Payload components per BAL's Preliminary Technical Definition (PTD):

Assumptions:
IO responsible for:
experiment design, manufacture, and test prior to payload integration;
any testing, calibration of experiment equipment once integrated into
 payload;
preconditioning of experiment signals going to encoder (temperature,
 etc.);
any GSE required to support experiment testing or calibration;

BAL responsible for:
design, manufacture or procurement, and test/calibration of payload
 support systems described in this proposal.

Instruments:
ISG, GPS, temperature sensor, chemiluminescent ozonesonde(?)

Subsystems:
despin, separation, parachute recovery system, AVC (BAL will provide
 tested unit to IO who will integrate system into science package and 
 calibrate)

Electrical support:
sequencing and control (g-timer: despin, separation), 
pyrotechnics (despin, separation), 
sensors and diagnostics (3-axis accelerometer, 3-axis magnetometer, 
 motor pressure, battery temperature, battery voltage, battery current, 
 pyrotechnic circuit monitors, GPS), 
data acquisition and encoding 
(CCD data voltages -> RNRZ encoder -> pre-mod filter -> transmitter, 
 housekeeping monitors -> BAL single-board encoder -> transmitter, 
 AVC -> transmitter),
telemetry (3 links as above: 
 10 MHz data bandwidth for CCD data, wideband 2W S-band transmitter;
 2 MHz data bandwidth for AVC data, wideband 2W S-band transmitter;
 low bandwidth for housekeeping data, narrowband 2W S-band transmitter;
 combined in triplexer and applied to S-band antenna),
tracking (C-band radar transponder baselined if required by CRR), 
power (baseline 20W experiment, 3*22.4W transmitters, 7W encoder, 4.3W
 AVC, 1.4W accelerometer, 0.24W magnetometer, 16.8W transponder, 14W
 GPS+L-band antenna preamplifier; total 110.8W)
(2 hr * 4.17 A => 8.34 A-hr; LiCl non-rechargeable cells baselined => 
 pre-launch payload operation must use alternate power)

Mechanical support:
payload bay, deck plates, structure, battery box

Weight breakdown much as before: 166.5 lb 

Vehicle:
Orion motor: nominal 130 lb for 85-km apogee; improved Orion motor is
 available and may lift given weight to required apogee
Additional hardware:
 tail assembly (vehicle fins and tail can),
 nosecone (3:1 SS ogive),
 manacle rings - hold payload to motor, cut prior to separation,
 deployment guns,
 launch lugs - hold vehicle to launch rail,
 igniter - ignites motor.

Payload GSE:
Payload control/service provided by CSA ground control microsconsole for
 checkout and operations;
External power during test and checkout;
Umbilical line harnesses connect GSE and payload;
Umbilical communications:
 housekeeping data sent via RS422 protocol;
 CCD data may be sent via RS422 protocol (TBD);
 AVC data via coax cable.

Telemetry GSE:
2 wideband receivers,
1 narrowband receiver,
2 bit syncs,
2 decommutators,
1 video recorder,
data recorders for CCD and housekeeping TM data streams,
video display,
telemetry channel display,
RS422 to single-ended signal converter,
RS232 reconstructor for GPS (possibly, if real time data is needed)