Technique for aerodynamic force measurement within milliseconds in shock tunnel

Naumann, K. W.; Ende, H. van den; Mathieu, G.

doi:10.1007/bf01413797

Cited by 33 publications

(8 citation statements)

References 3 publications

(1 reference statement)

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“…Hence, for hydrogen at a measured supply pressure, a value of discharge coefficient was calculated via Eq. (12).…”

Section: Mass Flow Rate Measurementmentioning

confidence: 95%

“…Thus, as shown by the block diagram of Fig. 1, an input of yields an output of F where the system's transfer function is [12,15]. For this system, the relationship between the convolution integral and the Fourier domain can be specifically expressed as (1) Equation (1) relates the input and the output via the system's transfer function which can be determined as follows.…”

Section: A System Transfer Functionmentioning

confidence: 99%

“…Instead, a third-order least-squares fit was chosen to portray the variation of discharge coefficient with the supply pressure. The equation is (12) where is the supply pressure in MPa and is the discharge coefficient for hydrogen gas. The correlation coefficient for this fit was 0.99.…”

Section: Mass Flow Rate Measurementmentioning

confidence: 99%

“…A force measurement method which requires identification of the system's dynamic parameters has been wellestablished in thrust and drag measurements in shock tunnels [10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25][26] and appears feasible for application to PDEs. In fact, as an intermediate step, these force measurement techniques can be directly applied to a single-shot…”

Section: Introductionmentioning

confidence: 99%

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Unsteady Thrust Measurement for Pulse Detonation Engine

Joshi¹,

Lu²

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A new approach to thrust measurement for pulse detonation engines (PDEs) was developed to account for the effects of system dynamics. The approach was applied to a PDE operating at 10 and 20 Hz. Important system parameters such as steady-state response, effective mass of PDE and thrust measurement rig structure, and mass flow rates of fuel/oxidizer were first determined. The system dynamics of the PDE, deconvolved in the frequency domain, was studied. The system's transfer function between the thrust and a corresponding pressure obtained by a single propagating detonation pressure history during a typical PDE operation was established and used to reconstruct the thrust response for pulsed operation. A proper reconstruction of the deconvolved thrust values was accomplished through this technique. The acceleration experienced by the PDE thrust measurement rig during a typical operation was also measured. This measured acceleration when multiplied by the determined effective mass gave an estimate of the inertial force. The estimated inertial force when subtracted from the deconvolved force gave actual thrust. The measured and compensated thrust were expressed in the form of impulse.

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“…Hence, for hydrogen at a measured supply pressure, a value of discharge coefficient was calculated via Eq. (12).…”

Section: Mass Flow Rate Measurementmentioning

confidence: 95%

Section: A System Transfer Functionmentioning

confidence: 99%

Section: Mass Flow Rate Measurementmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Unsteady Thrust Measurement for Pulse Detonation Engine

Joshi¹,

Lu²

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…A practical and widely used solution is acceleration compensation [1,3,8,9,11,13,14]. That is, to embed some accelerometers into the balance in the hope that the vibration signal can be removed from the balance signal produced.…”

Section: Introductionmentioning

confidence: 99%

Wave system fitting: A new method for force measurements in shock tunnels with long test duration

Luo

Wang

Chun

et al. 2015

Mechanical Systems and Signal Processing

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a b s t r a c tForce measurements in shock tunnels are difficult due to the existence of vibrations excited by a sudden aerodynamic loading. Accelerometer inertia compensation could reduce its negative effect to some extent, but has inherent problems. A new signal decomposition method, wave system fitting (WSF), is proposed to remove vibration waves of low frequency. The WSF is accelerometer-free. It decomposes the balance signal and can separate vibration waves without the influence on the DC component, and it does work no matter the cycle of the sample signal is complete or not. As a standard signal postprocessing tool in JF-12, the application results show that it works reliably with high accuracy, and it can also explain puzzling signals encountered in JF-12. WSF method is especially useful and irreplaceable whenever only a few cycles of a periodic signal could be obtained, as is usual for shock tunnels.

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Dynamic Calibration of a Stress-Wave Force Balance Using Hybrid Soft Computing Approach

Nayak

Sahoo

2022

Nonlinear Dynamics and Applications

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Technique for aerodynamic force measurement within milliseconds in shock tunnel

Cited by 33 publications

References 3 publications

Unsteady Thrust Measurement for Pulse Detonation Engine

Unsteady Thrust Measurement for Pulse Detonation Engine

Wave system fitting: A new method for force measurements in shock tunnels with long test duration

Dynamic Calibration of a Stress-Wave Force Balance Using Hybrid Soft Computing Approach

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