CN110815078B - Undercarriage strut test clamping device and method - Google Patents
Undercarriage strut test clamping device and method Download PDFInfo
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- CN110815078B CN110815078B CN201911116197.4A CN201911116197A CN110815078B CN 110815078 B CN110815078 B CN 110815078B CN 201911116197 A CN201911116197 A CN 201911116197A CN 110815078 B CN110815078 B CN 110815078B
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- 238000012360 testing method Methods 0.000 title claims abstract description 47
- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000000149 penetrating effect Effects 0.000 claims abstract description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 9
- 239000010959 steel Substances 0.000 claims description 9
- 238000012545 processing Methods 0.000 claims description 6
- 238000003754 machining Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
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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
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Testing Of Engines (AREA)
Abstract
The invention belongs to the field of design of tool fixtures, relates to a clamping device and method for an undercarriage strut test, and solves the problems of positioning accuracy and clamping stability in the undercarriage strut buffer test process. The method comprises the following steps: step one, mounting a top support, and fixing the upper part of the top support by using a bolt after the upper part of the top support corresponds to the center of a pressure head of a test press; step two, mounting a fixed rod to be connected with a positioning hole at the lower part of the top support, and connecting the connecting block and the adjusting positioning block with the fixed rod through the mounting hole; thirdly, connecting and contacting the hollow positioning sleeve with the landing gear support column, integrally penetrating the hollow positioning sleeve into a central positioning hole in the lower part of the top support, installing a bottom jacking block, vertically placing the landing gear support column, and fixing the hollow positioning sleeve with the top support column through a nut; and step four, an adjusting groove is formed in the adjusting and positioning block, the bolt positioning hole is aligned to the fork ear hole of the landing gear strut, the fixing pin is inserted through the bolt hole of the adjusting and positioning block, the bolt is firmly fixed, the gasket is added, and the cotter pin is inserted.
Description
Technical Field
The invention belongs to the field of design of tool fixtures, and relates to a clamping device and a clamping method for an undercarriage strut test.
Background
The supporting column of the landing gear of a certain type of helicopter is novel in structure, the existing tool cannot realize test clamping on the supporting column, and a new clamping tool and a new clamping method are urgently needed.
Disclosure of Invention
The purpose of the invention is as follows: the landing gear support test clamping device and method solve the problems of positioning accuracy and clamping stability in the process of a landing gear support buffer test.
The technical scheme is as follows:
a landing gear strut test clamping device comprises:
the device comprises a top support 1, a connecting block 2, a fixing rod 3, an adjusting and positioning block 4, a bolt 5, a gasket 6, a split pin 7, a hollow positioning sleeve 8, a nut 9 and a bottom top block 10;
the center of the upper part of the top support 1 is a circular positioning table, mounting holes are formed in the periphery of the positioning table, the center of the lower part of the top support 1 is a circular hole and is coaxial with the upper positioning table, and the upper part of the top support 1 is correspondingly fixed with the center of an upper pressure head of the test press; the connecting block 2 is connected with the fixed rod 3 and the adjusting positioning block 4 through mounting holes; the upper end face of the fixed rod 3 is connected with the positioning hole at the lower part of the top support 1 in a positioning manner, and the lower end face of the fixed rod is connected with the connecting block 2 and the adjusting positioning block 4 through mounting holes; the adjusting positioning block 4 is provided with an adjusting groove, and the end part of the adjusting positioning block is provided with a positioning hole of a bolt 5; the bolt 5 is inserted into a fork lug hole of the landing gear strut through a bolt 5 positioning hole of the adjusting positioning block 4; a positioning groove is formed in the hollow positioning sleeve 8, and a positioning round table of the hollow positioning sleeve 8 penetrates through a central circular hole in the lower part of the top support 1 and is fixed by a nut 9; and the positioning excircle of the bottom ejector block 10 is in contact with a concave table at the lower part of the landing gear strut, and the excircle and the end face at the lower part of the landing gear strut are fixed at the center of the lower part of the bed body of the test press machine.
The bolt 5 is a step cylindrical pin.
And the positioning groove of the hollow positioning sleeve 8 is matched with the outer circle of the step at the upper part of the landing gear strut to abut against.
The end part of the bolt 5 is provided with a limiting hole, the gasket 6 is sleeved at the end part of the bolt 5, and after the gasket 6 is sleeved, the cotter pin 7 is inserted into the limiting hole of the bolt 5 for limiting;
the top support 1 is formed by integrally processing a welded steel pipe and a welded steel plate.
The fixed rod 3 is formed by integrally processing welded steel plates, mounting holes are formed in the upper connecting plate and the lower connecting plate, and the upper end face and the lower end face are parallel.
