CN104384920B - A kind of light helicopter structural member assembly devices and methods therefor - Google Patents
A kind of light helicopter structural member assembly devices and methods therefor Download PDFInfo
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- CN104384920B CN104384920B CN201410424669.3A CN201410424669A CN104384920B CN 104384920 B CN104384920 B CN 104384920B CN 201410424669 A CN201410424669 A CN 201410424669A CN 104384920 B CN104384920 B CN 104384920B
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- locator
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- fuselage
- reference platform
- type frame
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P21/00—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control
- B23P21/002—Machines for assembling a multiplicity of different parts to compose units, with or without preceding or subsequent working of such parts, e.g. with programme control the units stationary whilst being composed
Abstract
A kind of helicopter structure part assembly device and assembly method, belong to helicopter general assembly field.It is characterized in that installing fuselage main framing locator in the middle part of the stand column and beam of " 7 " font semi open type, fuselage is realized simultaneously by the way of interior positioning and being driven the location and installation of two Large Structure Systems.The unification of reference for assembling is realized between the different system structure of helicopter.It is small particular for light-duty unmanned helicopter airframe structure, the characteristics of narrow space, the assembly method is using the principle for concentrating assembly, reduce positioning link, so that assembly work reduction of area is small, it not only solves helicopter fuselage structure and is driven the coordination sex chromosome mosaicism of Standard between two big systems, ensure that structural member assembly precision, also improve efficiency of assembling.
Description
Technical field
The present invention relates to a kind of light helicopter structural member assembly jig and its assembly methods, belong to helicopter final assembly technique
Field.
Background technology
The assembly of light helicopter structural member includes mainly airframe structure assembly and conventional system architecture assembly, it is helicopter
Primary link during general assembly, it is maximum that assembly work amount accounts for general assembly workload proportion.Due to the number of light helicopter structural member
Amount, size and weight are many smaller for large and medium-sized helicopter, therefore in the assembly idea and method of structural member
Also there is very big difference.The independent dress such as fuselage, endpiece and undercarriage before, during and after traditional helicopter fuselage structure is generally divided into
With unit, assembly generally takes the form of sectional and component Butt Assembling, this assembly method to bring rapport
Complexity, and coordinating order of accuracy require it is also very high, and drive system structure part be after the completion of airframe structure assembly again therewith
Coordinate installation, the structure installation of two systems is that front and back substep is independent.This structural member assembly method is mainly used in big-and-middle
Type helicopter reduces assembly work amount on frame its purpose is to expand assembly work face, improves and criticizes production efficiency, but for
For the Standard of light helicopter, the fitting surface of transition dispersion not only increases type frame quantity, while bringing coordination link
It is more more complicated.
Invention content
The purpose of the present invention：A kind of light helicopter structural member assembly devices and methods therefor is proposed, can realize light-duty nothing
The requirement of people's (or someone) helicopter fuselage positioning assembly synchronous with two big system component of transmission.It is light-duty straight the purpose is to improve
Machine airframe structure system general assembly and its assembly coordination accuracy between drive system structure part are risen, structural member assembly essence is improved
Degree and efficiency of assembling.
Technical scheme of the present invention：
(1) assembly technology scheme
The technology invention is assembled for compact-sized, the process characteristic of narrow space of light helicopter using concentrating
Principle, it is determined that between two big system of transmission and airframe structure use same reference for assembling basic scheme.Program master
If being main coordination means with assembly jig, using the fuselage main framing positioned at airframe structure stage casing as primary location and installation
Part, remaining airframe structure part and drive system structure part are coordinated to install by it with assembly jig, solve helicopter general assembly
In the mostly important two big component of a system of airframe structure and drive mechanism assembly positioning.Middle fuselage skeleton is in type frame using interior
The positioning method of positioning.
(2) the characteristics of assembly jig
Assembly jig is the necessary means for realizing this assembling method.Assembly jig is usually by type frame main structure, structure
The compositions such as locator, adjustable jacking mechanism.Type frame is using the assembly technology benchmark of light helicopter transmission system as design basis.It should
Benchmark generally takes rotor centers axis and its mounting surface on Helicopter Main Reducer.The establishment of this benchmark realizes type frame design
Benchmark, assembly technology benchmark and the coincidence for detecting measuring basis.Advantageously ensure that installation of the transmission system in assembly jig
Accuracy, airframe structure part are equally installed with this technological datum.Reference Transforming in this way makes airframe structure and transmission
System structure technological datum is realized unified.Visible Fig. 3 of transformational relation of benchmark.
