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Brian Erson Attitude Control Systems

Brian Erson Attitude Control Systems. Trans Lunar Phase Thruster Analysis. 1. Thruster Analysis. Consultation with Purdue Hybrid(H202) Rocket Team led to development of an alternate OTV attitude control system System consists of 4 small H202 tanks enclosed within OTV

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Brian Erson Attitude Control Systems

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  1. Brian ErsonAttitude Control Systems Trans Lunar Phase Thruster Analysis 1 [Brian Erson] [Attitude]

  2. Thruster Analysis • Consultation with Purdue Hybrid(H202) Rocket Team led to development of an alternate OTV attitude control system • System consists of 4 small H202 tanks enclosed within OTV • Each system is independent • All payload cases can be developed in-house for a fraction of purchase cost 2 [Brian Erson] [Attitude]

  3. Reaction Wheel Update • Each Reaction Wheel had to be upgraded within each payload to account for increases in system mass • Relevant changes to note: 3 [Brian Erson] [Attitude]

  4. Backup Slide 1 Cost Savings Calculation: 100g General Kinetics Cost for 4 – 1N thrusters: $12,000 In-house Manufacturing cost: $5,000 Cost Savings: $7,000 10kg General Kinetics Cost for 4 – 1N thrusters: $12,000 In-house Manufacturing cost: $6,000 Cost Savings: $6,000 Arbitrary General Kinetics Cost for 4 – 13N thrusters: $48,000 In-house Manufacturing cost: $10,000 Cost Savings: $38,000 4 [Brian Erson] [Attitude]

  5. Backup Slide 2 Inert Mass Calculations Density of H202: 1.11 kg/L Mass of aluminum tank per .001 m^3: 3.68 kg Kg(prop) = massflow*(sec/thrust)*thrusts Kg(tank) = (3.68/.001)*volumeH202 100g 4 – 0.0048kg H202 Tanks 0.064 kg 4 – 0.02N H202 Thrusters 0.36 kg Feed Lines, Valves 1.5 kg Total Inert Mass 1.924 kg 10kg 4 – 0.315kg H202 Tanks 1.16 kg 4 – 0.03N H202 Thrusters 0.36 kg Feed Lines, Valves 1.5 kg Total Inert Mass 3.02kg Arbitrary 4 – 2.65kg H202 Tanks 8.8 kg 4 – 0.26N H202 Thrusters 0.36 kg Feed Lines, Valves 1.5 kg Total Inert Mass 13.84kg 5 [Brian Erson] [Attitude]

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