CN104118575A - Aircraft main landing gear hatch door assembling coordinate platform - Google Patents
Aircraft main landing gear hatch door assembling coordinate platform Download PDFInfo
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- CN104118575A CN104118575A CN201310145376.7A CN201310145376A CN104118575A CN 104118575 A CN104118575 A CN 104118575A CN 201310145376 A CN201310145376 A CN 201310145376A CN 104118575 A CN104118575 A CN 104118575A
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- hatch door
- aircraft
- landing gear
- main landing
- frame
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Abstract
The invention belongs to the technical field of aircraft assembling, and relates to an aircraft main landing gear hatch door assembling coordinate platform which comprises a foundation, a main frame, hatch door intersection positioning assemblies, hatch door appearance detecting boards, main landing gear fairing process fake frames and a tension belt assembly. The main frame is installed on the foundation. The hatch door intersection positioning assemblies, the hatch door appearance detecting boards, the main landing gear fairing process fake frames and the tensioning belt assembly are installed on the main frame. The positioning coordinates of the hatch door intersection positioning assemblies are the same as the assembling interaction coordinates of an aircraft actual hatch door. The inner shape of the hatch door appearance detecting boards is the same as the theoretical appearance of the hatch door, and the inner shape of the hatch door appearance detecting boards is larger than the theoretical appearance of the hatch door. The two ends of the coordinate platform are provided with the main landing gear fairing process fake frames which are totally the same with aircraft main landing frame fairing lap joint frames in appearance. By means of the aircraft main landing gear hatch door assembling coordinate platform, the production cost and assembly risk are reduced, actual assembling workloads are reduced, and the development cycle is shortened.
Description
Technical field
The invention belongs to aircraft assembly technique field, relate to a kind of Aircraft Main undercarriage door assembly coordination platform.
Background technology
Aircraft door generally has strict functional and reliability requirement, the especially unlatching of hatch door, closes and outer rim accuracy and interchangeability requirement, and cause the manufacture of hatch door to be installed is the difficult point in aircraft assembly technique field always.For hatch door, install and all there is the constructional features such as turning joint, fixing and locking device, in order to guarantee the strict right alignment of turning joint and fixing and locking device, position degree requirement, during assembling hatch door, often need to realize by assembling fixture.These fixtures, by the system of getting of master body and gauge, guarantee the turning joint of single hatch door, right alignment and the position degree of fixing and locking device.In order to guarantee the functional and reliability requirement of hatch door assembling, existing process is often expending huge fund aspect the input of the standard frocks such as master body, involutory gauge, guarantee hatch door harmony, cause aircraft development cost greatly to increase, and exemplar, the coordination of gauge and the development of standard frock and management also can greatly increase the whole lead time of aircraft etc.
Meanwhile, for the assembling of a plurality of hatch doors, only meet the assembly coordination of single hatch door, can not guarantee to meet the assembly coordination between a plurality of hatch doors simultaneously.In the actual installation process of hatch door, tend to occur occur larger profile jump between hatch door and hatch door, between hatch door and hatch door, gap is inhomogeneous, interferes to wait and assemble risk between hatch door and hatch door.The appearance of these problems in installation process, deals with very thornyly, can reduce to a certain extent Aircraft Quality, increases cost and cycle that aircraft development is paid.
Summary of the invention
Technical matters to be solved by this invention is: a kind of Aircraft Main undercarriage door assembly coordination platform is provided, can assembles time of day by simulated aircraft MLG Door, complete gap repair between a plurality of hatch doors, jump inspection and the inspection of motion angle of release.
Technical scheme of the present invention is: a kind of Aircraft Main undercarriage door assembly coordination platform, is characterized by: described coordination platform comprises ground 1, main frame 2, hatch door intersection point positioning component 3, hatch door profile measurement clamp 4, the false frame 5 of main landing gear fairing technique and fastening belt assembly 6; Described main frame 2 is arranged on ground 1; Described hatch door intersection point positioning component 3, hatch door profile measurement clamp 4, the false frame 5 of main landing gear fairing technique, fastening belt assembly 6 are arranged on main frame 2; Described hatch door intersection point positioning component 3 elements of a fix are consistent with the actual hatch door assembling of aircraft intersecting point coordinate; The interior shape of described hatch door profile measurement clamp 4 is consistent with the theoretical profile of hatch door, and the interior shape of hatch door profile measurement clamp 4 is greater than the theoretical profile of hatch door; The two ends of described coordination platform arrange the false frame 5 of Aircraft Main landing gear trousers technique, in full accord with Aircraft Main landing gear trousers overlap joint frame profile.