(3) structural member installs implementation steps
The first step：Before the assembly of airframe structure part, fuselage main framing locator bottom benchmark is detected by support post first
Plane whether shift relative to the relative altitude value h (see Fig. 1) of type frame main structure base platform and its bottom plane or
Torsion.The height of support post and the location hole 6- Φ C (see Fig. 1) of end face are utilized when detection, be aided with clearance gauge and standard pin into
Row detection.
Second step：Fuselage main framing is located by connecting by fuselage main framing bottom platform location hole 6- Φ C (see Fig. 1).
Number 6 depends on the quantity in hole.Platform location hole takes the main reducing gear positioning hole on fuselage main framing platform.After positioning
Fuselage main framing is held out against by adjustable jacking mechanism again so that fuselage main framing realizes fixation in type frame main structure.This opportunity
Body main framing is in steady status in type frame main structure (see Fig. 4).
Third walks：Helicopter forebody component location and installation；Radome fairing other than radome fairing locator by way of positioning
Installation；Tail structure (beam containing tail pipe, flat, vertical fin) passes through drive system structure locator and tail aligner location and installation；Afterwards
Frame assembly is coordinated to install with type frame main structure, fuselage main framing and tail structure.Not due to different model structure forms
Equally, the positioning method of locating piece is changed according to actual conditions, and installation steps adjust according to actual needs.
4th step：Helicopter Transmission System device (including belt drive component, tail transmission component, tail reducer etc.) is to pass
Location and installation on the basis of dynamic system structure locator, tail aligner and J axis.It, can be substantially complete before airframe structure undercarriage
At the installation of transmission system.
Support post recovery after airframe structure undercarriage, is installed to type frame main structure pedestal reference platform five by the 5th step
On (1.e), to support type frame main structure rigid, type frame main structure is avoided to be conducted oneself with dignity and deformed.
Key point of the present invention：
For the general feature of light helicopter structural member assembly.Propose airframe structure and biography two system structure wholly
The method of the whole location and installation of part.The reference for assembling for having unified all key structure parts in a type frame, improves structure
Coordinating order of accuracy when part assembles.
In the assembly of fuselage main structure, reasonable to determine tab order and assemble sequence, usually first positioning has good rigid
The fuselage main framing of property, this is most important for the stability of Standard benchmark, such as certain type machine middle fuselage skeleton is in type frame
In positioning (see Fig. 4), fuselage main framing is usually to subtract the positioning hole of mounting platform and main framing locator using its master
Realize connection positioning.
When type frame main structure designs, it is proposed that " 7 " font column design.The type frame main structure of this semi open type is set
Meter, provides more spacious operating space.
Devise multiple reference platforms on assembly jig pedestal and each column, reference platform layout each column with
Pedestal junction, the junction of structural locator and pedestal and each column.For type frame main structure and locator and folder
Specific installation positioning.
The Standard type frame has fully considered the operation requirement that measurement is detected in assembling process.Type frame main structure pedestal base
Quasi- platform can provide measuring basis, also can be used as the mounting platform of measuring apparatus and instrument, such as pedestal reference platform eight
(1.h)。
Beneficial effects of the present invention：
The present invention proposes a kind of globality and systematic Standard type frame and method, it is in helicopter fuselage knot
Unify structure reference for assembling between structure and traditional two big systems, improves light helicopter structural member assembly precision and efficiency.It is suitable
For the assembly of nobody most light-duty (or someone) helicopter structure parts, this method has fully merged mounting technology, Fixture Design
Manufacturing technology, detection measuring technique are in one；Propose a kind of system new approaches of helicopter structure assembly.
Description of the drawings
Fig. 1 is the invention assembly jig overall pattern (front view)
Fig. 2 is the invention assembly jig overall pattern (left side view)
Fig. 3 is the invention Reference Transforming relational graph
Fig. 4 is the state diagram of the inventive embodiments middle fuselage main framing in type frame
Fig. 5 is pedestal figure in the inventive embodiments
Fig. 6 is middle part column figure in the inventive embodiments
Fig. 7 is the inventive embodiments middle fuselage main framing locator figure
Specific implementation mode
Below in conjunction with the accompanying drawings, the present invention is described in further details by taking certain type machine Standard as an example.
