NASA – The Rumor Mill

Following on the Tuesday meeting at NASA headquarters concerning revamping the governance structure, and Wednesday’s meeting between NASA administrator Charles Bolden and President Barack Obama, the rumor mill has been if full fury.

Wayne Hale offered this tweet: “Wondering if reports on Obama-Bolden meeting are accurate or just blather. No hard news has appeared.” To which Bob Jacobs, NASA’s deputy assistant administrator of Public Affairs responded: “Inaccurate. The meeting was informational, not decisional…”. Of course, that’s NASA’s spokesperson. Amy Klamper at Spacenews.com thinks “New Direction for NASA Could Wait Until February.”

Now comes Science magazine’s (AAAS) Insider report concerning the outcome of the meeting:

President Barack Obama will ask Congress next year to fund a new heavy-lift launcher to take humans to the moon, asteroids, and the moons of Mars, ScienceInsider has learned. The president chose the new direction for the U.S. human space flight program Wednesday at a White House meeting with NASA Administrator Charles Bolden, according to officials familiar with the discussion. NASA would receive an additional $1 billion in 2011 both to get the new launcher on track and to bolster the agency’s fleet of robotic Earth-monitoring spacecraft.

The major elements include:

• Elimination of the Ares I rocket
• Recommend Commercial development of Low Earth Orbit (LEO) launch capability for cargo and then crew.
• Development of a smaller heavy lift rocket along the lines proposed by the old NLS (National Launch System) NASA investigated in the early 1990’s and revived by the Direct Team between 2005 and today.
• Addition of $1 Billion to the Budget for NASA
• European countries, Japan, and Canada would be asked to work on a lunar lander and modules for a moon base.
• Focus on being able to perform a variety of missions including Near Earth Objects, Lagrange points, the Moon, the moons of Mars (Phobos and Deimos). See Option “5D”
• Additional probes to the Moon, Mars and and the moons of Mars.

Immediate blow back is expected from Senator Richard Shelby, who has asked the Inspector General at NASA to investigate “corruption” within the Augustine Commission. Shelby stated that several Augustine panel members were registered lobbyists who took “direct advantage of their temporary roles on the Commission to further their personal business.” This has been interpreted as a shot across the bow in the fight over Ares I and the jobs it creates at the Marshall Space Flight Center in Shelby’s state of Alabama. Whose bow it was aimed at is in question, and it looks like an act of desperation.

However, as noted in our Wrap Up report on the Augustine Commission, time is of the essence with regard to jobs and the retention of skills associated with building the 8.4 meter External Tank used by the space shuttle and the proposed heavy launch vehicle derived from the shuttle. If the politicians resist the change that’s coming to NASA, they may lose everything.

Denials to the Science Insider article came immediately from NASA and the White House. NASA spokesman Morrie Goodman said the article was “speculation.” White House spokesman Nicholas Shapiro echoed that characterization.

NASA – Change Is Coming

Considering the conclusions of the Final Report of the Augustine Commission (see our Wrap Up), change at NASA is inevitable. Can NASA change? Will NASA change?

Two items of interest.

First, Obama will be meeting with Gen. Charlie Bolden, NASA Administrator, today. The President’s schedule has the following entry:

3:05PM THE PRESIDENT meets with NASA Administrator Charles Bolden
Oval Office
Closed Press

Second, Keith Cowling at NASAWatch, reports that on Tuesday, 15 December:

All of NASA’s field center directors met today in a closed door session in one of the Administrator’s Conference Rooms on the 9th floor of NASA HQ. In addition to all of the center directors who were seated around the table, a dozen or so staffers stood around the periphery of the room. Their collective task was to work out and then agree upon a new governance structure for the agency – one that would best implement the new (revised) direction that the White House is providing to NASA. There are apparently 5 or so specific areas that the agency will be re-organizing itself to implement. As such, there may be a recasting of the “directorate” model in favor of “divisions”. All of the participants were sworn to secrecy and were not going to be leaving the room until a new governance model was agreed to.

