Marc Protacio
DPL
Preliminary Risks
Risk
1. Inability to meet the design tolerances and
specified size limits given by the rules
when manufacturing.
2. Not enough initial funding
3. Structures may fail due to aerodynamics
loads in flight.
4. Aircraft may not fly.
5. Aircraft may not take-off within required
distance.
Method for Mitigation or Remediation
Ask Aero Design Club about their current
manufacturing capabilities.
Intentionally design aircraft dimensions less
than the upper size limit given by the rules.
Make tolerances relatively large.
Research supplies that may not be of the
highest quality but will still perform the
required job.
Try to ask for more funding and justify the
additional money with valid reasons.
If strength of materials is of concern, research
less costly materials with the same properties
needed.
Ensure that manufacturing is done carefully so
as to avoid needing to purchase more
materials when mistakes are made.
Perform extensive mechanics of solids
analysis, both theoretical and with finite
element analysis software in conjunction with
computational fluid dynamics software.
Add an adequate factor of safety when
choosing materials based on strength.
Perform extensive aerodynamics and flight
dynamics analysis, both theoretical and with
flight simulation and computational fluid
dynamics software.
Perform wind tunneling testing to
compare/contrast pressure distributions
obtained through CFD.
Ensure Wing is sized to provide initial
adequate lift using theoretical calculations and
include a sizing factor of safety.
Ensure elevator is adequately sized to provide
adequate pitching moment using theoretical
calculations and a sizing factor of safety.
Ensure elevator deflection angle range is
adequate using theoretical calculations and an
angle range factor of safety.
Ensure flaps are adequately sized to provide
additional lift assist using theoretical
calculations and a sizing factor of safety.
Ensure flap deflection angle range is adequate
6. Aircraft may not land within the required
distance.
7. Aircraft may not be able to carry a
“competitive” payload.
8. Aircraft may not be designed and built
within the required time frame.
9. Poor weather during flight demonstration
may inhibit aircraft performance
10. Poor controllability of aircraft during flight.
11. Electronics may fail.
12. Lack of electronics integration experience.
using theoretical calculations and an angle
range factor of safety.
Ensure engine provides adequate thrust to get
aircraft to the required initial velocity by
testing the thrust capability of the engine on a
test stand.
Have discussion with pilot to discuss required
landing velocity and ensure that he/or she
plans to obtain that requirement when
approaching the land.
Make sure elevator and flaps are adequately
sized and have adequate angular range, as
discussed previously when taking-off, to trim
aircraft during landing.
Make sure rudder is adequately sized and has
sufficient angular deflection capability to
remove any sideslip angle, using theoretical
calculations and applying a factor of safety.
Research previous winning aircrafts and the
payloads that they were able to carry.
Design the aircraft to carry more than that
payload, and include a factor of safety in the
lifting capability.
Test aircraft to ensure the designed payload
weight is carried prior to competition.
Develop Gantt scheduling chart and follow it
strictly.
Include a scheduling factor of safety (allocate
extra time for tasks) to account for problems
experienced and mistakes made in the
process.
- Test aircraft in a variety of weather
scenarios to give pilot experience flying
with poor flight conditions.
- Properly size control surfaces using
theoretical calculations and a sizing factor
of safety.
- Ensure control surface deflection angle
range is adequate using theoretical
calculations and an angle range factor of
safety.
- Allow pilot adequate time to test the
aircraft so that he or she is comfortable
flying it.
- Purchase spare electronic components.
- Inspect/test electronics prior to flight.
- Consult with the Aero Design Club for
-
13. Engine may not be able to provide
adequate thrust.
-
14. Lack of aeronautical engineering
knowledge amongst team members.
-
-
common methods of electronics
integration.
Refer to previous SAE Aero design reports
to learn about other electronics
integration methods.
Calculate required thrust using theoretical
calculations and ensure that a thrust factor
of safety is implemented.
Test the thrust capability of the engine on
a test stand.
Consult with textbooks regarding
aeronautical engineering theory as well as
aircraft design methods.
Refer to previous SAE Aero design reports
to learn about design methods used.
Assemble team members that are in the
“Aero” option.