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 DIFFUSION ASSOCIATED NEOCLASSICAL INDIGENOUS SYSTEM OF HALL ASSEMBLY (DANISHA)   

DIFFUSION ASSOCIATED NEOCLASSICAL INDIGENOUS SYSTEM OF HALL ASSEMBLY (DANISHA)

Dr. A.B.Rajib Hazarika, PhD, MIAMP(Germany),FRAS(Lond.),MWASET,A.E.S.
Lecturer, Dept. of Mathematics,
Diphu Govt. College, Diphu
Assam, India
The present study is related different geometry of the Hall thrusters in which I have tried to get better results than the simple Hall thrusters available at present with the future next generation device Duo Triad Tokomak collider (DTTC) hub by the using new type of code Diffusion Associated Neoclassical Indigenous Hall Assembly (DANISHA).
Hall thrusters were studied independently in the US and the USSR in the 1950s and '60s. However, the concept of a Hall thruster was only developed into an efficient propulsion device in the former Soviet Union, whereas in the US, scientists focused instead on developing girded ion thruster. Two types of Hall thrusters were developed in the Soviet Union:
(A)Thruster with wide acceleration zone, SPD (Russian), SPT, (Stationary Plasma Thruster) at Design Bureau Fake. 
(B) Thruster with narrow acceleration zone, DAS in English: TAL, (Thruster with Anode Layer), at the Central Research Institute for Machine Building (TsNIIMASH). 
 
 
Soviet and Russian SPD thrusters
The common SPD design was largely the work of A. I. Morozov. SPD engines were operated since 1972. They were mainly used for satellite stabilization in North-South and in East-West directions. Since then until the late 1990s 118 SPD engines completed their mission and some 50 continued to be operated. Thrust of the first generation of SPD engines, SPD-50 and SPD-60 was 20 and 30 mN respectively. In 1982 SPD-70 and SPD-100 were introduced, their thrust being 40 mN and 83 mN. In the post-Soviet Russia high-power (a few kilowatts) SPD-140, SPD-160, SPD-180, T-160 and low-power (less than 500 W) SPD-35 were introduced. SPT-100 has a life time of 8000 hrs, efficiency of 52%.Soviet and Russian DAS-type engines include D-38 and D-55. 
Soviet-built thrusters were introduced to the West in 1992 after a team of electric propulsion specialists, under the support of the Ballistic Missile Defense Organization, visited Soviet laboratories and experimentally evaluated the SPD-100 (i.e., a 100 mm diameter SPT thruster). Over 200 Hall thrusters have been flown on Soviet/Russian satellites in the past thirty years. They were used mainly for station keeping and small orbital corrections. Currently Hall Thruster research, design, and theoretical modeling are led by experts at NASA Glenn Research Center and the Jet Propulsion Laboratory. A considerable amount of development is being conducted in industry, such as Aerojet and Busek Co.
This technology was used on the European lunar mission SMART-1 and is used on a number of commercial geostationary satellites. 
What's a Hall Thruster?    The Hall thruster is a type of plasma-based propulsion systems for space vehicles. The amount of fuel that must be carried by a satellite depends on the speed with which the thruster can eject it. Chemical rockets have very limited fuel exhaust speed. Plasmas can be ejected at much higher speeds; therefore less fuel need be carried on board. The Hall thruster was invented in the late 1950's. Until the mid 1990's, it has been developed primarily by the Russians. During the past 30 years, the Russian placed in orbit more than 100 Hall thrusters. However, the vast majority of satellites worldwide have relied on chemical thrusters and, to a lesser extent, arc jet thrusters and ion thrusters.
    A conventional electrostatic ion thruster consists of two grids, an anode and a cathode, between which a voltage drop occurs. Positively charged ions accelerate away from the anode toward the cathode grid and through it. After the ions get past the cathode, electrons are added to the flow, neutralizing the output to keep it moving. A thrust is exerted on the anode-cathode system, in a direction opposite to that of the flow. Unfortunately, a positive charge builds up in the space between the grids, limiting the ion flow and, therefore, the magnitude of the thrust that can be attained.  
    In a Hall thruster, electrons injected into a radial magnetic field neutralize the space charge. The magnitude of the applied magnetic field is approximately 100-200 gauss, strong enough to trap the electrons by causing them to spiral around the field lines in the coaxial channel. The magnetic field and a trapped electron cloud together serve as a virtual cathode. The ions, too heavy to be affected by the field, continue their journey through the virtual cathode. The movement of the positive and negative electrical charges through the system results