CN104340376A - Anti-instability structure for composite plate part during airworthiness verification tests - Google Patents
Anti-instability structure for composite plate part during airworthiness verification tests Download PDFInfo
- Publication number
- CN104340376A CN104340376A CN201310336958.3A CN201310336958A CN104340376A CN 104340376 A CN104340376 A CN 104340376A CN 201310336958 A CN201310336958 A CN 201310336958A CN 104340376 A CN104340376 A CN 104340376A
- Authority
- CN
- China
- Prior art keywords
- instability
- fixed
- composite plate
- composite
- tests
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Abstract
The invention relates to the technical field of composite structure part tests, in particular to an anti-instability structure for a composite plate part during airworthiness verification tests. The anti-instability structure comprises a base (1), side supporting seats (4) and clamping blocks (5), wherein the side supporting seats (4) are fixed to a T-shaped groove (9) of the base (1) by T-shaped groove bolts (2); the clamping blocks (5) are fixed to the long holes (8) of the side supporting seats (4) by bolts (3); the whole set of anti-instability structure is fixed with a loading device (7) through the T-shaped groove bolts (2). According to the anti-instability structure, the problem of redesign of a test tool for composite plate test parts with different specifications is solved, and the commonality of the test tool is achieved; the anti-instability structure is successfully applied to three different aircraft component or detail component tests, the conformity of the composite aircraft component structure with respect to terms 23.307, 23.603 and 23.613 in CCAR23R3 is verified, and test data support is provided for type evidence.
Description
Technical field
Aircraft Composite Structure part testing technique field of the present invention, particularly relates to the anti-unstability structure of a kind of composite material plate-shaped members seaworthiness certification testing.
Background technology
At present, that applies in aviation field along with composite structure gets more and more, and its seaworthiness verification technique also progressively becomes the core technology of aviation field, comprising the certification testing to composite material template element, details part.Because composite material template test article central area has honeycomb sandwich construction usually, anti-unstability structure requires the one fixed width scope being clamped in test article both sides mostly, not the unnecessary position of admissible constraint, requires higher to the clamping zone of anti-unstability structure.The anti-unstability structure of this type of test mostly is Special test frock, poor universality at present, and experimentation cost is higher.
Summary of the invention
The technical problem to be solved in the present invention:
The object of the invention is: design general adjustable anti-unstability structure, to adapt to the composite material template test article of different size, save experimentation cost.
Technical scheme of the present invention:
Technical conceive of the present invention is: design a kind of anti-unstability structure, make it have the free adjustment space in three directions, reaches the length according to test article, object that width, thickness regulate anti-unstability scantling of structure; Finally anti-unstability structure and force-input device are connected firmly.
The anti-unstability structure of a kind of composite material plate-shaped members seaworthiness certification testing, this anti-unstability structure comprises base 1, collateral seat 4, fixture block 5 form.Collateral seat 4 T-slot bolt 2 is fixed in the T-slot 9 of base 1, and fixture block 5 bolt 3 is fixed on the elongated hole 8 of collateral seat 4, and a whole set of anti-unstability structure is fixed by T-slot bolt 2 and force-input device 7.
Beneficial effect of the present invention:
The composite material template test article that the invention solves different size needs the problem redesigning test tool, achieves the general of test tool.This anti-unstability structure is successfully applied in three different aircraft component, the test of details part, demonstrates the accordance of technique for aircraft composite component structure about CCAR23R3 the 23.307th, 23.603,23.613 articles, for model evidence obtaining provides test figures support.
Accompanying drawing explanation
Fig. 1 is anti-unstability structural representation, and wherein, 1 is base, and 2 is T-slot bolt, and 3 is bolt, and 4 is collateral seat, and 5 is fixture block, and 6 is test article, and 7 is force-input device, and 8 is elongated hole, and 9 is T-slot.
Detailed description of the invention
The present invention, by the fixture block of design different size, makes the size of its applicable all size test article length direction; Application T-slot and the adjustable collateral seat of T-slot bolt composition connect, and make the size of its applicable all size test article Width; Collateral seat adopts elongated hole to fix fixture block, makes the size of its applicable all size test article thickness direction.The adjustable function of anti-unstability structure is realized by the structure of three direction-agile sizes.
This anti-unstability structure comprises base 1, collateral seat 4, fixture block 5 form.Collateral seat 4 T-slot bolt 2 is fixed in the T-slot 9 of base 1, and fixture block 5 bolt 3 is fixed on the elongated hole 8 of collateral seat 4, and a whole set of anti-unstability structure is fixed by T-slot bolt 2 and force-input device 7.