What did they decide upon? Stay tuned.

Space Shuttle Atlantis – Landed

The Space Shuttle Atlantis Landed at Kennedy Space Center at 9:44 AM EST as Scheduled. Enjoy the eye candy.

Atlantis on Approach to Kennedy	Image Credits: NASA TV
Lined up and Straight	Atlantis View from the Cockpit. Headsup Display
Landing – Looking for that 15,000 Foot Runway	Flare over the Runway
Touchdown	Chute
Slowing	Atlantis Stopped – With Eagle

The Augustine Commission – Final Report – Hits and Misses – Wrapped Up

“The Augustine Commission for Dummies”

(Part 1. Part 2. Part 3. Part 4. Part 5. Wrap Up.)

Given the intent of the politicians to fight for the funding their districts currently receive from the Constellation Program (CxP – the current program developing the Ares I and Ares V rockets) as well as go begging for more, and given the budget constraints the NASA faces, it is instructive to see where this course will end up. In the Senate, Richard Shelby has announced his intention to fight for Constellation and will try to increase funding to the Marshall Space Flight Center in Alabama. Senator Bill Nelson of Florida is fighting for Kennedy Space Center and all the jobs and funding there. In the House, Gabrielle Giffords of Arizona and Pete Olson of Texas have dug in their heels and reiterated their backing of the Constellation program (See Space News, 21 November 2009).

All this is taking place against the backdrop of the Augustine Commission’s Final Report, which has made it clear that Ares I is over budget and underpowered. As Jeff Greason said at the Committee deliberations, if Santa Clause gave us Ares I and Ares V tomorrow, we would have to scrap them immediately because they would be too expensive to operate.

The Forum at NasaSpaceFlight has been for many years the authoritative site for information on all things NASA. It has been home to the rebel alliance of NASA and industry engineers that have advocated the in-line shuttle derived launch vehicle for the past four years.

The source of this concern was former Administrator Michael Griffin’s decision in 2005 to replace the dual-launch, in-line shuttle derived architecture recommended by NASA engineers, with his personal choice of a small Ares I and a very large Ares V. Instead of building one rocket using existing shuttle components as Congress had directed, he would build two brand new rockets. This decision came just two weeks before the scheduled release of the NASA document on the Constellation program.

Now, four years later in 2009, when the in-line shuttle derived launch vehicle should have been making its first flight, we are five or six years away from Ares I making its first flight. The Shuttle is scheduled for retirement next year and America will have to buy seats on the Russian Soyuz to get to the International Space Station. And the International Space Station is scheduled for de-commissioning in 2015 and would be de-orbited into the Pacific Ocean.

This reality gave birth to the Augustine Commission and its Final Report. We have covered in detail the findings of the Committee. Now we look to consider the possible outcomes.

Philip Metschan (writing as ‘Phoegh’), a long time contributor to the Forum at NasaSpaceFlight, has produced a marvelous interactive series of graphics available at directlauncher.com that illustrate the options identified by the Augustine Commission.

The Budget and Time Line for these options are given in the following table. Included are destinations beyond low Earth orbit (LEO) and the impact of each option on the existing workforce.

Option	Extra $ / Yr	Through 2020	Through 2030	Moon	NEO	Depot	Workforce
Option 1	$0	$99 B	$205 B	?	?	?	50% Loss
Option 2	$0	$105 B	$200 B	?	?	?	60% Loss
Option 3	$3 B	$127 B	$275 B	2025	?	?	53% Loss
Option 4	$3 B	$121 B	$264 B	2030	?	?	70% Loss
Option 4B	$3 B	$118 B	$255 B	2029	?	2026	25% Loss
Option 5A	$3 B	$128 B	$272 B	?	?	?	75% Loss
Option 5B	$3 B	$123 B	$268 B	2029	2026	2024	90% Loss
Option 5C	$3 B	$120 B	$256 B	2030	2027	2025	30% Loss
Option 5D	$1 B	$116 B	$239 B	2019	2022	2028	15% Loss

