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

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Velocity increment - 12- Required Velocity Change ≡ Velocity increment ∆v (m/s) of launch/space maneuvers. (Change in velocity imparted to the launcher/spacecraft by the propulsion system to complete space maneuvers; data listed are indicative only) START Kourou (French Guiana) DESTINATION LEO GTO TYPICAL ∆V REQUIREMENT m/s 9 300 11 443 REMARKS Equatorial (∆v-gain by earth rotation: 465 m/s) Cap Canaveral LEO 9 500 Equatorial (USA) GEO 13 600 LEO GEO 4 260 Change of inclination: 28°, Cap Canaveral GTO GEO LEO (parking) GEO GEO Earth orbit escape Lunar orbit Mars orbit 1 500 1 800 North/South station-keeping: ≈ 50 /year East/West station-keeping: ≈ 3 –6 /year Attitude control: ≈ 3% of total propellant budget 3 200 3 900 5 700 Change of inclination: 9°, Kourou Change of inclination: 28°, Cap Canaveral On orbit operations (orbit maintenance requirements per year) Into planetary trajectory Legend: LEO = Low Earth Orbit (≈300 km) GTO = Geostationary Transfer Orbit (Apogee: ≈36 000 km; Perigee: ≈200 km) GEO = Geostationary Earth Orbit (≈36 000 km)
S.6 Spacecraft Propulsion - 13- Spacecraft Propulsion is characterized in general by its complete integration within the spacecraft (e.g. satellites). Its function is to provide forces and torques in (empty) space to: - transfer the spacecraft: used for interplanetary travel - position the spacecraft: used for orbit control - orient the spacecraft: used for attitude control SMART-1 Spacecraft Mission to Moon to demonstrate innovative and key technologies for scientific deep-space missions. Nov. 2003 – Sept. 2006 While jet propulsion systems for launching rockets are also called primary propulsion systems, spacecraft, e.g. satellites, are operated by secondary propulsion systems.
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: S.5 Jet Propulsion System - 11- The
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
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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
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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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