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

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- 14- S.7 Characteristics of Spacecraft Propulsion Systems In order to fulfill attitude and orbit operational requirements of spacecraft, spacecraft propulsion systems are characterized in particular by: Very high velocity increment capability (many km/s) Low thrust levels (1 mN to 500 N) with low acceleration levels Continuous operation mode for orbit control Pulsed operation mode for attitude control Predictable, accurate and repeatable performance (impulse bits) Reliable, leak-free long time operation (storable propellants) Minimum and predictable thrust exhaust impingement effects
Impulse bits - 15- Impulse bit is the smallest change in momentum required to allow for e.g. fine attitude and orbit control of a spacecraft. Storable propellants Storable Propellants are liquid (or gaseous) at ambient temperature and can be stored for long periods in sealed tanks, e.g. monopropellant hydrazine (see chapter S1B8C3). In contrast, cryogenic propellants, which are liquefied gases at low temperature, such as liquid oxygen (-147 °C) or liquid hydrogen (-253 °C) are difficult to be used for long space flight missions. Note: at present only storable propellants are used for space flight missions.
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 and 10: Solar Sails - 9-
Page 11 and 12: S.5 Jet Propulsion System - 11- The
Page 13: S.6 Spacecraft Propulsion - 13- Spa
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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S.1 Spacecraft Propulsion Systems Chapter 1: Introduction to ...

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