Post on 01-Jan-2016
description
AAE 450- Propulsion LV
Stephen Hanna
Critical Design Review
02/27/01
Launch Vehicle (Stephen Hanna)
Energia Total Payload to LEO
~179 Tonnes $1.2 billion – $2.8 billion
per launch (2000 dollars)
All facilities Exist Available for licensed
production overseas
30.48 m
15.24m Max
3.9 m
7.985 m D
54.864 m
24.00 m NTR
{~8 m}
LV Flight Sequence (Stephen Hanna)
Flight Time (Min:Sec) 1) Liftoff00:00 2) Booster Staging 2:20 3) Core Separation6:30
Disposal Area Side Boosters
• Side Booster from launch site 400 Km
• At altitude of 80km
Core• Core from Launch
Site19200 Km • At altitude of 110Km
Effective Atmosphere
1
23
Earth
LV Reliability (Stephen Hanna)
Reliability is important as ~90% of all sever emergencies in space occurring during launch.
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 insertiono 66% reliability neededo No success rate that is practical
Overall Reliability 87.5% Reliability needed for successful mission based on booster 96% Success rate based on booster
Therefore Zero Abort is needed to improve overall success rate
Considered Launch Failures Destruction of launcher caused by
(28.3%)* Boost explosion Structural failure Any of the following causes
Ignition failure (25.7%)* Loss of Thrust or Insufficient Thrust
– depending where in mission profile demes if it is critical( 15.9%)*
Loss of Attitude (13.2%)* Guidance failure Loss of control
Stage separation failure and other (10.6%)*
*Launch failures of unmanned launchers
Launch Risk** Coverage of the Mission***
On- The- Pad escape systems2.5%
Intact abort12.5% Open injection seats
64% 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)
1) Zero altitude – Ejection seat abort 2) Booster separated at altitude of 80km speed is Ejection seat is viable
Theoretical not viable higher than 40km b/c of pressure suits but has been used at 90 km with survival
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
Effective Atmosphere
1
23
Earth
Abort Scenario Earth cont… (Stephen Hanna)
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
• 40kg 10 kg per person * 4
Ejection Seats Self Contained
• Propulsive device
• Autonomous oxygen
• Parachutes (drone chute and main chute)
816 kg for all four seats (conservative estimates)
• 204kg each*4 crew = 816 kg total
Proven at varied speeds and altitudes
Abort Scenario Earth (Stephen Hanna)
Pyrotechnics
**Not to scale
Abort Scenario Earth (Stephen Hanna)
Pyrotechnics
**Not to scale
Ohh! Spaghetti O’s!!
Abort Scenario Mars
CTV is jettisoned using RCS thrusters from MLV
Parachutes are deployed for landing in use with RCS thrusters
Ejection Pod
Mass of Ejection Pod 140 kg + Ejection seats 816 kg + Suits 40 kg 996kg
Costly 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 = 18,680kg
• ‘Dry Mass’ Rocket= 6,125 Kg
• Mass prop = 12555 Kg
{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
Assumptions:Liquid engineSafety height of 1 kmUsing solid rocket motor 6 seconds burn timeMax acceleration of 12g’sStructural mass of 10%Reduces payload capacity by less than 20% of its own mass?No drag or gravity considered