- Page 7 and 8: vii3.20 Timeline for Fourth Rendezv
- Page 10 and 11: 1CHAPTER 1INTRODUCTIONOn October 4,
- Page 12 and 13: 3payloads or satellites; eight perc
- Page 14 and 15: 5As mentioned above, space debris r
- Page 16 and 17: 7growing space debris problem will
- Page 18 and 19: 9-The general technical properties
- Page 20 and 21: 11Designing for self-disposal in ne
- Page 22 and 23: 13number of impacts from debris imp
- Page 24 and 25: 15The numbers refer to arbitrary sa
- Page 26 and 27: 17Orbit altitude is the most signif
- Page 28 and 29: 19Figure 1.12 14 . The left image w
- Page 30: 21command and control processes wer
- Page 34 and 35: 25Figure 1.14 Thrust-I sp Range of
- Page 36 and 37: 27generation constellation were des
- Page 38 and 39: 29to the management of space debris
- Page 40 and 41: 31Figure 2.1 Moving Frame Attached
- Page 42 and 43: 33Figure 2.2 Relative Motion of Ell
- Page 44 and 45: 35The symbol ∆ is used to represe
- Page 46 and 47: ̂37⃗⃗⃗⃗. (2.17)From Figure
- Page 48 and 49: 39where n is the mean motion of tar
- Page 50 and 51: 41∆ ̇ ∆ ̇ (∆ ∆ ) (2.30)Su
- Page 52 and 53:
43Now that we have finished solving
- Page 54 and 55:
45Figure 2.5 Rendezvous Trajectory
- Page 56 and 57:
⃗ ⃗ ⃗ ⃗ or ∆ ⃗ ∆ ⃗
- Page 58 and 59:
49Table 3.1 Orbital Characteristics
- Page 60 and 61:
51Assuming that there are two disti
- Page 62 and 63:
53optimization process can only be
- Page 64 and 65:
55Table 3.2 Orbital Characteristics
- Page 66 and 67:
57Using these circular velocities g
- Page 68 and 69:
59rendezvous for the first stack of
- Page 70 and 71:
61Table 3.7 Location of Burn to Cha
- Page 72 and 73:
63Table 3.10 Circular Velocities fo
- Page 74 and 75:
65MSCO-4 2.1576 1.562 0.6195 -- 2.2
- Page 76 and 77:
670.25258740.20.150.1Delta V0.0500
- Page 78 and 79:
69approach phase position. Using th
- Page 80 and 81:
71Figure 3.8 Rendezvous of SRS with
- Page 82 and 83:
73Table 3.18 Timeline for Third Ren
- Page 84 and 85:
75Table 3.20 Timeline for Fourth Re
- Page 87 and 88:
78Table 3.22 Timeline for Fifth Ren
- Page 89 and 90:
80The ∆V calculations proceeded a
- Page 91 and 92:
82and, allowing time for actual ren
- Page 93 and 94:
84Table 3.25 Required ∆V and Need
- Page 95 and 96:
86Table 3.27 Burn Times for the Mis
- Page 97 and 98:
88a single mother ship was shown to
- Page 99 and 100:
9012. Finkleman D., Oltrogge D.,
- Page 101 and 102:
92APPENDIX ABASIC ORBITAL MECHANICS
- Page 103 and 104:
94∑ ⃗ ̇ ⃗ ⃗ (A.7)Defining
- Page 105 and 106:
96Now, to solve equation Equation (
- Page 107 and 108:
98Figure A.4 Area Swept by Position
- Page 109 and 110:
100see that r will have its minimum
- Page 111 and 112:
102Figure A.6 Elliptical Orbit Arou
- Page 113 and 114:
104(A.35)comparing equation Equatio
- Page 115 and 116:
106ZSatelliteR e Perigeeh iInertia
- Page 117 and 118:
108motion is;:The mean angular rate