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Free-flight force measurement technique in a shock tunnel

Tanno, Hideyuki und Komuro, Tomoyuki und Sato, Kazuo und Itoh, Katsuhiro und Takahashi, Masahiro und Fujita, Kazuhisa und Laurence, Stuart und Hannemann, Klaus (2012) Free-flight force measurement technique in a shock tunnel. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 09. - 12. Jan. 2012, Nashville, TN, USA. DOI: 10.2514/6.2012-1241. ISBN eISBN: 978-1-60086-936-5.

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A novel force measurement technique has been developed at the impulsive facility HIEST, in which the test model is completely non-restrained for the duration of the test, so it experiences completely free-flight conditions for a period on the order of milliseconds. This technique was demonstrated with a three-component aerodynamic force measurement with a blunted cone of total length 318 mm and a total mass of 22 kg in hypervelocity test flow. A miniature modelonboard data-logger, which was a key technology for this technique, was also developed in order to store the measured data. The data-logger was designed to be small enough to be instrumented in test models, with an overall size of 100 mm x 100 mm x 70 mm, including batteries. Since the logger was designed to measure force and pressure, it includes six piezoelectric amplifiers and four piezoresistive amplifiers, as well as high-speed analogue-digital converters, which digitize the measured data with 16-bit resolution. The logger’s sampling rate and sample size are 500 kHz and 400 ms, respectively. For the autonomous operation, the logger waits for a trigger signal (accelerometer output) and then starts to take measurements with arbitrary adjustable trigger threshold level and pre-trigger delay time. Measured data is stored to static memory for transfer to a PC via a USB interface after a wind tunnel test. To demonstrate the entire measurement system, wind tunnel experiments were conducted in HIEST. In the present wind tunnel test campaign, records of pressure, axial force, nominal force and pitching moment were obtained under conditions of H0 = 4 MJ/kg, P0 = 14 MPa. This demonstrated that the system worked correctly in the short test duration and harsh conditions typical of HIEST. Use of this data-logger allows the elimination of a large-diameter sting, ending concerns about the sting’s interference with the base flow of the model, which could cause serious errors in measurement in wind tunnel tests.

Dokumentart:Konferenzbeitrag (Vortrag, Paper)
Titel:Free-flight force measurement technique in a shock tunnel
AutorenInstitution oder E-Mail-Adresse der Autoren
Tanno, HideyukiJAXA
Komuro, TomoyukiJAXA, Miyagi
Sato, KazuoJAXA, Miyagi
Itoh, KatsuhiroJAXA
Takahashi, MasahiroJAXA, Miyagi
Fujita, KazuhisaJAXA, Tokyo
Laurence, StuartStuart.Laurence@dlr.de
Datum:9 Januar 2012
Referierte Publikation:Nein
In Open Access:Ja
In ISI Web of Science:Nein
DOI :10.2514/6.2012-1241
Seitenbereich:Seiten 1-10
Name der Reihe:Conference Proceedings online
ISBN:eISBN: 978-1-60086-936-5
Stichwörter:Force measurement, shock tunnel
Veranstaltungstitel:50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
Veranstaltungsort:Nashville, TN, USA
Veranstaltungsart:internationale Konferenz
Veranstaltungsdatum:09. - 12. Jan. 2012
Veranstalter :American Institute of Aeronautics and Astronautics
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Raumtransport
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):R - Raumfahrzeugsysteme - Anlagen u. Messtechnik
Standort: Göttingen
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Raumfahrzeuge
Hinterlegt von: Stuart Laurence
Hinterlegt am:14 Aug 2012 11:06
Letzte Änderung:13 Sep 2012 16:41

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