lander propulsion overview and technology requirements ... landertechneeds-final.pdf · lander...

ADVANCED CONCEPTS BRANCH

Lander Propulsion Overview and TechnologyLander Propulsion Overview and Technology

Requirements DiscussionRequirements Discussion

Constellation Technology ConferenceConstellation Technology Conference

Galveston, TXGalveston, TX

November 14 November 14 –– 15, 2007 15, 2007

ADVANCED CONCEPTS BRANCH 2

AgendaAgenda

• Lander Project Overview

– Project Evolution/Design Cycles

– Lunar Architecture & Lander Reference Missions

– Lander Concept Configurations

• Descent Module Propulsion Overview

• Ascent Module LOX/CH4 Propulsion Overview

• Initial Technology Requirements Development


Lander Project Overview


Lander Project TimelineLander Project Timeline

• Constellation Level III Lander Project stood up in March

2007 (Laurie Hansen-PM, Dan Schumacher-DPM)

• Lander Team Kickoff in early April 2007

• Lander Design Analysis Cycle 1, (LDAC-1) April, 28 –

July 1, 2007.

• Currently in LDAC-1 Delta – Cargo Optimized Lander –

redirection after discussions with LAT II.

• LDAC-2 to start in Nov/Dec


LDAC-1 Starting PointLDAC-1 Starting Point

• Developed Packaging Concept

– Brainstorming with NASA centers across the country

– Maintain CG along CL (independent of payload mass)

– Single decent engine on CL – present minimum approach

– 8.4 meter shroud (7.5 meter internal)

• 3 DRMs with Timelines and Functional Allocations

– Sortie Mission to South Pole! 4 Crew / 7 Days on Surface / No support from surface assets

! No restrictions on ‘when’ (accommodating eclipse periods)

– Outpost Mission to South Pole

! 4 Crew with Cargo Element (LAT Campaign option 2)

! Outpost provides habitation on surface (down and out)

! 210 Days with surface support (power)

– Cargo Mission to South Pole

! Common descent stage design with kits

• LDAC-1 optimized crewed Lander to deliver LAT payload! How much mass could be delivered in the required volume?


CaLV Launch

CLV Launch

TLI

EDS Disposal

LOI

Descent

Ascent

Ascent Stage

Disposal

Trans - lunar Coast

1

2

3

4

5

6

7

9

10

8

Surface

Mission

CaLV Launch

CLV Launch

TLI

EDS Disposal

LOI

Descent

Ascent

Ascent Stage

Disposal

Trans - lunar Coast

11

22

33

44

55

66

77

99

1010

88

Surface

Mission

Mission ArchitectureMission Architecture


Key Minimum Functional LanderKey Minimum Functional LanderDesign FeaturesDesign Features

• Propulsion – AM is single MMH / NTO engine (sizing for AM mass

resulted in Shuttle / CEV similar OME). DM is single LOX/LH2

expander cycle engine.

• Structures – Composite panel with aluminum or titanium honeycomb

core. Composite and metallic struts. Optimization of DM in work (truss

vs panel).

Key features do not represent “baselines” rather an

initial solution from which to evaluate engineering

trades, etc..


LDAC-1 Sortie ConfigurationLDAC-1 Sortie Configuration


LDAC -1 DeltaLDAC -1 Delta

Task: Design a descent stage (structure and propulsion tanks) that

is optimized for the cargo mission. Must also perform the crewed

Outpost (down and out) and Sortie missions - but not delivering

crew + large payload. Propulsion tanks will be sized for the cargo

mission.

• Unchanged from DAC 1

– Single descent engine on CL (RL-10 A4 CECE)

– Shroud diameter (7.5 meter internal)

– Lander performs LOI burn

– TLI control masses

– DRMs and timelines (minor changes)

Initial results indicate achievable PL mass not enough to support

original LAT II Lunar logistics. Lander configuration and focus re-

directed for LDAC-1 Delta


Descent Module

Propulsion System


Key Propulsion Trades

Results of Descent Main Propulsion Study (3/9/2007)Results of Descent Main Propulsion Study (3/9/2007)

Throttle requirement is based on a minimum stage thrust of 5600 lbf.

Estimated payload losses do not include penalties due to throttling effects on Isp.

