on two first segment support arms foremost and relatively can make fortune of sliding by this joint support arm
Dynamic, each measurement arm is connected with vertical section by cradle head respectively, vertical section then pass through mounting seat-sleeve and foremost the
One joint support arm vertically connects, and described measurement arm and vertically section are all carved with size scale line.
The final section support arm of described telescopic boom uses fast joint structure with the junction of longitudinal rail, is specially
Being fixed with plural C-shaped mounting seat on longitudinal rail, the outside weldings of final section support arm has locating piece, locating piece and C
Shape mounting seat is connected.
Described C-shaped mounting seat includes open C shape part, opening inner washer and base respectively, and wherein base is installed with electromotor
Car guide rail connects, and opening inner washer is between open C shape part inwall and final section support arm outer wall, and C-shaped piece opening portion leads to
Crossing draw-in groove and knuckle joint is provided with hasp/hasp lock and quickly connects fixing and provision for disengagement, described hasp/hasp lock quickly connects
Connecing to fix and design for standard with provision for disengagement, it includes straight-flanked ring hasp and mounting seat-spanner and adnexa.
The end of described measurement arm and the contact surface of enging cabin structure are provided with rubber cover, and this rubber cover can
To use elastic or spring charging device, it is therefore an objective to ensure that measuring arm fits with enging cabin close structure, to obtain accurately
Measurement data.
Described clamp use hard plastic board, thickness is 8-15mm, and the interior profile of described clamp be coated with rubber layer or
It is bonded with protection adhesive tape, the surface of enging cabin of can avoiding damaging.
Connect in the front of clamp base and have crossbeam handle, manually launching and shrinkage operation as whole alignment system
Handle.
The localization method of aircraft engine installing vehicle, have employed above-mentioned aircraft engine installing vehicle alignment system, its bag
Include regulation of longitudinal angle deviation and the measurement of lateral displacement deviation and control, method particularly includes:
(1) for measurement and the control of regulation of longitudinal angle deviation: first, obtain with cutting transverse section according to a certain height levels
To intersection be transverse axis to choose aircraft reference section transverse axis and to install car clamp face with reference to transverse axis；Secondly, survey aircraft reference
Section transverse axis and the angle of installation car clamp face reference transverse axis；Finally, by controlling aircraft reference section transverse axis and installing car card
Plate face makes the angle of deviation control at 0.5-1 ° with reference to the angle of transverse axis；The measurement of described regulation of longitudinal angle deviation is concrete with control method
For: first, use measurement arm to take two measurement point m1 and m2 on same level height on enging cabin structural edge face,
Two distances measured between point are L, and L is less than the spacing between two set telescopic boom；Secondly, utilize and measure arm and matched
Prop up arm measure with graduated first segment and obtain measuring point m1 and m2 to air line distance L1 in clamp face and L2. both subtract each other
To difference △ L, then angu-lar deviation △ θ ≈ (△ L/L) × (360 °/2 π)；Finally, according to above-mentioned formula, can be by controlling
△ L makes the angle of deviation control at 0.5-1 °, i.e. carrys out control deviation angle by control linear dimension air line distance difference；
(2) for measurement and the control of lateral displacement deviation: include bigness scale and accurate measurement two ways, bigness scale mode is applicable to
Coarse positioning on remote, i.e. when telescopic boom is at or approximately at maximum extension state, by the range estimation specific erect-position of aircraft
The enging cabin external surface in face and the deviation of profile in electromotor installation car coarse positioning clamp, preliminary judgement range deviation, and can
Monitor angular deviation simultaneously；Accurate measurement mode is applicable at the precise positioning closely gone up, and i.e. uses measurement arm measure m1 and m2 to arrive
Distance L3 in the centrosymmetry face of two set telescopic boom and L4, both difference half are lateral attitude deviation.
Beneficial effects of the present invention: the present invention, by using the design of Multi-section telescopic support arm, is effectively improved alignment system
Operating distance so that it is just play positioning action in larger distance, and during installation garage enters final operating position
All being always maintained at effectively working, therefore the present invention is actually a kind of lasting alignment system, and the precision of system is along with installing car
Improve with reducing of aircraft engine nacelle distance；The alignment system of the present invention not only has the spies such as simple and practical, easy and simple to handle
Point, and ensure that electromotor installs car location and the efficiency of electromotor installation exercise and quality；The localization method of the present invention
Subsystem degree deviation and lateral displacement deviation have carried out accurately and effectively measuring and controlling, and lateral displacement deviation uses coarse positioning
The mode combined with fine positioning so that the localization method that the present invention provides is accurately, quickly, efficiently.
Accompanying drawing explanation
Fig. 1 is the overall schematic of alignment system of the present invention.
Fig. 2 is the A direction view (clamp part) in Fig. 1.
