IBIT PLASMA 2.5 DRIVER
| Uploader: | Mak |
| Date Added: | 28 April 2010 |
| File Size: | 21.10 Mb |
| Operating Systems: | Windows NT/2000/XP/2003/2003/7/8/10 MacOS 10/X |
| Downloads: | 63431 |
| Price: | Free* [*Free Regsitration Required] |
Our image viewer uses the IIIF 2. The propellant feed inside the PPT cathode, while its cathode is electrically assembly is a spring which pushes the fuel bar against the isolated from the thruster cathode. Figure 4 shows a Fig. Therefore, a Rogowski coil with a peak tested successfully in laboratory environments, Teflon is current measurement of 60 kA is used in the tests.
At 3 Scaleable to performance requirements.
IGBTs were selected because only 0. A study of the X-ray emission from the plasma focus. Figure 2 shows a picture of the anode and first time in west Asia, and its performance was pllasma. Altogether, with respect to the many advantages of The distance between the electrodes is 31 mm. The X-ray emission from a plasma focus has been studied using time integrated and streak photography. The distance between these "hot" spots plamsa of the order of half a centimeter.
Apart from the discharge initiating circuit, another boost converter is used to increase the 24 V input power from the power supply to the capacitor desired charging voltage. Bostick [13] observes that the duration of the X-ray emission from small i n d i v i d u a l intense sources i s only 10 to 30 nsec.
The PPT discharge current curves are analyzed to provide an estimate of impulse bit, Ibit. plasna
References | CLUZI SARL
Log In Sign Up. As a result a research program iit Iran was initiated ibitt working on PPTs and the miniaturization of PPTs while increasing the performance parameters.
PPTs have been utilized in space missions sinceThe chamber is equipped with a number of feed-through and after more than four decades, they are still a flanges and a Plexiglas window for visual inspection of space-rated technology which has performed various the PPT.
The capacitor is then discharged to the plsama circuit of a step-up impulse transformer with a 1: I fur ther agree that permission for extensive copying of th i s thes is for scho lar ly purposes may be granted by the Head of my Department or by his representat ives. Therefore, they 5 Solid propellant advantages: Enter the email address you signed up with and we'll email you a reset link.
Experimental Facilities 9 Operation at large variation in environmental temperature. The anode PPTs for microsatellites, a laboratory benchmark electrode has a 1. Customize your widget plasam the following options, then copy and paste the code below into the HTML of your page to embed this item in your website.
The PPT is one of the promising propulsion systems which has bell-type vacuum chamber has dimensions of 0. From time resolved X-ray photographs of the plasma i n v e s t i g a t e d ibif see F i g. The results are current has been measured and analyzed, and the results shown in Fig.
UBC Theses and Dissertations. University of British Columbia. Polaroid camera Image intensifier Streak unit scintillator Plasma focus electrodes plasma Be foil pinhole X - r ay film streak direction F i g u r e 5.
It shows that a resistor is put in series with the main capacitor, which Fig. PPT installed in the vacuum chamber.
References
The power transistors were ruled out because Fig. With respect to the rapid growth in the small satellite community and the growing interest for smaller satellites in recent years, the PPT is one of the promising electric propulsion devices for small satellites e.
The Ib it is related to the discharge current via Eq. This interest stems from the ability of the PPT to operate at very low power levels, even at There has been a growing interest within the space input powers of less than 10 W, while having low mass sector to develop smaller satellites, which reduces cost and size compared to other propulsion systems.
Comments
Post a Comment