We can draw the following conclusions, which are illustrated in the Graphics mentioned earlier and shown below. We start with Option 1, the Program of Record (POR – Constellation) and the funding level provided in FY 2010:

• Option 1 – Ares I crew vehicle is ready a year after the ISS is de-orbited (2015) and Ares V is completed in 2028 with no funds to conduct exploration. There is no Moon in the picture.
• Option 2 – Scrap Ares I and substitute Commercial Crew Access to LEO. The money saved is used to keep the ISS operating until 2020. Ares V is completed in 2028 with no funds to conduct exploration. There is no Moon in the picture.
• Option 3 – Add $3 Billion per year to the existing program. Ares I crew vehicle is ready a year after the ISS is de-orbited (2015) and Ares V is completed in 2019. The Moon is reached in 2025, but no other destinations beyond LEO can be funded.
• Option 4 – Add $3 Billion per year to the existing program. Scrap Ares I and substitute Commercial Crew Access to LEO. The money saved is used to keep the ISS operating until 2020. Ares V is completed in 2023. The Moon is reached in 2030, but no other destinations beyond LEO can be funded.
• Option 4B – Add $3 Billion per year to the existing program. Extend the Shuttle to 2015. Scrap Ares I and substitute Commercial Crew Access to LEO. The money saved is used to keep the ISS operating until 2020. Ares V is completed in 2023. Develop the Propellant Depot by 2026. The Moon is reached in 2030.
• Option 5A – Add $3 Billion per year to the existing program. Scrap Ares I and substitute Commercial Crew Access to LEO. The money saved is used to keep the ISS operating until 2020. Scrap Ares V in favor of a smaller Ares V Lite, which is completed in 2023. Visit EML-1 or EML-2 in 2026. Visit a Near Earth Object (NEO) Sometime in the Future.
• Option 5B – Add $3 Billion per year to the existing program. Scrap Ares I and substitute Commercial Crew Access to LEO. The money saved is used to keep the ISS operating until 2020. Scrap Ares V in favor of a commercial heavy launch capability, which is completed in 2021. Develop the Propellant Depot by 2024. Visit a Near Earth Object (NEO) in 2026 and Phobos in 2028. Return to the Moon in 2029.
• Option 5C – Add $3 Billion per year to the existing program. Scrap Ares I and substitute Commercial Crew Access to LEO. The money saved is used to keep the ISS operating until 2020. Scrap Ares V in favor of a the Direct Team’s Jupiter 241, which is completed in 2022. Visit EML-1 or EML-2 in 2023. Develop the Propellant Depot by 2024. Visit a Near Earth Object (NEO) in 2027 and Phobos in 2029. Return to the Moon in 2030.

Those are the options explored by the Augustine Commission in their Final Report.

Notice, however, that there is one more slide, Option 5D. This is the architecture that was presented to the Augustine Commission during their first public session on 17 June 2009 by the Direct Team. It provides for:

• Add $1 Billion per year to the existing program.
• Extend Shuttle until 2012.
• Scrap Ares I and develop the Jupiter Core (Jupiter 130) for carrying crew on Orion to LEO and ISS by 2014.
• Develop Commercial Crew Access to LEO to replace the Jupiter 130 by 2015. Use Jupiter 130 for ferrying the few large payloads needed by ISS.
• Continue ISS operations until 2020.
• Scrap Ares V in favor of the Upper Stage for the Jupiter Core (Jupiter 241 or Jupiter 246), which is completed in 2017.
• Visit EML-1 or EML-2 in 2018.
• Orbit the Moon in 2019.
• Visit a Near Earth Object (NEO) in 2022.
• Visit Phobos in 2025.
• Develop the Propellant Depot by 2028.

The key here is that the goal of expansion of human civilization into the Solar System is better served, is accomplished sooner, and costs less. Indeed, even without the additional $1 Billion per year, only the extension of the Shuttle operation need be eliminated.

