lifting body / winged CEV

So I don't know if this is the right group but whatever.

So I've been reading speculation on the CEV's shape, and I got to
wondering. If it where a winged or lifting body design, how would you
attach a LEM? I would imagine that the configuration would be along the
lines of Apollo, with some type of SM in the back, with the lunar
module in the front. If you were to attach it to some kind of docking
port on the nose of the CEV, wouldn't the presence of the docking
hardware make reentry difficult? ( like seams and stuff). And if you
didn't attack the LEM to the nose, where would you put it, if you
stuck it on top, would it get torqued off or something?

"Steve" wrote in message
oups.com...
So I don't know if this is the right group but whatever.

So I've been reading speculation on the CEV's shape, and I got to
wondering. If it where a winged or lifting body design, how would you
attach a LEM? I would imagine that the configuration would be along the
lines of Apollo, with some type of SM in the back, with the lunar
module in the front. If you were to attach it to some kind of docking
port on the nose of the CEV, wouldn't the presence of the docking
hardware make reentry difficult? ( like seams and stuff). And if you
didn't attack the LEM to the nose, where would you put it, if you
stuck it on top, would it get torqued off or something?


I somehow don't see the first vehicle being winged. What is the point?

However, if you were going to create such a vehicle, it would not take much
to think of ways around your self created problem.

If we are having other modules, then why not a re entry fairing to dock to?

I'd persoanlly imagine the docking area would be on top though, inside some
doors as per Shuttle, as you would probably still need radiators, and
possibly solar panels as well, so why re-invent the wheel? Hide the docking
hardware inside doors containing these on the upper surface and the
underside of the doors.

Brian

--

Brian Gaff....Note, this account does not accept Bcc: email.
graphics are great, but the blind can't hear them
Email:
__________________________________________________ __________________________________________________ __________

Steve wrote:
So I don't know if this is the right group but whatever.

So I've been reading speculation on the CEV's shape, and I got to
wondering. If it where a winged or lifting body design, how would
you
attach a LEM? I would imagine that the configuration would be along
the
lines of Apollo, with some type of SM in the back, with the lunar
module in the front. If you were to attach it to some kind of
docking
port on the nose of the CEV, wouldn't the presence of the docking
hardware make reentry difficult? ( like seams and stuff). And if you
didn't attack the LEM to the nose, where would you put it, if you
stuck it on top, would it get torqued off or something?

The configuration is To Be Determined right now.
At present, contractors are preparing to compete
for a chance to build the boilerplate Crew Exploration
Vehicle (CEV) component. The "Lunar Surface Access
Module" (LSAM) and "Earth Departure Stage" (EDS) would
be developed for "Spiral 2" of the Constellation
Program. Spiral 2 won't happen for years, and then
only if some future Administration/Congress approves
the funding.

Among the many unknowns is what the CEV Launch Vehicle
(CEVLV) is going to be. If CEVLV is tailored for Low
Earth Orbit (LEO) CEV missions (Spiral 1 requirement),
then if seems likely that a Spiral 2 CEV would be
launched separately from the LSAM/EDS components, to
perform an Earth Orbit Rendezvous type mission. EDS/LSAM
could be launched in pieces by several existing "Heavy"
boosters, or all at once by one really big new launch
vehicle. The new NASA administrator is said to favor
the latter approach, but the final decision will all
come down to cost and funding.

For an overview, read Attachment J-1 at the following link.
"http://prod.nais.nasa.gov/cgi-bin/eps/sol.cgi?acqid=113638"

- Ed Kyle

"Brian Gaff" wrote in message
k...
"Steve" wrote in message
oups.com...
So I've been reading speculation on the CEV's shape, and I got to
wondering. If it where a winged or lifting body design...

I somehow don't see the first vehicle being winged. What is the point?

There wasn't much of a point in making the X-38 (and the CRV that would have
followed) a lifting body.

The faster, cheaper, better solution would have been to start with an Apollo
CSM mold-line, perhaps scaled up a bit to take advantage of the shuttle's
larger diameter payload bay and perhaps offset the CG a bit more to add more
hypersonic lift to the design. If you want better control over the landing
location, ditch the parachutes and use a large parafoil, just as X-38 had to
due because its landing speed would have been far too high for comfort.

