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

Recommendations

Info

Main Characteristics - 64- The table below summarizes the main characteristics of some candidate spacecraft propulsion systems (data listed are indicative only): Type of Propulsion Thrust level Exhaust Velocity Advantages Disadvantages System [N] [m/s] Cold Gas (N2) 0.0045 - 10 700 Extremely simple, Very low performance, highest reliable, very low cost mass of all systems Monopropellant 0.5 2 200 – 2 300 Simple, reliable, Low performance, higher mass (Hydrazine) relatively low cost than bipropellant Bi-Propellant 4 – 500 2 850 – 3 110 High performance More complicated system than (MMH/MON) monopropellant Solid Propellant 50 – 50 000 2 400 – 3 000 Simple, reliable, low Limited performance, higher cost thrust PACT, Hydrazine (Power Augmented Catalytic Thruster) 0.1 – 0.5 3 000 High performance, low power, simple feed system More complicated interfaces, more power than chemical thrusters, low thrust High power, complicated interfaces (specially thermal) ARC-JET (Hydrazine) 0.2 5 000 High performance, simple feed system Stationary Plasma SPT 0.08 16 000 High performance High power, low thrust, 100 (Ion Engine) complicated Kaufman, UK-10 (Ion- 0.011 30 000 Very high performance Very high power, low thrust, Engine) complicated Radio-frequency RIT 10 0.01 31 400 Very high performance Very high power, low thrust, (Ion-Engine) complicated Field-Emission 10 -5 – 2·10 -3 60 000 -100 000 Extreme high Very high power, very low performance thrust
Chapter 4: Spacecraft Propulsion System Selection Peter Erichsen, September 2006 S.1 Introduction - 1 - The selection of the best propulsion system for a given spacecraft missions is a complex process. Selection criteria employed in the design trades include performance, cost, availability, etc. The selection process involves a variety of propulsion options, such as systems operated with cold gas, liquid monopropellant and bipropellant, or some form of electric propulsion. The evolution of future spacecraft systems will be mainly determined by a reduction of space mission costs and extend exploration of the solar system up to interstellar missions. A software program can be used, which is based on the evaluation of system-specific impulses, Issp, and determination of the overall propulsion system mass fraction, mPS/mS/C. The Issp-program can be downloaded from the Swedish Space Corporation (SSC) website http:www.ssc.se/ssd Issp Program
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 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-
Page 51 and 52: - 13-
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) -
Page 61 and 62: - 23-
Page 63 and 64: - 25-
Page 65 and 66: Diaphragm Tank - 27-
Page 67 and 68: Advantages Simplicity and reliabili
Page 69 and 70: Bipropellant Systems (Operate) - 31
Page 71 and 72: - 33-
Page 73 and 74: - 35-
Page 75 and 76: Propellant Tanks - 37-
Page 77 and 78: Unified Propulsion Systems - 39-
Page 79 and 80: - 41-
Page 81 and 82: - 43- Main Performance of Bipropell
Page 83 and 84: - 45- Dual-Mode systems use hydrazi
Page 85 and 86: Under Development: - 47- A new fami
Page 87 and 88: Solid Propellant Motor - 49-
Page 89 and 90: - 51- Main Performance of Solid Pro
Page 91 and 92: Electric Propulsion Systems - 53- E
Page 93 and 94: Note: - 55- For electric propulsion
Page 95 and 96: Power Augmented Catalytic Thruster
Page 97 and 98: Electrostatic Systems - 59- Electro
Page 99 and 100: - 61- Survey of Electrical Thruster
Page 101: S.9 Summary - 63- Main characterist
Page 105 and 106: - 3 - S.3 Propulsion System Selecti
Page 107 and 108: Important indication - 5 - If we as
Page 109 and 110: S.4 Outline of Advanced Spacecraft
Page 111 and 112: Exploration of the Solar System - 9
Page 113 and 114: - 11 - For micro- and nanospacecraf
Page 115 and 116: wafer 4 wafer 3 wafer 2 wafer 1 Sev
Page 117 and 118: - 15 - Potential increase in perfor
Page 119 and 120: - 17 - New Approaches in Advanced P
Page 121 and 122: - 19 - New Approaches in Advanced P
Page 123 and 124: - 21 - Exotic Propulsion Methods: A
Page 125: Literature - 23 - Wiley J. Larsson
show all

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

Create successful ePaper yourself

Delete template?

Save as template?