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Home Page: suave.stanford.edu
License: GNU Lesser General Public License v2.1
An Aircraft Design Toolbox
Home Page: suave.stanford.edu
License: GNU Lesser General Public License v2.1
should move this to the aerodynamics model
mission doesn't converge properly for different climb speeds of the 3rd climb segment (code line 443)
example: converges for speed = 389., 391., but not for 390.
Summer 2014 Priority: 1
The forward analysis function
It should be ok with infeasibility
Input (Python script for this)
Geometric Parameters
Max Take Off Weight
Mission Profile
Function (Python function for this)
Build up empty weight (Andrew)
Evaluate mission
evaluate lift and drag
evaluate thrust (evaluate propulsor interface - Anil, Emilio)
evaluate stability (get this in to mission - Andrew)
Evaluate Landing and Takeoff Field (Tarik)
Evaluate Noise Correlations
# Evaluate Cost
# Evaluate Structure
Outputs (Data Structure for this - Trent)
Component Weights
Total Weights
Range, Endurance
Lift, Drag
Stability Moment Derivatives
Thrust, Fuel Burn, SFC, Efficiencies
Landing Field Length
Takeoff Field Length
Second Segment Climb Gradient
# Direct Operating Cost
# Structure loads (Dive, Gust, Cruise)
Magical fuel
Magical thrust
Summer 2014 Priority: 6
Placard Diagram
VN Diagram
Mission Profiles
Drag polar
Payload-Range
just making sure this works with the new class structure
root was added as a consolidated interface for scipy's root finding functions in 0.11
list the things that are unclear
update fidelity zero tofl and lfl estimate tests, make sure they have expected values
Summer 2014 Priority: 4
Use the aircraft function and simple drivers
Defer the issue of speed to a later task
Prototype a generic sizing interface
Sizing functions:
Mission by Fixed Range
input: aircraft geometry, mission profile(range, cruise alt)
variable: range of cruise segment, max togw
constrain: total range
Mission by fixed fuel burn
Mission by fixed mission time
Vertical Tail Geometry
Horizontal Tail Geometry
Main Wing Geometry
Engine Characteristics
# TODO: elaborate on inputs, variables, and constraints for each method
We need to break out sweep into the sweeps data class with fields leading_edge, quarter_chord, and half_chord.
Check that proper efficiency is being used for calculation. Current method uses full aircraft efficiency with aspect ratio of main wing.
vary aoa, ma, re; test cl, cd, and components
Parasite drag functions do not include skin friction drag on the propulsion system.
Summer 2014 Priority: 7
Write the wrappers and drivers
Test whether suave behaves with GBO
An important demonstration of the code
Defer speed considerations to later task
Summer 2014 Priority: 3
Make sure we’re happy with the names of variables and outputs
Identify and clean out dead variables
reference this document:
https://docs.google.com/document/d/1L_T05NWoyAKlwvofUGF6MZHFxmtGtLuSxU-w5v3l2C8
We need to include in the mission for the Boeing 737 a point that we can evaluate the second segment climb gradient.
could initialize on weight of previous segment
Variables such as wing area are copied into several different structures for the full setup. Different copies are used in different methods and determining which one to change in the optimizer is difficult. Changing all at once is also difficult.
Replace operational empty with the correct operating_empty, mostly within the aircraft function.
Summer 2014 Priority: 12
Target: January SciTech
Summer 2014 Priority: 14
Geometry (CAD, OpenVSP, EGADS)
Analysis tools (avl, xfoil, su2, nastran)
Summer 2014 Priority: 5
Implement automatic_regression protocol for unit tests
Evaluate smoothness for continuous variables
For sub modules of the aircraft function too (ie Aero, Propulsor)
Test whether it accepts crazy values, and returns useful results
Summer 2014 Priority: 9
What Method?
Complex Step
Automatic Differentiation
Analytic Differentiation
When climbing with constant throttle and fixed speed, if the vehicle is not able to climb (too much drag, or lack of thrust) the solver will never converge since the final condition for altitude is higher than initial.
We must find a way to obtain some result different than error.
Try changing additional_drag_coefficient variable (line 35) from 0.0000 to 0.0075.
Summer 2014 Prioirty: 11
Like eating broccoli
Tutorials
for example: "Main Wing" -> "main_wing"
to match style and allow attribute acces
update the cmalpha, cnbeta test scripts to use the new naming convention
also consider adding warnings
might be something like experimental -> regression -> suave method -> suave attribute
the_aircraft_function.py is a good example here
vary throttle, maybe Ma, Re
check thrust force
left over of issue #8
Need an explicit name for eta to match conventions. (I assume eta is a ratio of dynamic pressures for S&C). Tim, let me know if you have any questions.
Current segments are only tested to run across multiple condition points. Add functionality if necessary and test segments at a single point.
update test missions to use the_aircraft_function
currently - it's part of aerodynamics_model, and doesnt need to be
Summer 2014 Priority: 2
Fill out the test suite with functions that support
“The Aircraft Function”, so that we detect broken code
Spool up cruise control for nightly checks
Scripts:
aircraft at one design point, single analyses
start at low level (unit tests)
examples
tests
benchmarks
Summer 2014 Priority: 8
Profile the code to find bottle necks
Goal: 100 evals / min for “The Aircraft Function” at low fidelity
Summer 2014 Prioirty: 10
Check for dead code
Check for good comments and style
Summer 2014 Priority: 13
Input: python script
Output: Text table in the Embraer Format
Change solar network convergence to torque based rather than Cp based. This will preserve generality for the propeller model when used in conjunction with a variety of engine types.
Fuselage contribution to the Cn_beta appears to be too high. Check for the K_Rel (#K_Rel: Correction for fuselage Reynolds number. Roskam VI, page 400.)
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