# Presentation: 173856

## LUNAR CAPABILITIES CONCEPT REVIEW

**LUNAR CAPABILITIES CONCEPT REVIEW**
**NAC OVERVIEW**
**RICK HAUCK**
**	****JULY 10, 2008****	****	**** **

**For Section 508 Compliance, charts with photos, illustrations and/or graphics are described on the page following.**

## LCCR Scope

**LCCR was conducted to define an integrated Point of Departure (POD)********* transportation architecture for the CxP Lunar Capability including capabilities to:**
**Deliver and return crew to the surface of the moon for short durations, i.e. Human Lunar Return (HLR)**
**Support a range of lunar exploration scenarios and possible surface system architectures, including establishment of a lunar outpost**
**The review satisfied Mission Concept Review (MCR) criteria for Ares V and Altair (crewed and cargo)**
**Identified conceptual designs and key driving requirements**
**Reviewed technology drivers and alternative designs**
**Showed design concepts that meet mission and programmatic requirements**
**The review assumed the capabilities of Ares I and Orion for the lunar missions**
**Lunar Surface System concepts were explored but no POD selected by this review**

**Page 2**

## Key LCCR Objectives

**Show that key architectural decisions have been made for HLR POD architecture approval**
**Key drivers for the architecture **
**Operational concept for the POD HLR architecture **
**Possible surface mission sets enabled by the transportation architecture**
**HLR architecture impacts on the Initial Capability**
**Mutually compatible performance, cost, schedule and risk**
**Show path forward (plan/schedule) to HLR SRR**
**Future architecture/system analysis integrated into mainstream cycles**
**Technical baseline assessment **

## Background

**Background**

## Constellation Architecture Team – Lunar (CxAT_Lunar)

## Drawings and image from page 5:

**On the left are drawings of Ares-1, Ares-V, Orion, Lander component elements I.e., the Lunar Transportation Architecture.**
**On the right is an artist’s conception of the lunar surface architecture with multiple habitation modules, large solar arrays, rovers.**

## DRMs/Mission Key Driving Requirements Lunar Sortie Design Reference Mission

**DRMs/Mission Key Driving Requirements ****Lunar Sortie Design Reference Mission**

*Sizing:  Altair *Δ*V for ****LOI***
*1,000 m/s (3,281 ft/s)*

- ~4d

**MOON**

**EARTH**

**LLO 100 km (54nm)**

**ERO up to 241km (130nm), minimum 222 km, LEO attitude = Gravity Gradient**

- 1 - 5 d

- 1-5d

- 7 d

- ≥ 90 min.

- Altair Performs **LOI**
- 1,000 m/s (3,281 ft/s)
- (Propellant load for 950 m/s)

- TEI 1,492 m/s (4,895 ft/s)
- (Tanks sized for 1, 560 m/s (5,118 m/s)

## Graphic from page 7:

**Chart depicting various stages of the Design Reference Mission to the Moon for a sortie mission and the associated driving requirements:**
**Launch Ares-1 with Orion (crew)**
**90 minutes later launch Ares-V with Earth Departure Stage and Altair Lander**
**Earth-orbit rendezvous/docking within 4 days**
**Translunar Injection into Lunar Orbit**
**Altair descent to lunar surface for 7 day mission leaving Orion in Lunar Orbit**
**Ascent and rendezvous with Orion for return trip to Earth**
**Jettison Orion Service module before reentry**
**Parachute for landing**

**Page 8**

## Surface Systems

**Surface Systems**

- Concepts

- Inputs to Campaign Assessment

- Consistency with Transportation

## Graphics and image from page 9:

**Schematic and artist’s drawings to demonstrate analysis of Surface Systems concepts, consistency with Transportation capabilities, and establishment of infrastructure to support campaign:**
**Top left image and proposed specifications for pressurized lunar rover as an example of a concept.**
**Top right image and specifications to support accommodation of rover on Altair lander within Ares-V payload compartment and on lunar surface.**
**Bottom right graph of crewed and cargo launches for Fiscal Years 2018 through 2030 (x-axis) versus cumulative days on lunar surface from 0 to 2,500 (y-axis) with pictures of notional deliveries of surface infrastructure elements.**
**Bottom left artist’s conception of lunar outpost with multiple habitation modules, pressurized rovers, unpressurized rovers, entry/exit ports to habitation modules, and solar arrays.**

## Lunar Transportation Figures of Merit - Summary

**Lunar Transportation Figures of Merit - Summary**

**Affordability**
- DDT&E
- Recurring
- Budget wedge left for surface systems
- Cost confidence

**Operations / Extensibility**
- Facilities impacts
- Operational flows
- Mars feed-forward

## Graphics from page 11:

**4 panel schematic representation of how Figures of Merit  were used to balance outcome:**
**Upper left:  Performance**
**Ability to support lunar outpost**
**Mass to surface crew and cargo**
**Robustness of margins by system**
**Surface coverage I.e., global access**
**Upper right:  Affordability**
**Design, Development, Test, and Evaluation**
**Recurring**
**Budget wedge left for surface systems**
**Cost confidence**
**Lower right: Operations/Extensibility**
**Facilities impacts**
**Operational flows**
**Mars feed-forward**
**Lower left:  Risk**
**Loss of Crew/Loss of Mission**
**Technical performance risk**
**Schedule risk**
**Commonality**