The hollow positioning sleeve 8 is formed by machining, and the coaxial line of the positioning round platform and the positioning groove is guaranteed.
The hollow positioning sleeve 8 is provided with a local annular maintenance groove.
A landing gear strut test clamping method comprises the following steps:
step one, mounting a top support, and fixing the upper part of the top support by using a bolt after the upper part of the top support corresponds to the center of a pressure head of a test press;
step two, mounting a fixed rod to be connected with a positioning hole at the lower part of the top support, connecting the connecting block and the adjusting positioning block with the fixed rod through the mounting hole, and fixing by adopting a bolt;
thirdly, connecting and contacting the hollow positioning sleeve with the landing gear support column, integrally penetrating the hollow positioning sleeve into a central positioning hole in the lower part of the top support, installing a bottom jacking block, vertically placing the landing gear support column, and fixing the hollow positioning sleeve with the top support column through a nut;
step four, an adjusting groove is formed in the adjusting and positioning block, the bolt positioning hole is aligned to the fork lug hole of the landing gear strut, the bolt is inserted through the bolt hole of the adjusting and positioning block, the bolt is firmly fixed, a gasket is added, and a cotter pin is inserted;
further comprising:
and fifthly, after the test work is finished, loosening along the opposite step, taking out the landing gear support column, and putting back all the parts to the initial position.
Has the advantages that:
the invention has accurate positioning, simple structure and convenient installation, can meet the test requirements of the landing gear with different specifications by replacing the hollow positioning sleeve 8, and has safe and reliable process and high stability through test demonstration.
Drawings
FIG. 1 is an isometric view of the landing gear strut test clamping device of the present invention (when clamping a part);
FIG. 2 is an isometric view of the landing gear strut test clamping device of the present invention (when no part is clamped);
FIG. 3 is a major side view of the hollow locating sleeve 8 and nut 9 of the landing gear strut test clamping device of the present invention;
FIG. 4 is an isometric view of the attachment block 2 of the landing gear leg test fixture of the present invention;
figure 5 is an isometric view of a fixed rod 3 of the landing gear strut test fixture of the present invention;
FIG. 6 is an isometric view of an adjusting locating block 4 of the landing gear strut test clamping apparatus of the present invention;
fig. 7 is an axial view of the fixing pin, the washer 6, and the cotter pin 7 of the landing gear leg test jig of the present invention.
Detailed Description
The following provides a more detailed description of the embodiments of the present invention. Referring to fig. 1 to 7, the invention provides a landing gear strut test clamping device, which comprises a top support 1, a connecting block 2, a fixing rod 3, an adjusting positioning block 4, a bolt 5, a gasket 6, a split pin 7, a hollow positioning sleeve 8, a nut 9 and a bottom top block 10; the center of the upper part of the top support 1 is a circular positioning table, mounting holes are formed in the periphery of the positioning table, the center of the lower part of the top support 1 is a circular hole and is coaxial with the upper positioning table, and the upper part of the top support 1 is correspondingly fixed with the center of an upper pressure head of the test press; the connecting block 2 is connected with the fixed rod 3 and the adjusting positioning block 4 through mounting holes and fixed by bolts; the upper end face of the fixed rod 3 is connected with the positioning hole at the lower part of the top support 1 in a positioning manner, and the lower end face of the fixed rod is connected with the connecting block 2 and the adjusting positioning block 4 through mounting holes; the adjusting positioning block 4 is provided with an adjusting groove, and the end part of the adjusting positioning block is provided with a positioning hole of a bolt 5; the pin 5 is a stepped cylindrical pin and is inserted into a fork lug hole of the landing gear strut through a pin 5 positioning hole of the adjusting positioning block 4; and the positioning round platform of the hollow positioning sleeve 8 penetrates through a central round hole at the lower part of the top support 1 and is fixed by a nut 9. And a positioning groove is arranged in the hollow positioning sleeve 8 and matched with the outer circle of the step at the upper part of the landing gear strut to abut against the hollow positioning sleeve. And the positioning excircle of the bottom ejector block 10 is in contact with a concave table at the lower part of the landing gear support, and the excircle and the end face of the lower part are fixed at the center of the lower part of the bed body of the test press.
More specifically, the top support 1 is formed by integrally processing a welded steel pipe and a welded steel plate, and an upper positioning hole, a lower positioning hole and a positioning table are ensured to be coaxial.
More specifically, the dead lever 3 is formed by integrally processing after welding steel plates, the upper and lower connecting plates are provided with mounting holes, and the upper and lower end faces are guaranteed to be parallel.
