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The MicroShuttle


To: ModelNet, Astronomy Forum, Math/Science Forum

From: David Ketchledge 75066,10

Subject: MICROSHUTTLE THESIS COMPLETION

After seven years of research and development the Microshuttle
thesis is now finished and about to be copyrighted. This work is
available to interested members of the above forums. Topics covered
in the 614 page work are as follows:

LAUNCH TO ORBIT ANALYSIS
ORBITAL MECHANICS (IN ONE PLANE ONLY )
REENTRY ANALYSIS (PITCH & BANK MODULATION SIMULATION)
MAIN PROPULSION AND RCS THRUSTER SYSTEM
VEHICLE AERODYNAMICS AND FLIGHT MECHANICS
(SUB,SUPER AND HYPERSONIC)
STRUCTURAL ANALYSIS (ORBITER ONLY)
SHOCKWAVE ANALYSIS AND AEROTHEMODYNAMIC HEATING ON REENTRY
Vehicle Guidance and Control

Each chapter first develops the thoerical models in both
written and mathematical terms, then the software is discussed
in detail. finally the results are presented. Of special
interest is the software which can be operated on any PC using
basic. For forum members in model rocketry, many of the programs
can be applied in determining model performance, engine
parameters and boost glider design.

Forum users in the RC airplane hobby will find the
dynamic flight simulator useful in designing model planes, This
program is outlined below:

FLIGHT SIMULATION PROGRAM

Monitors 45 flight variables and coupling coefficients on
a vehicle. Data is stored in matrix form on disk 60
iterations deep. Source code Basic
Compiled via BASCOM-80 , Loop time=~3 seconds.
Method: Lineraized Differentials equations for effect
of control surfaces. Length of flight data base=8 mega
bytes total. Inputs: via keyboard numerics pad that move
the various control surfaces.

Forum members in both engineering or the aerospace areas
are welcome to review the below information on the Microshuttle:

VEHICLE DATA TABLE:
I. CONFIGURATION:
Boosters: Two strap on units of 320000 lbf each with 4 engines
and two sets of turbo pumps. ISP=283, Diameter=10 ft.
length=57 feet. Lower portion house 4 engines and separates
the remaining tank acts as an external tank feeding the
orbiter after the separation event. The rest
of the strap on continues to feed the orbiter up to 90
miles alt. and 217 miles downrange. Then stap-on's are
jettisoned (i.e. not recovered) (Note: booster engines
in their RV reenter from 70 miles Alt. and are recovered.
Orbiter: Mass=14627.5 lbm. empty,Propulsion 4 engines at
35000 lbf each, internal tankage=15000 lbm wings are a
double clipped delta planform---> section type: 64A009
structure: aluminum with graphite (ATJ and pryrolitic
reentry material with boron glass filler under the
graphite and bonded to the aluminum. All leading edges
are pryrolitic graphite. Fuselage X-section: trapezoidal
(width 6 ft. 5 inches, height 5 ft. 5 inches,) (ie tight
fit for the crew), Wing span: 38 feet.

Crew: Pilot and Flight engineer
Control surfaces: All movement rudder,plain flaps
Elevons (ailerons and elevators)
Wing area: 281.0 FT^2
Wing Loading Approx.=50 lbm/ft^2
Landing gear: tricycle

LAUNCH SIMULATION DATA:
INPUT DATA:
Booster tankage weight=3972.86 lbm. /both
Booster Propulsion weight (both)=7160 pounds
orbiter empty weight=14627.498 lbm
Orbiter propellant mass (main system)=15000 lbm
Booster propellent mass (both)= 705,000 lbm
liftoff weight=749,787.498 lbm
Initial thrust= 780000 lbf.
aerodynamic K factor (P*.5*Fa)=.7691782
OUTPUT DATA:
time to achieve orbit=522 seconds
altitude at orbit insert=87.895 miles
Downrange at insert of orbit=1042.37 miles
Vx=25680.3 ft/sec. Vy=-65.8414 ft/sec.
Excess VX at orbit insert=78.348 ft/sec.
Orbital mass at insert=21199.658 lbm.
(approximately 5000 pounds of propellant in
main tankage left )
Note:SIMULATION WAS INTO A POLAR ORBIT

FLIGHT SEQUENCE:
t= 00:0 ALL ENGINES IGNITE ORBITER AND STRAP ON'S. STRAP ON'S
PROVIDE PROPELLANT TO ALL ENGINES
t=116 sec. Two booster engines in each strap-on shutdown for pro-
per fuel management. Altitude=294361 feet
Vy=3439.12 fps,Vx=3302.79 ft/sec.
Downrange=19.736 miles
t=296 sec. Remaining booster engines shutdown followed by their
RV seperation. Vx=13078.7 fps, Vy=284.849 fps,
Altitude=552803 ft. Downrange=279.114 miles
t=488 sec. Orbiter engines go on internal orbiter tankage,
Strap-on tankage is seperated from the vehicle
Altitude=90.04 miles downrange=808 miles (aprox)
t=490 seconds (two orbiter engines shutdown) done to keep
G loads down on the crew
t=522 seconds orbit Achieved ( 90 miles by 176.255 miles)

<PROPULSION SYSTEM>
Propellant (Main and rcs)= hydrozine and Nitrogen Tetraoxide
with cross feed between both systems in emergency
Orbiter engines use a single turbopump unit with a
discharge pressure of ~1100 psi at 293 lbm/sec.
Nozzles are regenitively cooled and are Inconel 750X alloy
Valve type in Orbiter and Strap-on's: Ball (low head loss)

GUIDANCE SYSTEM:

3 IBM PC's (2 XT's and (1) PC AT) with 25 Micromint BCC-52
computer controllers/BCC-30 style 16 channel ADC units. Also
the controller system has 16 channel DAC's as standard. Each
controller\PC is interconnected via IEEE-488 ports via a fiber
optic system at a communication rate of 28 MPS. Controller
software is written in 8052AH assembler code and encoded in
EPROMS. This method allows for scanning up to 200 analog in-
puts per second and determination of input faults.

Members interested in obtaining a copy of the work can write
Dave Ketchledge at 75066,10 via EMAIL or call 208-529-9407 M-F after
9 pm mountain time or any time on weekends. Besides the written thesis
copies of the software are available as well as is a video dissertation
These materials are not free of change due to printing, mailing
and other associated costs, but are along the same for a college text
book. Members who do purchase any of the above materials may call
for assistance on software or help in using the paper towards their
own projects.

David A. Ketchledge 75066,10
 
To the best of our knowledge, the text on this page may be freely reproduced and distributed.
If you have any questions about this, please check out our Copyright Policy.

 

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