**Page12**

## Campaign Analysis: Figures of Merit Overview

- A comprehensive set of high-level FOMs must cover four or five major areas:
**Affordability **- *Comparison(s) between the projected costs of the campaign and the projected budget*
**Benefit **- *Measure(s) of the total worth or value produced by the campaign across all themes of interest; including direct benefit items (e.g. science, operation experience, and public engagement) and indirect benefit items (e.g. extensibility to other destinations, enablement of future lunar activities)*
**Safety & Mission Assurance **- *Measure(s) expected losses due to the uncertainty or reliability of the system*
**Programmatic Risk **- *Evaluation of the likelihood and consequence of changes in the performance of the campaign due to multiple types of programmatic uncertainty (component performance, technology development, schedule, budget, reliability, etc.)*
***Sustainability***** **- *Measure(s) of the campaigns ability to maintain a level of value (or perceived value) over time that justifies continued investment in the program*

## Graphic from page 13:

**Graphic representations of analytical results for each of the Figures of Merit.**

## Altair Lunar Lander

**Altair Lunar Lander**

**4 crew to and from the surface **
**Seven days on the surface**
**Lunar outpost crew rotation**
**Global access capability**
**Anytime return to Earth**
**Capability to land 14 to 17 metric tons of dedicated cargo **
**Airlock for surface activities**
**Descent stage:**
**Liquid oxygen / liquid hydrogen propulsion**
**Ascent stage:**
**Hypergolic Propellants or Liquid oxygen/methane**

## Image from page 15:

**Image on the right is an artist’s concept of Altair Lunar Lander on the surface with a crewmember walking toward it.**

**Page 16**

## Ares V Trade Space - March 2008

**  ****Current Ground Rules and Assumptions**
-  4-day loiter/29 degree,130nmi insertion/100nmi TLI departure
-  TLI Payload Goal: 75.1 mT
-  Lander (45.0 mT) + Orion (20.2 mT) + Margin
**  ****Note: Performance (light blue) is TLI payload in conjunction with Ares I.  Cost shown as delta from LCCR Study    **
**    ****Reference.  Reliability is overall LOM.**

**Ares V Trade Space - March 2008**

**Spacers: 1**

**Spacers: 1**

**Spacers: 0**

| Common Design Features |
| --- |
| Composite Dry Structures for Core Stage, EDS & Shroud |
| Metallic Cryo Tanks for Core Stage & EDS |
| RS-68B Performance:
Isp = 414.2 sec
Thrust = 797k lbf @ vac |
| J-2X Performance:
Isp = 448.0 sec
Thrust = 294k lbf @ vac |
| Shroud Dimensions:
Barrel Dia. = 10 m
Usable Dia. = 8.8 m
Barrel Length = 9.7 m |

## Graphic from page 17:

**Schematic matrix showing Ares-V trades and selection of point of departure design:**
**#51.0.39 - Standard core + 5 RS-68B engines with 5 segment solid rockets using PBAN propellant in steel cases; reusable: delivers 63.6mT**
**#51.0.40 - Standard core + 5 RS-68B engines with 5 segment solid rockets using HTPB propellant in composite cases; expendable: delivers 69.7mT**
**#51.0.41 - Standard core + 5 RS-68B engines with 5.5 segment solid rockets using PBAN in steel cases; reusable:  delivers 67.4mT**
**#51.0.46 - Optional core length + 6 RS-68B engines with 5 segment solid rockets using PBAN propellant in steel cases; reusable: delivers 68.6mT**
**#51.0.47 - Optional core length + 6 RS-68B engines with 5 segment solid rockets using HTPB propellant in composite cases; expendable: delivers 74.7mT**
**#51.0.48 - Optional core length + 6 RS-68B engines with 5.5 segment solid rockets using PBAN propellant in steel cases; reusable: delivers 71.1mT**
**Point of departure design selected is 51.0.48 with 51.0.47 as an option.**

## Recommended New Ares V Point of Departure- Vehicle 51.0.48 -

**Recommended New Ares V Point of Departure****- Vehicle 51.0.48 -**

_***Vehicle 51.0.48 recommended***_
- 6 Engine Core, 5.5 Segment PBAN Steel Case Booster
- Provides Architecture Closure with Margin
**Recommend Maintaining Vehicle 51.0.47 with Composite HTPB Booster as Ares V Option**
- Final Decision on Ares V Booster at Constellation Lunar SRR (2010)
- Additional Performance Capability if needed for Margin or requirements
- Allows for competitive acquisition environment for booster
**Near Term Plan to Maintain Booster Options**
- Fund key technology areas: composite cases, HTPB propellant characterization
- Competitive Phase 1 Industry Studies