The invention has the beneficial effects as follows: Aircraft Main undercarriage door assembly coordination platform of the present invention, the all theoretical profiles of frock and product spare part, space intersection are controlled by numerical control, laser means, accurately simulated the true confined state of Aircraft Main undercarriage door, can complete gap repair between a plurality of hatch doors, jump inspection and the inspection of motion angle of release, guarantee the functional and reliability requirement of hatch door assembling; Meanwhile, the present invention has avoided the use of standard frock, has reduced productive costs and assembling risk, has reduced actual installation work capacity, has shortened the lead time.
Accompanying drawing explanation
Fig. 1 is the front view of Aircraft Main undercarriage door assembly coordination platform of the present invention;
Fig. 2 is the left view of MLG Door assembly coordination platform of the present invention shown in Fig. 1;
Fig. 3 is the attached view of MLG Door assembly coordination platform of the present invention shown in Fig. 1;
Fig. 4 is the block diagram of MLG Door assembly coordination platform of the present invention shown in Fig. 1;
Wherein, 1-ground, 2-main frame, 3-hatch door intersection point positioning component, 4-hatch door profile measurement clamp, the false frame of 5-main landing gear fairing technique, 6-fastening belt assembly.
The specific embodiment
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described further.
Referring to Fig. 1, Fig. 2, Fig. 3, a kind of Aircraft Main undercarriage door assembly coordination platform, comprises ground 1, main frame 2, hatch door intersection point positioning component 3, hatch door profile measurement clamp 4, the false frame 5 of main landing gear fairing technique and fastening belt assembly 6; Described main frame 2 is arranged on ground 1; Described hatch door intersection point positioning component 3, hatch door profile measurement clamp 4, fastening belt assembly 6 are arranged on main frame 2; Described hatch door intersection point positioning component 3 elements of a fix are consistent with the actual hatch door assembling of aircraft intersecting point coordinate; The interior shape of described hatch door profile measurement clamp 4 is consistent with the theoretical profile of hatch door, and the interior shape of hatch door profile measurement clamp 4 is greater than the theoretical profile of hatch door; The two ends of described coordination platform arrange the false frame 5 of Aircraft Main landing gear trousers technique, in full accord with Aircraft Main landing gear trousers overlap joint frame profile; The rotation intersection point of each MLG Door, lock intersection point, all located by corresponding positioning component, and flexible tension takes up supplemental support and the effect of being strained and fixed.
The concrete manufacture of aircraft MLG Door assembly coordination platform and use step are as follows:
1) simulated aircraft assembling time of day, coordinates platform system of axes and aircraft axes in full accord, and space orientation point is aircraft location true coordinate is installed, and sets up model, digitalisation manufacture, installation assembly coordination platform;
2) two upper lower wall panels and 11 MLG Doors are arranged in coordination platform successively, with each frame knock hole and hatch door pan, lockpin hole, position, clamp;
3) check the confined state of each hatch door;
4) use hatch door profile measurement clamp to detect the profile of 11 hatch doors;
5) check gap between 11 hatch doors, according to detail of design repair, guarantee gap evenly, in dimension limit;
6) check jump situation between 11 hatch doors, optionally adjust;
7) single hatch door is carried out to the inspection of motion angle of release, optimize and revise;
8) check jump and the gap situation between hatch door and upper lower wall panels, optionally adjust;
9), after hatch door state is adjusted, in coordinating platform, decompose undercarriage;
10) carry out actual installation work.
