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

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

doi:10.2514/3.11730

Cited by 48 publications

(8 citation statements)

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“…In fact, the suspension system decides the feasibility of accelerometer balance system for use in short duration testing applications. One such free flying mounting systems described by Naumann et al [8] releases the model just before the flow and grips it again after the free flight duration of 1-2 ms. But the complete measurement system is cumbersome and moreover it is difficult to maintain the necessary level of accuracy during measurement.…”

Section: Introductionmentioning

confidence: 99%

Design and analysis of a flat accelerometer-based force balance system for shock tunnel testing

et al. 2007

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Section: Introductionmentioning

confidence: 99%

Design and analysis of a flat accelerometer-based force balance system for shock tunnel testing

et al. 2007

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“…Moreover, the technique was also applied in an HIEST test campaign involving the HYFLEX lifting body to measure the body-flap (Elevon) efficiency under high-temperature real-gas conditions. 6 used direct acceleration measurements with miniature accelerometers mounted inside the model in experiments carried out in a shock tunnel. Through a cleverly designed model injection and catching system, the test model could experience free-flight conditions over 10 milliseconds.…”

Section: Introductionmentioning

confidence: 99%

Free-flight aerodynamic tests of reentry vehicles in high-temperature real-gas flow (Invited)

Tanno

Sato

Komuro

et al. 2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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Aerodynamic tests conducted in the HIEST free-piston high-enthalpy shock tunnel were reported. A novel multi-component force-measurement technique was implemented, which involved the test model being completely non-restrained for the duration of the test and thus experiencing free-flight conditions for a period in the order of milliseconds. Compared with conventional free-flight techniques, the present one has the advantage of no aerodynamic interference with the model support system and less variation in the model position and attitude during the test. The measurement accuracy and precision of the technique were compared to a conventional blow-down wind tunnel and evaluated in a HIEST test campaign with a blunted cone. During the test campaign, the pitching-moment coefficient under the HIEST high-enthalpy condition differed significantly from that of low enthalpy, which was considered attributable to high-temperature real-gas effects. The technique has already been applied to a HIEST test campaign for the Japanese HTV-R re-entry capsule to determine its trim angle at re-entry. Moreover, the technique was also adopted to measure the body flap (elevon) efficiency of the HYFLEX lifting body. NomenclatureAOA = Angle of attack CA = Axial force coefficient CN = Normal force coefficient CMy = Pitching moment coefficient P 0 = Stagnation pressure P Pitot = Free-stream Pitot pressure PI = Prediction interval X = Model displacement (x-direction) Y = Model displacement (y-direction)  = Standard deviation *

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“…For the conventional hypersonic shock tunnel, mechanical vibration of the model-balance-sting system (MBSS) occurs and cannot be damped during a shock tunnel run because of the short test time (generally 500 µs-20 ms) [1][2][3][4]. Therefore, if an averaging method is adopted during signal processing, then at least five cycles of balance signal, with the lowest vibrational frequency of the MBSS, should be observed during the test time to obtain better measurement results [2].…”

Section: Introductionmentioning

confidence: 99%

Design of a pulse-type strain gauge balance for a long-test-duration hypersonic shock tunnel

2016

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When the measurement of aerodynamic forces is conducted in a hypersonic shock tunnel, the inertial forces lead to low-frequency vibrations of the model, and its motion cannot be addressed through digital filtering because a sufficient number of cycles cannot be obtained during a tunnel run. This finding implies restrictions on the model size and mass as the natural frequencies are inversely proportional to the length scale of the model. Therefore, the force measurement still has many problems, particularly for large and heavy models. Different structures of a strain gauge balance (SGB) are proposed and designed, and the measurement element is further optimized to overcome the difficulties encountered during the measurement of aerodynamic forces in a shock tunnel. The motivation for this study is to assess the structural performance of the SGB used in a long-test-duration JF12 hypersonic shock tunnel, which has more than 100 ms of test time. Force tests were conducted for a large-scale cone with a 10 • semivertex angle and a length of 0.75 m in the JF12 long-test-duration shock tunnel. The finite element method was used for the analysis of the vibrational characteristics of the Model-Balance-Sting System (MBSS) to ensure a sufficient number of cycles, particularly for the axial force signal during a shock tunnel run. The higher-stiffness SGB used in the test shows good performance, wherein the frequency of the MBSS increases because of the stiff construction of the balance. The experimental results are compared with the data Communicated by K. Hannemann and A. Higgins.

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

Cited by 48 publications

References 1 publication

Design and analysis of a flat accelerometer-based force balance system for shock tunnel testing

Design and analysis of a flat accelerometer-based force balance system for shock tunnel testing

Free-flight aerodynamic tests of reentry vehicles in high-temperature real-gas flow (Invited)

Design of a pulse-type strain gauge balance for a long-test-duration hypersonic shock tunnel

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