New calibration technique for multiple-component stress wave force balances

Abdel–jawad, Madhat; Mee, D. J.; Morgan, Richard G.

doi:10.1063/1.2744235

Cited by 26 publications

(10 citation statements)

References 9 publications

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“…The objective of the work was to experimentally derive the side force, pitching, and yawing moments on the model using an impulse response function of the system, where the construction of the model assembly, sensor uncertainties, restraint of the test model, and ultrashort duration effects do not influence the results. The results obtained by this method are believed to be more accurate in comparison with other data reduction methodologies [7].…”

Section: Introductionmentioning

confidence: 80%

Impulse Force Balance for Ultrashort Duration Hypersonic Test Facilities

Singh

Menezes

Irimpan

et al. 2015

Shock and Vibration

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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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Section: Introductionmentioning

confidence: 80%

Impulse Force Balance for Ultrashort Duration Hypersonic Test Facilities

Singh

Menezes

Irimpan

et al. 2015

Shock and Vibration

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“…These four constraints are equivalent to the methodology described in Ref. 31. In this work the weighting factors w k jl were defined according to the reference load distribution shown in Figure 6 with the balance centre taken as coinciding with the centre of force of the distribution.…”

Section: Iiib Force Balance Calibrationmentioning

confidence: 99%

Measurement of Three-Components of Force on an Airframe Integrated Scramjet at Mach 10

Doherty¹,

Smart²,

Mee³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Force balance experiments have been conducted within The University of Queensland's T4 Stalker Tunnel with a small airframe-integrated three-dimensional scramjet engine using a three-component stress wave force balance. The tests were conducted at conditions replicating flight at Mach 10 and a dynamic pressure of 52 kPa or 28 kPa. The internal flowpath featured a rectangular-to-elliptical shape transition (REST) inlet, an elliptical combustor with a constant area and a diverging section, and a three-dimensional thrust nozzle. This flowpath was integrated with a forebody and streamlined external geometry to provide the test model. Gaseous hydrogen fuel was injected either through portholes on the inlet, from a series of portholes behind the rearward facing step at the combustor entrance, or a combination of the two. The fuel-off drag coefficient was measured to be 0.246 ± 0.025 and 0.312 ± 0.032 at the high and low dynamic pressure test conditions respectively. At a fuel equivalence ratio of 1.20, the drag coefficient reduced to 0.118 ± 0.034 for a combined injection scheme at the high dynamic pressure test condition, corresponding to a specific impulse increment of 2160 s and a specific thrust increment of 740 N s/kg. This work represents the first time that force data have been measured for a hydrogen fuelled REST scramjet engine at true-flight Mach 10 test conditions. NomenclatureA area, m 2 A axial direction, m a axial coordinate, m A o output specification matrix A F projected frontal area, m 2 A p projected planar or planform area, m 2 a vi element of output specification relating strain output v to stress bar i outputheat of formation, J/kg ρ density, kg/m 3 d k j moment arm for calibration hit in direction k at calibration location j, m F force, N

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“…5 This sti®ness dominated force measurement concept has been then considered for various applications. [6][7][8] Odeen and Lundberg experimentally measured acceleration and strain for prediction of the force applied by one object on the other during impact. 9 Three objects (truncated cone of Nylon-6, compound cylinder of Nylon-6 and aluminum and long cylindrical steel rod) were considered for these experiments.…”

Section: Introductionmentioning

confidence: 99%

Experimental Assessment of Noncontact Type Laser-Based Force Measurement Technique for Impulsive Loading

Pallekonda

Bommana

Kulkarni

et al. 2014

Int. J. Str. Stab. Dyn.

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Force measurement is an essential element in the design of mechanical or nonmechanical systems. The choice of a particular technique, among the numerous measurement techniques available, depends on various parameters within which the nature of force is an important one. The measurement of impulse force is considered in this study using two techniques. In view of this, an experimental setup has been developed to understand the applicability and assessment of a laser-based extrusive technique, along with the established intrusive accelerometer-based technique for impulsive force measurement. The accelerometer-based measurements can be used to precisely predict the magnitude and temporal nature of the force. However, the velocitybased impulse prediction shows some limitation on complete representation of the system. In addition, the indirect measurement of acceleration from the velocity measured seems to have better prediction of the force.

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New calibration technique for multiple-component stress wave force balances

Cited by 26 publications

References 9 publications

Impulse Force Balance for Ultrashort Duration Hypersonic Test Facilities

Impulse Force Balance for Ultrashort Duration Hypersonic Test Facilities

Measurement of Three-Components of Force on an Airframe Integrated Scramjet at Mach 10

Experimental Assessment of Noncontact Type Laser-Based Force Measurement Technique for Impulsive Loading

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