Type frame main structure：The type frame main structure includes pedestal 1, middle part column 2, support post 7 and tail portion column 6.Pedestal 1
In " Gu " character form structure, substructure height is designed as 600~620mm.Column 2 in the middle part of " 7 " font semi open type, provides more wide
Spacious operating space operates convenient for Standard.In order to reinforce the rigidity of " 7 " font column, reinforcing rib is set.Support post
7 and tail portion column 6 be " I " type straight-bar type.It is all made of square tube and platform welding structure on pedestal 1 and all columns, passes through machine
Add flatness, the height for ensureing all reference platforms.As shown in figure 5, reference platform one (1.a) and reference platform three (1.c) are used
In the installation of middle part column 2, adjustable jacking mechanism 8 and radome fairing locator 5；Reference platform five (1.e) is used to support column 7
Installation；Reference platform two (1.b) and reference platform four (1.d) are used for the installation of adjustable jacking mechanism 8 and radome fairing locator 5；
Reference platform six (1.f) is installed for rear body locator；Reference platform seven (1.g) is installed for tail portion column 6；Reference platform
Eight (1.h) are used as measuring table.
Structural locator：The main locator of type frame main structure has fuselage main framing locator 3, drive system structure positioning
Device 4, radome fairing locator 5, tail aligner 9.Fuselage main framing locator 3 is the simulating piece of main reducing gear, in the main knot of type frame
The inside of structure is installed in hanging shape on 2 crossbeam of column of middle part, it provide rotor shaft and transmission shaft both direction axis and
Coordinate systems of one installation bottom surface C as type frame main structure；Rotor axis direction is Z axis, and transmission shaft is X-axis, and Z axis crosses installation bottom surface
The face that C is vertically formed with X, Y-axis；3 bottom plane location hole of fuselage main framing locator is overlapped with installation retarder mounting hole position；
Drive system structure locator 4 is the apotting spindle for extending out from transmission input shaft axis direction, is installed on fuselage main framing
On locator 3；Radome fairing locator 5, in being all around laid out, passes through on middle part column 2 and pedestal 1 points in type frame main structure
8 reference platform anchor points, structure type are indescribably supplied to be generally fuselage appearance snap-gauge.Tail aligner 10 passes through tail portion column
6 location and installations coordinate the positioning for providing afterbody and tail transmission component with drive system structure locator 4 (see Fig. 1).Before,
Rear body locator category conventional positioner, herein without explanation.
Adjustable jacking mechanism 8 is the clamp body in type frame main structure (see Fig. 1).After it can realize the positioning of fuselage main framing,
Realization is adjusted by the structure in tri- directions X, Y, Z to hold out against.
Type frame pedestal 1 is installed on solid horizontal foundation.Size when type frame main structure installation and debugging is coordinated with fuselage
On the basis of rotor centers axis and its baseplane on main framing locator.It is correct in type frame main structure in order to detect the benchmark
Property, it avoids type frame main structure from causing benchmark to change because a variety of causes deforms in manufacture and using process, support post 7 can be used
Detection.Support post 7 is used to detect the installation condition of fuselage main framing locator 3.Matched with standard setting pin and clearance gauge when detection
Close detection.Another effect of support post 7 is to be used to support the rigidity of type frame main structure.
Structural member installs implementation steps：
The first step：Before the assembly of airframe structure part, 3 bottom base of fuselage main framing locator is detected by support post 7 first
Whether directrix plane deforms relative to the height value of type frame pedestal 1 and bottom location hole position.It is vertical that support is utilized when detection
The height of column 7 and the location hole 6- Φ C (see Fig. 1) of end face, are aided with clearance gauge and standard pin are detected.
Second step：Fuselage main framing is located by connecting by reference platform location hole.Main reducing gear positioning hole is located at
11 middle part of fuselage main framing, is mounting-positioning holes of the main reducing gear on airframe structure.Fuselage main framing after positioning passes through again
Adjustable jacking mechanism 8 is held out against so that fuselage main framing realizes fixation in type frame main structure.Fuselage main framing 11 is in type frame at this time
State in main structure is shown in Fig. 4.
Third walks：Helicopter forebody component location and installation；Radome fairing other than radome fairing locator 5 by way of positioning
Installation；Tail structure (beam containing tail pipe, flat, vertical fin) passes through 9 location and installation of drive system structure locator 4 and tail aligner；
Rear body component is coordinated to install with type frame main structure, fuselage main framing and tail structure.Due to different model structure forms
Different, the positioning method of locating piece is changed according to actual conditions, and installation steps adjust according to actual needs.
