AAE 450 Propulsion LV Stephen Hanna Critical Design

AAE 450 - Propulsion LV Stephen Hanna Critical Design Review 02/27/01

Launch Vehicle (Stephen Hanna) q Energia 15. 24 m Max § Total Payload to LEO ~179 Tonnes § $1. 2 billion – $2. 8 billion per launch (2000 dollars) 30. 48 m 24. 00 m NTR {~8 m} 54. 864 m 3. 9 m 7. 985 m D q All facilities Exist q Available for licensed production overseas

LV Flight Sequence q Flight Time (Min: Sec) q Disposal Area § 1) Liftoff 00: 00 § 2) Booster Staging 2: 20 § 3) Core Separation 6: 30 y b Effective Atmosphere 3 (Stephen Hanna) § Side Boosters • Side Booster from launch site 400 Km • At altitude of 80 km § Core • Core from Launch Site 19200 Km • At altitude of 110 Km 2 1 Earth

LV Reliability (Stephen Hanna) q Reliability is important as ~90% of all sever emergencies in space occurring during launch. q Reliability by component § Booster- similar to zenith first stage • One booster failure is acceptable o 87. 5% reliability needed • 96% success rate using Zenith first stage record § Main Core- 3 engines • 2 engines needed for LEO insertion o 66% reliability needed o No success rate that is practical q Overall Reliability § 87. 5% Reliability needed for successful mission based on booster § 96% Success rate based on booster q Therefore Zero Abort is needed to improve overall success rate

Considered Launch Failures q Destruction of launcher caused by (28. 3%)* § Boost explosion § Structural failure § Any of the following causes q Ignition failure (25. 7%)* q Loss of Thrust or Insufficient Thrust – depending where in mission profile demes if it is critical( 15. 9%)* q Loss of Attitude (13. 2%)* § Guidance failure § Loss of control q Stage separation failure and other (10. 6%)* *Launch failures of unmanned launchers Launch Risk** Coverage of the Mission*** q On- The- Pad escape systems 2. 5% q Intact abort 12. 5% q Open injection seats 64% q Escape Cabin 84% **89% of failures occur during launch ***85% of launch failures in first stage therefore 15% scaled for upper stages

Abort Scenario Earth (Stephen Hanna) q 1) Zero altitude – Ejection seat abort q 2) Booster separated at altitude of 80 km speed is Ejection seat is viable § Theoretical not viable higher than 40 km b/c of pressure suits but has been used at 90 km with survival q 3) Main core separation at altitude of 110 km - abort to orbit using RCS thruster usable after main core separation with a 99%* success rate *3 failures out of 207 launches after 1970 improvements to system y b Effective Atmosphere 3 2 1 Earth

Abort Scenario Earth cont… q Pressure suits § Protect against loss of pressure up to an altitude of 40 km § Extreme temperatures and dynamic pressure in case of an abort § Suits self contained • Autonomous oxygen • Survival kits and Backup Parachutes • 40 kg 10 kg person * 4 (Stephen Hanna) q Ejection Seats § Self Contained • Propulsive device • Autonomous oxygen • Parachutes (drone chute and main chute) § 816 kg for all four seats (conservative estimates) • 204 kg each*4 crew = 816 kg total § Proven at varied speeds and altitudes

Abort Scenario Earth (Stephen Hanna) q. Pyrotechnics **Not to scale

Abort Scenario Earth q. Pyrotechnics (Stephen Hanna) Ohh! Spaghetti O’s!! **Not to scale

Abort Scenario Mars q. CTV is jettisoned using RCS thrusters from MLV q. Parachutes are deployed for landing in use with RCS thrusters

Ejection Pod q Mass of Ejection Pod 140 kg + Ejection seats 816 kg + Suits 40 kg 996 kg q Costly q Effects total payload due to volume requirements of system therefore reducing payload capacity

Escape Tower • Mass Total = 93, 680 Kg (can we do this? ) • Mass payload = 75, 000 Kg • Escape Tower = 18, 680 kg • ‘Dry Mass’ Rocket= 6, 125 Kg • Mass prop = 12555 Kg q. Assumptions: q. Liquid engine q. Safety height of 1 km q. Using solid rocket motor q 6 seconds burn time q. Max acceleration of 12 g’s q. Structural mass of 10% q. Reduces payload capacity by less than 20% of its own mass? q. No drag or gravity considered {Mass of tower/ Mass of Cabin} Historically: Mercury = 0. 29 Apollo = 0. 71 Soyuz = 0. 31 Hermes = 0. 43 Ariane = 0. 44 Comparison Our system=0. 25