asteroid 2junesatellite system application for path deviation of an asteroid between moon and earth...

7/22/2019 Asteroid 2juneSATELLITE SYSTEM APPLICATION FOR PATH DEVIATION OF AN ASTEROID BETWEEN MOON AND EARTH

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SATELLITE SYSTEM APPLICATION FOR PATH DEVIATION OF AN ASTEROID BETWEENMOON AND EARTH TO AVERT DISASTER

C. Sathiya Vel Avioi!" S!hola# $ D#. A. %ai Ra& C#yo'ei!" P#o(e""o#De)a#t*et o( Ae#oa+ti!al E'iee#i', PSN Colle'e o( E'iee#i' $ Te!holo'yMelathe-iyoo#/01230, Palaya*4ottai Tal+4, Ti#+elveli Di"t#i!t, Ta*il Na-+, I-ia

Asteroids are minor planets, especially those of the inner Solar System. There are also located at the stableLagrange points of the Earth-Moon system. Most asteroids consist of carbon-rich minerals, which most meteorites arecomposed stony iron. The mass of near earth Asteroids as a function of its diameter is the range of densities from1.g!cm" to ".#g!cm" .$or e%ample, a &-m diameter asteroid with a density of 1.g!cm" has a mass of order ',( )g. *f this

Asteroid falls on earth then the earth will be destroyed. The present pro+ect is how we can aert this great danger for nearfuture with the aboe mass of Asteroid. The present analyses a new satellite system for the application of path deiation ofan Asteroid between moon and earth. This deiates angle from 1 to & with help of Satellite system $igure A/. Thesatellite is includes the following subsystem - communication subsystem, electric propulsion subsystem, parasuitesubsystem, control system mechanism, solar power subsystem and thermal control subsystem. The Simulation 0ased onstudying of path deiation of a near earth Asteroid between Moon and Earth. The totally fie uantity of Electric propulsiontechni2ues is used. The satellite will go around the earth in this initial orbit the point which is at minimum distance from theearth in that orbitperigee/ is at &(( )m height and the point ma%imum distance in that orbit is at &(,333 )m. The asteroid

is passes through orbit of capture mechanism satellite/,its after satellite system is moe in the pitch up direction, due tonearest of the asteroid with help of one uantity of Electric propulsion techni2ues, then the parasuite is released and theshrin)s of parasuite together with of Asteroid. The path of heay asteroid could be deiated from 1 to &with help oanother 4 2uantity of Electric propulsion Techni2ues. Electric propulsion thruster system is e%pected to become popularwith the deelopment of ion-ion pair techni2ues because of their stimulated of low propellant5 the re2uired amount of pathdeiation thrust range is 46 with high elocity 1.1(%13(m!s .The chlorine gas is used for this application.

Fi'+#e A Satellite "y"te* a))li!atio (o# )ath -eviatio o( a a"te#oi-

Let us see more details about these disasterous stones. There are many small solid ob+ects in theSolar System called asteroids. The ast ma+ority are found in a swarm called the asteroid belt, locatedbetween the orbits of Mars and 7upiter at an aerage distance of &.1 to "." astronomical units A8/ fromthe Sun. Scientists )now of appro%imately 9,333 large asteroids of a diameter of 1 )ilometer or more, and
http://en.wikipedia.org/wiki/Minor_planethttp://en.wikipedia.org/wiki/Inner_Solar_Systemhttp://en.wikipedia.org/wiki/Minor_planethttp://en.wikipedia.org/wiki/Inner_Solar_System


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of millions of small asteroids with a diameter of " meters or more. :eres, ;allas, and e range than preiously thought.These are ob+ects of (3 meters or more in diameter in a near-Earth orbit without the tail or coma of acomet. As of May &31&, #,##3 near-Earth asteroids are )nown, ranging in si>e from 1 meter up to G"&)ilometers 13"9 ?anymed/. The number of near-Earth asteroids oer one )ilometer in diameter isestimated to be about #1. The composition of near-Earth asteroids is comparable to that of asteroidsfrom the asteroid belt, reflecting a ariety of asteroid spectral types.

6EAs surie in their orbits for +ust a few million years. They are eentually eliminated byplanetary perturbations which cause e+ection from the Solar System or a collision with the Sun or a planet.Hith orbital lifetimes short compared to the age of the Solar System, new asteroids must be constantlymoed into near-Earth orbits to e%plain the obsered asteroids. The accepted origin of these asteroids isthat asteroid-belt asteroids are moed into the inner Solar System through orbital resonances with 7upiter.The interaction with 7upiter through the resonance perturbs the asteroids orbit and it comes into the innerSolar System. The asteroid belt has gaps, )nown as Iir)wood gaps, where these resonances occur asthe asteroids in these resonances hae been moed onto other orbits. 6ew asteroids migrate into theseresonances, due to the Jar)os)y effect that proides a continuing supply of near-Earth asteroids.