Fig. 3 is the B direction view (measurement arm section) in Fig. 1.
Fig. 4 is the connection diagram of C-shaped mounting seat and longitudinal rail.
Detailed description of the invention
As it is shown in figure 1, aircraft engine installing vehicle alignment system, this alignment system include two set Multi-section telescopic support arms 3,
4, clamp base 5 of one clamp and a pair measurement arm 6, wherein two set telescopic boom 3 are placed in parallel and are separately mounted to peace
The outside of two longitudinal rails 2 in entrucking front end, described telescopic boom 3 uses multi-joint telescoping structure, is positioned at the final section of rear end
Support arm is connected as canned paragraph is fixing with longitudinal rail 2, and the some joints being positioned at front end can freely stretch as active segment or shorten,
It is carved with size scale line on first segment support arm 10 the most foremost.Clamp 4 and clamp base 5 are transversely mounted on foremost first
On the end of joint support arm 10, connect in the front of clamp base 5 and have crossbeam handle 11.
As in figure 2 it is shown, described clamp base 5 is put together by three sections of slots, described clamp 4 is plugged on clamp by slot
On base 5, being rapidly assembled and disassembled of clamp 4 can be realized, and be convenient for changing the clamp of different profile, with applicable different electromotors
The location in cabin needs, thus ensure that the present invention installs the versatility of car.Clamp base 5 is transversely mounted on first segment foremost and props up
Link into an integrated entity on the end of arm 10 and by two set telescopic boom 3, make alignment system have enough bonding strengths and rigidity.Institute
The plate face stating clamp 4 is vertical with the axis of telescopic boom 3, and described clamp 4 uses hard plastic board, and thickness is 8-15mm, clamp 4
Interior profile profile consistent and interior with enging cabin 1 profile be coated with rubber layer or be bonded with protection adhesive tape.
As it is shown on figure 3, the pair of measurement arm 6 is placed horizontally towards each other, each measurement arm is separately mounted to two foremost
First segment support arm 10 on and relatively can make sliding motion by this joint support arm, each measurement arm respectively by cradle head 7 with perpendicular
Straight section 8 connects, and vertical section 8 is then connected with first segment support arm 10 vertical sliding motion foremost by mounting seat-sleeve 9, measures arm 6
May be implemented in a range of adjustable angle and height adjustable.Described mounting seat-sleeve 9 can not rotate relative to support arm, as
Really support arm cross section is circular, then need to output anti-rotation groove on support arm, is correspondingly provided with cooperation at mounting seat-sleeve 9 simultaneously
Flange.Described measurement arm and vertically section 8 are all carved with size scale line, measure the end of arm and the contact surface of enging cabin 1 structure
It is provided with rubber cover.
As shown in Figure 4, the final section support arm of described telescopic boom 3 uses with the junction of longitudinal rail 2 and is quickly connected
Structure, is specially and is fixed with plural C-shaped mounting seat on longitudinal rail 2, and the outside weldings of final section support arm has fixed
Position block, locating piece is connected with C-shaped mounting seat.Described C-shaped mounting seat includes open C shape part, opening inner washer 15 and respectively
Base, wherein base is connected with electromotor installation car guide rail 2, and opening inner washer 15 is positioned at open C shape part inwall and final section
Between support arm outer wall, C-shaped piece opening portion is provided with hasp/hasp lock by draw-in groove and knuckle joint and quickly connects fixing and tear open
Handler 13, described hasp/hasp lock quickly connects fixing and provision for disengagement 13 and designs for standard, it include straight-flanked ring hasp with
Mounting seat-spanner and adnexa.
The requirement of alignment system of the present invention and localization method thereof is electromotor to be installed car longitudinal direction datum axis send out with aircraft
The mounting axis of motivation 12 aligns, and angular deviation (at horizontal plane) between two axial lines is controlled within the specific limits (about
0.5-1 °), electromotor is installed special datum point and corresponding point in aircraft engine mounting axis on car datum axis simultaneously
Lateral deviating distance controls within the specific limits, such as ± 10-20mm.
Based on considering that directly carrying out longitudinal axis aligns and there is technical barrier, localization method of the present invention changes Traditional Thinking side
Formula, uses the transverse section/transverse axis vertical with longitudinal datum axis to carry out amount of deflection measurement and control, and then realizes the most accurate
Location.Described transverse section is front end clamp 4 and the structural edge face of a certain erect-position of aircraft engine nacelle 1.Owing to electromotor is pacified
During dress, aircraft is jack-uped level, and electromotor is installed roof and also adjusted to level, therefore certain height level
The intersection that face obtains with cutting transverse section is transverse axis, including aircraft reference section transverse axis and installation car clamp face reference transverse axis.
