RU2015144207A - TOOL TEST BEND FOR CONSTRUCTIVE SIMILAR SAMPLES OF HYBRID WING PANEL - Google Patents

TOOL TEST BEND FOR CONSTRUCTIVE SIMILAR SAMPLES OF HYBRID WING PANEL Download PDF

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Publication number
RU2015144207A
RU2015144207A RU2015144207A RU2015144207A RU2015144207A RU 2015144207 A RU2015144207 A RU 2015144207A RU 2015144207 A RU2015144207 A RU 2015144207A RU 2015144207 A RU2015144207 A RU 2015144207A RU 2015144207 A RU2015144207 A RU 2015144207A
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RU
Russia
Prior art keywords
support
length
stringer
loading tip
similar samples
Prior art date
Application number
RU2015144207A
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Russian (ru)
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RU2625685C2 (en
Inventor
Евгений Николаевич Каблов
Владимир Сергеевич Ерасов
Виталий Васильевич Автаев
Николай Юрьевич Подживотов
Елена Алексеевна Котова
Евгений Игоревич Орешко
Original Assignee
Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ")
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Application filed by Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") filed Critical Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ")
Priority to RU2015144207A priority Critical patent/RU2625685C2/en
Publication of RU2015144207A publication Critical patent/RU2015144207A/en
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Publication of RU2625685C2 publication Critical patent/RU2625685C2/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N3/00—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust
    • F01N3/02—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust

Landscapes

  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
  • Sampling And Sample Adjustment (AREA)

Claims (3)

1. Оснастка в виде двух одинаковых опор и нагружающего наконечника со скругленными контактными поверхностями для испытаний на трехточечный изгиб конструктивно-подобных образцов гибридной панели крыла с продольными стрингерами, отличающаяся тем, что длина нагружающего наконечника больше длины хотя бы одной из сторон обшивки образца панели, каждая опора имеет форму прямого бруса с прямоугольным поперечным сечением, длина каждой опоры больше расстояния между внешними боковыми гранями полок крайних стрингеров, каждая опора имеет вырез прямоугольного сечения для каждого стрингера, глубиной не менее высоты полки стрингера и шириной основания выреза равной ширине полки стрингера с основным отклонением Н и точностью не хуже 9 квалитета, причем скругленное основание каждого выреза является контактной поверхностью опоры, а площадь контактной поверхности нагружающего наконечника и площадь контактной поверхности каждой опоры определяется из условия возникновения в образце напряжений при испытании ниже напряжения локального смятия и хрупкого разрушения гибридных накладок.1. Equipment in the form of two identical supports and a loading tip with rounded contact surfaces for three-point bending tests of structurally similar samples of a hybrid wing panel with longitudinal stringers, characterized in that the length of the loading tip is greater than the length of at least one side of the panel sample sheathing, each the support has the shape of a straight bar with a rectangular cross section, the length of each support is greater than the distance between the outer side faces of the shelves of the extreme stringers, each support has a cut a cross-section for each stringer with a depth not less than the height of the stringer shelf and the width of the cutout base equal to the width of the stringer shelf with the main deviation H and accuracy no worse than 9 degrees, the rounded base of each cutout is the contact surface of the support, and the contact surface area of the loading tip and the contact area the surface of each support is determined from the conditions of occurrence of stresses in the sample when tested below the stress of local collapse and brittle fracture of the hybrid plates . 2. Оснастка по п. 1, отличающаяся тем, что длина нагружающего наконечника больше любой стороны обшивки образца панели.2. Equipment according to claim 1, characterized in that the length of the loading tip is greater than either side of the panel sample sheathing. 3. Оснастка по п. 1 или 2, отличающаяся тем, что вырез в каждой опоре для каждого стрингера сквозной.3. Equipment according to claim 1 or 2, characterized in that the cut-out in each support for each stringer is through.
RU2015144207A 2015-10-15 2015-10-15 Equipment for flexure testing constructive-like samples of hybrid wing panel RU2625685C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2015144207A RU2625685C2 (en) 2015-10-15 2015-10-15 Equipment for flexure testing constructive-like samples of hybrid wing panel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2015144207A RU2625685C2 (en) 2015-10-15 2015-10-15 Equipment for flexure testing constructive-like samples of hybrid wing panel

Publications (2)

Publication Number Publication Date
RU2015144207A true RU2015144207A (en) 2017-04-25
RU2625685C2 RU2625685C2 (en) 2017-07-18

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU2015144207A RU2625685C2 (en) 2015-10-15 2015-10-15 Equipment for flexure testing constructive-like samples of hybrid wing panel

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RU (1) RU2625685C2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114701659A (en) * 2022-04-02 2022-07-05 航天特种材料及工艺技术研究所 Characterization testing device and method for small-load bending and torsion deformation of composite material airfoil

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5654055B2 (en) * 2011-02-04 2015-01-14 三菱重工業株式会社 Composite structure, aircraft main wing and aircraft fuselage provided with the same
CN103837410B (en) * 2014-03-20 2016-01-20 中南大学 A kind of SHCC ductility method of testing for reinforcing existing cracking structure
RU2559334C1 (en) * 2014-04-29 2015-08-10 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Национальный исследовательский Томский государственный университет" (ТГУ) Test method of printed circuit boards under combined mechanical and thermal actions

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114701659A (en) * 2022-04-02 2022-07-05 航天特种材料及工艺技术研究所 Characterization testing device and method for small-load bending and torsion deformation of composite material airfoil

Also Published As

Publication number Publication date
RU2625685C2 (en) 2017-07-18

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