S.1 Spacecraft Propulsion Systems Chapter 1: Introduction to ...
S.1 Spacecraft Propulsion Systems Chapter 1: Introduction to ...
S.1 Spacecraft Propulsion Systems Chapter 1: Introduction to ...
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Main Characteristics<br />
- 64-<br />
The table below summarizes the main characteristics of some candidate spacecraft<br />
propulsion systems (data listed are indicative only):<br />
Type of <strong>Propulsion</strong> Thrust level Exhaust Velocity Advantages Disadvantages<br />
System<br />
[N]<br />
[m/s]<br />
Cold Gas (N2) 0.0045 - 10 700 Extremely simple, Very low performance, highest<br />
reliable, very low cost mass of all systems<br />
Monopropellant<br />
0.5 2 200 – 2 300 Simple, reliable, Low performance, higher mass<br />
(Hydrazine)<br />
relatively low cost than bipropellant<br />
Bi-Propellant<br />
4 – 500 2 850 – 3 110 High performance More complicated system than<br />
(MMH/MON)<br />
monopropellant<br />
Solid Propellant 50 – 50 000 2 400 – 3 000 Simple, reliable, low Limited performance, higher<br />
cost<br />
thrust<br />
PACT, Hydrazine<br />
(Power Augmented<br />
Catalytic Thruster)<br />
0.1 – 0.5 3 000 High performance, low<br />
power, simple feed<br />
system<br />
More complicated interfaces,<br />
more power than chemical<br />
thrusters, low thrust<br />
High power, complicated<br />
interfaces (specially thermal)<br />
ARC-JET (Hydrazine) 0.2 5 000 High performance,<br />
simple feed system<br />
Stationary Plasma SPT 0.08 16 000 High performance High power, low thrust,<br />
100 (Ion Engine)<br />
complicated<br />
Kaufman, UK-10 (Ion- 0.011 30 000 Very high performance Very high power, low thrust,<br />
Engine)<br />
complicated<br />
Radio-frequency RIT 10 0.01 31 400 Very high performance Very high power, low thrust,<br />
(Ion-Engine)<br />
complicated<br />
Field-Emission 10 -5 – 2·10 -3 60 000 -100 000 Extreme high<br />
Very high power, very low<br />
performance<br />
thrust