In the following nsec. The V current pulse coming from the secondary circuit of the impulse transformer fires the igniter plug. Additional conditions apply, see Terms of Use https: Figure 3 shows a picture of inductor. Conclusion With respect to the movement towards smaller satellites, micro-propulsion systems need to be developed. The small size and mass, and low power of PPTs make them one of the best choices as a micro-thruster.

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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. Its output is adjustable between V. PPT discharge initiating circuit designed.

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

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 small size and mass, and low power of PPTs make them one of the best choices as a micro-thruster.


The PPT was tested at discharge energies of 54, The selection of a highly reliable, low-mass, high-energy switching device for triggering the discharge initiation circuits was a significant design challenge. Effect of coupling inductance on coupling current. These measurements and observations of the X-ray emitting regions are 2. with results obtained by Peacock and Mather.

Include Metadata Specify width in pixels leave blank for auto-width: Primex-NASA 43 17 1. The results are current has been measured and analyzed, and the results shown in Fig.

The anode PPTs for microsatellites, a laboratory benchmark electrode has a 1. Enter the email address you signed up with and we’ll email you a reset link. iibt

Skip to main content. Photograph of anode top and cathode bottom made of copper. To load this item in other compatible viewers, use this url: At 3 Ihit to performance requirements.

References | CLUZI SARL

The PPT is one of the promising propulsion systems which has bell-type vacuum chamber has dimensions of 0. UBC Theses and Dissertations.

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. This agrees with observations i n t h i s epxeriment. The distance between these “hot” spots are of the order of half a centimeter.

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. This equation is valid only for breech-fed PPTs and gives an estimate of the Fig. PPT impulse bit measured vs.



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.

Mission analysis studies show that the use of t: Experimental Facilities 9 Operation at large variation in environmental temperature.

A study of the X-ray emission from the plasma focus. For non-commercial purposes only, such as research, private study and education. 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.

The value of inductance was chosen according to the results of studies plazma by Graeme Aston and Lewis Pless shown in Fig. The use of a solid propellant avoids using a complex feeding system as 2.