A novel free floating accelerometer force balance system for shock tunnel applications

The purpose of this study is testing the force of green energy lift mechanism and analyzes its result to get the key technology for green energy (saving force and energy). At first, the green energy lift mechanisms on the market are surveyed, then the mechanism are analyzed in this study. The force balance system of the mechanism is used to save force and energy. The position limitation of saving force and energy for the force balance system will be investigated. Universal testing machine is used to test the driving force by the different loads during the lift mechanism moving downward. The tested results of the driving force will be estimated. The study results show that the loads influence significantly the driving force. The angle between pulley and wire is the key factor of the driving force.

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Virtual Modelling and Testing of the Single and Contra-Rotating Co-Axial Propeller

Drones ◽

10.3390/drones4030042 ◽

2020 ◽

Vol 4 (3) ◽

pp. 42

Author(s):

Balram Panjwani ◽

Cecile Quinsard ◽

Dominik Gacia Przemysław ◽

Jostein Furseth

Keyword(s):

Experimental Data ◽

Experimental Testing ◽

Measurement Data ◽

Force Balance ◽

Virtual Model ◽

Balance System ◽

Thrust Measurement ◽

Lift And Drag ◽

Full Scale Tests ◽

Thrust And Torque

Propellers are a vital component to achieve successful and reliable operation of drones. However, the drone developer faces many challenges while selecting a propeller and a common approach is to perform static thrust measurement. However, the selection of a propeller using a static thrust measurement system is time-consuming. To overcome a need for the static thrust system a virtual model has been developed for measuring both the static and dynamic thrust of a single and coaxial propeller. The virtual model is reliable enough to minimize the need for full-scale tests. The virtual model has been built using two open-source software Qblade and OpenFoam. Qblade is employed to obtain the lift and drag coefficients of the propeller’s airfoil section. OpenFoam is utilized to perform the flow simulations of propellers and for obtaining the thrust and torque data of the propeller. The developed virtual model is validated with experimental data and the experimental data are obtained by developing a multi-force balance system for measuring thrusts and torques of a single and a pair of coaxial contra-rotating propellers. The data obtained from the propeller virtual model are compared with the measurement data. For a single propeller, the virtual model shows that the estimated forces are close to the experiment at lower rotational speeds. For coaxial propellers, there are some deviations at the rear propeller due to the turbulence and flow disturbance caused by the front propeller. However, the computed thrust data are still accurate enough to be used in selecting the propeller. The studies indicate that in the future, these virtual models will minimize a need for experimental testing.

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Performance Evaluation of an Aerodynamic Blade Model Using a Bottom-mounted Force Balance System

AIAA Propulsion and Energy 2019 Forum ◽

10.2514/6.2019-4160 ◽

2019 ◽

Cited By ~ 1

Author(s):

C.U. Ebuzeme ◽

Z.A. Quadri ◽

Olugbenga Noah ◽

Emmanuel O. Ogedengbe ◽

Charles Eguma

Keyword(s):

Performance Evaluation ◽

Force Balance ◽

Balance System ◽

Blade Model

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A new method for force prediction in an accelerometer force balance system using support vector regression

Transactions of the Institute of Measurement and Control ◽

10.1177/0142331219895645 ◽

2020 ◽

Vol 42 (4) ◽

pp. 880-889

Author(s):

Sushmita Deka ◽

Pallekonda Ramesh Babu ◽

Maneswar Rahang

Keyword(s):

Support Vector Regression ◽

Force Measurement ◽

Aerodynamic Force ◽

Accurate Prediction ◽

Force Balance ◽

Support Vector ◽

Inference System ◽

Force Prediction ◽

Balance System ◽

Testing Data

The accurate prediction of force is very important in the present scenario of aerodynamic force measurement. The high accuracy of force prediction during calibration facilitates a better accuracy of force measurement in aerodynamic facilities like shock tunnels and wind tunnels. The present study describes the force prediction in an accelerometer force balance system using support vector regression (SVR). The comparison of SVR with the existing force prediction techniques namely, adaptive neuro-fuzzy inference system (ANFIS) and artificial neural network (ANN) has also been carried out. The accelerometer force balance used in the current experimentation consists of a tri-axial accelerometer to measure the response on an aluminium hemispherical model on the application of force. The impulse forces were applied along the axial, normal and azimuthal directions. The forces were predicted using the accelerations obtained from the tri-axial accelerometer. SVR method was able to predict the forces quite accurately as compared to ANFIS and ANN. However, SVR has the advantage over ANFIS and ANN in that it is independent of the magnitude of the training and testing data. It is capable of an accurate prediction of forces with any magnitude of training and testing data, unlike ANFIS and ANN.

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Measurement of aerodynamic forces for missile shaped body in hypersonic shock tunnel using 6-component accelerometer based balance system

Shock Waves ◽

10.1007/978-3-540-85168-4_102 ◽

2009 ◽

pp. 637-642

Author(s):

S. Saravanan ◽

G. Jagadeesh ◽

K.P.J. Reddy

Keyword(s):

Shock Tunnel ◽

Aerodynamic Forces ◽

Shaped Body ◽

Balance System ◽

Hypersonic Shock ◽

Hypersonic Shock Tunnel

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Dynamic Calibration of Three-Component Accelerometer Force Balance System Using Deconvolution

Advances in Mechanical Engineering - Lecture Notes in Mechanical Engineering ◽

10.1007/978-981-15-0124-1_145 ◽

2020 ◽

pp. 1675-1683

Author(s):

Sushmita Deka ◽

Pallekonda Ramesh Babu ◽

Maneswar Rahang

Keyword(s):

Force Balance ◽

Dynamic Calibration ◽

Balance System

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Impulse Force Balance for Ultrashort Duration Hypersonic Test Facilities

Shock and Vibration ◽

10.1155/2015/803253 ◽

2015 ◽

Vol 2015 ◽

pp. 1-8

Author(s):

P. Singh ◽

V. Menezes ◽

K. J. Irimpan ◽

H. Hosseini

Keyword(s):

Impulse Response ◽

Aerodynamic Force ◽

Delta Wing ◽

Shock Tunnel ◽

Force Balance ◽

Test Model ◽

Impulse Response Functions ◽

Response Functions ◽

Test Assembly ◽

Hypersonic Shock

This paper presents the measurement of side force, pitching, and yawing moments on a model, using an accelerometer force balance, in a short duration hypersonic shock tunnel. The test model is a blunt-nosed, flapped delta wing, mounted on a support sting through a force balance. The flexible rubber bushes constituting the balance allow the model to float freely on the sting during the test. The accelerometers were located in the model to record accelerations in the directions of interest. The model was tested in shock tunnel at Mach 8 at different angles of incidence with the freestream. Dynamic calibration of the test assembly was carried out for the acquisition of impulse response functions for the above components of force and moments, using an impulse hammer. The convolution technique was applied to derive the impulse response functions. The accelerometer outputs from the model in the hypersonic freestream were processed using the respective impulse response functions to derive the unknown aerodynamic force and moments. The newly adopted convolution technique has been found very effective for data reduction from accelerometer force balances developed for shock tunnel applications.

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