Wind-Tunnel Technique for Determining Stability Derivatives from Cable-Mounted Models

Bennett, Robert M.; Farmer, M. G.; Mohr, R. L.; Hall, W. E.

doi:10.2514/3.58360

Cited by 32 publications

(8 citation statements)

References 3 publications

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“…The traditional rigid suspension systems have some unavoidable drawbacks for the experiments of static and dynamic derivatives such as the serious interference of the strut on the streamline flow (Zhang et al 2006;Roas, 2001;Bernhardt and Williams, 2000;Cao andDeng, 1998 andDu andWang, 2003). The cable-mounted systems for wind tunnel tests, developed in the past several decades, deal with the contradiction between the supporting stiffness and the interference on the streamline flow (Bian et al 1999;Shen and Huang, 1999;Bennett et al 1978;Liu et al 2001, Wang et al 2004and Griffin 1991. However their mechanism is not robotic and consequently quite different from wire-driven parallel suspension systems in attitude-control schemes and force-measuring principle.…”

Section: A Manually-operated Wdpss-8 Prototype Validated In a Closed-mentioning

confidence: 99%

Preliminary Step Towards Wire-Driven Parallel Suspension Systems for Static and Dynamic Derivatives of the Aircraft in Low-Speed Wind Tunnels

et al. 2010

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The wind tunnel test is one important way to obtain the aerodynamic derivatives of aircrafts. These derivatives are necessary when the guidance and control systems of the aircraft are designed and when the dynamic quality of the aircraft is analyzed as well. The results of experiments of the static derivatives and dynamic derivatives of the aircraft in low-speed wind tunnels have revealed that there are some unavoidable drawbacks such as the interference of the streamline flow brought about by the strut in the traditional strut suspension system. A cable-mounted system is very suitable for experiments of the static derivatives of an aircraft, but it cannot be used in the experiments of dynamic derivatives. In order to use the same wire-driven parallel suspension system to realize the static and dynamic derivates experiments in low-speed wind tunnels, a survey of the research work addressed within the Wire-Driven Parallel Suspension Systems (WDPSS-8) project is presented in this paper. The results show that WDPSS-8 can be successfully used in experiments of static derivatives, and that it has potentiality to be used in experiments of dynamic derivatives. In the issues in the theoretical aspect the issues have been handled. However, much work should be done in the experimental aspects. The research outcomes of WDPSS-8 will help the Chinese set up Chinese brands in the field of wind tunnel tests of aircrafts.

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Section: A Manually-operated Wdpss-8 Prototype Validated In a Closed-mentioning

confidence: 99%

Preliminary Step Towards Wire-Driven Parallel Suspension Systems for Static and Dynamic Derivatives of the Aircraft in Low-Speed Wind Tunnels

et al. 2010

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“…The mounting of wind tunnel models by wires is not new. In an earlier study Bennett (1978) used wire-mounted models to determine the oscillatory modes of the system for stability testing. His work focused on a scale F-14 model with 4 cables, and increased the tunnel speed until the lift produced by the wings balanced the model weight.…”

Section: Iii1 the Wind Tunnel Modelmentioning

confidence: 99%

Fluidic Actuation and Control of Munition Aerodynamics

Glezer¹

2009

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“…In an earlier study Bennett 19 used wire-mounted models to determine the oscillatory modes of the system for stability testing. In more recent work, Magill et al 20 used a wire suspension model for virtual flight testing of missile dynamics coupled with load cells to measure the tension. As shown in Figure 2, the wires are connected to a frame that consists of two steel circular hoops that are each 3 mm thick and 48cm in diameter, placed 70cm apart using four aluminum rods (2cm in diameter) that run along the tunnel length.…”

Section: Ii1 the Wind Tunnel Modelmentioning

confidence: 99%

Fluidic Control of Steering Aerodynamic Forces on Axisymmetric Bodies using a Mid-Body Cavity

Abramson

Vukašinović

Glezer

2009

39th AIAA Fluid Dynamics Conference

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The aerodynamic steering forces and moments on an axisymmetric bluff body are fluidically controlled by segmented vectoring of the outer flow through a mid-body axisymmetric cavity. Control is effected by an array of four individually-addressable, aft-facing synthetic jet actuators that emanate from the upstream end of the cavity over an integrated Coanda surface. The model is wire-mounted in the wind tunnel such that each support wire is instrumented with a miniature inline strain gage sensor for direct dynamic force measurements. The cavity flow field associated with quasi-steady and transitory actuation that results in asymmetric forces and moments is also characterized using high-resolution PIV measurements. It is shown that single jet actuation generates a quasi-steady, nearlymatched force couple at the upstream and downstream ends of the cavity. Transitory activation of multiple jets can be used to control the onset and sequencing of the couple forces and therefore the time history of the resultant force and moment.

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Wind-Tunnel Technique for Determining Stability Derivatives from Cable-Mounted Models

Cited by 32 publications

References 3 publications

Preliminary Step Towards Wire-Driven Parallel Suspension Systems for Static and Dynamic Derivatives of the Aircraft in Low-Speed Wind Tunnels

Preliminary Step Towards Wire-Driven Parallel Suspension Systems for Static and Dynamic Derivatives of the Aircraft in Low-Speed Wind Tunnels

Fluidic Actuation and Control of Munition Aerodynamics

Fluidic Control of Steering Aerodynamic Forces on Axisymmetric Bodies using a Mid-Body Cavity

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