MARYLAND Orbital Maneuvering

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Single-Axis Motion • Assume single-axis motion with constant torque (all cross-coupling treated as noise) τ = I ˙˙ θ ⇒ ˙˙ θ = • Integrate over time to get ˙ I θ = t + ˙ θ0 τ • Integrate again to get U N I V E R S I T Y O F MARYLAND I τ 1 I 2 θ = t + ˙ θ t+ θ 2 τ 0 0 Orbital Maneuvering Principles of Space Systems Design
Shuttle Standard Rendezvous Approach U N I V E R S I T Y O F MARYLAND Orbital Maneuvering Principles of Space Systems Design
Page 1 and 2: Orbital Maneuvering • Fundamental
Page 3 and 4: Principal Axis System • Every obj
Page 5 and 6: Calculating Vehicle Inertia Tensor
Page 7 and 8: Gemini OAMS Translational Control U
Page 9 and 10: Gemini Reentry Control System U N I
Page 11 and 12: Lunar Module Reaction Control Syste
Page 13 and 14: Orbiter Forward RCS Pod U N I V E R
Page 15: Design Issues for Reaction Control
Page 19 and 20: V-Bar Approach Technique U N I V E
Page 21: R-Bar Velocity Scheduling Curves U

MARYLAND Orbital Maneuvering

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