NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
5.8kV SiC PiN Diode for Switching of High-Efficiency Inductive Pulsed Plasma Thruster CircuitsInductive Pulsed Plasma Thruster (IPPT) pulse circuits, such as those needed to operate the Pulsed Inductive Thruster (PIT), are required to quickly switch capacitor banks operating at a period of μs while conducting current at levels on the order of at least 10 kA. [1,2] For all iterations of the PIT to date, spark gaps have been used to discharge the capacitor bank through an inductive coil. Recent availability of fast, high‐power solid state switching devices makes it possible to consider the use of semiconductor switches in modern IPPTs. In addition, novel pre‐ionization schemes have led to a reduction in discharge energy per pulse for electric thrusters of this type, relaxing the switching requirements for these thrusters. [3,4] Solid state switches offer the advantage of greater controllability and reliability, as well as decreased drive circuit dimensions and mass relative to spark gap switches. The use of solid state devices such as Integrated Gate Bipolar Transistors (IGBTs), Gate Turn‐off Thyristors (GTOs) and Silicon‐Controlled Rectifiers (SCRs) often involves the use of power diodes. These semiconductor devices may be connected antiparallel to the switch for protection from reverse current, or used to reduce power loss in a circuit by clamping off current ringing. In each case, higher circuit efficiency may be achieved by using a diode that is able to transition, or 'switch,' from the forward conducting state ('on' state) to the reverse blocking state ('off' state) in the shortest amount of time, thereby minimizing current ringing and switching losses. Silicon Carbide (SiC) PiN diodes offer significant advantages to conventional fast‐switching Silicon (Si) diodes for high power and fast switching applications. A wider band gap results in a breakdown voltage 10 times that of Si, so that a SiC device may have a thinner drift region for a given blocking voltage. [5] This leads to smaller, lighter devices for high voltage applications, as well as reduced forward conduction losses, faster reverse recovery time (faster turn‐off), and lower‐magnitude reverse recovery current. In addition, SiC devices have lower leakage current as compared to their Si counterparts, and a high thermal conductivity, potentially allowing the former to operate at higher temperatures with a smaller, lighter heatsink (or no heatsink at all).
Document ID
20140012458
Acquisition Source
Marshall Space Flight Center
Document Type
Abstract
Authors
Toftul, Alexandra
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Polzin, Kurt A.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Hudgins, Jerry L.
(Nebraska Univ. Lincoln, NE, United States)
Date Acquired
September 23, 2014
Publication Date
July 28, 2014
Subject Category
Electronics And Electrical Engineering
Report/Patent Number
M14-3241
Report Number: M14-3241
Meeting Information
Meeting: AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Location: Cleveland, Oh
Country: United States
Start Date: July 28, 2014
End Date: July 30, 2014
Sponsors: American Society of Mechanical Engineers, American Society for Electrical Engineers, American Inst. of Aeronautics and Astronautics, Society of Automotive Engineers, Inc.
Distribution Limits
Public
Copyright
Public Use Permitted.
No Preview Available