Mission Design for the CubeSat OUFTI-1

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CHAPTER 5- The squares of the orbital period of planets are directly proportional tothe cube of the semi-major axes of their orbit.The same laws can be applied to the motion of a satellite around a planet.In orbital mechanics, the spacecraft and the central body are considered aspoints with mass but without dimensions. As to describe the position and thespeed of a point in a tridimensional space we need six parameters, to completelycharacterize the motion of the satellite over an orbit we need the six so-calledorbital elements: the semi-major axis a, the eccentricity e, the true anomalyϑ or ν, the inclination i, the longitude or right ascension of ascending nodeΩ or RAAN and the argument of perigee ω. As shown in fig.5.8, the firsttwo describe the orbit shape and the last three the position of the orbit planerespect to the earth. The true anomaly, sometimes substituted by the time sinceperigee passage, introduces the position of the satellite on the orbit starting fromthe perigee: it’a the only parameter that varies along the orbit as long as wemaintain the hypothesis of ideal motion.Figure 5.8: Orbital ParametersThe motion is in fact considered to be ideal and determined only by thegravity force between the masses and the fictitious centrifugal force, withoutany perturbation as the aerodynamic drag and the presence of others bodies.Starting from the Newton’s laws and from the gravitational laws, we can definesthe orbital elements and some other parameters that can be useful for thecontinuation.We place ourself on the orbit plane and we call r p and r a the radius respectivelyof perigee and apogee and µ the earth gravitational constant. We definethen the following parameters that remain constant:Galli Stefania 34 University of Liège
CHAPTER 5.MISSION ANALYSIS• the semi-major axis:a = r p + r a2(5.1)• the eccentricity:• the angular momentum and its magnitude:e = r a − r pr a + r p(5.2)h = r × v h = |h| = rvcos(γ) (5.3)where r is the radius, v the speed and γ the flight angle.• the orbit parameter which represents the radius of the circular orbit havingthe same angular momentum:p = a ( 1 − e 2) = h2µ = r c (5.4)• the speed on the circular orbit having the same angular momentum:v c = µ h(5.5)• the energyE = − µ 2a = v22 − µ rwhere v and r are the magnitude of speed and the radius.(5.6)• the periodT = 2π√a 3µ(5.7)Introducing the true anomaly ϑ we can identify the radius on each orbitpoint:r =p1 + ecos(ϑ)(5.8)Galli Stefania 35 University of Liège
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Page 7 and 8: CONTENTS1 Introduction 132 The LEOD
Page 9 and 10: LIST OF FIGURES4.1 A typical 1-unit
Page 11: LIST OF TABLES5.1 Comparison betwee
Page 15 and 16: CHAPTER2THE LEODIUM PROJECTThe LEOD
Page 17: CHAPTER3THE FLIGHT OPPORTUNITYThe E
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Page 22 and 23: CHAPTER 4have to be smooth and thei
Page 25 and 26: CHAPTER5MISSION ANALYSISThe mission
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Page 31 and 32: CHAPTER 5.MISSION ANALYSISFigure 5.
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Page 37 and 38: CHAPTER 5.MISSION ANALYSISt − t 0
Page 39 and 40: CHAPTER 5.MISSION ANALYSISIn figure
Page 41 and 42: CHAPTER 5.MISSION ANALYSIS• if m
Page 43 and 44: CHAPTER 5.MISSION ANALYSIS5.3.3 The
Page 45 and 46: CHAPTER 5.MISSION ANALYSISwhere ϑ
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Page 55: CHAPTER 5.MISSION ANALYSISFigure 5.
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Page 60 and 61: CHAPTER 6Figure 6.2: ISIS structure
Page 62 and 63: CHAPTER 6Figure 6.3: P-POD: deploym
Page 64 and 65: CHAPTER 77.1 Inertia propertiesBefo
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Page 76 and 77: CHAPTER 8We have now the vector ˆN
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Page 80 and 81: CHAPTER 8Figure 8.5: Total power pr
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CHAPTER 88.4 Battery and operating
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CHAPTER 99.1 Passive thermal-contro
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CHAPTER 99.3 Nodes modelThe CubeSat
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CHAPTER 9where c p is the material
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CHAPTER 9We have now all the parame
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CHAPTER 9A typical layout of a Ther
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CHAPTER10COMMUNICATION SYSTEMThe co
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CHAPTER 10.COMMUNICATION SYSTEMstre
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CHAPTER 10.COMMUNICATION SYSTEM•
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CHAPTER 10.COMMUNICATION SYSTEMWe c
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CHAPTER11TESTSThe launch and space
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CHAPTER 11.TESTSof asking for some
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CHAPTER 11.TESTSThe random vibratio
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CHAPTER12FUTURE DEVELOPMENTSThe fea
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CHAPTER 12.FUTURE DEVELOPMENTSspace
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AcronymsAARACRACSADADCSASIAVUMBOLCC
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BIBLIOGRAPHY[1] Wiley J. Larson, Ja
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AcknowledgmentsI would like to than
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Mission Design for the CubeSat OUFTI-1

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