Jeff
--
Remove icky phrase from email address to get a valid address.

ed kyle wrote:


Among the many unknowns is what the CEV Launch Vehicle
(CEVLV) is going to be. If CEVLV is tailored for Low
Earth Orbit (LEO) CEV missions (Spiral 1 requirement),
then if seems likely that a Spiral 2 CEV would be
launched separately from the LSAM/EDS components, to
perform an Earth Orbit Rendezvous type mission. EDS/LSAM
could be launched in pieces by several existing "Heavy"
boosters, or all at once by one really big new launch
vehicle. The new NASA administrator is said to favor
the latter approach, but the final decision will all
come down to cost and funding.

For an overview, read Attachment J-1 at the following link.
"http://prod.nais.nasa.gov/cgi-bin/eps/sol.cgi?acqid=113638"


It might be useful to post Attachment J-1 for reference here,
as well as to protect against 404age.

So here it is:

ATTACHMENT J-1

STATEMENT OF OBJECTIVES

Statement of Objectives for the Crew Exploration Vehicle

1.0 Introduction

On January 14, 2004, the President of the United States directed the
National Aeronautics and Space Administration (NASA) to embark on a
robust space exploration program that will advance the Nation's
scientific, security, and economic interests. To meet the goals and
objectives of our new vision, NASA plans to deploy a set of systems,
large and small, that will be integrated into a "system of
systems". This includes Earth-to-orbit and in-space transportation
systems, systems required for human health and performance, and robotic
systems that will assist humans as they travel and explore.

CEV is the first component in the system-of-systems that will be built
under the NASA Constellation Program and is the subject of this request
for proposals.

2.0 Scope

The Statement of Objectives (SOO) for the Crew Exploration Vehicle
represents a programmatic and technical baseline for the purposes of
the Offeror's proposal. The SOO will be maintained and updated by
NASA as a contractor programmatic and technical baseline until the
System Requirements Review (SRR) (see Section 5).

The SOO will be part of the Model Contract.

The SOO is augmented by a Constellation System of Systems Point of
Departure (POD) Architecture requirements suite through spiral 3 (see
figure 1). NASA plans on developing a clear set of performance and
functional requirements as well as external interface requirements for
the CEV system by SRR (see Section 5). In the event of a conflict with
the current revision of the Constellation System of System requirements
suite the SOO will take precedence until SRR.


3.0 Spiral Development and Constellation Program Objectives

A key challenge for NASA is to develop new capabilities in a manner
that is pragmatic - so that new capabilities can be developed and
used to advance exploration in the near term - while also being
flexible, in order to incorporate new technologies and respond with
agility to scientific discoveries. To meet this challenge, NASA will
develop exploration capabilities in stages, or "spirals." Each
spiral will usher in a set of major new capabilities in support of the
Vision for Space Exploration. Spirals will be structured based on
specific requirements, well-defined goals and endpoints, then-current
technologies, management risks, an executable budget, and knowledge
gained from prior in-space activities. NASA's acquisition strategy
encourages the use of open-systems architectures that facilitate
upgrades and augmentation while enabling interoperability among
systems. Capabilities to be provided by the first three spirals a

Spiral 1: Earth Orbit Capability.

Spiral 1 establishes the capability to test and checkout crew
transportation system elements in Low Earth Orbit in preparation for
future human exploration missions to the Moon. As new exploration
elements necessary for future spirals are developed, they will be
tested with the Spiral 1 CEV in the space environment to prepare for
future exploration. The objective of crewed access to low earth orbit
will be met by 2014.

Spiral 2: Extended Lunar Exploration.

Spiral 2 establishes the capability to conduct human exploration
missions on the surface of the Moon for extended durations. In this
context, extended duration is defined as the capability to support the
crew on the surface of the Moon for a minimum of four days. This
objective will be met in the 2015-2020 timeframe.

Spiral 3: Long Duration Lunar Exploration.

Spiral 3 establishes the capability to conduct routine human long
duration missions on the surface of the Moon to test out technologies
and operational techniques for expanding the human presence to Mars and
beyond. Missions in Spiral 3 will extend in duration from those
obtained in Spiral 2 up to several months to serve as an operational
analog of future short stay Mars missions. This objective will be met
after 2020.

A key aspect to spiral development will be to develop new technologies
that improve performance and lower cost over time. This is crucial to
maintaining affordability and achieving the Nation's goals for future
exploration.

Accordingly, major portions of NASA's resources have been allocated
to technology development with two major portfolios, Exploration
Systems Research and Technology (ESRT) and Human System Research and
Technology (HSRT), specifically focused on the exploration mission. To
build a sustainable program, all developments within the
system-of-systems must have a strategy for incorporating new
technologies that result from both NASA-sponsored and outside research.


