Electromagnetic Launcher

Electromagnetic Launcher

Electromagnetic Launcher

Rohit Pawar1, Ninad Nimbalkar2, Nikhil Mali3, Akshay Bangar4

BE EXTC Student KCCEMSR,Kopri, Thane

1rohitpawar808@gmail.com, 2ninadni@gmail.com, 3extcextc@gmail.com, 4akii319@gmail.com

1. INTRODUCTION

   In past 40 years, mankind has ventured into space using well-established rocket technology involving liquid fuel and/or solid propellants. This approach has advantage for astronauts and other payloads that rocket starts, slowly from the surface of the Earth with its full fuel load and as thy fuel is burned off, the altitude and are thermal loads, this provides relatively modest acceleration. Offsetting these remarkable success is the very high cost of burning chemical fuel with a modest efficiency in a rocket engine to get out of the Earth's gravitational field. Present estimates are that it costs more that

   $20,000 to get one kilogram of material into orbit. Unless alternatives can be found, it seems likely that mankind's ventures into space will be limited to a few adventures that can only be undertaken by wealthy nations. Hence to overcome this drawbacks, and reduce the cost of the projection, we decided to use the electromagnetic properties to launch the space shuttle as proposed in May 2007, Dallas IEEE paper. In this project we are going to deal with the electromagnetic properties of the conducting material to produce the desired outcome with full safety and efficiency..

2. SYSTEM ARCHITECTURE

   Fig 2.1Receiver Section

   Fig. 2.2Transmitter Section

   In main structure the current conducting coil connected to the relay contactor. Relay contactor is used to pass the current in the coils. The replay contactor is connected to Replay Driver which is used to drive the relay contactor. Now, the microprocessor µp 8951 is connected to the Replay driver, decoder and LCD display(16×2). Power supply is provided to the microprocessor. RF Receiver is connected to the decoder circuitry. RE receiver consist of an antenna. This antenna receives the signal from the remote which controls the microprocessor. In this, microprocessor is the major component which controls all the operations.

3. CIRCUIT DIAGRAM AND EXPLANATION

   In remote receiver section we use IC 8951. This IC is same as that of IC 8951, only difference is IC

   Fig 3.1 Receiver Section

   • Port 2

     Port 2 is used to control the output of the controller. Port 2 is connected to the Relay

     8951 has 4KB flash memory. There are two types

     driver, which is connected

     to the NPN

     of IC 8951, IC 89C51 and IC 89S51. Here "C" is

     for CMOS which requires 12v supply and "S" stands for ISP, In System Program, which requires 5v supply. Hence, we use IC 89S51. For a controller 3 things are needed Power supply, clock

     transistor(NPN BC 549). Collector of each transistor are connected together and given to the relay contactor. 12V supply is given to the electromagnetic relay contactor. There are two pins, No ieNormally open, which goes to coil.

     and reset. IC89S51 is 40 pin IC.

     Pin 40 is

     Other pin is common to

     ground. In this

     connected to VCC, 5V supply. Pin 20 is connected to the ground. Pin 18, Pin 19 are oscillator pin. Crystal oscillator of 11.0592MHz is connected to

     arrangement current limiting resistor of 1k is used.

   • Port 3

     it. It contains two 22pf capacitors,

     which helps

     Port 3 is very important in receiving

     crystal to start the oscillations. Pin 9 is a Power ON

     Reset pin. It contains one resistor and one capacitor. Power ON reset pin means as power supply switched ON the controller gets a pulse and it gets reset. There are four ports in IC 89S51,

     the transmitted signal. RF receiver is a 4 pin device. one pin is connected to the antenna, second to the supply, third to the ground and fourth to the Data. As this receiver data is in encoded form, to decode this encoded data we

     Potr0, Port1,Port2, Port3. All ports

     are 8 pin

     need decoder IC HT12D. In

     this there are

     bidirectional ports.

     • Port 0

       address pins A0-A7 which all are grounded. The data pins D0, D1, D2, D3 are connected to

       Port 0 is connected to the LCD

       the port 3. DataIN pin of

       IC HT12D is

       display for 16×2. The VCC of 5V in given to the LCD display. There are three control pins Data/Command, Read/Write, Enable,. There are 4 data pins as D4,D5,D6,D7. These pins send 4 bit data

       connected to the RF receivers data pin. Oscillator pin contains resister of 47K. VT pin stands for Valid Transmission. If signal is valid, without any noise then this pin gets high. For indication this, a LED is used. If

       two times and 8 bit data gets displayed.