More specifically, hollow position sleeve 8 adopts machining to form, and the coaxial line is guaranteed with inside constant head tank to outside location platform. In addition, the hollow positioning sleeve 8 is provided with a local annular maintenance groove, and the bolt at the end part of the landing gear strut can be adjusted and checked in the test process.
The undercarriage strut test clamping device is accurate in positioning, simple in structure and convenient to install, the requirement of undercarriage tests of different specifications can be met by replacing the hollow positioning sleeve 8, and the process is safe and reliable and high in stability through experimental demonstration.
The use method of the landing gear strut test clamping device comprises the following steps:
step one, mounting a top support, and fixing the upper part of the top support by using a bolt after the upper part of the top support corresponds to the center of a pressure head of a test press;
step two, mounting a fixed rod to be connected with a positioning hole at the lower part of the top support, connecting the connecting block and the adjusting positioning block with the fixed rod through the mounting hole, and fixing by adopting a bolt;
thirdly, connecting and contacting the hollow positioning sleeve with the landing gear support column, integrally penetrating the hollow positioning sleeve into a central positioning hole in the lower part of the top support, installing a bottom jacking block, vertically placing the landing gear support column, and fixing the hollow positioning sleeve with the top support column through a nut;
step four, arranging an adjusting groove through an adjusting positioning block, aligning a bolt positioning hole with a fork hole of a landing gear strut, inserting a fixing pin through the bolt hole of the adjusting positioning block, firmly fixing a bolt, adding a gasket, and inserting a cotter pin;
and fifthly, after the test work is finished, loosening along the opposite step, taking out the landing gear support column, and putting back all the parts to the initial position.
Claims (10)
1. The utility model provides an experimental clamping device of undercarriage pillar which characterized in that includes:
the device comprises a top support (1), a connecting block (2), a fixing rod (3), an adjusting positioning block (4), a bolt (5), a gasket (6), a split pin (7), a hollow positioning sleeve (8), a nut (9) and a bottom top block (10);
the center of the upper part of the top support (1) is a circular positioning table, mounting holes are formed in the periphery of the positioning table, the center of the lower part of the top support (1) is a circular hole and is coaxial with the upper positioning table, and the upper part of the top support (1) is correspondingly fixed with the center of an upper pressure head of a test press; the connecting block (2) is connected with the fixing rod (3) and the adjusting positioning block (4) through mounting holes; the upper end face of the fixed rod (3) is connected with the positioning hole at the lower part of the top support (1) in a positioning manner, and the lower end face of the fixed rod is connected with the connecting block (2) and the adjusting positioning block (4) through mounting holes; the adjusting positioning block (4) is provided with an adjusting groove, and the end part of the adjusting positioning block is provided with a positioning hole of a bolt (5); the bolt (5) is inserted into a fork lug hole of the landing gear strut through a positioning hole of the bolt (5) of the adjusting positioning block (4); a positioning groove is formed in the hollow positioning sleeve (8), and a positioning round table of the hollow positioning sleeve (8) penetrates through a central circular hole in the lower part of the top support (1) and is fixed by a nut (9); and the positioning excircle of the bottom ejector block (10) is in contact with a concave table at the lower part of the landing gear strut, and the excircle and the end face of the lower part of the landing gear strut are fixed at the center of the lower part of the test press machine body.
2. The landing gear strut test clamping device of claim 1,
the plug pin (5) adopts a step cylindrical pin.
3. The landing gear strut test clamping device of claim 1,
and the positioning groove of the hollow positioning sleeve (8) is matched with the outer circle of the step at the upper part of the landing gear strut to abut against.
4. The landing gear strut test clamping device of claim 1,
the end part of the bolt (5) is provided with a limiting hole, the gasket (6) is sleeved at the end part of the bolt (5), and after the gasket (6) is sleeved, the cotter pin (7) is inserted into the limiting hole of the bolt (5) for limiting.
5. The landing gear strut test clamping device of claim 1,
the top support (1) is formed by integrally processing a welded steel pipe and a welded steel plate.
6. The landing gear strut test clamping device of claim 1,
the fixing rod (3) is formed by integrally processing welded steel plates, mounting holes are formed in the upper connecting plate and the lower connecting plate, and the upper end face and the lower end face of the fixing rod are parallel.
7. The landing gear strut test clamping device of claim 1,
the hollow positioning sleeve (8) is formed by machining, and the positioning round platform and the positioning groove guarantee the coaxial line.
8. A landing gear strut test clamping device according to claim 7,
the hollow positioning sleeve (8) is provided with a local annular overhaul groove.
