Mission Design for the CubeSat OUFTI-1

CHAPTER 5where:( F ⊥,sun = sin (i) cos 2 ɛ)2− cos (i) sin (ɛ) sin (λ ⊙ )d = MJD − 150195.5epsilon = 23.44 ◦( sin (λ ⊙ − Ω) − sin (i) sin 2 ɛ2ms 2M ⊙ = 358 ◦ .48 + 0 ◦ .98560027dλ ⊙ = 279 ◦ .70 + 0 ◦ .9856473d + 1 ◦ .92sin(M ⊙ ))sin (λ ⊙ + Ω)MJD is the Modified Julian Date: Julian Date - 2400000.5.As shown in figure 5.15 this acceleration is much less intense than the one causedby the aerodynamic drag.Figure 5.15: Solar pressure acceleration for the first day mission5.3.4 Orbital parameters variationThe acceleration obtained above for the solar pressure and the atmosphere dragcan be used the quantify the variation of orbital elements:⎧⎪⎨⎪⎩ȧ = 2a2µ vf tė = 2 (e + cos (ϑ)) f v t − r sin (ϑ) f av n˙i = r cos h (ϑ∗ ) f ⊥e ˙ω = 2sin(ϑ) fv t + ( (5.20)2e + r sin (ϑ)) 1f a v n − e ˙Ωcos (i)˙Ωsin (i) = r sin h (ϑ∗ ) f ⊥Galli Stefania 44 University of Liège