4.0CEV Project Objectives

An anchoring capability of the Constellation Program is a human-rated
CEV that will carry human crews from Earth into space and back again.
Coupled with transfer stages, landing vehicles, and surface exploration
systems, the CEV will serve as an essential component of the
architecture that supports human voyages to the Moon and beyond. Given
an acquisition strategy utilizing spiral development, a
system-of-systems implementation, and reliance on technology for
sustainability and affordability, the following project objectives have
been established:

1.Ensure that the CEV is designed from the outset as a key element of
the Constellation "System of Systems" meeting at minimum Spiral 2
requirements with a clear plan to meet Spiral 3 requirements. Meeting
Spiral 3 from the outset is a goal.

2.Ensure crew safety within the limitations of meeting system
performance requirements and achieving mission objectives.

3.Design and execute a meaningful risk mitigation program that
culminates in a risk reduction flight effort and PDR by the end of
calendar year 2008.

4.Deliver a quality design that ensures simplicity and addresses all
aspects of human spacecraft development, certification and operations.
5.Execute a human flight in 2014 utilizing a CEV.

6.Perform to an established cost, schedule and technical baseline.

7.Maximize the use of existing technology in the design of the CEV.

8.Base the vehicle design on an Open Systems Architecture.

9.Simplify the interface design between the CEV and other Constellation
elements to optimize integration.

10.Certify by test to the maximum extent possible.

11.Develop technology portfolios and define requirements for advanced
development projects for technology insertion.

12. Implement innovative designs for the CEV spacecraft and ground
systems to achieve efficient and effective operations.

This solicitation for the CEV component of the Crew Transportation
System utilizes a phased approach. Phase 1 of the acquisition calls for
a maximum of two contractors to:

Evaluate NASA's ESRT and HSRT programs for potential CEV program
integration as part of a concerted effort to improve system
effectiveness and affordability.
Conduct a series of trade analyses on critical performance drivers for
the purposes of identifying threshold and objectives for the CEV
system.

Affordability, sustainability, and extensibility to future spirals will
be the focus of the analyses.

Participate fully in a System Requirements Review (SRR) to develop
accurate, comprehensive, consistent, and verifiable requirements for
the CEV system through Spiral 3 of the Constellation System of Systems.

Conduct a System Definition Review (SDR) for the CEV system meeting at
a minimum Spiral 2 with a clear implementation plan for Spiral 3.

Conduct a Preliminary Design Review (PDR) for the CEV system meeting at
a minimum Spiral 2 with a clear implementation plan for Spiral 3.

Provide an iterative analysis of cost, risk and performance based on
realistic timelines and estimates of cost.

Conduct a comprehensive risk management program which will mitigate
program uncertainties by establishing priorities, options, adequate
margins of safety, and "off-ramps" for risk mitigation during Phase
1 and a plan to retire the residual risk during phase 2.

Conduct a risk reduction flight effort to: (1) validate industry's
capability to perform on cost, on schedule and on performance, and (2)
retire associated CEV program risks (Flight Application of Spacecraft
Technology (FAST)).

CEV Phase 1 ends with a planned down select to a single prime
contractor in late 2008. Phase 2 of the CEV acquisition calls for a
single Contractor to complete the development, test, and deployment of
a human-rated CEV. After completion of phase 2, the contractor shall
provide, as Government options, sustaining engineering services and
production capability to support additional flights and additional CEV
spacecraft. The Government reserves the right to perform a down select
at any time and to not select either contractor in 2008.

5.0 Requirements Baseline for Constellation

NASA's process for formulating and prioritizing requirements is
targeted to enable sustainable and affordable exploration. An
overriding goal in the definition of the requirements set for future
exploration systems is to maximize value while minimizing cost. This
will be accomplished by:

Architecture trade space evaluations via iterative analyses of cost,
risk and performance based on realistic timelines and estimates of
cost.

Scheduling the incorporation of mature technologies to improve system
effectiveness and reduce cost.

Planning for uncertainties by establishing priorities, options,
adequate margins of safety, and "off-ramps."

Once finalized, the requirements are documented formally and approved
by NASA.

Once approved at the Agency level, requirements can only be modified by
NASA.

To allow flexibility in implementation, objectives and associated
thresholds will be established for major design and cost drivers.

