Attitude Determination and Control Stephen LevinStankevich Jeff Parker
- Slides: 8
Attitude Determination and Control Stephen Levin-Stankevich Jeff Parker Tim Shilling
Internal Hardware Magnetometers Sun Sensors Horizon sensors Magnetic Torquers Rate Gyros
Electrical Safety Hardware will not receive power until given by Power subsystem. Wire sizing and circuit protection requirements will be met per NASA TM 102179.
Fracture Control Parts will meet requirements for low-risk fracture classification – Failure will not result in catastrophic hazard to the space shuttle. – All materials including hardware components and fasteners will be low-risk acceptable per NASA-STD-5003 or acceptable under a materials usage agreement (MUA)
Parts and Materials Instruments will meet safety specifications for limited outgassing of CVCM <. 1% and TML < 1%. Corrosion requirements will be met through the use of space-rated materials or surface treatments.
Gravity Gradient Boom Tether Material – Three braided strands Spectra 1000 material 0. 003 inches thick Rip-stop protection, not load-bearing – Plastic sheath Low-density polyethylene tape 1 inch wide, 0. 005 inches thick 0. 002173 kg/m 3 Total Mass less than 0. 045 kg.
Outgassing In-depth analysis of outgassing properties for tether material required. Required properties are CVCM <. 1% and TLM < 1%.
Other Concerns Prior to deployment the tether does not bear the load of the tip mass. Non-Fracture Critical per low-released mass part requirements. Safety concerns dealing with deployment or stowage of the tether and mass will be addressed by the structures/deployables team.
