Письмо с AROCKET:
HOT NEWS - The payload has been recovered and the data analyzed. It verifies
just over 77 miles max altitude.
Anything plastic touching the inside skin of the nose cone was melted from
the heat. The stickers were all gone but the anodizing held up. The nose
cone tip was damaged on impact so ablation effects couldn't be determined.
The electronics were all in great shape. Weightless for over 7 minutes.
Now my original post that I was writing...
Korey and I were there to share in this wonderful experience. The launch was
flawless. The team assembled by Ky and led by Jerry Larson was running like
a well oiled machine. The base camp included the GoFast bus and GoFast
helicopter, there for search and rescue, along with a significant array of
ground station electronics and antennas. I am confident that the data will
be retrieved and will validate the rockets travels into space. It was a real
privilege to be part of the team and we extend our thanks and
congratulations to all involved.
Now a little bit about our involvement with the team. We are newest members
of the CSXT team joining only six months ago. Since that time, in
collaboration with Ky and Jerry, we have designed, developed, and built the
largest amateur rocket motor ever. The solid propellant motor contained a
derivation of the propellant that I have used for my O and P motors for the
past few years. The motor is designated as an S-50000 containing 435 lbs of
AP based propellant configured in a monolithic case-bonded grain with a
central fin-o-cyl core with a nearly neutral thrust profile. The case was
aluminum 6061 with an OD of 10" and 175" long. The end closures were
retained with two rows of radial bolts. The nozzle was created from a new
process using a combination of graphite, carbon fiber, and ablative
materials and featured a bell shaped exit cone. A number of static tests
were performed on 3" and 6" hardware to characterize the propellant. A full
scale static firing revealed issues with the motors end closures that were
corrected for the flight motor. Chuck Rogers assisted in designing the test
configurations and in addressing issues such as erosive burning and nozzle
losses. The propellant, known as D8, in 6" P-motor sub-scale testing had a
delivered Isp of 222.6 seconds. This results in a final minimum delivered
total impulse of 96,831 lb-sec. We believe that the flight motor should have
had a slightly higher delivered Isp due to altitude effects and delivered
just over 100,000 lb-sec.
Video of the launch is at http://www.hybrids.com/video/csxt_flight.mpg