NASA has defined an initial set of requirements for Spiral 1, 2, and 3
and identified major factors that drive performance and cost for the
CEV. Based on these initial requirements, a technical solution has
been developed using a Point-of-Departure (POD) architecture that meets
the exploration objectives through Spiral 3 (see Figure 1 for POD Spec
Tree and the following documents in attachment J-4: Constellation
Requirements in ESMD-RQ-0010, -0011, -0012, -0013; CEV Concept of
Operations in ESMD-RQ-0019). The POD will be used as a baseline
against which cost and operational performance trades can be made with
the goal of optimizing the exploration architecture and finalizing the
Spiral 3 requirements at SRR in July, 2006. Salient features of the
POD architectu

Spiral 1 components include the CEV, a CEV launch vehicle, and ground
support systems infrastructure. The CEV and launch elements will
safely transport the crew from the surface of the Earth to Low Earth
Orbit and return them to the Earth's surface at the completion of the
mission. The Launch System provides the capability to launch the CEV
to Low Earth Orbit. The CEV provides the necessary crew habitation
functions during ascent, on-orbit, and entry, including mission aborts.

Spiral 2 consists of the Spiral 1 elements, or derivatives of those
elements, plus the Earth Departure Stage (EDS) to transport elements to
the lunar vicinity as well as the Lunar Surface Access Module (LSAM)
that provides the capability for the crew to access the lunar surface.
The CEV provides crew habitation from launch to lunar orbit and return
to the Earth surface, including aborts during Earth ascent. The CEV
provides the transportation functions to return from lunar orbit to the
Earth surface. The EDS provides the propulsive accelerations needed to
transfer the various flight elements (CEV and LSAM) from Low Earth
Orbit to lunar orbit and provides the deceleration for lunar orbit
insertion. The LSAM provides the crew habitation and transportation
functions from lunar orbit, to the lunar surface, and return back to
lunar orbit. In addition, the LSAM provides the capability for the crew
to conduct science and perform routine EVA on the surface of the Moon.


Finally, the Cargo Delivery System (CDS) is used to deliver un-crewed
elements to low Earth orbit and/or lunar orbit. The CDS consists of an
EDS and a Cargo Launch Vehicle.

Spiral 3 requires various additional surface elements to support the
crew for the long duration missions. These surface elements have not
been completely defined at this point, but will provide basic
functional capabilities including habitation, communication, power,
extended range mobility, enhanced science capabilities, and other
functions.

It must be emphasized that the requirements baseline captured in the
point of departure architecture may be amended to reflect cost and
performance trade analysis results conducted during the CEV Phase 1
activities. The process for requirements and integrated design
development are documented in the Constellation SE&I White Paper:
Constellation System Engineering Management White Paper (see Applicable
Documents). NASA will maintain and update the SOO to reflect the
evolution of the Constellation System of System requirements suite
through SRR, as well as the Applicable Documents for the CEV system
development activities. At SRR the CEV System Requirements Document
(SRD) and External Interface Requirements Documents (EIRD's) will
become the baseline for the CEV system.

6.0CEV Technical Requirements

The contractor shall meet the following non-tradeable objectives:

The CEV system shall:

1.Ensure crew safety through all mission phases within the limitations
of meeting system performance requirements and achieving mission
objectives.

2.Integrate with required elements of the Constellation System of
Systems.

Based on the POD architecture, a set of Initial Performance Parameters
(IPPs) has been defined for the CEV. For purposes of this request for
proposals, industry is expected to provide an initial concept for a CEV
spacecraft that shall:

1.Have a total gross liftoff weight (GLOW) of less than 20 metric tons.

2.Provide an abort capability during all phases of flight.

3.Be 2-fault tolerant to hardware component failures within safety
critical systems except where design to minimum risk is approved by
NASA.

4.Integrate with the Launch Vehicle (LV) to achieve low earth orbit.

5.Integrate with the Earth Departure Stage (EDS) to achieve lunar
orbit.

6.Integrate with the Lunar Surface Access Module to achieve lunar
surface mission objectives.

7.Integrate with Ground Support Systems for launch processing and
mission control.

8.Integrate with In Space Support Systems to support overall
Constellation command, control, communication, and information
requirements.

9.Be capable of orbital maneuvers and rendezvous/docking with other
Constellation systems.

10.Be capable of return from lunar orbit to the earth surface without
assistance from external Constellation elements.

11.Be capable of supporting human life from launch on the earth surface
through mission complete on earth surface during a maximum CEV crewed
mission duration of 16 days.

12.Abort capability independent of LV or EDS flight control.

13.Be capable of unmanned operations for test flight purposes during
Spiral 1 efforts and during lunar surface activities for Spirals 2 and
3.

14.Minimizing ground processing interfaces while maintaining redundancy
separation standards and minimizing potential hazards.

