| Frequency Range: |
1-30 MHz |
| Antenna: |
Crossed dipoles (transmitter)
Four short dipoles (receiver) |
| Transmit Power: |
10 to 200 W |
| Pulse Width: |
30-100 µs (coded) |
| Sweep Speed: |
Variable (typical MHz/s) |
| Frame Time: |
Variable (typical 30 s) |
| Receiver: |
Software-controlled |
| Receiver Dynamic Range: |
100 to 120 dB |
| Orbit: |
1500 to 2000 KM. |
| Inclination: |
65 degrees (to include HAARP)
45 degrees (for mid-latitude) |
| Data Storage: |
On-orbit processing |
System Integration Plan and Engineering Design
Satellite System: Other sensors, payload
mass, power requirements, thermal requirements, pointing
control and knowledge, on-board data reduction and compression,
data storage, telemetry, command handling, interaction
among sensors, redundancy, and environmental issues. Much
of this will depend on the selection of the appropriate
satellite bus, e.g., buses made by Spectrum Astro, OSC,
and Ball Aerospace.
Launch System: Launch vehicle, launch
site, and certification. This will reflect the payload,
satellite bus, and desired orbit. Possibilities include
Pegasus and Taurus, but consideration will include others.
Ground Segments: S-band versus X-band
telemetry; one versus multiple ground stations; command
structure, and control; cross-links; data reduction, visualization,
and archiving; and data distribution to end users.
Operational Plan: Agencies, experimental
priorities, and experimental plans.
