Space Propulsion - IAP/TU Wien

Space Propulsion
Gravitational trajectories
r
=
1+
1+
h
2
/ μ
2ε.
h
2
μ
2
.cosθ
ε > 1 → specific
ε = 1 → specific
ε < 1 → specific
energy
energy
energy
ε > 0 → hyperbola
ε = 0 → parabola
ε < 0 → ellipse
numerical excentricity ε
of conical section
p =
2
h
μ
ε =
1+
2ε.
h
2
μ
2
parameter, semimajor axis and num.
excentricity of trajectory follow from kinetic
and dynamic parameters by analogy of anal.
solution with geometry of conical sections
from
geometry
p
a =
2
1−
ε
a
μ
= −
2ε
all trajectories with same semimajor axis have
same (specific) total energy