QUOTE (ugordan @ May 26 2008, 06:18 PM)
To cope with varying atmospheric density, an active entry of some kind might be envisioned that adjusts lift/drag effects on the heatshield to compensate for modeled/measured deceleration profile. That's just arm-waving on my side, though.
The atmospheric variability at 12km is only about +/-5% from nominal density (+/- 10% @ 2km). Vertical wind variability isn't that large either (horizontal wind speeds may vary over 30m/s). All said I believe the total uncertainty in drag coefficient was up to +/-20% although I don't know anymore were that number came from.
Deployable/inflatable aerodynamic structures reduce ballistic coefficient increase the possible landed mass as well. As we are getting to do aerocapture we need to actively control the drag coefficients. Then the technology/hardware is in place to do it during the less harsh EDL. At the moment a large portion of the problems are due to errors in IMU initialization before entry. Better IMU's, improved orbital navigation (optical systems, spacecraft-to-spacecraft tracking), and improving the mars atmospheric model might do the trick.
If you hadn't had the heat shield you could use radar/lidar