support an attached property name and an intial state, but this can easily
be extended to configure a switch to be a circuit breaker with a max rating,
etc.
current draw. This is only one piece of the puzzle, but as we move forward,
the idea is better modeling of the ammeter, and we could automatically pop
circuit breakers if the current gets too high.
- Modified the rpm vs. suction formula to hit much more realistic numbers.
We should be seeing just over 4 inhg at idle and approaching 5 inhg at
full throttle.
scene management code and organizing it within simgear. My strategy is
to identify the code I want to move, and break it's direct flightgear
dependencies. Then it will be free to move over into the simgear package.
- Moved some property specific code into simgear/props/
- Split out the condition code from fgfs/src/Main/fg_props and put it
in it's own source file in simgear/props/
- Created a scene subdirectory for scenery, model, and material property
related code.
- Moved location.[ch]xx into simgear/scene/model/
- The location and condition code had dependencies on flightgear's global
state (all the globals-> stuff, the flightgear property tree, etc.) SimGear
code can't depend on it so that data has to be passed as parameters to the
functions/methods/constructors.
- This need to pass data as function parameters had a dramatic cascading
effect throughout the FlightGear code.
the whole electrical system. We will also need a mechanism to kill
individual suppliers (such as the alternator), but this is good enough
for most training.
Ok, I found the problem. You're computing the dynamic pressure in
"psf" and adding it to the static pressure in "inHg" to form the
total pressure. The attached patch is the simple fix to the source.
With that fix, failing the pitot while in cruise at 3k' will cause
the airspeed to indicate beyond redline during climb ... well before 4k'.
Thus, a pitot problem can be detected on any IFR altitude change.
Similarly, failing the static (with working pitot) while cruising 4k'
causes the airspeed to indicate beyond redline during a descent
well before reaching 3k' (during which, of course, the ALT looks fine).
Thus, a static failure can be detected before the aircraft breaks out
of the pilot tolerance range and is blatantly conspicuous soon after.
The code reads the electrical system config and contructs an internal model.
Nothing is done beyond that yet ... the electrical system is not updated,
nor is it connected to the property system in anyway.