Option 1a 1b 2 3 4 5 ESAS

Engines 1 1 2 3 4 4 4

Engine Thrust (lbf) 28,000 18,600 13,500 13,500 9,000 13,500 15,000

Engine-out No No Partial Yes Yes Yes 1+1 Yes 1+1

Stage Thrust (lbf) 28,000 18,600 27,000 40,500 36,000 54,000 60,000

PDI Thrust (lbf) 28,000 18,600 27,000 27,000 27,000 27,000 30,000

Throttle 5.0 3.3 4.8 7.2 6.4 9.6 10.7

1/Thr 0.20 0.30 0.21 0.14 0.16 0.10 0.09

PDI Throttle 1.00 1.00 1.00 0.67 0.75 0.50 0.50

100% Isp (sec) 450 450 446 446 446 446 455

PDI Isp (sec) 450 450 446 440 441 435 455

LOI Burn Time 394 593 405 270 304 203 186

PDI Burn Time * 594 775 610 602 603 595 560

Total Burn Time 988 1368 1015 872 907 798 746

0.0

200.0

400.0

600.0

800.0

1000.0

1200.0

1400.0

15000 20000 25000 30000 35000 40000

PDI Thrust (lbf)

Re

lati

ve

Pa

ylo

ad

In

eff

icie

nc

y (

lbm

)

4 Engines, 1+1

Engine Out

3 or 4 Engines,

1 Engine Out

Single Engine,

NO Engine Out

Assuming

14 Mt Lander PL

~ 1% PL Loss

~ 2% PL Loss

~ 3% PL Loss0

.25

T/W

0.0

200.0

400.0

600.0

800.0

1000.0

1200.0

1400.0

15000 20000 25000 30000 35000 40000

PDI Thrust (lbf)

Re

lati

ve

Pa

ylo

ad

In

eff

icie

nc

y (

lbm

)

4 Engines, 1+1

Engine Out

3 or 4 Engines,

1 Engine Out

Single Engine,

NO Engine Out

Assuming

14 Mt Lander PL

~ 1% PL Loss

~ 2% PL Loss

~ 3% PL Loss0

.25

T/W

Off-optimal single engine solution

chosen for LDAC-1 due to low

technology risk, and system

complexity benefits


LDAC-1 Delta: Descent Main Propulsion Schematic

Engin

e #

1

LO

X-1

LO

X-2

LO

X-3

LO

X-4

P P P P

GHe

s

TVS TVS TVS TVS

VRVRVRVR

sss

s

s

LOX Vent

LOX Fill/Drain

LH2 Fill/Drain

ss

GH

e F

ill/V

ent

Pneumatics/Purge

Pre

ss/P

re-p

ress

TVS

s

VR

PPneumatic Valve

Pneumatic

Vent/Relief Valve

Relief Valve

Solenoid Valve

Check Valve

Pressure Regulator

Filter

Thermodynamic

Vent System

Diffuser

TIVOx1 TIVOx2 TIVOx3 TIVOx4

TIVOx1-P TIVOx2-P TIVOx3-P TIVOx4-P

GHe

s

GHeGHe

Power System

Interface

PP

LH

2-1

LH

2-2

LH

2-3

LH

2-4

P P P Ps

TVS TVS TVS TVS

VRVRVRVR

sss

TIVF1 TIVF2 TIVF3 TIVF4

TIVF1-P TIVF2-P TIVF3-P TIVF4-P

LH2

Vent

TVCA-1a

TVCA-1b

Simplified Schematic


Ascent Module

Propulsion System


Ascent Module PropulsionAscent Module Propulsion

• Both NTO/MMH and LOX/CH4 under consideration

• Initial LDAC-1 design assumed NTO/MMH integrated RCS/MPS

• After completion of LDAC-1, Ascent Propulsion System re-

designed using LOC/CH4

• LOX/CH4 AM design completed by LAT-II team lead by Eric

Hurlbert (Many CFM Project team members involved)

• Following Charts – from LDAC-1 LOX/CH4 activity, not sized for

LDAC-1 Delta (Cargo Optimized) Lander.


LDAC-1b: Ascent Main/RCS Propulsion SchematicUnchanged from LDAC-1a

S

t1

MMH

tp2

pp1

RCS Thruster Quads

GHe

p5

GHetHe2

pHe1

S S

S S

S S

S

p1

p2

Function:

Service Hand Valve, HV

High Pressure Latching Valve, HP

Regulator, Rg

Check Valve, CV

Filter, F

Low Pressure Latching Valve, LV

Solenoid Valve (dual coil), SV

Burst Disk/ Relief Valve RV

Heater Ht

Pressure Sensor P

Temperature Sensor T

HVHe01

HPHe1

FHe1

RgHe1

CVHe1

FHe5

LVFu1

RVFu1

HVFu01

HVFu2

HVFu3

CVHe2

FHe6

LVOx1

LVFu2

RVOx2

HVOx1

HVOx2

HVOx3

FFu1FOx1

LVOx2

t2

t4t3

Fluids:

