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