15.Provide the capability to conduct missions with 1, 2, 3, and 4
crewmembers with a minimum habitable volume of 3.54 cubic meters per
crew member.

These IPP's are not meant to curtail innovation or alternate
architectural concepts during Phase 1 activities. To that end, a set
of focused cost and performance trades will be conducted prior to SRR
against these IPP's to include:

1.Launch weight mass trades (both increases and decreases), including
taking advantage of performance gains by mass reduction during ascent

2.Ability to abort anytime during all mission phases

3.Inclusion of the LSAM functionality within the CEV system

4.CEV direct return vs. Earth Capture

5.Mission Duration (both manned and unmanned mission phases)

6.Crew size (up to 6 crew members) and crew habitable volume
allocations.

7.Splitting CEV functionality into modules (e.g., earth surface to
LEO, LEO to Lunar orbit, Lunar orbit to Earth return)

8.Human Rating Requirements cost drivers

9.CEV system support of spiral 3

10.CEV support for transfer of crew to and from International Space
Station (ISS)

11.CEV support of Extra-Vehicular Activities (EVA) operations

12.Provisions for common Constellation System elements (eg Docking
systems, Communication systems)

Through this competition, industry partners will be selected to work
with NASA in conducting cost/performance analysis for alternatives to
the point-of-departure architecture and CEV requirements. At the same
time, the CEV contractors will mature their designs for the CEV while
working their risk reduction demonstrations. NASA's intent is to
finalize the Spiral 3 requirements in July, 2006, complete the FAST and
PDR in 2008, move onto final design and fabrication in support of the
first crewed flight in 2014, and then continue on to the moon, Mars,
and beyond.

wrote in message
ups.com...
15.Provide the capability to conduct missions with 1, 2, 3, and 4
crewmembers with a minimum habitable volume of 3.54 cubic meters per
crew member.

That's an odd number. By my calculations, that works out to a cube with a
side of exactly 5 feet in length. So, what research did they use to arrive
at exactly 125 cubic feet per crewmember?

I wonder if the engineers at NASA are still working with feet and inches?
;-)

Jeff
--
Remove icky phrase from email address to get a valid address.

Thanks Th,

I refuse to use MS products and all the documents are in MS Word format
- figures for the backward moronic dimensions of the project from the
idiotic author of it. (Fool + Liar = Bush) (any of them)

Laurs killed her high school sweetheart intentionally by t-boning his
car from the driver side. Lovely people. What an uber-mensch.

Thanks,

Rick


wrote:
ed kyle wrote:



Among the many unknowns is what the CEV Launch Vehicle
(CEVLV) is going to be. If CEVLV is tailored for Low
Earth Orbit (LEO) CEV missions (Spiral 1 requirement),
then if seems likely that a Spiral 2 CEV would be
launched separately from the LSAM/EDS components, to
perform an Earth Orbit Rendezvous type mission. EDS/LSAM
could be launched in pieces by several existing "Heavy"
boosters, or all at once by one really big new launch
vehicle. The new NASA administrator is said to favor
the latter approach, but the final decision will all
come down to cost and funding.

For an overview, read Attachment J-1 at the following link.
"http://prod.nais.nasa.gov/cgi-bin/eps/sol.cgi?acqid=113638"



It might be useful to post Attachment J-1 for reference here,
as well as to protect against 404age.

So here it is:

ATTACHMENT J-1

STATEMENT OF OBJECTIVES

Statement of Objectives for the Crew Exploration Vehicle

1.0 Introduction

On January 14, 2004, the President of the United States directed the
National Aeronautics and Space Administration (NASA) to embark on a
robust space exploration program that will advance the Nation's
scientific, security, and economic interests. To meet the goals and
objectives of our new vision, NASA plans to deploy a set of systems,
large and small, that will be integrated into a "system of
systems". This includes Earth-to-orbit and in-space transportation
systems, systems required for human health and performance, and robotic
systems that will assist humans as they travel and explore.

CEV is the first component in the system-of-systems that will be built
under the NASA Constellation Program and is the subject of this request
for proposals.

2.0 Scope

The Statement of Objectives (SOO) for the Crew Exploration Vehicle
represents a programmatic and technical baseline for the purposes of
the Offeror's proposal. The SOO will be maintained and updated by
NASA as a contractor programmatic and technical baseline until the
System Requirements Review (SRR) (see Section 5).

The SOO will be part of the Model Contract.

