Integrated automation and instrumentation system for static and life testing of full-scale modern maneuverable aircraft

Serioznov, A. N.; Metyolkin, N.G.; Ryabinov, M.I.

doi:10.1109/korus.1999.875856

Cited by 4 publications

(2 citation statements)

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“…The current aircraft fatigue loading test urgently needs to shorten the time: It takes 2 to 6 years [ 5 ] to complete. Because the average life of modern civil aircraft is as high as 60,000 flight hours multiple life tests are required in the test [ 6 , 7 ]. The key to influencing the test time now is the limitation of the loading frequency and the strong coupling between the channels [ 8 , 9 ].…”

Section: Introductionmentioning

confidence: 99%

Motion Synchronous Composite Decoupling with Fewer Sensors on Multichannel Hydraulic Force Control for Aircraft Structural Loading Test System

Bai

Jiao

Yao

et al. 2018

Sensors

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The aircraft full-scale fatigue test is widely used in the modern aircraft industry for the safety of flight. Generally, the aircraft full-scale fatigue test is achieved by structural loading; multiple hydraulic actuators are used to apply load for force control. The fatigue loading test takes approximately several years. A key challenge is how to accelerate the loading frequency to shorten the total test time. Nevertheless, when pluralities of hydraulic actuator simultaneously increase the loading frequency, the mutual coupling force from the low rigidity of the aircraft structure will cause a large loading error, meaning that the test cannot be implemented. Although it is possible to reduce error by adding sensors, the force sensors need to connect several kilometers of cable. This paper proposed a novel motion synchronous composite decoupling control strategy with fewer sensors. The control method compensates the negative coupling effect of the channels by integrating the command signals and feedback signals of all channels. It can suppress coupling force and reduce errors at higher frequencies, thereby shortening the experiment time. Opposed to traditional decoupling control methods, advantages of this strategy are that it only needs force sensors and it does not need additional displacement or velocity and acceleration sensors to collect state variables for building the state space. Furthermore, it has been experimentally verified that the new motion synchronous composite decoupling control method can indeed guarantee sufficient control accuracy when the test frequency is increased. The method has great economic significance for shortening test duration.

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Section: Introductionmentioning

confidence: 99%

Motion Synchronous Composite Decoupling with Fewer Sensors on Multichannel Hydraulic Force Control for Aircraft Structural Loading Test System

Bai

Jiao

Yao

et al. 2018

Sensors

View full text Add to dashboard Cite

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“…Static loading test is to study the characteristic problem of engineering structures under static loading in strength, stiffness and static stability; it is the basis for other structural test [1][2][3]. Current aircraft structural test mainly focused on the centralized type of hydraulic energy to drive multi-channel hydraulic loading actuators, and the main problem is large and complex piping which makes the test-bed hard to change, especially for large-scale aircraft structural test [4][5][6][7]. By learning the power-by-wire concept of flight control actuation system, we can design the actuator in the form of power-bywire.…”

Section: Introductionmentioning

confidence: 99%

A new type of electro-hydraulic actuator used for aircraft structural test

Caijin¹,

Zhang²,

Wang³

2012

International Conference on Automatic Control and Artificial Intelligence (ACAI 2012)

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escribthe system components and working principle of a new type of electro-hydraulic actuator used for aircraft structural loading test, the mathematical model of electro-hydraulic actuator is established, modelled and simulated by using advanced modeling and simulation environment AMESim. It is shown that using AMESim to model and simulate performance more directly and veritably, and can complete the design task accurately and quickly. The simulation results show that the design of electro-hydraulic actuator performance target achieves the expected requirements, and it can be used widely in aircraft structural loading test system.

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Direct load sensitive electro-hydrostatic force control actuator for asymmetric cylinder with switch valve: Design and simulation

Weiyi

Zongxiao

Zhang

2015

2015 International Conference on Fluid Power and Mechatronics (FPM)

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Integrated automation and instrumentation system for static and life testing of full-scale modern maneuverable aircraft

Cited by 4 publications

References 0 publications

Motion Synchronous Composite Decoupling with Fewer Sensors on Multichannel Hydraulic Force Control for Aircraft Structural Loading Test System

Motion Synchronous Composite Decoupling with Fewer Sensors on Multichannel Hydraulic Force Control for Aircraft Structural Loading Test System

A new type of electro-hydraulic actuator used for aircraft structural test

Direct load sensitive electro-hydrostatic force control actuator for asymmetric cylinder with switch valve: Design and simulation

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