SU1607558A1 - Device for test strength of flap of aircraft - Google Patents
Device for test strength of flap of aircraftInfo
- Publication number
- SU1607558A1 SU1607558A1 SU4675621/23A SU4675621A SU1607558A1 SU 1607558 A1 SU1607558 A1 SU 1607558A1 SU 4675621/23 A SU4675621/23 A SU 4675621/23A SU 4675621 A SU4675621 A SU 4675621A SU 1607558 A1 SU1607558 A1 SU 1607558A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- flap
- rhombs
- tested
- aircraft
- weight
- Prior art date
Links
Abstract
FIELD: aviation. SUBSTANCE: decrease of effect of weight of level system simulating aerodynamic load on tested flap and increased authenticity of tests due to it are provided by installation of balancing mechanism composed of links 9 and 10, 11 and 12, 13 and 14 forming two rhombs on axle around which lever system and tested flap turn. Value B of one of rhombs of hinged to lever system 8 and is placed in center of its mass. Weight 15 balancing system 8 is suspended from vertex C of the other rhomb. EFFECT: making conditions of tests closer to real ones. 2 dwg
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU4675621/23A SU1607558A1 (en) | 1989-04-11 | 1989-04-11 | Device for test strength of flap of aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SU4675621/23A SU1607558A1 (en) | 1989-04-11 | 1989-04-11 | Device for test strength of flap of aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
SU1607558A1 true SU1607558A1 (en) | 1994-11-30 |
Family
ID=60527799
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU4675621/23A SU1607558A1 (en) | 1989-04-11 | 1989-04-11 | Device for test strength of flap of aircraft |
Country Status (1)
Country | Link |
---|---|
SU (1) | SU1607558A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102680236A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Structural strength test loading device for aircraft wing-mounted engine |
CN103308295A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Control and check test method for flight control mechanical control system |
CN103303493B (en) * | 2013-01-05 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of large aircraft strength test wing loads bringing device |
CN109163961A (en) * | 2018-08-22 | 2019-01-08 | 中国飞机强度研究所 | A kind of loading device of big deformation wing |
CN113138133A (en) * | 2021-04-20 | 2021-07-20 | 中国飞机强度研究所 | Variable camber wing leading edge functional strength test load loading device |
CN113138133B (en) * | 2021-04-20 | 2024-05-17 | 中国飞机强度研究所 | Load loading device for bending-variable wing leading edge functional strength test |
-
1989
- 1989-04-11 SU SU4675621/23A patent/SU1607558A1/en active
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102680236A (en) * | 2012-05-11 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Structural strength test loading device for aircraft wing-mounted engine |
CN103308295A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Control and check test method for flight control mechanical control system |
CN103303493B (en) * | 2013-01-05 | 2015-12-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of large aircraft strength test wing loads bringing device |
CN109163961A (en) * | 2018-08-22 | 2019-01-08 | 中国飞机强度研究所 | A kind of loading device of big deformation wing |
CN113138133A (en) * | 2021-04-20 | 2021-07-20 | 中国飞机强度研究所 | Variable camber wing leading edge functional strength test load loading device |
CN113138133B (en) * | 2021-04-20 | 2024-05-17 | 中国飞机强度研究所 | Load loading device for bending-variable wing leading edge functional strength test |
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