METHOD 2

This second method is not as obvious as the previous one. It is based on four impulses: Getting out from the earth to a low circular orbit, making a Hohmann transfer to a higher circular orbit which in a near future would be tangent to the asteroid orbit. Before making the calculations, here is presented an image to explain better the process:

Image 6: Resume of the second method. ©

First Stage - Circular low orbit

Firstly, the main rocket with the Cupsats is put on a low circular orbit.

Second Stage - Hohmann transfer

Secondly a Hohmann transfer is done to move the system from the low circular orbit to a high circular orbit, which in a future will be tangent to the asteroid orbit. This Hohmann transfer include a rotation of 8,6432º of the orbital plane, also calculated in the MatLab program.

The increment of velocity required is the following (All the calculations are done in the MatLab program which is presented in the Software section and it can be found in the official page of the project):

Third Stage - Movement to the Asteroid Orbit

Finally, the satellite is in a high circular orbit which, due to the movement of the earth (and so, the movement of this orbit) intercepts the asteroid orbit in a tangent point where the satellite does the movement. This means another impulse from the circular orbit to the asteroid orbit:

*All the calculus has been done with the supposition of having a rocket that provides an specific impulse of 336 s.

Fuel mass required for the transfer

Using Tsiolkovsky rocket equation and estimating that the delivered payload of the Cubesat is 10 kg, the fuel mass required for all the transfers has been estimated to be 75 kg.

This calculation is also made in the programme.

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