Helium He

Nitrogen Tetroxide (NTO) Ox

Monomeythhydrazine (MMH) Fu

Thruster 1,2,3,4 Thruster 5,6,7,8

Thruster 9,10,11,12 Thruster 13, 14, 15, 16

p4

HVFu4

HVOx4t6

t5

S S S S

t12t11t10t9

S S S S

t7

t8

S S S S S S S St24t23t22t21

p6

p3

HVFu5

HVOx5

MMH NTO NTO

Ascent Engine

t16t15t14t13

t20t19t18t17

tp1

tp4

tp3

tp6

tp5

tp8

tp7

pp2

tHe1

GHe GHetHe2tHe1


ADVANCED CONCEPTS BRANCH

Ascent Stage

LO2/LCH4 Integrated Propulsion System

Notional Schematic (Minimalist)

S

t1

LCH4

tp2

pp1

RCS Thruster Quads

GHe

p5

GHetHe2

pHe1

S S

S S

S S

S

p1

p2

Function:

Service Hand Valve, HV

High Pressure Latching Valve, HP

Regulator, Rg

Check Valve, CV

Filter, F

Low Pressure Latching Valve, LV

Solenoid Valve (dual coil), SV

Burst Disk/ Relief Valve RV

Heater Ht

Pressure Sensor P

Temperature Sensor T

HVHe01

HPHe1

FHe1

RgHe1

CVHe1

FHe5

LVFu1

RVFu1

HVFu01

HVFu2

HVFu3

CVHe2

FHe6

LVOx1

LVFu2

RVOx2

HVOx1

HVOx2

HVOx3

FFu1FOx1

LVOx2

t2

t4t3

Fluids:

Helium He

Liquid oxygen (LO2) Ox

Liquid Methane (LCH4) Fu

Thruster 1,2,3,4 Thruster 5,6,7,8

Thruster 9,10,11,12 Thruster 13, 14, 15, 16

p4

HVFu4

HVOx4t6

t5

S S S S

t12t11t10t9

S S S S

t7

t8

S S S S S S S St24t23t22t21

p6

p3

HVFu5

HVOx5

LCH4 LO2 LO2

Ascent Engine

t16t15t14t13

t20t19t18t17

tp1

tp4

tp3

tp6

tp5

tp8

tp7

pp2

tHe1

TVS / Vent valve

Bleed valvesBleed valves

Eric Hurlbert/JSC



CFM - Storage of LO2 and LCH4CFM - Storage of LO2 and LCH4for the Outpostfor the Outpost

• Design

– LO2 and Methane are loaded subcooled and allowed to

absorb heat leak and warm over the LEO loiter, transit, and

210 day surface stay

• Thermal Modeling Has been performed by GRC and

MSFC to validate this approach

– Both models show heat leaks that result in zero boil-off for

the outpost mission

– Sortie Mission capability for zero boil-off also exists

Steve Sutherlin, MSFC

Bob Christie, GRC

Dave Plachta, GRC

Solar/Surface-Shields under concept

investigation for application to LOX/CH4

surface Storage


Technology Requirements Development


• LOX/LH2 Deep Throttling Pump Feed Engine(s)

• LOX/CH4 Pressure Feed Main Engine

• LOX/CH4 RCS Thrusters

• Cryogenic Propellant Storage and management

– LOX/LH2

– LOX/CH4

• Cryo Mass Gauging

– LOX, LH2, LCH4

• Low Heat Transfer Tank Mountings, and interfaces

• Variable area valve and actuation technology

Technology Needs


• LOX/LH2 Ascent Propulsion

– 1 – 4 engines

– 28 – 30 klbf optimal stage thrust

– 35 – 40 klbs optimal stage thrust (engine out configurations)

– Throttle range (3.3 to 1) – (8 to 1)

– LOX/LH2 Main Engine (Expander Cycle)

! 4500 lbf – 6500 lbf

! 448 sec Isp (maximize @ 100% RPL)

! 2 – 4 starts per mission

– LOX/LH2 Storage & Fluid Management

! 14 – 28 days LEO

! 3 days Transit

! 2 days LLO

Descent Propulsion Technology Assumptions


• LOX/CH4 Ascent Propulsion

– LOX/CH4 Main Engine (Pressure Feed)

! 4500 lbf – 6500 lbf

! 355 sec Isp

! 1 – 3 starts per mission

– LOX/CH4 RCS Thrusters

! 100 lbf

! 80 ms pulse length (40 ms growth risk)

! 300 + sec Isp

– LOX/CH4 Storage & Fluid Management

! 14 – 28 days LEO

! 3 days Transit

! 2 days LLO

! 210 days Lunar surface

Ascent Propulsion Technology Assumptions


Additional Questions and Answers

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