The method measuring two transverse axis (aircraft reference section transverse axis and installation car clamp face are with reference to transverse axis) angle: first, make
Taking two measurement point m1 and m2 on same level height on enging cabin structural edge face with measuring arm, two measure point
Between distance be the spacing that L(is slightly less than between two set telescopic boom)；Secondly, utilize and measure arm and matched with scale
First segment prop up arm measure and obtain measuring point m1 and m2 to air line distance L1 in clamp face and L2. both subtract each other and obtain difference △
L, then angu-lar deviation △ θ ≈ (△ L/L) × (360 °/2 π)；Finally, according to above-mentioned formula, deviation can be made by controlling △ L
Angle controls at zone of reasonableness, i.e. carrys out control deviation angle by control linear dimension air line distance difference.
The present invention has bigness scale and accurate measurement two ways for lateral deviating distance.Bigness scale mode is applicable on remote
Coarse positioning, i.e. when telescopic boom is at or approximately at maximum extension state, by estimating the enging cabin in aircraft specific erect-position face
External surface and the deviation of profile, preliminary judgement range deviation in electromotor installation car coarse positioning clamp, and angle can be monitored simultaneously
Deviation.Accurate measurement mode is applicable at the precise positioning closely gone up, and i.e. uses measurement arm measure m1 and m2 fixed to installing car both sides
Distance L3 of position benchmark (being approximately the centrosymmetry face of two set telescopic boom) and L4, both difference half are that lateral attitude is inclined
Difference.
During work, operator promotes electromotor to install car (location installed the most by electromotor 12) from original position to
In the traveling process of whole operating position, alignment system realizes electromotor and installs the car continuous positioning relative to aircraft, by both
Benchmark longitudinal axis drift angle and lateral attitude deviation control in the least scope so that the work that car accurately reaches final installed by electromotor
Make position.Hereafter, electromotor installation is put in place by operator by installing the feeding of car, lifting and micro-tensioning system.
Claims (7)
1. aircraft engine installing vehicle alignment system, is installed on electromotor and installs on car, it is characterised in that: this alignment system bag
Including two sets Multi-section telescopic support arm (3), a clamp (4), a clamp base (5) and a pair and measure arm (6), wherein two sets are flexible
Support arm (3) is placed in parallel and is separately mounted to install the outside of two longitudinal rails (2) of Herba Plantaginis end, and described telescopic boom (3) is adopted
Using multi-joint telescoping structure, the final section support arm being positioned at rear end is connected as canned paragraph and longitudinal rail (2) are fixing, is positioned at front end
Some joints can freely stretch as active segment or shorten, first segment support arm (10) the most foremost is carved with size scale
Line；Described clamp base (5) is put together by three sections of slots, and described clamp (4) is plugged on clamp base (5) by slot,
Clamp base (5) is transversely mounted on the end of first segment support arm (10) foremost and two sets telescopic boom (3) is connected into one
Body, the plate face of described clamp (4) is vertical with the axis of telescopic boom (3), the interior profile of described clamp (4) and enging cabin (1)
Profile is consistent；The pair of measurement arm (6) is placed horizontally towards each other, and each measurement arm is separately mounted to two first segments foremost
Support arm (10) is upper and relatively can make sliding motion by this joint support arm, and each measurement arm is respectively by cradle head (7) and vertical section
(8) connecting, vertical section (8) is then connected by mounting seat-sleeve (9) is vertical with first segment support arm (10) foremost, described survey
Amount arm and vertically section (8) are all carved with size scale line；The final section support arm of described telescopic boom (3) and longitudinal rail (2)
Junction uses fast joint structure, is specially and is fixed with plural C-shaped mounting seat on longitudinal rail (2), last
The outside weldings of joint support arm has locating piece, locating piece to be connected with C-shaped mounting seat.
2. aircraft engine installing vehicle alignment system as claimed in claim 1, it is characterised in that: described C-shaped mounting seat is divided
Not including open C shape part, opening inner washer (15) and base, wherein base is connected, in opening with electromotor installation car guide rail (2)
Packing ring (15) is between open C shape part inwall and final section support arm outer wall, and draw-in groove and hinge-connection are passed through in C-shaped piece opening portion
Head is provided with hasp/hasp lock and quickly connects fixing and provision for disengagement (13), and described hasp/hasp lock quickly connects fixing and tears open
Handler (13) designs for standard, and it includes straight-flanked ring hasp and mounting seat-spanner and adnexa.
3. aircraft engine installing vehicle alignment system as claimed in claim 1, it is characterised in that: the end of described measurement arm
It is provided with rubber cover with the contact surface of enging cabin (1) structure.
4. aircraft engine installing vehicle alignment system as claimed in claim 1, it is characterised in that: described clamp (4) uses
Hard plastic board, thickness is 8-15mm, and the interior profile of described clamp (4) is coated with rubber layer or is bonded with protection adhesive tape.
