Discover how the daVinci project is utilizing the technologies provided by our sponsors
technology was widely utilized throughout all stages of the
project and included external and internal loading of the space
capsule, landing impact loading, parachute deployment, rocket
block ground handling, vibration analysis and static and dynamic
inertial loading of the flight hardware.
ANSARI X-PRIZE Team Summary Sheet
published Summer 2004
Part 1 of FEA gets da Vinci Project off the Ground
published Summer 2003 issue of ANSYS Solutions E-zine.
Part 2 of FEA
gets da Vinci Project off the Ground
- published Fall
2003 issue of ANSYS Solutions E-zine.
da Vinci Space Project Mission Analysis(pdf)
On the 24-27
of March, at the 3rd International Symposium: Atmospheric Re-entry Vehicles
and Systems in Arcachon, France, da Vinci Project Volunteers presented a
review paper authored by V. Kudriavtsev, B. Feeney, M. Buneta, J. Porcher, A.
Ania, M. Trauttmansdorff, T-L. Hsu, M. Krzeminski and K. Rooz.
The following is an abstract of the
Toronto, March 27, 2003 -
In the present article we review engineering and research efforts conducted
by a group of volunteers with the help of advanced engineering commercial
software (CFD-ACE+, ANSYS, CFD-FASTRAN, Matlab/Simulink, Autodesk Inventor,
Maple) in support of the da Vinci Project, the first Canadian competitor in
the International X Prize Competition.
The da Vinci Project has an objective
of launching the first commercial sub-orbital manned space flight by 2004.
Under X Prize rules the vehicle must be reusable, built to hold 3 people and
complete 2 flights within a 2 week period.
The basic launch configuration is
to lift the rocket using a reusable helium balloon to a launch altitude of
24,400 meters (80,000 feet). The paper describes in detail the various major
subsystem components of the Rocket, Balloon Launch Platform, Ground
Operations and Logistics and the multidisciplinary approach to arrive at a
viable and safe design.
A state of the art software and engineering data
management methodology is described. All parameters that effect the design
are ported through a data management software linking, CFD, FEA and Flight
Simulation software's directly to the primary CAD platform resulting in
direct updates to the CAD model. This process allows an iterative design to
develop rapidly, multiple configurations to be assessed and a final design
output in the shortest overall timeframe.
The data management software
contains every parameter in the rockets design including all rocket engine
Running a variation on the engine Isp (Specific Impulse) results in the CAD
drawings updated with new tank sizes etc, yet still driven by constrictions
such as maximum diameter of the vehicle. Lowering of the Isp in such case
would result in the need for more fuel to reach the minimum assigned
altitude of 115 Kms. The rockets length would automatically be increased,
given a diameter restriction. CG and CP values for instance are
automatically recalculated for stability analysis.
||Wild Fire MKVI
||8 m (26 feet) long, 2 m (78 in) in
|Gross Take-Off Weight:
||3,860 kg (8,500 lbm)
||1,660 kg (3,650 lbm)
||2 m (78 in) diameter sphere
||Pressurized to 1 atm with pressure suits
||410 kg (900 lbm)
||Single, pressure-fed, hybrid engine
||Nitrous Oxide and proprietary solid
||80,000 N (18,000 lbf)
|Reaction Control System:
||Cold gas nitrogen integrated with GPS and INS for
||Two drogue chutes and two mains on
the capsule deploy and it repeats again separately for the
propulsion section during decent.