The Dynamic Model and Acceleration Compensation for the Thrust Measurement System of Attitude/Orbit Rocket

Ren, Zongjin; Sun, Bingrong; Zhang, Jun; Qi, Min

doi:10.1109/wmso.2008.61

Cited by 5 publications

(4 citation statements)

References 2 publications

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“…Runyan et al [37] discussed the need to account for the dynamic excitation of the supporting base to estimate the actual thrust generated by small rockets. Ren et al [38] used an analytical model which utilized a weight coefficient analogous to the effective mass to implement acceleration compensation. The concept of effective mass was comprehensively presented and utilized for implementing acceleration compensation in aerodynamic force measurements in hypervelocity facilities by Storkmann et al [28].…”

Section: B Impact Hammer Test For Effective Massmentioning

confidence: 99%

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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Section: B Impact Hammer Test For Effective Massmentioning

confidence: 99%

Unsteady Thrust Measurement for Pulse Detonation Engine

Joshi¹,

Lu²

2014

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

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“…Junqing Ma [10] proposes a dynamic compensation method to broaden operation frequency based on the frequency response function for two-dimension force sensor. Zongjin Ren [11] proposes a dynamic compensation method based on acceleration for a rocket vector force test system reducing the dynamic error. J. Roj [12] develops real-time dynamic error correction of transducers based on a novel neural network.…”

Section: Introductionmentioning

confidence: 99%

A Novel Dynamic Method to Improve First-order Natural Frequency for Test Device

Zhang

Ren

et al. 2018

Measurement Science Review

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It is important to improve the natural frequency of test device to improve measurement accuracy. First-order frequency is basic frequency of dynamic model, which generally is the highest vibration energy of natural frequency. Taking vector force test device (VFTD) as example, a novel dynamic design method for improving first-order natural frequency by increasing structure stiffness is proposed. In terms of six degree-of-freedom (DOF) of VFTD, dynamic model of VFTD is built through the Lagrange dynamic equation to obtain theoretical natural frequency and mode shapes. Experimental natural frequency obtained by the hammering method is compared with theoretical results to prove rationality of the Lagrange method. In order to improve the stiffness of VFTD, increase natural frequency and meet the requirement of high frequency test, by using the trial and error method combined with curve fitting (TECF), stiffness interval of meeting natural frequency requirement is obtained. Stiffness of VFTD is improved by adopting multiple supports based on the stiffness interval. Improved experimental natural frequency is obtained with the hammering method to show rationality of the dynamic design method. This method can be used in improvement of first-order natural frequency in test structure.

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“…Xing et al 10 developed a piezoelectric thrust dynamometer to measure the thrust of low-thrust liquid pulsed rocket engines. Ren et al 11 proposed the dynamic pulse performance measurement of an attitude/orbit rocket with the piezoelectric sensors. The pairs of piezoelectric sensors were used by Mateescu et al 12 to detect the cracks in the wing structures subjected to oscillatory aerodynamic loads.…”

Section: Introductionmentioning

confidence: 99%

Design and calibration method for a novel six-component piezoelectric balance

Jia

Gao

Ren

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part C:

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Wind tunnel balance is one of the most important measurement equipments in aerodynamic testing. In this paper, a new six-component piezoelectric balance is developed to measure the dynamic impact loading force in the wind tunnel. The arrangement mode of the triaxial piezoelectric load cells is confirmed based on the theory analysis. Furthermore, the mathematical model is established according to the calibration experimental results. Support vector machine is proposed to develop the piezoelectric balance calibration. It is an effective method to predict the model using small samples and reduce the duration of the calibration. The results of prediction are compared to the conventional calibration and the dynamic step response. The linearity and repeatability of the balance are within 0.2% and 0.5%, respectively, and the interference error has been reduced using the support vector machine method. The experimental results have shown that the four supports arrangement mode can reduce the area of attack and enhance the measuring range of the balance. The dynamic characteristics of the piezoelectric balance performed by the step response test show that the designed balance is feasible to measure the dynamic impact airloads in a wind tunnel.

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The Dynamic Model and Acceleration Compensation for the Thrust Measurement System of Attitude/Orbit Rocket

Cited by 5 publications

References 2 publications

Unsteady Thrust Measurement for Pulse Detonation Engine

Unsteady Thrust Measurement for Pulse Detonation Engine

A Novel Dynamic Method to Improve First-order Natural Frequency for Test Device

Design and calibration method for a novel six-component piezoelectric balance

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