Final Conclusions

• Options 1, 2 and 3, which are favored by the politicians with space flight facilities, get us nowhere and cost far too much.
• Options 4 and 4B get us to the Moon, but neither builds infrastructure for support of future exploration.
• Options 5A, 5B and 5C builds the skills and infrastructure for space exploration, but leave us a crew to LEO gap of five to six years.
• Option 5D builds the skills and infrastructure for space exploration, reduces the crew to LEO gap to one or two years, and gives the international community the ability to descend to the surface of the Moon and Mars.

Time is of the Essence

Finally, this note about the political realities. First, if a decision is delayed for four to six months while the politicians fight for every last bit of funding they want, the infrastructure on which the Jupiter program builds will be dismantled and Options 4B, 5C and 5D will be eliminated.

Second, Congress will likely decide that the Constellation program as currently envisioned is too costly for what will be developed and not worth throwing more money down the drain. Options 1, 2, 3, 4B and 5A will be eliminated.

Thus, only commercial crew and cargo capabilities will be funded. NASA will be reduced to research and contracting for services. The Marshall Space Flight Facility will have little purpose. And the politicians will lose most of the jobs and funding that their districts currently enjoy.

Special thanks are in order to Philip Metschan for permission to use screen shots of his presentation.

(Part 1. Part 2. Part 3. Part 4. Part 5. Wrap Up.)

The Augustine Commission – Final Report – Hits and Misses – Part 5

(Part 1. Part 2. Part 3. Part 4. Part 5. Wrap Up.)

In Part 1, we looked at the pieces strewn about our living room floor. In Part 2, we examined the Goals and Destinations in Chapter 3.0. And in Part 3, the three current Human Space Flight programs were reviewed (International Space Station, the Space Shuttle and the Constellation Program). In Part 4, we looked at the launch vehicles examined by The Augustine Commission.

Chapter 6 of the Augustine Commission Final Report deals with Program Options and Evaluation. This is one of the many contentious issues commentators have with the Commission. While they did select five possible exploration programs (Chapter 6), and while they did evaluate various launch vehicles (Chapter 5), the Committee seems to have ignored the possibility that different launch vehicles have greater or lesser ability to cover the five exploration programs. This failure may in the end, prove to be disastrous for human space exploration. As we write, the Space Shuttle infrastructure is being actively dismantled. The end result of failing to evaluate the physical infrastructure and the human infrastructure capable of supporting a Shuttle derived architecture may be that the United States is left with no heavy lift human space flight capability for at least the next several decades. We may have surrendered our space faring capability to Europe, China, Russia, India and Japan.

6.1 Evaluation Criteria

As noted by the Commission:

The Committee did not intend that the evaluation would generate a single numerical score; rather, it would provide a basis for comparison across options, highlighting the opportunities and challenges associated with each. Assigning weights to individual figures of merit is within the purview of the ultimate decision-makers.

Three primary evaluation dimensions were identified:

• Benefits to Stakeholders
• Risk
• Budget Realities

These three dimensions were expanded into 12 criteria for comparing the options.

• Exploration Preparation
• Technology Innovation
• Science Knowledge
• Expanding and Protecting Human Civilization
• Economic Expansion
• Global Partnerships
• Public Engagement
• Schedule and Programmatic Risk
• Mission Safety Challenges
• Workforce Impact
• Programmatic Sustainability
• Life-Cycle Cost

6.2 Key Decisions and Integrated Options

6.2.1 Key Decisions

1. What should be the future of the Space Shuttle?
2. What should be the future of the International Space Station (ISS)?
3. On what should the next heavy-lift launch vehicle be based?
4. How should crews be carried to low-Earth orbit?
5. What is the most practicable strategy for exploration beyond low-Earth orbit?

6.2.2 Integrated Options

The Committee identified five basic options: One based on the Program of Record (POR – Constellation – Ares I and V, Orion and Altair), and four alternatives. Options 2 and 3 were budget compatable alternatives to the POR. Option 4 was a Moon First program (with two variations), and Option 5 was the Flexible Path (avoiding the gravity well of the Moon).

