SU1607558A1 - Device for test strength of flap of aircraft - Google Patents

Device for test strength of flap of aircraft

Info

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
Application number
SU4675621/23A
Other languages
Russian (ru)
Inventor
В.А. Сумароков
В.М. Курушин
Original Assignee
В.А. Сумароков
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by В.А. Сумароков filed Critical В.А. Сумароков
Priority to SU4675621/23A priority Critical patent/SU1607558A1/en
Application granted granted Critical
Publication of SU1607558A1 publication Critical patent/SU1607558A1/en

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
SU4675621/23A 1989-04-11 1989-04-11 Device for test strength of flap of aircraft SU1607558A1 (en)

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)

* Cited by examiner, † Cited by third party
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

Cited By (6)

* Cited by examiner, † Cited by third party
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

Similar Documents

Publication Publication Date Title
EP0198641A3 (en) A set of parts and methods for testing and/or strengthening pelvic floor muscles
Staron et al. Comparison of soleus muscles from rats exposed to microgravity for 10 versus 14 days
SU1607558A1 (en) Device for test strength of flap of aircraft
BERINGER et al. Exploring situational awareness- A review and the effects of stress on rectilinear normalization((aircraft pilot performance))
GB716572A (en) Improved means for detecting and indicating the approach of failure of a structure or stuctural element subjected to varying loads
Bahna et al. 160. IgE in cytomegalovirus mononucleosis (CMV mono)
JPS5544968A (en) Weighing tester
SU1360443A1 (en) Method of simulating overloads, which act on human organism during flight
TURNAGE et al. The use of surrogate measurement for the prediction of flight training performances
Man et al. Dynamic Fracture Toughness--the Method of Testing and Evaluation
Herteman et al. The simulation of fatigue loads in aeronautics
UNRUH et al. Design and test of aircraft engine isolators for reduced interior noise[Final Report]
SU1182407A1 (en) Method of testing null-point instruments for resistance to combined actions
TARDY Methods used for optimizing the simulation of Concorde SST using flight test results
HOROWITZ Measurement and effects of transport delays in a state-of-the-art F-16 C flight simulator(Final Report, Aug. 1985- Sep. 1987)
Koehler Simulator tests of air-to-ground tracking
RU1803764C (en) Bench for testing delta plane
SAULNIER et al. LocArch shelter[Final Report, Dec. 1973- Aug. 1974]
Hoffer et al. Economic Riveting
HARRIS Acceptance testing of flying qualities and performance, cockpit motion, and visual display system simulation for flight simulators[Final Report, Jul. 1974- Jan. 1977]
Maguire Product-Improvement Test of OH-6A Helicopter Tail-Rotor Balancing Equipment.
EDWARDS et al. Bearingless tail rotor loads and stability[Final Report, Mar. 1975- Jan. 1976]
SIEM Predictive validity of an automated personality inventory for Air Force pilot selection(Interim Technical Paper, Jun. 1987- Jun. 1990)
Wilcox et al. The Effects of Two Instrument Lighting Systems on Dark Adaptation
JORNA et al. Simulator flight as a selection device: Effects of test anxiety on subjective and objective measures of performance(Final Report)