## Drawing from page 19:

**Drawing of Ares-V #51.0.48 on left**

## Ares V Elements- Recommended Ares V POD (51.0.48) -

**Ares V Elements****- Recommended Ares V POD (51.0.48) -**

**Altair Lunar Lander**

**Interstage**

**Solid Rocket Boosters (2)**
- Two recoverable 5.5-segment PBAN-fueled, steel-casing boosters (derived from current Ares I first stage

**J–2X**

**Payload Shroud**

**RS–68B**
**Engines (6)**

**Loiter Skirt**

**Earth Departure Stage (EDS)**
- One Saturn-derived J–2X LOX/LH2 engine (expendable)
- 10 m (33 ft) diameter stage
- Aluminum-Lithium (Al-Li) tanks
- Composite structures, Instrument Unit and Interstage
- Primary Ares V avionics system

**Core Stage**
- Six Delta IV-derived RS–68B LOX/LH2 engines (expendable)
- 10 m (33 ft) diameter stage
- Composite structures
- Aluminum-Lithium (Al-Li) tanks

**Payload Adapter**

**Two representative configurations shown**
**Multiple configurations for adding a 6th Engine being traded **

## Drawing from page 21:

**Drawing of Ares-V elements**

## Global Access/LOI Δ-V/LLO loiter

**Global Access/LOI **Δ**-V/LLO loiter**

**Access to all lunar landing sites (“global access”) requires a combination of additional LOI **Δ**-V, pre-descent LLO loiter, and post-ascent LLO loiter**
**Minimum energy LLO maneuvers are sufficient for polar outpost missions**
**Altair to size tanks for 1000 m/sec LOI maneuver, load consumables for 4 additional days of LLO loiter**

## Graphics from page 23:

**Representation of analysis of how global access can be attained and the required Ares-V mass using Low Lunar Orbit loitering prior to descent and after ascent.**

## Recommendations

**Recommendations**

**Ares-V**
- Maximize commonality between Lunar and Initial Capabilities:  **Ares-V 51.0.48**
- 6 engine core, 5.5 segment PBAN steel case booster
- Provides architecture closure with additional margin
- High commonality with Ares I
- Continue to study the benefits/risk of improved performance: **Ares-V 51.0.47**
- Final decision on Ares V booster at Program SRR (6/2010)
- Additional performance capability if needed for margin or requirements
- Allows for competitive acquisition environment for booster
- Requires further study and technology investment funding
**Altair**
- Provide a robust capability to support Lunar Outpost Missions:
- Optimize for crew missions (**500 kg + airlock with crew**)
- Lander cargo delivery:  **~ 14,500 kg** in cargo only mode
- Size the system for global access while allowing future mission and system flexibility
- Size Altair tanks for **1,000 m/s LOI delta-v**
- Size for an additional **4 days of Low-Lunar Orbit loiter** (site specific)
- Retain adequate margins:
**~1,000 kg Program reserve at TLI**
**Minimum of 40% total Altair margin/reserve**
**Orion**
- Continue to mature Orion vehicle concept
- Maintain strong emphasis on mass control
- Continue to hold Orion control mass to **20,185 kg** at TLI
- Increase emphasis on evolution of Orion Block 2 to support lunar Outpost missions

## Drawing from page 25:

**On the right, three artist’s conceptions illustrating the features of Ares-V (top), Altair (middle), and Orion (bottom).**

**Page 26**

## LCCR Summary

**LCCR identified a point of departure transportation architecture sufficient to proceed with Ares V and Altair project formulation**
**Program HLR SRR scheduled for June 2010**
**MCR criteria were satisfied for Ares V and Altair**
**Groundwork was laid for development of Lunar Surface System Concepts**
**MCR for LSS planned for June 2010**

## LCCR BOARD COMMENTS

**“****Well-integrated. Technical depth”**
**“****Phenomenal”**
**“****Good story.  It holds together”**
**“****No precedent for this kind of review for such a tightly coupled program”**
**“****Good margins story”**
**“****Don’t break up the team”**
**“****Great new tools”**
**“****Historic milestone”**
**“****Whole program back together after being disconnected a year ago”**
**“****Great to see such a fine in house technical review”**
**“****Great team.  Let’s go to the moon”**

## OBSERVATIONS

**First major revision of program process in 40 years (NPR 7120). **
**Program’s “first milestone review,” focused on the conceptual designs and key driving requirements for Ares V and Altair.**
**One year ago program elements were disconnected.**
**Program is now well integrated, working collegially and synergistically across all involved centers.**
**Depth and breadth of analysis is impressive.**
**Positioned well to proceed to System Readiness Review in 2010.**