Hyperion
II
The Hyperion II is a continuation of the successes of
the Hyperion I program. The Hyperion II is designed as
a 12" diameter sounding rocket capable of lofting a 100lb
payload to an altitude of over 100 miles for use as a
research or atmospheric target rocket. The hybrid propulsion
system is a combination of a metalized solid fuel and
self-pressurizing nitrous oxide. One of the key design
elements is a restart capability. Six full-scale firings
have been done to fully characterize the system. One of
these tests demonstarted the use of an in flight thrust
termination and restart capability. This was ground tested
with a firing that lasted for 10 seconds, was shut down
for 15 seconds, and finally burnt for an additional 5
seconds with no external ignition input. The delay can
be set to any duration from 5 to 90 seconds. The final
full-up firing produced an average thrust of 5000 lbs
for just over 34 seconds with a 98% fuel utilization.
Additional achievements of this program include the development
of new nozzle technology. Future work will focus on reducing
inert mass through composite technology. |
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