4th step：Helicopter Transmission System device (including belt drive component 12, tail transmission component, tail reducer etc.) is logical
Cross location and installation on the basis of drive system structure locator 4 and tail aligner 9.It, can be basic before fuselage main structure undercarriage
Complete the installation of transmission system.
After airframe structure undercarriage, the recovery of support post 7 is installed on 1 reference platform of type frame pedestal, five 1.e for 5th step,
To support type frame main structure rigid, type frame main structure is avoided to be conducted oneself with dignity and deformed.
Claims (10)
1. a kind of light helicopter structural member assembles device, which is characterized in that including type frame main structure, structural locator and adjustable
Jacking mechanism (8), type frame main structure include pedestal (1), middle part column (2), support post (7) and tail portion column (6)；Structure is fixed
Position device includes fuselage main framing locator (3), drive system structure locator (4), radome fairing locator (5), forebody positioning
Device, rear body locator, tail aligner (9)；Fuselage main framing locator (3) is the simulating piece of main reducing gear, provides master
The axis and an installation bottom surface C of retarder rotor shaft and transmission shaft both direction are as type frame main structure coordinate system；Rotor shaft
Direction is Z axis, and transmission axis direction is X-axis, and Y-axis crosses installation bottom surface C perpendicular to the faces XZ；Drive system structure locator (4) is from biography
The apotting spindle that driven input shaft axis direction extends out is installed on fuselage main framing locator (3)；Radome fairing locator
(5) structure type is fuselage appearance snap-gauge, and layout is all around total to everywhere in type frame main structure；Tail aligner (9) is logical
Cross tail portion column (6) location and installation.
2. light helicopter structural member according to claim 1 assembles device, which is characterized in that the pedestal (1) uses
Square tube and plate welding, shape are in " Gu " character form structure, and substructure height is 600~620mm；It is equipped with reference platform one in pedestal
(1.a), reference platform two (1.b), reference platform three (1.c), reference platform four (1.d), reference platform five (1.e), benchmark are flat
Platform six (1.f), reference platform seven (1.g) and reference platform eight (1.h), layout are fixed in each column and pedestal junction and structure
Position device installation place, provides type frame main structure and structural locator location and installation benchmark；Wherein reference platform one (1.a) and benchmark
Platform three (1.c) is used for the installation of middle part column (2), adjustable jacking mechanism (8) and radome fairing locator (5)；Reference platform five
(1.e) is used to support the installation of column (7)；Reference platform two (1.b) and reference platform four (1.d) are used for adjustable jacking mechanism
(8) and the installation of radome fairing locator (5)；Reference platform six (1.f) is installed for rear body locator；Reference platform seven
(1.g) is installed for tail portion column (6)；Reference platform eight (1.h) is used as measuring table.
3. light helicopter structural member according to claim 1 assembles device, which is characterized in that the middle part column (2),
Support post (7) and tail portion column (6) are all made of square tube and tablet welding structure；Wherein, middle part column (2) is " 7 " font half
Open type frame structure, middle part column (2) are equipped with reference platform nine (2.a), reference platform ten (2.b), reference platform 11
The installation that (2.c) and reference platform 12 (2.d), wherein reference platform 11 (2.c) provide fuselage main framing locator (3) is flat
Platform；Reference platform 12 (2.d) is middle part column (2) in the mounting platform of pedestal；Support post (7) and tail portion column (6) are equal
For " I " shape straight-bar type, platform on the basis of upper lower platform.
4. light helicopter structural member assembles device according to claim 1, which is characterized in that the fuselage main framing positioning
Two orientation axis of device (3) are overlapped with the output of installation retarder and input axis respectively；Bottom plane location hole and installation
Retarder mounting hole position overlaps；It is installed on column (2) crossbeam of middle part in hanging shape in the inside of type frame main structure.
5. light helicopter structural member according to claim 1 assembles device, which is characterized in that the drive system structure
Locator (4) apotting spindle axis is overlapped with afterbody locator (9) axis；Drive system structure locator (4) positioning peace
Loaded on fuselage main framing locator.
6. light helicopter structural member according to claim 1 assembles device, which is characterized in that the radome fairing locator
(5) it is fuselage radome fairing shape snap-gauge, is installed between middle part column (2) and pedestal (1), with the faces Y0 all around symmetrical cloth
Office provides the coordination of radome fairing shape.
7. light helicopter structural member according to claim 1 assembles device, which is characterized in that the tail aligner
(9) it is installed on tail portion column (6) reference platform, coordinates with drive system structure locator (4) and afterbody and tail biography are provided
The reference for installation of dynamic component.
