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Force Measurement Using Non-Restrained Models in a Shock Tunnel

Tanno, Hideyuki und Sato, Kazuo und Komuro, Tomoyuki und Takahashi, Masahiro und Itoh, Katsuhiro und Fujita, Kazuhisa und Laurence, Stuart und Hannemann, Klaus (2011) Force Measurement Using Non-Restrained Models in a Shock Tunnel. 7th European Symposium on Aerothermodynamics for Space vehicles, 9. Mai - 12. Mai 2011, Brugge, Belgien.

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Kurzfassung

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 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. At the beginning of the wind tunnel test, the blunted cone test model was suspended from electromagnets fixed on the test-section ceiling. The model was released when a triggering signal arrived from the tunnel start signal. The model then fell so that it met the hypersonic test flow just as it arrived in the test section, and made a soft landing on a model catcher with four hydraulic shock absorbers. A miniature model-onboard 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 50 mm x 70 mm x 50 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 analog-digital converters, which digitize the measured data with 16-bit resolution. The logger’s sampling rate and sample size are 500 kHz and 200 ms, respectively. The logger waits for a trigger signal (accelerometer output) and then starts to take measurements. The trigger threshold and pre-trigger delay time can be adjusted arbitrarily. 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 and axial force 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:Force Measurement Using Non-Restrained Models in a Shock Tunnel
Autoren:
AutorenInstitution oder E-Mail-Adresse der Autoren
Tanno, HideyukiJAXA, Miyagi
Sato, KazuoJAXA, Miyagi
Komuro, TomoyukiJAXA, Miyagi
Takahashi, MasahiroJAXA, Miyagi
Itoh, KatsuhiroJAXA, Miyagi
Fujita, KazuhisaJAXA, Tokyo
Laurence, StuartStuart.Laurence@dlr.de
Hannemann, KlausKlaus.Hannemann@dlr.de
Datum:2011
Referierte Publikation:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Name der Reihe:Conference Proceedings
Status:veröffentlicht
Stichwörter:Force and moment measurement, Hypersonic wind tunnel, on-board data-acquisition
Veranstaltungstitel:7th European Symposium on Aerothermodynamics for Space vehicles
Veranstaltungsort:Brugge, Belgien
Veranstaltungsart:internationale Konferenz
Veranstaltungsdatum:9. Mai - 12. Mai 2011
Veranstalter :ESA
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: Dagmar Brennecke-Hosseinzadeh
Hinterlegt am:30 Nov 2011 11:53
Letzte Änderung:18 Jan 2012 12:04

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