     • Port 1

   Port 1 is kept open for any further

   addition.

   transmitter and receiver in range, if communication is taking place then only the LED glows.

   Fig 3.2Transmitter Section

   Remote transmitter section contains RF Transmitter Module. It works on 433 MHz carrier frequency with ASK(Amplitude Shift Keying) Modulation.

   RF transmitter contains 4 pins. A Helical antenna of 5-15cm is connected to the pin1, supply of 3v is connected to the pin2, pin3 is connected to the ground and pin4 is a Dada pin. Data pin is connected to the encoder IC HT12E, here HT stand for Holtek and E for encoder.

   In this IC there are 8 address lines A0-A7 which are connected to the ground as we are not dealing with addresses.

   There are 4 data pins, D0,D1,D2,D3. This data pins are connected to the buttons like UP, DOWN, FIRE,FIRE to do the respected operations.

   (TE) is transmit enable pin, when it is low it transmit the signal, so it is grounded.

   OSC is oscillator pin. Resistor of 1M is connected. Data out pin goes to RF Transmitter data pin.

   Vcc pin is provided with 2v supply.

   The data is in train of pulses in which 8 bits are address and 4 bits are data.

4. CONCLUSION

   In this project the projectile is launched in the space without using any liquid or solid fuel. We used electromagnetic properties of the material i.e. when small current is passed through the current carrying coil it produces magnetic field around it. This field attracts the projectile in upward direction and make the projectile in motion. This project is based on Electromagnetic & RF Circuitry. Except changing the angle of projection whole project is automatic in which all the devices are controlled by microcontroller 89S51. Hence instead of burning non conventional solid or liquid fuel we used electricity to launch the projectile in the space.

5. RESULT

   Hence after initial setup the metallic projectile is launched. Current in each coil is for 25 mS. After taking few readings it is noted that the projectile covers the distance up to 6 meter, with maximum speed of 5 m/s.

6. REFERENCE

1. L. A. Miller, E. E. Rice, R. W. Earhart, and

   R. J. Conlon, Preliminary analysis of space mission applications for electromagnetic launchers, Battelle Columbus Lab., Final Tech. Rep. to NASA on Contract NAS 3-23 354, Aug. 30, 1984.

2. M. R. Palmer and A. E. Dabiri, Electromagnetic space launch: A re-evaluation in light of current technology and launch needs and feasibility of a near-term demonstration, IEEE Trans. Magn., vol. 25, pp. 393399, Jan. 1989.

3. B. Turman, Long range naval coilgun technology, Presentation to NSWL, Dahlgren, VA, Feb. 21, 2001.

4. L. erelmutter et al., Plasma propagation and ignition of propellant in the chamber of a SPETC gun, IEEE Trans. Magn., vol. 35, pp. 213 217, Jan. 1999.

5. J. W. Hunter and R. A. Hyde, A light gas gun system for launching building material into low earth orbit, in AIAA, July 3, 1989, 89-2439- (1989) and UCRL Preprint 99 623.

6. A. Hertzberg, A. P. Bruckner, and D.W. Bogdanoff, Ram accelerator:A new method of accelerating projectiles to ultrahigh velocities, in AIAA,

vol. 26, 1988, pp. 195203. [7] C. Knowlen and

A. P. Bruckner, Direct space launch using ram accelerator technology, in Space Technology and Applications International Forum2001, M. S. El- Genk, Ed: American Institute of Physics, Feb.

2001.

1. P. V. Kryukov, BALSADBallistic system for anti-asteroid defense, in Abstr. 2nd Int. Workshop RAM Accelerators (RAMAC-II), Seattle, WA, July 1720, 1995.

2. D. Wilson and Z. Tan, The blast wave acceleratorFeasibility study, in Space Technology and Applications International Forum2001, M. S. El-Genk, Ed: American Institute of Physics, Feb. 2001.

3. D. A. Tidman, Sling launch of a mass using superconducting levitation, IEEE Trans. Magn., vol. 32, pp. 240247, Jan. 1996.