5. aircraft engine installing vehicle alignment system as claimed in claim 1, it is characterised in that: at clamp base (5)
Front connects crossbeam handle (11).
6. the localization method of aircraft engine installing vehicle, have employed aircraft engine installing vehicle as claimed in claim 1 with fixed
Position system, it is characterised in that include regulation of longitudinal angle deviation and the measurement of lateral displacement deviation and control, particularly as follows:
(1) for measurement and the control of regulation of longitudinal angle deviation: first, obtain according to a certain height levels and cutting transverse section
Intersection is that transverse axis is to choose aircraft reference section transverse axis and to install car clamp face with reference to transverse axis；Secondly, survey aircraft reference section
Transverse axis and the angle of installation car clamp face reference transverse axis；Finally, by controlling aircraft reference section transverse axis and installing car clamp face
The angle of reference transverse axis makes the angle of deviation control at 0.5-1 °；
(2) for measurement and the control of lateral displacement deviation: include bigness scale and accurate measurement two ways, bigness scale mode is applicable to far
Apart from upper coarse positioning, i.e. when telescopic boom is at or approximately at maximum extension state, by range estimation aircraft specific erect-position face
Enging cabin external surface and the deviation of profile in electromotor installation car coarse positioning clamp, preliminary judgement range deviation, and can be simultaneously
Monitoring angular deviation；Accurate measurement mode is applicable at the precise positioning closely gone up, and i.e. uses and measures arm measure m1 and m2 to two set
Distance L3 in the centrosymmetry face of telescopic boom and L4, both difference half are lateral attitude deviation.
7. the localization method of aircraft engine installing vehicle as claimed in claim 6, it is characterised in that described regulation of longitudinal angle deviation
Measurement and control method particularly as follows: first, use and measure arm and take two in same level on enging cabin structural edge face S
Measurement point m1 and m2 on height, two distances measured between point are L, and L is less than the spacing between two set telescopic boom；Secondly,
Utilize and measure arm and matched carry graduated first segment to prop up arm measure to obtain measuring the straight line putting m1 and m2 to clamp face
Distance L1 and L2. both subtract each other and obtain difference △ L, then angu-lar deviation △ θ ≈ (△ L/L) × (360 °/2 π)；Finally, according to
Above-mentioned formula, can make the angle of deviation control at 0.5-1 ° by controlling △ L, i.e. next by controlling linear dimension air line distance difference
Control deviation angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510137599.8A CN104724300B (en) | 2015-03-27 | 2015-03-27 | Aircraft engine installing vehicle alignment system and localization method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510137599.8A CN104724300B (en) | 2015-03-27 | 2015-03-27 | Aircraft engine installing vehicle alignment system and localization method thereof |
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| Publication Number | Publication Date |
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| CN104724300A CN104724300A (en) | 2015-06-24 |
| CN104724300B true CN104724300B (en) | 2016-12-07 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564605B (en) * | 2016-10-26 | 2019-01-11 | 湖北航天技术研究院总体设计所 | The built-in engine installation structure of aircraft and its walk assembly method |
| CN107356175A (en) * | 2017-08-28 | 2017-11-17 | 安徽安凯汽车股份有限公司 | A kind of locating and detecting device of engine mounting holes |
| CN112461071B (en) * | 2020-11-20 | 2023-12-01 | 中国人民解放军63698部队 | Method for measuring repeated installation errors of inertial navigation equipment |
| CN114353623B (en) * | 2022-01-07 | 2024-03-12 | 中国航发贵阳发动机设计研究所 | Measuring ruler and method for airplane accessory case loader |
| CN116086340B (en) * | 2023-04-07 | 2023-07-21 | 成都飞机工业（集团）有限责任公司 | Method, device, equipment and medium for measuring level of whole aircraft |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5816367A (en) * | 1995-11-30 | 1998-10-06 | Stanley Aviation Corporation | Jet aircraft engine transport apparatus |
| WO1999002404A1 (en) * | 1997-07-07 | 1999-01-21 | Stanley Aviation Corporation | Shipping frame for fan section of aircraft engine |
| GB0613929D0 (en) * | 2006-07-13 | 2006-08-23 | Rolls Royce Plc | An engine core stand arrangement and method of removal and transportation of an engine core |
| US8262050B2 (en) * | 2008-12-24 | 2012-09-11 | General Electric Company | Method and apparatus for mounting and dismounting an aircraft engine |
| US10160076B2 (en) * | 2012-09-18 | 2018-12-25 | The Boeing Company | Edge stabilizing system and method for composite barrel segments |
| CN103935528B (en) * | 2014-05-05 | 2016-01-20 | 沈阳飞研航空设备有限公司 | Dismounting engine motorcycle |
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