6.2.3 Methodology for Analyzing the Integrated Options

Two budgets were used. The “Constrained Budget” used the FY 2010 budget, while the “Less Constrained Budget” allowed for an increase by 2014 of $3 Billion per year higher than FY 2010.

6.2.4 Reference Cases of the Entirely Unconstrained Program of Record

The Program of Record was evaluated and found to be a total of $45 Billion over the FY 2010 budget by 2020, wherein it is $5 Billion a year over FY 2010 in 2016 and $7 Billion per year over FY 2010 in 2019.

6.3 Integrated Options Constrained to the FY 2010 Budget

6.3.1 Evaluation of Integrated Options 1 and 2

Option 1 was found to allow for rocket development, but lacked funds for exploration. Option 2 extends the lifetime of the ISS, delays rocket development, and has no funds for exploration.

6.3.2 Examination of alternate budget guidance

The Committee found no alternatives to Options 1 or 2 that were viable under the FY 2010 budget. This conclusion has been disputed.

6.4 Moon First Integrated Options Fit to the Less-Constrained Budget

6.4.1 Evaluation of Integrated Options 3 and 4

Option 3 was to execute the POR under a less constrained budget. The ISS is de-orbited in 2010, and the Shuttle flies the remaining missions into 2011. Human lunar return occurs in the mid 2020s and the lunar base becomes operation late in the decade. An alternate extending ISS to 2020 was found to push these dates out by three to four more years.

Option 4 uses the less constrained budget, scraps Ares I and substitutes commercial crew services by 2016 It extends the ISS to 2020. Ares V is scrapped in favor of a dual-launch Ares V Lite vehicle for lunar missions.

Option 4A retires the Shuttle in 2011, while Option 4B extends the Shuttle to 2015 and develops a Shuttle Derived Heavy Lift vehicle in place of Ares V Lite.

6.4.2 Examination of the key decision on the ISS extension

Given the International Partnerships that have been developed, and the fact that the extension to 2020 would only delay the lunar return by a few years, the Committee found that the extension provides greater value than ending the ISS mission.

6.4.3 Examination of the key decision on Ares V vs. Ares V Lite dual launch

Baseline Ares V has more launch capability than the Saturn V, but current NASA studies show that when used in combination with Ares I, it does not have enough launch capability to robustly deliver the currently planned landing and surface systems to the Moon.

The Committee concluded that Ares V Lite represents less development risk, likely will reduce costs and provides more substantial margin for the lunar mission.

6.4.4 Examination of the key decision on the provision of crew transport to low-Earth orbit

Commercial crew services, based on a high-reliability rocket with a capsule and launch escape system could significantly reduce development costs, as well as lower operating costs.

6.4.5 Examination of the key question on Shuttle extension

The Committee favored early retirement of the Shuttle (2010 or 2011), although they noted several advantages to Shuttle extension to 2015, including up-mass and down-mass capability and workforce retention.

6.5 Flexible Path Integrated Options Fit to the Less-Constrained Budget

6.5.1 Evaluation of Integrated Option 5

Option 5 operates the Shuttle into 2011 and extends the International Space Station mission until 2020. A variety of destinations beyond low earth orbit are possible. The Committee developed three variants of this option.

• Option 5A develops the Ares V Lite, visits the Lagrange points, near Earth objects, on-orbit refueling and achieves a lunar return by the end of the 2020s.
• Option 5B develops commercial heavy lift capability, restructures NASA, and follows a similar mission profile as 5A, but on a slower time line.
• Option 5C scraps Ares V Lite and develops a Shuttle Derived Heavy Lift vehicle. 5C follows a similar mission profile as 5A, but on a slower time line.

