Aerodynamic force measurement of free-flight models in a hypervelocity shock tunnel

1966 ◽  
Author(s):  
L. LAM ◽  
E. STOLLENWERK
Keyword(s):  
Force Measurement ◽  
Aerodynamic Force ◽  
Shock Tunnel ◽  
Free Flight

scholarly journals Aerodynamic characteristics of a free-flight scramjet vehicle in shock tunnel

2021 ◽  
Vol 62 (7) ◽  
Author(s):  
Marie Tanno ◽  
Hideyuki Tanno
Keyword(s):  
System Analysis ◽  
Force Measurement ◽  
Prediction Interval ◽  
Angular Acceleration ◽  
Aerodynamic Characteristics ◽  
Measurement Precision ◽  
Shock Tunnel ◽  
Free Flight ◽  
Vehicle Model ◽  
Aerodynamic Test

Abstract A multi-component aerodynamic test for an airframe-engine integrated scramjet vehicle model was conducted in the free-piston shock tunnel HIEST. A free-flight force measurement technique was applied to the scramjet vehicle model named MoDKI. A new method using multiple piezoelectric accelerometers was developed based on overdetermined system analysis. Its unique features are the following: (1) The accelerometer’s mounting location can be more flexible. (2) The measurement precision is predicted to be improved by increasing the number of accelerometers. (3) The angular acceleration can be obtained with single-axis translational accelerometers instead of gyroscopes. (4) Through the averaging process of the multiple accelerometers, model natural vibration is expected to be mitigated. With eight model-onboard single-axis accelerometers, the three-component aerodynamic coefficients (Drag, Lift, and Pitching moment) of MoDKI were successfully measured at the angle of attack from 0.7 to 3.4 degrees under a Mach 8 free-stream test flow condition. A linear regression fitting revealed a 95% prediction interval as the measurement precision of each aerodynamic coefficient. Graphical abstract

scholarly journals Intelligent Force-Measurement System Use in Shock Tunnel

Sensors ◽  
2020 ◽  
Vol 20 (21) ◽  
pp. 6179
Author(s):  
Yunpeng Wang ◽  
Zonglin Jiang
Keyword(s):  
Deep Learning ◽  
Measurement System ◽  
Force Measurement ◽  
Aerodynamic Force ◽  
Low Frequency ◽  
Shock Tunnel ◽  
New Method ◽  
Test Results ◽  
Force Measurement System ◽  
The Impact

The inertial vibration of the force measurement system (FMS) has a large influence on the force measuring result of aircraft, especially on some tests carried out in high-enthalpy impulse facilities, such as in a shock tunnel. When force tests are conducted in a shock tunnel, the low-frequency vibrations of the FMS and its motion cannot be addressed through digital filtering because of the inertial forces, which are caused by the impact flow during the starting process of the shock tunnel. Therefore, this paper focuses on the dynamic characteristics of the performance of the FMS. A new method—i.e., deep-learning-based single-vector dynamic self-calibration (DL-based SV-DSC) of an impulse FMS, is proposed to increase the accuracy of aerodynamic force measurements in a shock tunnel. A deep-learning technique is used to train the dynamic model of the FMS in this study. Convolutional neural networks with a simple structure are applied to describe the dynamic modeling so that the low-frequency vibration signals are eliminated from the test results of the shock tunnel. By validation of the force test results measured in a shock tunnel, the current trained model can realize intelligent processing of the balance signals of the FMS. Based on this new method of dynamic calibration, the reliability and accuracy of force data processing are well verified.

scholarly journals Free-flight force measurement technique in shock tunnel

2012 ◽  
Author(s):  
Hideyuki Tanno ◽  
Tomoyuki Komuro ◽  
Kazuo Sato ◽  
Katsuhiro Itoh ◽  
Masahiro Takahashi ◽  
...  
Keyword(s):  
Measurement Technique ◽  
Force Measurement ◽  
Shock Tunnel ◽  
Free Flight

Millisecond aerodynamic force measurement with side-jet model in theISL shock tunnel

AIAA Journal ◽  
1993 ◽  
Vol 31 (6) ◽  
pp. 1068-1074 ◽  
Author(s):  
K. W. Naumann ◽  
H. Ende ◽  
G. Mathieu ◽  
A. George
Keyword(s):  
Force Measurement ◽  
Aerodynamic Force ◽  
Shock Tunnel

Technique for aerodynamic force measurement within milliseconds in shock tunnel

Shock Waves ◽  
1991 ◽  
Vol 1 (3) ◽  
pp. 223-232 ◽  
Author(s):  
K. W. Naumann ◽  
H. Ende ◽  
G. Mathieu
Keyword(s):  
Force Measurement ◽  
Aerodynamic Force ◽  
Shock Tunnel

Aerodynamic Force Measurement in a Large-Scale Shock Tunnel

2019 ◽  
pp. 165-172
Author(s):  
Yunpeng Wang ◽  
Yunfeng Liu ◽  
Changtong Luo ◽  
Zonglin Jiang
Keyword(s):  
Large Scale ◽  
Force Measurement ◽  
Aerodynamic Force ◽  
Shock Tunnel
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