Claims (1)
1. an Aircraft Main undercarriage door assembly coordination platform, is characterized by: described coordination platform comprises ground (1), main frame (2), hatch door intersection point positioning component (3), hatch door profile measurement clamp (4), the false frame (5) of main landing gear fairing technique and fastening belt assembly (6); Described main frame (2) is arranged on ground (1); Described hatch door intersection point positioning component (3), hatch door profile measurement clamp (4), the false frame (5) of main landing gear fairing technique, fastening belt assembly (6) are arranged on main frame (2); Described hatch door intersection point positioning component (3) elements of a fix are consistent with the actual hatch door assembling of aircraft intersecting point coordinate; The interior shape of described hatch door profile measurement clamp (4) is consistent with the theoretical profile of hatch door, and the interior shape of hatch door profile measurement clamp (4) is greater than the theoretical profile of hatch door; The two ends of described coordination platform arrange the false frame (5) of Aircraft Main landing gear trousers technique, in full accord with Aircraft Main landing gear trousers overlap joint frame profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145376.7A CN104118575A (en) | 2013-04-24 | 2013-04-24 | Aircraft main landing gear hatch door assembling coordinate platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145376.7A CN104118575A (en) | 2013-04-24 | 2013-04-24 | Aircraft main landing gear hatch door assembling coordinate platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104118575A true CN104118575A (en) | 2014-10-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310145376.7A Pending CN104118575A (en) | 2013-04-24 | 2013-04-24 | Aircraft main landing gear hatch door assembling coordinate platform |
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| CN (1) | CN104118575A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105667831A (en) * | 2016-03-08 | 2016-06-15 | 哈尔滨飞机工业集团有限责任公司 | Rivet-assembling method for helicopter transitional section |
| CN105818999A (en) * | 2015-01-04 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Helicopter hatch door interchange coordination installation method |
| CN108190721A (en) * | 2018-02-23 | 2018-06-22 | 江苏恒神股份有限公司 | A kind of snap-gauge lifting of aircraft door assembling jig |
| CN109080850A (en) * | 2018-07-25 | 2018-12-25 | 陕西飞机工业（集团）有限公司 | A kind of installation adjusting method of Large aircraft landing gear nacelle |
| CN111731504A (en) * | 2020-06-12 | 2020-10-02 | 陕西飞机工业（集团）有限公司 | Positioning method of cockpit glass framework |
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| US6390762B1 (en) * | 2000-05-01 | 2002-05-21 | Strategic Technologies, Inc. | Apparatus for positioning a massive article under a second article for attachment thereto |
| CN202292077U (en) * | 2011-09-21 | 2012-07-04 | 浙江西子航空工业有限公司 | Airplane cabin door assembly fixture |
| CN102730199A (en) * | 2012-07-05 | 2012-10-17 | 浙江大学 | Large-opening shape-preserving device used for large-scale airplane assembly |
| CN102745340A (en) * | 2012-07-05 | 2012-10-24 | 浙江大学 | Digital positioning device of main intersection box of airplane and installation method |
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2013
- 2013-04-24 CN CN201310145376.7A patent/CN104118575A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6390762B1 (en) * | 2000-05-01 | 2002-05-21 | Strategic Technologies, Inc. | Apparatus for positioning a massive article under a second article for attachment thereto |
| CN202292077U (en) * | 2011-09-21 | 2012-07-04 | 浙江西子航空工业有限公司 | Airplane cabin door assembly fixture |
| CN102730199A (en) * | 2012-07-05 | 2012-10-17 | 浙江大学 | Large-opening shape-preserving device used for large-scale airplane assembly |
| CN102745340A (en) * | 2012-07-05 | 2012-10-24 | 浙江大学 | Digital positioning device of main intersection box of airplane and installation method |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105818999A (en) * | 2015-01-04 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Helicopter hatch door interchange coordination installation method |
| CN105818999B (en) * | 2015-01-04 | 2018-03-02 | 哈尔滨飞机工业集团有限责任公司 | One kind, which is gone straight up to cabin door and exchanged, coordinates installation method |
| CN105667831A (en) * | 2016-03-08 | 2016-06-15 | 哈尔滨飞机工业集团有限责任公司 | Rivet-assembling method for helicopter transitional section |
| CN108190721A (en) * | 2018-02-23 | 2018-06-22 | 江苏恒神股份有限公司 | A kind of snap-gauge lifting of aircraft door assembling jig |
| CN108190721B (en) * | 2018-02-23 | 2023-08-18 | 江苏恒神股份有限公司 | Cardboard hoist and mount of aircraft hatch door assembly jig |
| CN109080850A (en) * | 2018-07-25 | 2018-12-25 | 陕西飞机工业（集团）有限公司 | A kind of installation adjusting method of Large aircraft landing gear nacelle |
| CN111731504A (en) * | 2020-06-12 | 2020-10-02 | 陕西飞机工业（集团）有限公司 | Positioning method of cockpit glass framework |
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Application publication date: 20141029 |