S.1 Spacecraft Propulsion Systems Chapter 1: Introduction to ...

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- 10- Momentum Transfer Devices of TUB-Sat Part of micro-satellite “DLR-TUBSAT” with reaction Wheels (Technical University of Berlin). Reaction wheels are used for three axis stabilization and orientation of the satellite. Each reaction wheel is connected with a laser gyro in the same axis. The complete control loop electronics is integrated in the reaction wheels. Each axis gets the angle or angle velocity command from the “On Board Data Handling System” (Central Processor) but all other activities are controlled by the reaction wheel itself.
S.5 Jet Propulsion System - 11- These systems are based on jet propulsion devices that produce thrust by ejecting stored matter, called the propellant. The main features of jet propulsion are: Rocket launch Launch Propulsion for launching rockets with the following characteristics: - high velocity increment capability (7 - 11.5 km/s) - very high thrust levels (ratio thrust/launch vehicle weight: >1.3 ) - low fraction of take-off mass of launch vehicle for payload mass (1 - 5%) of the launching vehicle - powerful chemical rockets
Page 1 and 2: - 1- Chapter 1: Introduction to Spa
Page 3 and 4: S.3 Need of Propulsion Propulsion i
Page 5 and 6: Orbit control ORBIT CONTROL compris
Page 7 and 8: S.4 Reaction-Control System - 7- Th
Page 9: Solar Sails - 9-
Page 13 and 14: S.6 Spacecraft Propulsion - 13- Spa
Page 15 and 16: Impulse bits - 15- Impulse bit is t
Page 17 and 18: Nuclear propulsion Note - 17- SCHEM
Page 19 and 20: - 1- Chapter 2: Basic Propulsion Eq
Page 21 and 22: S.3 Basic Equation of Thrust - 3- B
Page 23 and 24: S.4 Basic Rocket Equation Total Vel
Page 25 and 26: - 7- S.6 Propulsion Performance Fac
Page 27 and 28: Test - 9-
Page 29 and 30: - 11- S.8 Propulsion System Perform
Page 31 and 32: - 13- S.9 Type of Propulsion System
Page 33 and 34: Rocket propulsion device basic part
Page 35 and 36: - 17- The Effective Exhaust Velocit
Page 37 and 38: Kinetic energy in the expelled mass
Page 39 and 40: - 1- Chapter 3: Spacecraft Propulsi
Page 41 and 42: - 3- S.3 Propulsion System Options
Page 43 and 44: Chemical Propulsion Systems - 5- Ch
Page 45 and 46: S.4 Cold and Hot Gas Systems - 7- C
Page 47 and 48: Cold Gas Systems (Operate) - 9- Col
Page 49 and 50: Typical System - 11-
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Page 53 and 54: Advantages Simplicity and reliabili
Page 55 and 56: Liquid Propellants - 17- Characteri
Page 57 and 58: S.6 Liquid Propellant Systems - 19-
Page 59 and 60: Monopropellant Systems (Operate) -
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Diaphragm Tank - 27-
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Advantages Simplicity and reliabili
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Bipropellant Systems (Operate) - 31
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Propellant Tanks - 37-
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Unified Propulsion Systems - 39-
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- 43- Main Performance of Bipropell
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- 45- Dual-Mode systems use hydrazi
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Under Development: - 47- A new fami
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Solid Propellant Motor - 49-
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- 51- Main Performance of Solid Pro
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Electric Propulsion Systems - 53- E
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Note: - 55- For electric propulsion
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Power Augmented Catalytic Thruster
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Electrostatic Systems - 59- Electro
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- 61- Survey of Electrical Thruster
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S.9 Summary - 63- Main characterist
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Chapter 4: Spacecraft Propulsion Sy
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- 3 - S.3 Propulsion System Selecti
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Important indication - 5 - If we as
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S.4 Outline of Advanced Spacecraft
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Exploration of the Solar System - 9
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- 11 - For micro- and nanospacecraf
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wafer 4 wafer 3 wafer 2 wafer 1 Sev
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- 15 - Potential increase in perfor
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- 17 - New Approaches in Advanced P
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- 19 - New Approaches in Advanced P
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- 21 - Exotic Propulsion Methods: A
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Literature - 23 - Wiley J. Larsson
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