The SOO is augmented by a Constellation System of Systems Point of
Departure (POD) Architecture requirements suite through spiral 3 (see
figure 1). NASA plans on developing a clear set of performance and
functional requirements as well as external interface requirements for
the CEV system by SRR (see Section 5). In the event of a conflict with
the current revision of the Constellation System of System requirements
suite the SOO will take precedence until SRR.


3.0 Spiral Development and Constellation Program Objectives

A key challenge for NASA is to develop new capabilities in a manner
that is pragmatic - so that new capabilities can be developed and
used to advance exploration in the near term - while also being
flexible, in order to incorporate new technologies and respond with
agility to scientific discoveries. To meet this challenge, NASA will
develop exploration capabilities in stages, or "spirals." Each
spiral will usher in a set of major new capabilities in support of the
Vision for Space Exploration. Spirals will be structured based on
specific requirements, well-defined goals and endpoints, then-current
technologies, management risks, an executable budget, and knowledge
gained from prior in-space activities. NASA's acquisition strategy
encourages the use of open-systems architectures that facilitate
upgrades and augmentation while enabling interoperability among
systems. Capabilities to be provided by the first three spirals a

Spiral 1: Earth Orbit Capability.

Spiral 1 establishes the capability to test and checkout crew
transportation system elements in Low Earth Orbit in preparation for
future human exploration missions to the Moon. As new exploration
elements necessary for future spirals are developed, they will be
tested with the Spiral 1 CEV in the space environment to prepare for
future exploration. The objective of crewed access to low earth orbit
will be met by 2014.

Spiral 2: Extended Lunar Exploration.

Spiral 2 establishes the capability to conduct human exploration
missions on the surface of the Moon for extended durations. In this
context, extended duration is defined as the capability to support the
crew on the surface of the Moon for a minimum of four days. This
objective will be met in the 2015-2020 timeframe.

Spiral 3: Long Duration Lunar Exploration.

Spiral 3 establishes the capability to conduct routine human long
duration missions on the surface of the Moon to test out technologies
and operational techniques for expanding the human presence to Mars and
beyond. Missions in Spiral 3 will extend in duration from those
obtained in Spiral 2 up to several months to serve as an operational
analog of future short stay Mars missions. This objective will be met
after 2020.

A key aspect to spiral development will be to develop new technologies
that improve performance and lower cost over time. This is crucial to
maintaining affordability and achieving the Nation's goals for future
exploration.

Accordingly, major portions of NASA's resources have been allocated
to technology development with two major portfolios, Exploration
Systems Research and Technology (ESRT) and Human System Research and
Technology (HSRT), specifically focused on the exploration mission. To
build a sustainable program, all developments within the
system-of-systems must have a strategy for incorporating new
technologies that result from both NASA-sponsored and outside research.


4.0CEV Project Objectives

An anchoring capability of the Constellation Program is a human-rated
CEV that will carry human crews from Earth into space and back again.
Coupled with transfer stages, landing vehicles, and surface exploration
systems, the CEV will serve as an essential component of the
architecture that supports human voyages to the Moon and beyond. Given
an acquisition strategy utilizing spiral development, a
system-of-systems implementation, and reliance on technology for
sustainability and affordability, the following project objectives have
been established:

1.Ensure that the CEV is designed from the outset as a key element of
the Constellation "System of Systems" meeting at minimum Spiral 2
requirements with a clear plan to meet Spiral 3 requirements. Meeting
Spiral 3 from the outset is a goal.

2.Ensure crew safety within the limitations of meeting system
performance requirements and achieving mission objectives.

3.Design and execute a meaningful risk mitigation program that
culminates in a risk reduction flight effort and PDR by the end of
calendar year 2008.

4.Deliver a quality design that ensures simplicity and addresses all
aspects of human spacecraft development, certification and operations.
5.Execute a human flight in 2014 utilizing a CEV.

6.Perform to an established cost, schedule and technical baseline.

7.Maximize the use of existing technology in the design of the CEV.

8.Base the vehicle design on an Open Systems Architecture.

9.Simplify the interface design between the CEV and other Constellation
elements to optimize integration.

10.Certify by test to the maximum extent possible.

11.Develop technology portfolios and define requirements for advanced
development projects for technology insertion.

12. Implement innovative designs for the CEV spacecraft and ground
systems to achieve efficient and effective operations.

This solicitation for the CEV component of the Crew Transportation
System utilizes a phased approach. Phase 1 of the acquisition calls for
a maximum of two contractors to:

Evaluate NASA's ESRT and HSRT programs for potential CEV program
integration as part of a concerted effort to improve system
effectiveness and affordability.
Conduct a series of trade analyses on critical performance drivers for
the purposes of identifying threshold and objectives for the CEV
system.

