Hi guys...please can someone help me out here...
So this is the problem...
Asteroid 2010J25 is a fictional asteroid predicted to impact the Earth, possibly over a major city, when it next reaches perihelion. It is known to be a carbonaceous monolithic asteroid with a diameter of 200 m and hence able to reach the Earth’s surface during an encounter.
In order to mitigate this threat, a spacecraft will be sent to asteroid 2010J25. The spacecraft will impact the asteroid and fire its thrusters in order to alter the asteroid’s trajectory. The asteroid’s trajectory is to be altered by 14 Earth radii in the vicinity of the Earth to avoid satellite damage.
And these are the questions...
1) The free trajectory options, associated Δv requirements and mission times to take a spacecraft from a low Earth orbit (in a non-ecliptic plane of your choice) to asteroid 2010J25, if 2010J25 is at apohelion.
2) Determine the Δv applied to the asteroid at apohelion necessary to alter the asteroid’s trajectory in order to avoid Earth impact if:
a. the asteroid perihelion distance is extended, and
b. the asteroid perihelion distance is reduced.
3) Determine the total delta v required to be carried on board the spacecraft to complete this mission. Select a rocket capable of providing enough Δv to alter the asteroid’s trajectory, if it exists anywhere in the world in 2010. Discuss the advantages and disadvantages of mitigating asteroid 2010J25 using this technique, including potential future encounters.
Assume impulsive thrusts only. Asteroid 2010J25 has a density of 225.0 kg/m3, semi-major axis 1.35 AU, perihelion 1.00 AU and eccentricity 0.301. For simplicity, take asteroid 2010J25 to have an inclination of 0.00˚ to the ecliptic plane and spherical shape.
Much appreciated...thanks to everyone for their help (in advance)
So this is the problem...
Asteroid 2010J25 is a fictional asteroid predicted to impact the Earth, possibly over a major city, when it next reaches perihelion. It is known to be a carbonaceous monolithic asteroid with a diameter of 200 m and hence able to reach the Earth’s surface during an encounter.
In order to mitigate this threat, a spacecraft will be sent to asteroid 2010J25. The spacecraft will impact the asteroid and fire its thrusters in order to alter the asteroid’s trajectory. The asteroid’s trajectory is to be altered by 14 Earth radii in the vicinity of the Earth to avoid satellite damage.
And these are the questions...
1) The free trajectory options, associated Δv requirements and mission times to take a spacecraft from a low Earth orbit (in a non-ecliptic plane of your choice) to asteroid 2010J25, if 2010J25 is at apohelion.
2) Determine the Δv applied to the asteroid at apohelion necessary to alter the asteroid’s trajectory in order to avoid Earth impact if:
a. the asteroid perihelion distance is extended, and
b. the asteroid perihelion distance is reduced.
3) Determine the total delta v required to be carried on board the spacecraft to complete this mission. Select a rocket capable of providing enough Δv to alter the asteroid’s trajectory, if it exists anywhere in the world in 2010. Discuss the advantages and disadvantages of mitigating asteroid 2010J25 using this technique, including potential future encounters.
Assume impulsive thrusts only. Asteroid 2010J25 has a density of 225.0 kg/m3, semi-major axis 1.35 AU, perihelion 1.00 AU and eccentricity 0.301. For simplicity, take asteroid 2010J25 to have an inclination of 0.00˚ to the ecliptic plane and spherical shape.
Much appreciated...thanks to everyone for their help (in advance)