9. A landing gear support test clamping method is characterized in that the landing gear support test clamping device of claim 1 is adopted, and the method comprises the following steps:
step one, mounting a top support, and fixing the upper part of the top support by using a bolt after the upper part of the top support corresponds to the center of a pressure head of a test press;
step two, mounting a fixed rod to be connected with a positioning hole at the lower part of the top support, connecting the connecting block and the adjusting positioning block with the fixed rod through the mounting hole, and fixing by adopting a bolt;
thirdly, connecting and contacting the hollow positioning sleeve with the landing gear support column, integrally penetrating the hollow positioning sleeve into a central positioning hole in the lower part of the top support, installing a bottom jacking block, vertically placing the landing gear support column, and fixing the hollow positioning sleeve with the top support column through a nut;
and step four, an adjusting groove is formed in the adjusting and positioning block, the bolt positioning hole is aligned to the fork lug hole of the landing gear strut, the bolt is inserted through the bolt positioning hole of the adjusting and positioning block, the bolt is firmly fixed, a gasket is added, and the cotter pin is inserted.
10. The landing gear strut test clamping method according to claim 9, further comprising:
and fifthly, after the test work is finished, loosening along the opposite step, taking out the landing gear support column, and putting back all the parts to the initial position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911116197.4A CN110815078B (en) | 2019-11-14 | 2019-11-14 | Undercarriage strut test clamping device and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911116197.4A CN110815078B (en) | 2019-11-14 | 2019-11-14 | Undercarriage strut test clamping device and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110815078A CN110815078A (en) | 2020-02-21 |
| CN110815078B true CN110815078B (en) | 2021-06-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911116197.4A Active CN110815078B (en) | 2019-11-14 | 2019-11-14 | Undercarriage strut test clamping device and method |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114674550B (en) * | 2022-03-29 | 2024-05-07 | 中航飞机起落架有限责任公司 | Airplane main strut running-in test device and test method |
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| CN208034152U (en) * | 2018-03-02 | 2018-11-02 | 苏州市昌星模具机械有限公司 | A kind of efficient high-accuracy fixture of undercarriage holder |
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| GB0605345D0 (en) * | 2006-03-16 | 2006-04-26 | Airbus Uk Ltd | Testing strut assembly |
| CN201597756U (en) * | 2010-03-02 | 2010-10-06 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear clamping device |
| GB201209419D0 (en) * | 2012-05-28 | 2012-07-11 | Airbus Operations Ltd | Landing gear for an aircraft |
| CN104773306B (en) * | 2015-04-07 | 2017-02-01 | 中国直升机设计研究所 | Main landing gear three-way loading test device |
| EP3109154B1 (en) * | 2015-06-23 | 2019-09-25 | Safran Landing Systems UK Limited | A method of preloading an aircraft assembly, a preloading tool and an aircraft assembly |
| DE202015005362U1 (en) * | 2015-07-29 | 2016-11-02 | Liebherr-Aerospace Lindenberg Gmbh | Strut for the landing gear of an aircraft |
| CN204988702U (en) * | 2015-08-11 | 2016-01-20 | 中国航空工业集团公司西安飞机设计研究所 | Undercarriage leg load mechanism |
| CN106441857A (en) * | 2016-11-29 | 2017-02-22 | 中国直升机设计研究所 | Fatigue testing apparatus for mounting joint of damper post of main gear |
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| CN208036591U (en) * | 2017-12-14 | 2018-11-02 | 中国航空工业集团公司成都飞机设计研究所 | A kind of adjustable undercarriage leg mounting structure for rotating shaft |
| US11161599B2 (en) * | 2018-01-26 | 2021-11-02 | The Boeing Company | Landing gear strut assembly and method therefor |
| CN209023161U (en) * | 2018-09-25 | 2019-06-25 | 陕西飞机工业（集团）有限公司 | A kind of aircraft slow test nose-gear loaded member |
| CN109969428B (en) * | 2019-02-28 | 2024-03-29 | 西安生淼机电科技有限责任公司 | Test method of comprehensive test device for reliability and static strength/rigidity of upper lock of nose landing gear of airplane |
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2019
- 2019-11-14 CN CN201911116197.4A patent/CN110815078B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107215480A (en) * | 2017-05-23 | 2017-09-29 | 中国民航大学 | A kind of Aircraft landing gear system brake dynamic simulation test bed frame |
| CN208034152U (en) * | 2018-03-02 | 2018-11-02 | 苏州市昌星模具机械有限公司 | A kind of efficient high-accuracy fixture of undercarriage holder |
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| CN110815078A (en) | 2020-02-21 |
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