6.5.2 Examination of the key question on Ares V family vs. Shuttle-derived heavy launcher

While the Shuttle derived in-line launch vehicle (SDLV) with two four-segment solid rocket motors (SRM) and the 8.4 meter external tank (ET) was the 2005 ESAS candidate for the cargo vehicle, it was forced to evolve into the Ares V due to the problems encountered with the underpowered Ares I. For some reason, the Committee decided that in order to match the capabilities of the Ares V, or the Ares V Lite dual-launch mission, that there had to be three SDLV launches. Therefore, operations would be more costly.

This is a clear Committee miss, as the current planned lunar return missions can be accomplished with good margin by a dual-launch SDLV program, thus costing less than the Ares V Lite. There is no need for the enhanced capabilities of the dual-launch Ares V Lite.

6.5.3 Examination of the key question on NASA heritage vs. EELV-heritage super-heavy vehicles

The Committee considers the EELV-heritage super-heavy vehicle to be a way to significantly reduce the operating cost of the heavy lifter to NASA in the long run. It would be a less-capable vehicle, but probably sufficiently capable for the mission. Reaping the long-term cost benefits would require substantial disruption in NASA, and force the agency to adopt a new way of doing business.

6.6 Comparisons Across Integrated Options

6.6.1 Cross-option comparisons

The Flexible Path program (Option 5A) scores more highly than the Baseline (Option 3) on 9 of the 12 criteria outlined in section 6.1 ( See figure 6.6.1-1). The higher rankings include:

• Exploration Preparation (due to much more capable launch system)
• Technology (due to investment in technology)
• Science (because of more places visited)
• Human Civilization (due to the ISS extension)
• Economic Expansion (because of commercial involvement in space elements and crew transport)
• Global Partnerships (gained by extending the ISS)
• Public Engagement (by visiting more new locations, and doing so each year)
• Schedule (exploring beyond low-Earth orbit sooner)
• Life-Cycle Costs (due to commercial crew services)

6.6.2 Examination of the key question on exploration strategy

Three exploration strategies were examined in Chapter 3. The choice of Mars First was found not to be viable due to technological problems. Two strategies remained:

• Moon First on the Way to Mars, with surface exploration focused on developing capability for Mars.
• Flexible Path to Mars via the inner solar system objects and locations, with no immediate plan for surface exploration, then followed by exploration of the lunar and/or Martian surface.

The Moon first is favorable to lunar science and exploration (although much can be done robotically). The Flexible Path missions explore more of the Solar System, while initially doing less on the Moon. Flexible Path has the advantage of developing infrastructure for deep space exploration, including the moons of Mars and Mars itself. The Committe notes that:

Considering that we have visited and obtained samples from the Moon, but not near-Earth objects or Mars, and also that the Flexible Path develops the ability to service space observatories, the Science Knowledge criterion slightly favors the Flexible Path. Broadly, the more complex the environment, the more astronaut explorers are favored over robotic exploration. In practice, this means that astronauts will offer their greatest value-added in the exploration of the surface of Mars.

Final Scoring

Although the Augustine Commission did not publish a final tally of the scores (for reasons they made clear), the following table does compare and tabulate the scores.

Option	Description	Science	Safety	Cost	Schedule	NASA / Industry Jobs	US Skills Retention	Exploration Capability	Technology	Space Colony Potential	Commercial Benefit	Public Engagement	international Cooperation	Sustainability	Total
1	The Status Quo	0	0	0	-2	-1	-1	-2	-2	-2	-1	-1	-2	-1	-15
2	ISS Extension plus Moon	0	0	1	-2	-1	-1	-2	1	-1	1	-1	0	0	-5
3	Status quo + $3 B	1	-1	0	0	0	-1	0	0	0	0	0	-2	0	-3
4	Shuttle + Moon	1	-1	1	0	0	-1	1	1	1	1	0	0	0	4
4B	Shuttle 2015 + Moon	1	-1	0	0	0	0	1	1	1	1	0	0	1	5
5A	Flexible Path + Ares Lite	2	-1	1	1	0	-1	2	1	1	2	1	0	0	9
5B	Flexible Path + Commercial	2	-2	2	1	0	-1	1	2	1	2	1	0	-1	8
5C	Flexible Path + Jupiter 241	2	-2	0	1	0	-1	1	1	1	2	1	0	1	7

Option 5D: We will have more to say about this proposal in our final segment: “Wrapped Up” or “The Augustine Commission for Dummies”.

