System Requirements Performance Upgrade Path Size and Weight Limits Operating Environment Power and Signal Calibration Remote/Autonomous Operation

System Requirements Performance –Spatial Coverage Minimum range resolution = 30 m Along track spacing comparable to range resolution –Sensitivity Minimum Detectable Signal (MDS) 10 km –Velocity and Reflectivity Accuracy < 1 dB = 10 dB

System Requirements Performance –Range/Velocity Ambiguity

System Requirements Performance Upgrade Path –Design system to be readily upgradeable to Phase B and C implementations Phase B: Adds Polarimetry (H-V), pulse compression Phase C: Adds Second wavelength (Ka-band) Initial system design incorporates electro-mechanical infrastructure of phases B and C Only antenna should be “throw away” to realize phase C

System Requirements Performance Upgrade Path Size and Weight Limits –Must fit within physical constraints of HIAPER wing pod Length: 158.5” Payload: 800 lbs. Diameter: 20”, o.d.

System Requirements Performance Upgrade Path Size and Weight Limits Operating Environment –Temperature: -65 C to +50 C –Pressure:1.6 psi. to 14.7 psi. –Shock:6g, 11 millisecond duration – per RTCA/DO-160D –Vibration:8g (rms), 10 Hz to 2000 Hz – per RTCA/DO-160D

System Requirements Performance Upgrade Path Size and Weight Limits Operating Environment Power and Signal –Power 20 Amps, 120 VAC, 60 Hz 20 Amps, 120 VAC, 400 Hz –Signal 8 pairs twisted shielded twinax Single 50 ohm coax for IRIG-B time code Single 75 ohm coax Two RJ-45 Gigabit Ethernet Four multimode fibers Three, 9 conductor shielded Two, 4 conductor shielded for ASCII data feed

System Requirements Performance Upgrade Path Size and Weight Limits Operating Environment Power and Signal Calibration –Requires both absolute and dynamic (real-time) calibrations –Details to follow…

System Requirements Performance Upgrade Path Size and Weight Limits Operating Environment Power and Signal Calibration Remote/Autonomous Operation –Autonomous in-flight operation requires: Status monitoring of all mission critical sub-systems Status reporting both within HIAPER and via satcom down-link to ground observer(s) Hardware and software controlled safety interlocks Self-test diagnostic capability –Remote in-flight operation requires: Autonomous operation plus satcom up-link from ground