Daedalus II

The second in the series of Daedalus Rockets was successfully launched in January 2006 in Argonia, Kansas.  Reaching an altitude of nearly 30,000 feet, this solid-fueled rocket served to verify our mathematical and modeling methods and test various electronics and communication systems. Originally designed as an upper stage for the Daedalus III, the rocket acted mainly as launch training for future rockets.

Documents:
Post Flight Launch Analysis
Motor Specifications
Sustainer Motor Thrust Curve

Daedalus II Launch

Launch Date:
January 8, 2006

Dimensions: 
93.688" (height); 3” (OD); 2.75” (ID)

Delta Fins: 
4;  Each Fin has a Semi Span of 1.5” with a 6” Sweep Length

Material: 
Aluminum 6061 (fin and fincan); Fiberglass (body)

Weight: 
15.5 Pounds (empty); 25.5 Pounds (w/fuel)

Motor: 
52% of a full N Class motor;  Designation: N3213

Motor Material: 
Aluminum 6061; Graphite Exit Nozzle; 4 BATES Grains

Fuel: 
The propellant includes a binder formed from the reaction of a hydroxy terminated polybutadiene with a diisocyanate, ammonium perchlorate as an oxidizer, aluminum as a fuel, and iron oxide as a bum rate modifier.

Max Thrust:
4347 Newtons               

Burn Time: 
3.2 Seconds

Total Impulse: 
10459 Ns

Payload(s): 
GPS Tracking, Video Transmitter with onboard camera, Data Transmitter, and Flight Computer with Barometric Sensor and Accelerometer for telemetry and staging.  2.4 GHz and 434 MHz payloads created.  434 MHz is the primary payload.

Recovery: 
24" Spherical Drogue and 120" Cruciform Main Chute