Option	Description	Science	Safety	Cost	Schedule	NASA / Industry Jobs	US Skills Retention	Exploration Capability	Technology	Space Colony Potential	Commercial Benefit	Public Engagement	international Cooperation	Sustainability	Total
5D	Flexible Path + Direct	2	-2	1	1	1	1	2	1	1	2	1	1	1	13

(Part 1. Part 2. Part 3. Part 4. Part 5. Wrap Up.)

STS-129 – Docking with ISS

This morning (7:45 AM Phoenix), we find Atlantis 27,000 feet from the International Space Station. Nicole Stott will be returning on Atlantis following her mission on the ISS. Live coverage on NASA TV.

Control Room prior to Docking. Image Credit: NASA TV

Atlantis Location and Attitude. Image Credit: NASA TV

Three miles from the ISS and Atlantis completes a short burn.

Nicole comments her ticket is stamped and ready to go for the return flight home.

8:11 AM Phoenix (10:11 EST) and Atlantis is 8,000 feet away. Docking is scheduled for 9:53 AM Phoenix time (11:53 EST)

And at 8:20, Atlantis is less than 5,000 feet away from ISS.

Control Room Approach Display. Image Credit: NASA TV	Atlantis Go for 600 Foot Approach. Image Credit: NASA TV
ISS from Atlantis. Image Credit: NASA TV	Atlantis Closing. Image Credit: NASA TV
Cargo Bay Open. Image Credit: NASA TV	Atlantis Closing on the IIS. Image Credit: NASA TV

At about 8:53 AM (10:53 EST), Atlantis will perform the heat shield inspection back flip.

Tile Inspection. Image Credit: NASA TV

Closing Display. Image Credit: NASA TV

Shuttle Atlantis closing at 0.2 feet per second with 20 minutes to go until docking.

Speed is now down 0.17 foot per second as Atlantis is less than 100 feet away from the docking port.

50 feet.

Final approach maneuver at 30 feet.

20 feet. 15 feet. 10 feet. 5 feet.

Docking confirmed at 9:51 AM Phoenix time.

Space Shuttle Launch – STS 129

The Space Shuttle Atlantis has completed LH2 and LOX fueling. Launch is scheduled for 12:28 Phoenix time. NASA TV is carrying the launch live.

Fueling. Image Credit: NASA TV

Orbiter. Image Credit: NASA TV

Weather remains an issue, and the probability of good weather has fallen from 90% to 70%.

Suiting Up. Image Credit: NASA TV

Strapping In. Image Credit: NASA TV

Its 12:10 AM EST (10:10 AM Phoenix). Extraneous items are being removed from the flight deck in preparation for closing the hatch.

Counting Down. Image Credit: NASA TV

T-Minus 82 Minutes. Image Credit: NASA TV

Weather forecast is improving. Currently alternate landing sites for the launch have satisfactory weather for launch. Atlantis is in the middle of a planned hold and the count will resume at t-minus 9 minutes (2:19 PM EST) at 12:19 PM in Phoenix.

The count has been picked up at T-minus 9 minutes. Weather is good.

Ignition. Image Credit: NASA TV	Liftoff. Image Credit: NASA TV
Solid Motor cutoff in 10 seconds. Image Credit: NASA TV	Separation. Image Credit: NASA TV

Main Engine Cutoff. OMS Burns were successful. Atlantis is now chasing the International Space Station, and is scheduled for docking on Wednesday.

