Transonic Dynamics Tunnel Aeroelastic Testing in Support of Aircraft Development

Cole, Stanley R.; Noll, Thomas; Perry, Boyd

doi:10.2514/2.6873

Cited by 31 publications

(3 citation statements)

References 8 publications

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“…In the morphing process, the unsteady dynamic aerodynamic features lack acknowledged analysis and support from relevant aerodynamic basic theories [53,54]. In terms of numerical simulation methodologies, the modern numerical simulation technology is capable of simulating the moving boundary's unstable dynamic aerodynamic properties [55,56]. However, there is no effective theory or verification and confirmation of wind tunnel experimental results, and their rationality and correctness lack solid support [57].…”

Section: Current Status Of Aeroelastic Numerical Simulation Of High-p...mentioning

confidence: 99%

Recent Progress on Aeroelasticity of High-Performance Morphing UAVs

Lv¹,

Zha²,

Zeng³

et al. 2022

Computer Modeling in Engineering &Amp; Sciences

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The high-performance morphing aircraft has become a research focus all over the world. The morphing aircraft, unlike regular unmanned aerial vehicles (UAVs), has more complicated aerodynamic characteristics, making itmore difficultto conduct its design, model analysis, and experimentation. This paper reviews the recent process and the current status of aeroelastic issues, numerical simulations, and wind tunnel test of morphing aircrafts. The evaluation of aerodynamic characteristics, mechanism, and relevant unsteady dynamic aerodynamic modeling throughout the morphing process are the primary technological bottlenecks formorphing aircrafts. The unstable aerodynamic forces have a significant impact on the aircraft handling characteristics, control law design, and flight safety. In the past, the structural analysis of morphing aircrafts, flight dynamics modeling, computational mesh morphing technology, and aerodynamic calculation were performed in promoting the development of next generation UAVs, with nonlinear dynamic challenges includingtransonic aeroelastic problems and high angle of attack aeroelastic problems. At present, many facets of these difficulties, together with the accompanying numerical simulation studies, remain under-explored. In addition, wind tunnel experiments face significant challenges in the dynamic morphing process. Finally, dynamic unsteady aerodynamic characteristics in the continuous morphing process still need to be verified by more related experiments.

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Section: Current Status Of Aeroelastic Numerical Simulation Of High-p...mentioning

confidence: 99%

Recent Progress on Aeroelasticity of High-Performance Morphing UAVs

Lv¹,

Zha²,

Zeng³

et al. 2022

Computer Modeling in Engineering &Amp; Sciences

View full text Add to dashboard Cite

show abstract

“…Therefore, transonic wind tunnel test is inevitable in aircraft design process [2,3] . In America, transonic flutter tests are usually conducted in NASA Langley Transonic Dynamics Tunnel (TDT).…”

Section: Introductionmentioning

confidence: 99%

Integrated flutter test of a horizontal-tail model in the large-scale continuous transonic wind tunnel

Han

Liu

Huang

et al. 2023

J. Phys.: Conf. Ser.

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Wind tunnel test is a critical way to investigate flutter characteristics of aircraft, particularly in identifying the transonic dip phenomenon in the aeroelastic design. The continuous wind tunnel has advantages over the blow-down wind tunnel in long running time, wide bandwidth of dynamic pressure, and stable flow field. Thus, the continuous wind tunnel is more suitable for transonic flutter tests. Flutter test techniques are studied for FL-62 wind tunnel, the first large-scale continuous transonic wind tunnel in China. A protection system and a real-time signal processing are developed to ensure the safety and efficiency. Flutter boundaries of a horizontal-tail model are investigated in FL-62 wind tunnel in the Mach number regime between 0.65 and 0.98. In the test, structural vibrations are measured via strain gauges, deformations and pressure distributions are measured via non-contact optical techniques, and flutter boundaries are predicted via a modal identification method.

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“…Using the flutter test of the component model to check the flutter properties of flight vehicles are workable when the component-to-component structure is not coupled or coupled in a low degree [4]. However, along with the development of modern flight vehicles, the composite material technology is more and more widely used in flight vehicles structure, which further enhances the structural nonlinearity and further makes complicated the component-to-component interaction.…”

Section: Introductionmentioning

confidence: 99%

The Floating Suspension System in the Transonic Wind Tunnel for Full-Model Flutter Test

Yang

et al. 2013

AMR

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Aiming at the 2.4m×2.4m wind tunnel, this paper introduces the floating suspension system (“FSS”) in the full-mode flutter test, analyzes the impact of the model’s “free” movement to the elastic vibration mode and verifies the control effect of the system to the pitching and rolling movements of the model. Test results show that the FSS system may realize the free movement of the flutter model in five directions other than the axial direction without impacting the elastic vibration mode; FSS system controls through two independent channels, namely, the pitch and the roll; load reduction on the model and the steel wire may be realized by cutting down the pitch and roll angles of the model and the control of FSS to the pitching and rolling movement of the model get guaranteed by selecting appropriate control parameters.

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Transonic Dynamics Tunnel Aeroelastic Testing in Support of Aircraft Development

Cited by 31 publications

References 8 publications

Recent Progress on Aeroelasticity of High-Performance Morphing UAVs

Recent Progress on Aeroelasticity of High-Performance Morphing UAVs

Integrated flutter test of a horizontal-tail model in the large-scale continuous transonic wind tunnel

The Floating Suspension System in the Transonic Wind Tunnel for Full-Model Flutter Test

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