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WP5 – AVIONICS
Combined navigation system of suborbital vehicle
(WP5 – Avionics)
Jinru ZHANG – Zihao WANG – Dazhen SHI
ESIEE, PARIS
Ideal navigation system in Suborbital Vehicle
should meet the following requirements:
global coverage; high relative precision and
absolute accuracy; good real-time response;
able to provide 3D position, 3D velocity and
attitude heading data; the work is not affected
by the external environment; be able to deal
with the interference of anti-human and non-
human activities, and ready to make
independent
fault
detection
and
troubleshooting; high reliability; low cost for
customers to accept.
Obviously, any single navigation system is
unable to meet the above requirements. So
combined navigation technology will gradually
become the main research and development
in the field of object navigation.
Combined Navigation System can bring the
advantages of each single navigation system
while they make up for their shortcomings,
can adapt to modern warfare navigation
systems.
Therefore,
it
multi-device
combinations, redundant design, and multi-
function combined navigation system is widely
used in the world.
In navigation system, subsystems are
complemented with each other; they can
share information together, thereby expanding
the scope of utilization and improving
navigation accuracy. Combined navigation
system has strong fault tolerance and
redundancy navigation capabilities, so that it
can increase the reliability of the navigation
system. In addition, using combined
navigation system for precision navigation can
reduce overall system cost.
Development of micro technology and digital
filtering greatly promoted research and
development of combined navigation
systems.
So we choose a combined navigation system
in our project, it’s a combination of Inertial
Navigation System (INS); Global Navigation
Satellite System (GNSS); Celestial Navigation
System (CNS).The INS/GNSS/CNS system
has a very high accuracy.
In this Challenge, we are mainly deal with the
following steps:
Firstly, we analyze the environmental
characteristics of the suborbital flight vehicle,
then we analyze the current stage of several
typical inertial navigation system. Then we
use Kalman Filter technology to design a
specific Kalman Filter, which is used in the
combined navigation system in suborbital
vehicle.
Secondly, we use module X-34 suborbital
flight path to establish the trajectory
simulation model by Matlab /Simulink. After
we set up the simulation parameters, we also
make some analysis on the results. And the
results verify the correctness of the system
model, showing that INS / GPS / CNS
combined navigation system with a Kalman
filter for filtering can achieve high accuracy
.