Claims (1)
1. the anti-unstability structure of composite material plate-shaped members seaworthiness certification testing, is characterized in that, this anti-unstability structure comprises base (1), collateral seat (4), fixture block (5) composition.Collateral seat (4) T-slot bolt (2) is fixed in the T-slot (9) of base (1), fixture block (5) bolt (3) is fixed on the elongated hole (8) of collateral seat (4), and a whole set of anti-unstability structure is fixed by T-slot bolt (2) and force-input device (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310336958.3A CN104340376A (en) | 2013-08-05 | 2013-08-05 | Anti-instability structure for composite plate part during airworthiness verification tests |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310336958.3A CN104340376A (en) | 2013-08-05 | 2013-08-05 | Anti-instability structure for composite plate part during airworthiness verification tests |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104340376A true CN104340376A (en) | 2015-02-11 |
Family
ID=52496969
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310336958.3A Pending CN104340376A (en) | 2013-08-05 | 2013-08-05 | Anti-instability structure for composite plate part during airworthiness verification tests |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104340376A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1548699A1 (en) * | 1985-10-14 | 1990-03-07 | Предприятие П/Я А-7840 | Grip for securing tubular specimens being tested for strength |
| US6141848A (en) * | 1997-06-28 | 2000-11-07 | The Boeing Company | Contoured stringer/clip drilling |
| CN201210128Y (en) * | 2008-05-05 | 2009-03-18 | 攀钢集团攀枝花钢铁研究院有限公司 | Combined clamp |
| CN201484667U (en) * | 2009-09-14 | 2010-05-26 | 哈尔滨飞机工业集团有限责任公司 | Universal combined frame for vertical assembling jig |
| CN102435508A (en) * | 2011-09-14 | 2012-05-02 | 江苏科技大学 | White car body static stiffness restriction device and static stiffness detection method |
-
2013
- 2013-08-05 CN CN201310336958.3A patent/CN104340376A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1548699A1 (en) * | 1985-10-14 | 1990-03-07 | Предприятие П/Я А-7840 | Grip for securing tubular specimens being tested for strength |
| US6141848A (en) * | 1997-06-28 | 2000-11-07 | The Boeing Company | Contoured stringer/clip drilling |
| CN201210128Y (en) * | 2008-05-05 | 2009-03-18 | 攀钢集团攀枝花钢铁研究院有限公司 | Combined clamp |
| CN201484667U (en) * | 2009-09-14 | 2010-05-26 | 哈尔滨飞机工业集团有限责任公司 | Universal combined frame for vertical assembling jig |
| CN102435508A (en) * | 2011-09-14 | 2012-05-02 | 江苏科技大学 | White car body static stiffness restriction device and static stiffness detection method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203409677U (en) | Jig for fixing touch screen | |
| CN103386617B (en) | The positioner of cylinder cap and processing cylinder cap | |
| CN104551747A (en) | Engine cylinder fixture | |
| WO2014035613A3 (en) | Attachment apparatus for ceramic matrix composite materials | |
| CN102680236A (en) | Structural strength test loading device for aircraft wing-mounted engine | |
| CN104340376A (en) | Anti-instability structure for composite plate part during airworthiness verification tests | |
| CN205096783U (en) | H -beam location frock | |
| CN203744901U (en) | Plate spring assembly detection tool | |
| CN203792206U (en) | Fixing device for detection of vehicle seats | |
| CN104477407B (en) | A kind of joist biaxial loadings fixing device | |
| CN109649682B (en) | Three-point bending and buckling fatigue test fixture for wing beam | |
| CN202461981U (en) | Braking sheet linear cutting clamp | |
| CN201410645Y (en) | Clamp locating pin adjusting shim group | |
| CN204255632U (en) | Test unit on a kind of testing machine | |
| CN203543842U (en) | Tail door decorating part convenient to load | |
| CN103551891A (en) | Milling tool of automotive torsion beam brake disc installation end surface | |
| CN205780079U (en) | A kind of attachment means in quick elimination gap | |
| CN205852238U (en) | A kind of filter resistors framework fitted position correcting unit | |
| EP2982495A1 (en) | System and method for applying pressure to structural components | |
| CN206002005U (en) | Automobile luggage racks assembly checking tool | |
| CN206779994U (en) | Alumiaum article processes clamping device | |
| CN204903172U (en) | Steam generator lays device | |
| CN202726775U (en) | Multi-angle connecting device for sample car trial-produce flexible fixture | |
| CN203772763U (en) | Shrinkage cavity detection jig | |
| CN217412341U (en) | Clamping device and system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150211 |
|
| RJ01 | Rejection of invention patent application after publication |