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Himanshu Mazumdar
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Dr.Himanshu S. Mazumdar, Senior member IEEE
hsmazumdar@hotmail.com

Scientific Projects:

·        High Resolution Spectrophotometer Satellite Payload.

·        IONS (Anuradha) experiment in Space Shuttle Space Lab-3

·        Rubidium Vapor Magnetometer

·        Proton Precession Magnetometer

·        Fluxgate Magnetometer

·        Multi Channel Pulse Height Analyzer

·        3D Simulation of Journey to Moon

 

 

Title: High Resolution Spectrophotometer Satellite Payload.

Objective: To Develop a high-resolution spectrophotometer payload for Electro Dynamic Explorer Satellite using cascaded double Fabry-Perot Etalon capable of detecting wind velocity of ionosphere with accuracy of 10 meters per second.

Description: A large bandwidth solid Etalon followed by narrowband piezo spaced Etalon is fabricated that is coupled to a photo-multiplier tube. Photon counting technique is used to measure intensity. High voltage sweep is applied to three piezo spacers to scan frequency. Intel8080 micro-controller is used for control; data acquit ion and onboard data analysis like parabolic curve fitting around the peaks to increase the resolution of the spectrophotometer.

Funding Agency: University College of London, UK.

 

Title: IONS (Anuradha) experiment in Space Shuttle Space Lab-3

Objective: To measure the Ionization states of Cosmic Rays from earth orbit ting experiment in Space Shuttle, Space Lab-3"

Description: The estimate of the direction and energy of high-energy particles (Cosmic Rays) is achieved by two relatively moving circular plastic stacks. Position of the moving bottom stack is recorded using a 16 bit optical encoder.  The stack is controlled using low backlash gear and a stepper motor. Space Lab’s central redundant computers control the experiment.

Funding Agency: NASA, USA and ISRO, India

 

Title: Rubidium Vapor Magnetometer

Objective: To develop a precision earth’s magnetic field measuring instrument by using rubidium vapor optical pumping technique.

Description:  A rubidium bulb is exited to glow using 100-MHz, 2-Watts oscillator. A rubidium vapor cell is exited using this rubidium lamp. The light is filtered to make monochromatic and polarized. Finally the light through the cell is detected and amplified using a low noise wide band (150-250 KHz) amplifier. The amplifier output is feedback to a coil wound around the cell. The light is modulated by Larmer frequency  (due to Zimon Split) that is proportional to the ambient magnetic field. This instrument is flown in Centaur Rocket to measure the earth’s magnetic field in Ionosphere (between 50 to 150 Km height).

Funding Agency: Space Research Council, UK and Physical Research Laboratory, India

 

Title: Proton Precession Magnetometer

Objective: To develop a precision earth’s magnetic field measuring instrument by measuring proton precession frequency in a hydrogenous liquid.

Description: A coil wound around kerosene filled cylinder is kept orthogonal to earth’s magnetic field. A large polarization current is flown through the coil for a second to align the hydrogen atoms with magnetic moment orthogonal to magnetic field. On releasing the polarizing field the hydrogen protons precession      around the ambient magnetic field. The frequency is proportional to ambient magnetic field (approx 1.8KHz for earth’s field). This signal is amplified using a low noise amplifier and a Phase Lock Loop filter. Using a digital frequency counter the magnetic field is estimated. This instrument is flown in Nike Apache Rocket to measure the earth’s magnetic field in Ionosphere (between 50 to 150 Km height).

Funding Agency: Physical Research Laboratory, India

 

Title: Fluxgate Magnetometer

Objective: To develop a precision earth’s vector magnetic field measuring instrument by measuring the asymmetry in the B-H curve of a tiny magnetic core in presence of earth’s magnetic field.

Description: A tiny tumbler Nickel Iron core is used as open flux loop transformer at 1KHz. The second harmonics is detected from secondary winding, amplified and a phase sensitive detector (PSD) is used. The PSD dc output is proportional to the magnetic field component in direction of the core. This instrument is flown in many rocket and balloon flights to monitor the spin of the vehicle.

Funding Agency: Physical Research Laboratory, India

 

Title: Multi Channel Pulse Height Analyzer

Objective: To develop a 4096 channel energy spectrum analyzer of nuclear radiation source.

Description: Input signal is detected using Sodium Iodide Centiliter and Photo Multiplier Tube Sensor. The   PM tube output is narrow pulses of random height and random frequency. The pulse height is proportional to incoming energy. A Wilkinson type ADC is developed for digitization and an Intel 8085 microprocessor based system is developed to count, store, display, and print the energy spectrum.

Funding Agency: Physical Research Laboratory, India

 

Title: 3D Simulation of Journey to Moon

Objective: To simulate the motion of the lunar orbiting satellite launched from earth.  The simulation of earth and moon surface is to be generated from actual satellite images.

Description: An animated satellite launching and its journey to moon considering different parking orbits are shown using OpenGL, VC++ program. The moon surface is rapped with Clementine Mission images of NASA.

Funding Agency: Physical Research Laboratory, India