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

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- 10 - Potential increase in performance of existing space propulsion systems – Chemical Propulsion For chemical propulsion high performance, i.e. high values of ''System-specific Impulse', Issp resulting in low values of ‘propulsion system mass fraction’, is primarily dictated by maximum values of 'Thruster-specific Impulse', Isp (ve); for details see Issp-Program. The performance of state-of the-art spacecraft engines operating with cold and hot gas, however, can be considered near to the theoretical limit for actual space storable propellant combinations. The emerging class of micro-and nanospacecraft require miniaturisation of the propulsion system with help of ‘Microelectromechanical System’ (MEMS) technology for acceptable values of Issp, in order to achieve a low ‘non-impulse system mass factor’ x. With increasing interest in environmental and safety issues, non-toxic monopropellant systems are under development, as already presented in Chapter 3. Consequently, actual designs of chemical spacecraft propulsion systems are well developed, but are being complemented by non-toxic monopropellant systems. The emerging class of micro-and nanospacecraft requires ‘Microelectromechanical System’ (MEMS) technology for miniaturisation of the propulsion system.
- 11 - For micro- and nanospacecraft with low ∆v requirements and low thrust levels, e.g. a cold/hot gas system based on ‘Microelectomechanical System’ (MEMS) technology is under development at the ‘Ångström Space Technology Centre’ Uppsala University/Sweden. Nano-Satellite with Micro Propulsion Cold/Hot Gas Thrusters for High Precision Drag-free / Attitude Control (Courtesy of 'Ångström Space Technology Centre’) Micropropulsion System The system consists of a number of thruster pods, each containing four proportional thrusters. The thruster pods have a spherical shape with 42.5-mm in diameter and accommodate four independent nozzles. The micro propulsion system may be also used for larger spacecrafts, which need high resolution of stabilization and attitude control.
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- 1- Chapter 1: Introduction to Spa
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S.3 Need of Propulsion Propulsion i
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Orbit control ORBIT CONTROL compris
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S.4 Reaction-Control System - 7- Th
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Solar Sails - 9-
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S.5 Jet Propulsion System - 11- The
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S.6 Spacecraft Propulsion - 13- Spa
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Impulse bits - 15- Impulse bit is t
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Nuclear propulsion Note - 17- SCHEM
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- 1- Chapter 2: Basic Propulsion Eq
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S.3 Basic Equation of Thrust - 3- B
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S.4 Basic Rocket Equation Total Vel
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Test - 9-
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Rocket propulsion device basic part
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- 17- The Effective Exhaust Velocit
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Kinetic energy in the expelled mass
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- 1- Chapter 3: Spacecraft Propulsi
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- 3- S.3 Propulsion System Options
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Chemical Propulsion Systems - 5- Ch
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S.4 Cold and Hot Gas Systems - 7- C
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Cold Gas Systems (Operate) - 9- Col
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Typical System - 11-
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Advantages Simplicity and reliabili
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Liquid Propellants - 17- Characteri
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S.6 Liquid Propellant Systems - 19-
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Monopropellant Systems (Operate) -
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Page 91 and 92: Electric Propulsion Systems - 53- E
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Page 125: Literature - 23 - Wiley J. Larsson
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