Affordability, sustainability, and extensibility to future spirals will
be the focus of the analyses.

Participate fully in a System Requirements Review (SRR) to develop
accurate, comprehensive, consistent, and verifiable requirements for
the CEV system through Spiral 3 of the Constellation System of Systems.

Conduct a System Definition Review (SDR) for the CEV system meeting at
a minimum Spiral 2 with a clear implementation plan for Spiral 3.

Conduct a Preliminary Design Review (PDR) for the CEV system meeting at
a minimum Spiral 2 with a clear implementation plan for Spiral 3.

Provide an iterative analysis of cost, risk and performance based on
realistic timelines and estimates of cost.

Conduct a comprehensive risk management program which will mitigate
program uncertainties by establishing priorities, options, adequate
margins of safety, and "off-ramps" for risk mitigation during Phase
1 and a plan to retire the residual risk during phase 2.

Conduct a risk reduction flight effort to: (1) validate industry's
capability to perform on cost, on schedule and on performance, and (2)
retire associated CEV program risks (Flight Application of Spacecraft
Technology (FAST)).

CEV Phase 1 ends with a planned down select to a single prime
contractor in late 2008. Phase 2 of the CEV acquisition calls for a
single Contractor to complete the development, test, and deployment of
a human-rated CEV. After completion of phase 2, the contractor shall
provide, as Government options, sustaining engineering services and
production capability to support additional flights and additional CEV
spacecraft. The Government reserves the right to perform a down select
at any time and to not select either contractor in 2008.

5.0 Requirements Baseline for Constellation

NASA's process for formulating and prioritizing requirements is
targeted to enable sustainable and affordable exploration. An
overriding goal in the definition of the requirements set for future
exploration systems is to maximize value while minimizing cost. This
will be accomplished by:

Architecture trade space evaluations via iterative analyses of cost,
risk and performance based on realistic timelines and estimates of
cost.

Scheduling the incorporation of mature technologies to improve system
effectiveness and reduce cost.

Planning for uncertainties by establishing priorities, options,
adequate margins of safety, and "off-ramps."

Once finalized, the requirements are documented formally and approved
by NASA.

Once approved at the Agency level, requirements can only be modified by
NASA.

To allow flexibility in implementation, objectives and associated
thresholds will be established for major design and cost drivers.

NASA has defined an initial set of requirements for Spiral 1, 2, and 3
and identified major factors that drive performance and cost for the
CEV. Based on these initial requirements, a technical solution has
been developed using a Point-of-Departure (POD) architecture that meets
the exploration objectives through Spiral 3 (see Figure 1 for POD Spec
Tree and the following documents in attachment J-4: Constellation
Requirements in ESMD-RQ-0010, -0011, -0012, -0013; CEV Concept of
Operations in ESMD-RQ-0019). The POD will be used as a baseline
against which cost and operational performance trades can be made with
the goal of optimizing the exploration architecture and finalizing the
Spiral 3 requirements at SRR in July, 2006. Salient features of the
POD architectu

Spiral 1 components include the CEV, a CEV launch vehicle, and ground
support systems infrastructure. The CEV and launch elements will
safely transport the crew from the surface of the Earth to Low Earth
Orbit and return them to the Earth's surface at the completion of the
mission. The Launch System provides the capability to launch the CEV
to Low Earth Orbit. The CEV provides the necessary crew habitation
functions during ascent, on-orbit, and entry, including mission aborts.

Spiral 2 consists of the Spiral 1 elements, or derivatives of those
elements, plus the Earth Departure Stage (EDS) to transport elements to
the lunar vicinity as well as the Lunar Surface Access Module (LSAM)
that provides the capability for the crew to access the lunar surface.
The CEV provides crew habitation from launch to lunar orbit and return
to the Earth surface, including aborts during Earth ascent. The CEV
provides the transportation functions to return from lunar orbit to the
Earth surface. The EDS provides the propulsive accelerations needed to
transfer the various flight elements (CEV and LSAM) from Low Earth
Orbit to lunar orbit and provides the deceleration for lunar orbit
insertion. The LSAM provides the crew habitation and transportation
functions from lunar orbit, to the lunar surface, and return back to
lunar orbit. In addition, the LSAM provides the capability for the crew
to conduct science and perform routine EVA on the surface of the Moon.


