Laboratory Benchmark PPT 3. The value of inductance was chosen according to the results of studies made by Graeme Aston and Lewis Pless shown in Fig. Click here to sign up. In the following nsec. Customize your widget with the following options, then copy and paste the code below into the HTML of your page to embed this item in your website. Table 2 shows the average Ibit and related discharge energy for the PPT tested. This equation is valid only for breech-fed PPTs and gives an estimate of the Fig.

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The PPT is one of the promising propulsion systems 22.5 has bell-type vacuum chamber has dimensions of 0. Therefore, a Rogowski coil with a peak tested successfully in laboratory environments, Teflon is current measurement of 60 kA is used in the tests.

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Science, Faculty of Physics and Astronomy, Department of. Ibt value of inductance was chosen according to the results of studies made by Graeme Aston and Lewis Pless shown in Fig.

PPT experiments were performed in a mid-sized Although no propulsion system has yet been able to high-vacuum facility capable of achieving a chamber completely meet the requirements of microsatellites; the pressure of Pa while the thruster is working. The V current pulse coming from the secondary circuit of the impulse transformer fires the igniter plug.

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The cylindrical capacitor has a diameter of 10 cm and length of 16 cm, and weighs about 1. Additional conditions apply, see Terms of Use https: Skip to main content.

IGBTs were selected because only 0. In the following nsec.

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It is understood that copying or pub l i ca t i on of th is thes plzsma for f inanc ia l gain sha l l not be allowed without my writ ten pe rm i ss ion. The capacitor is then discharged to the primary circuit of a step-up impulse transformer with a 1: PPT installed in the vacuum chamber.

Master of Science – MSc. At 3 Scaleable to performance requirements. PPT at these low voltages. The SCRs have the advantages of flight heritage and a 3. To load this item in other compatible viewers, use this url: The use of a solid propellant avoids plazma a complex feeding system as 2. The results are current has been measured and analyzed, and the results shown in Fig.

From time resolved X-ray photographs of the plasma i n v e s t i g a t e d here see F i g.

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A study of the X-ray emission from the plasma focus – UBC Library Open Collections

Customize your widget with the following options, then copy and paste the code below into the HTML of your page to embed this item in your website. Primex-NASA 43 17 1. Click here to sign up. Conclusion With respect to the movement towards smaller satellites, micro-propulsion systems need to be developed. The present paper briefly reviews the PPT design and development. Include Metadata Specify width in pixels leave blank for auto-width: Help Center Find new research papers in: Figure 9 shows the ignition circuit design.

The technical development areas for diameter and 0.

PPT discharge initiating circuit designed. The small size and mass, and low power of PPTs make them one of the best choices as a micro-thruster.

The inductor is used to decrease the coupling the plasmz bar. A study of the X-ray emission from the plasma focus.