A small number of 6E=s are e%tinct comets that hae lost their olatile surface materials,although haing a faint or intermittent comet-li)e tail does not necessarily result in a classification as anear-Earth comet, ma)ing the boundaries somewhat fu>>y. The rest of the near-Earth asteroids are

drien out of the asteroid belt by graitational interactions with 7upiter.There are three families of near-Earth asteroidsK

The Atens, which hae aerage orbital radii less than one A8 and aphelia of more than Earths

perihelion 3.#" A8/, placing them usually inside the orbit of Earth.

The Apollos, which hae aerage orbital radii more than that of the Earth and perihelia less than

Earths aphelion 1.31' A8/.

The Amors, which hae aerage orbital radii in between the orbits of Earth and Mars and

perihelia slightly outside Earths orbit 1.31'F1." A8/. Amors often cross the orbit of Mars, butthey do not cross the orbit of Earth.


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Many Atens and all Apollos hae orbits that cross though not necessarily intersect/ that of the Earth,so they are a threat to impact the Earth on their current orbits. Amors do not cross the Earths orbit andare not immediate impact threats. Doweer, their orbits may eole into Earth-crossing orbits in the future.

Also sometimes used is the Ar+una asteroid classification, for asteroids with e%tremely Earth-li)e orbits.There are also the asteroids located at the stable Lagrange points of the EarthFMoon system. Most as ofteroids consist of carbon-rich minerals, while most meteorites are composed of stony-iron. The ma+ority of6EAs hae densities between 1. g!cm" and ".# g!cm". ;resent Inowledge is G&3,(336EAs

133metersK about &(C discoered to date5 Millions of 6EAs 13meters and billions of 6EAs &meters.The satellite is includes the following subsystem - communication subsystem, electric propulsionsubsystem, parasuit subsystem, control system mechanism, solar power subsystem and thermal controlsubsystem.

Since the asteroids orbit would be by selection similar to Earths, the ma%imum communicationdistance would be G & A8. :ommunication to S6 "4 meter sites at Ia-band and N-band would beneeded before, during, and after the capture of the asteroid. The upper limit on the spin rate of theasteroid is 1 reolution per minute or 9 degrees per second. The asteroid capture process is assumed tota)e & hours with no interactie feedbac) loop with Earth. The process to de-spin is assumed to ta)e anadditional 4( minutes. The high initial possible spin rate of 9 degrees per second of the asteroid ma)esthe communication difficult. 6ormally antennas can trac) a target while communication with a spin rate of& degrees per second. Also, the antenna must be able to rotate continuously in both a%es. This resulted inthe preliminary selection of phased array antennas although this trade will be re-ealuated in future

studies. An N-band capability is included in the design for safe mode communication. This capability isbased on a &33-H N-band system with =mni directional antennas, and would proide a minimum datarate of &3 bps from the spacecraft to Earth. The E; subsystem concept includes a total of fie 13-)H Dallthrusters and ;ower ;rocessor 8nits ;;8s/. A ma%imum of 4 thruster!;;8 strings are operated at atime. *t also includes chlorine propellant tan)s, a propellant management assembly, and &-a%is gimbalsfor each ion-ion thruster. The electric propulsion subsystem concept incorporates one sparethruster!gimbals !;;8!N$: string to be single fault tolerant.

Each thruster is estimated to hae a mass of 1 )g, and would operate at a specific impulse of up to",333 s at a ;;8 input power leel of G13 )H. The chlorine propellant tan) design is based on acylindrical, composite oerwrap pressure essel :=;


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The Simulation 0ased on studying of path deiation of a near earth Asteroid between Moon andEarth. The totally fie uantity of Electric propulsion techni2ues is used. The satellite goes round theearth in this initial orbit the point which is at minimum distance from the earth in that orbit perigee/ is at&(()m height and the point ma%imum distance in that orbit is at &(,333 )m. The asteroid is passesthrough orbit of capture Mechanismsatellite/, its after satellite system is moe in the pitch up direction,due to nearest of the asteroid with help of one uantity of Electric propulsion techni2ues, then theparasuite is released and the shrin)s of parasuite together with of Asteroid. The path of heay asteroid

could be deiated from 1to &with help of another 4 2uantity of Electric propulsion Techni2ues.

asteroid 2junesatellite system application for path deviation of an asteroid between moon and earth...

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