Orbital Maneuvers - Orbital and Celestial Mechanics Website

Orbital Mechanics with MATLAB
final spacecraft mass 959.8933 kilograms
propellant mass 187.8393 kilograms
total inclination change 28.5000 degrees
total delta-v 5783.7751 meters/second
thrust duration 191.2624 days
initial yaw angle 21.9850 degrees
thrust acceleration 0.000350 meters/second^2
The software will also graphically display the time evolution of the thrust vector yaw angle,
spacecraft speed, inclination change and semimajor axis.
cdeorbit.m – single impulse de-orbit from a circular orbit
This MATLAB script calculates the single impulsive maneuver required to establish a reentry
altitude and flight path angle relative to a non-rotating, spherical Earth. The algorithm uses a
tangential delta-v applied opposite to the velocity vector of an initial circular orbit to establish
the de-orbit trajectory.
The scalar magnitude of the single impulsive maneuver required to de-orbit a spacecraft from an
initial circular orbit can be determined from the following expression
where
and
V
V
1 2r1 2r1
V Vc 1 V 1
e 2 c
i
2
r r r
1 1
cos
e cos
e
hi req ri
r
radius
ratio
h r r
ce
ci
e eq e
r
he req
r
hi req
e
i
local circular velocity at entry interface
local circular velocity of initial circular orbit
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