8. light helicopter structural member according to claim 1 assembles device, which is characterized in that the adjustable jacking mechanism
(8) adjusting on tri- change in coordinate axis direction of XYZ may be implemented, realize and hold out against from bottom after being positioned for fuselage main framing.
9. a kind of light helicopter structural member assembly method, which is characterized in that include the following steps：
The first step：Fuselage main framing main reducing gear mounting hole is fixed by fuselage main framing locator (3) bottom plane location hole
Position connection, fuselage main framing main reducing gear mounting hole are normally in the middle part of skeleton, and the fuselage main framing after positioning is again by adjustable
Jacking mechanism (8) is held out against so that fuselage main framing realizes fixation in type frame main structure, and fuselage main framing (11) is in type frame at this time
Stable state is in main structure；
Second step：Helicopter forebody component, middle fuselage component, rear body component are with type frame main structure and fuselage main framing (11)
Coordinate installation；
Third walks：Helicopter tail structure is fixed on the basis of drive system structure locator (4), tail aligner (9) and J axis
Position installation, since different type forebodys and endpiece structure is different, the positioning method of locating piece is changed according to actual conditions；
4th step：The tail that helicopter fuselage tail structure and its inside are positioned using drive system structure locator (4) is driven knot
Structure, before airframe structure undercarriage, installation radome fairing of being had a competition by way of being positioned other than radome fairing locator (5), and complete
The location and installation of drive system structure part；
5th step after airframe structure undercarriage, support post (7) recovery is installed in type frame main structure, to support the main knot of type frame
Structure rigidity, avoids type frame main structure from being conducted oneself with dignity and deformed.
10. light helicopter structural member assembly method according to claim 9, which is characterized in that in the first step machine
Before the assembly of body structure part, fuselage main framing locator (3) bottom plane is detected relative to type frame bottom by support post (7) first
Seat (1) reference platform five (1.e) relative altitude value h and fuselage main framing locator (3) bottom plane C mounting holes position whether
It shifts or reverses, the location hole of the height and end face of support post (7) is utilized in when detection, is aided with clearance gauge and the inspection of standard pin
It surveys.
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| CN201410424669.3A CN104384920B (en) | 2014-08-26 | 2014-08-26 | A kind of light helicopter structural member assembly devices and methods therefor |
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| CN201410424669.3A CN104384920B (en) | 2014-08-26 | 2014-08-26 | A kind of light helicopter structural member assembly devices and methods therefor |
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| CN104384920B true CN104384920B (en) | 2018-10-02 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104787302B (en) * | 2015-04-07 | 2017-11-03 | 中国直升机设计研究所 | A kind of attachment structure between tilting radome fairing and cant beam |
| CN105195990B (en) * | 2015-10-12 | 2017-10-31 | 湖北三江航天红阳机电有限公司 | One kind riveting type frame method for processing and assembling |
| CN106695319B (en) * | 2016-11-25 | 2018-11-30 | 北京强度环境研究所 | A kind of conjunction cover method of radome fairing in vibration tower |
| CN107585324A (en) * | 2017-10-11 | 2018-01-16 | 重庆通用飞机工业有限公司 | A kind of tail boom assembly fixture |
| CN108454878B (en) * | 2018-04-28 | 2020-08-18 | 成都致冠科技有限公司 | Assembly method of modular unmanned helicopter |
| CN111038733B (en) * | 2019-12-26 | 2023-07-07 | 航天神舟飞行器有限公司 | Unmanned helicopter frame assembly fixture |
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| CN1064897C (en) * | 1997-04-16 | 2001-04-25 | 西科尔斯基飞机公司 | Apparatus and method for assembling a helicopter main rotor blade subassembly |
| CN103818554A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Helicopter smoke generator mounting support |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6546616B2 (en) * | 2000-12-15 | 2003-04-15 | Bell Helicopter Textron Inc. | Six-axis alignment and installation tool |
| JP2013052853A (en) * | 2011-08-31 | 2013-03-21 | Ntc Ltd | Main rotor maintenance equipment |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1064897C (en) * | 1997-04-16 | 2001-04-25 | 西科尔斯基飞机公司 | Apparatus and method for assembling a helicopter main rotor blade subassembly |
| CN103818554A (en) * | 2012-11-16 | 2014-05-28 | 哈尔滨飞机工业集团有限责任公司 | Helicopter smoke generator mounting support |
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