Finally, the Cargo Delivery System (CDS) is used to deliver un-crewed
elements to low Earth orbit and/or lunar orbit. The CDS consists of an
EDS and a Cargo Launch Vehicle.

Spiral 3 requires various additional surface elements to support the
crew for the long duration missions. These surface elements have not
been completely defined at this point, but will provide basic
functional capabilities including habitation, communication, power,
extended range mobility, enhanced science capabilities, and other
functions.

It must be emphasized that the requirements baseline captured in the
point of departure architecture may be amended to reflect cost and
performance trade analysis results conducted during the CEV Phase 1
activities. The process for requirements and integrated design
development are documented in the Constellation SE&I White Paper:
Constellation System Engineering Management White Paper (see Applicable
Documents). NASA will maintain and update the SOO to reflect the
evolution of the Constellation System of System requirements suite
through SRR, as well as the Applicable Documents for the CEV system
development activities. At SRR the CEV System Requirements Document
(SRD) and External Interface Requirements Documents (EIRD's) will
become the baseline for the CEV system.

6.0CEV Technical Requirements

The contractor shall meet the following non-tradeable objectives:

The CEV system shall:

1.Ensure crew safety through all mission phases within the limitations
of meeting system performance requirements and achieving mission
objectives.

2.Integrate with required elements of the Constellation System of
Systems.

Based on the POD architecture, a set of Initial Performance Parameters
(IPPs) has been defined for the CEV. For purposes of this request for
proposals, industry is expected to provide an initial concept for a CEV
spacecraft that shall:

1.Have a total gross liftoff weight (GLOW) of less than 20 metric tons.

2.Provide an abort capability during all phases of flight.

3.Be 2-fault tolerant to hardware component failures within safety
critical systems except where design to minimum risk is approved by
NASA.

4.Integrate with the Launch Vehicle (LV) to achieve low earth orbit.

5.Integrate with the Earth Departure Stage (EDS) to achieve lunar
orbit.

6.Integrate with the Lunar Surface Access Module to achieve lunar
surface mission objectives.

7.Integrate with Ground Support Systems for launch processing and
mission control.

8.Integrate with In Space Support Systems to support overall
Constellation command, control, communication, and information
requirements.

9.Be capable of orbital maneuvers and rendezvous/docking with other
Constellation systems.

10.Be capable of return from lunar orbit to the earth surface without
assistance from external Constellation elements.

11.Be capable of supporting human life from launch on the earth surface
through mission complete on earth surface during a maximum CEV crewed
mission duration of 16 days.

12.Abort capability independent of LV or EDS flight control.

13.Be capable of unmanned operations for test flight purposes during
Spiral 1 efforts and during lunar surface activities for Spirals 2 and
3.

14.Minimizing ground processing interfaces while maintaining redundancy
separation standards and minimizing potential hazards.

15.Provide the capability to conduct missions with 1, 2, 3, and 4
crewmembers with a minimum habitable volume of 3.54 cubic meters per
crew member.

These IPP's are not meant to curtail innovation or alternate
architectural concepts during Phase 1 activities. To that end, a set
of focused cost and performance trades will be conducted prior to SRR
against these IPP's to include:

1.Launch weight mass trades (both increases and decreases), including
taking advantage of performance gains by mass reduction during ascent

2.Ability to abort anytime during all mission phases

3.Inclusion of the LSAM functionality within the CEV system

4.CEV direct return vs. Earth Capture

5.Mission Duration (both manned and unmanned mission phases)

6.Crew size (up to 6 crew members) and crew habitable volume
allocations.

7.Splitting CEV functionality into modules (e.g., earth surface to
LEO, LEO to Lunar orbit, Lunar orbit to Earth return)

8.Human Rating Requirements cost drivers

9.CEV system support of spiral 3

10.CEV support for transfer of crew to and from International Space
Station (ISS)

11.CEV support of Extra-Vehicular Activities (EVA) operations

12.Provisions for common Constellation System elements (eg Docking
systems, Communication systems)

Through this competition, industry partners will be selected to work
with NASA in conducting cost/performance analysis for alternatives to
the point-of-departure architecture and CEV requirements. At the same
time, the CEV contractors will mature their designs for the CEV while
working their risk reduction demonstrations. NASA's intent is to
finalize the Spiral 3 requirements in July, 2006, complete the FAST and
PDR in 2008, move onto final design and fabrication in support of the
first crewed flight in 2014, and then continue on to the moon, Mars,
and beyond.

"Rick Nelson" wrote ...
Thanks Th,

I refuse to use MS products and all the documents are in MS Word format

Open Office