More launch images:

Engine Ignition. Image Credit: NASA TV	Liftoff. Image Credit: NASA TV
Through the Clouds. Image Credit: NASA TV	Through the Clouds. Image Credit: NASA TV
Booster Separation. Image Credit: NASA TV	Booster Separation. Image Credit: NASA TV
Shuttle Rolls Upright. Image Credit: NASA TV	Shuttle Leaves External Tank. Image Credit: NASA TV

JWST – James Webb Space Telescope

Credit: NASA Video

The James Webb Space Telescope (JWST) is an infrared observatory, and a partial successor to the Hubble Space Telescope. JWST does not view visible light because light from the earliest universe has shifted toward the infrared (red shift). Infrared sensitivity is required in order to see further back in time toward the beginning of the universe than either Hubble or ground based observatories.The James Webb Space Telescope is a joint venture between NASA, the European Space Agency (ESA) and the Canadian Space Agency (CSA). In all, fifteen countries are making contributions to JWST. The are four main components to the scientific mission: Search for the first stars and galaxies that formed after the Big Bang Study galaxies and their formation and evolution Understand the formation of stars and planetary systems Study the origins of life on planetary systems

JWST is scheduled for launch in 2014 aboard an Ariane 5 rocket. It will take up residence at the Sun-Earth Lagrange point 2 (SEL-2). SEL-2 is 1,500,000 km beyond the Earth from the Sun (the Earth-Moon L2 is 61,500 km beyond the Moon). The location was chosen in order to be able to shield the telescope from the infrared radiation of the Sun and the Earth. Currently, SEL-2 is occupied by the Wilkinson Microwave Anisotropy Probe (WMAP), which was launched 30 June 2001, and the Herschel and Planck observatories, which were launched together on an Ariane 5 on 14 May 2009. The image at left is a cutaway diagram the the Ariane 5 rocket, illustrating how the JWST will fold up inside the payload fairing. With the large screen behind it, the JWST will be about 21 m in width. It will stand about three stories high. The main telescope mirror, which measures 6.5 m in diameter, is too large to launch in one piece. Instead, it consists of 17 individual mirror segments mounted on a frame which will be folded inside the fairing of the Ariane 5 at launch. Once it arrives at SEL-2, it will unfold, as this animation shows. There are four instruments designed to conduct the investigations on board the James Webb Space Telescope: Mid-Infrared Instrument, or MIRI – provided by the European Consortium with the European Space Agency (ESA), and by the NASA Jet Propulsion Laboratory (JPL) Near-Infrared Camera, or NIRCam – provided by the University of Arizona Near-Infrared Spectrograph, or NIRSpec – provided by ESA, with components provided by NASA/GSFC. Fine Guidance Sensor, or FGS – provided by the Canadian Space Agency. The FGS contains a dedicated Guider and a Tunable Filter Camera.

Credit: European Space Agency

Credit: NASA   Credit: NASA

The image at left shows the locations of the four instruments in the Integrated Science Instrument Module (ISIM). Below, the image shows the location of the instrument package within the JWST. The Mid-Infrared Instrument (MIRI) is an imager/spectrograph that covers the wavelength range of 5 to 27 micrometers. The camera provides wide-field broadband imagery, and the spectrograph module provides medium-resolution spectroscopy over a smaller field of view compared to the imager. The nominal operating temperature for the MIRI is 7K. Additional information can be found at the MIRI website, Space Telescope Science Institute. The Near Infrared Camera (NIRCam) is an imager with a large field of view and high angular resolution. The NIRCam covers a wavelength range of 0.6 to 5 micrometers. More on NIRCam. The Near Infrared Spectrograph (NIRSpec) measures the simultaneous spectra of more than 100 objects in a 9-square-arcminute field of view. This instrument provides medium-resolution spectroscopy over a wavelength range of 1 to 5 micrometers and lower-resolution spectroscopy from 0.6 to 5 micrometers. See the Space Telescope Science Institute information on NIRSpec. The Fine Guidance Sensor (FGS) sensor is used for both “guide star” acquisition and fine pointing. See information from the Space Telescope Science Institute about NIRSpec.

Recent Events

In October, the NIRSpec Engineering Test Unit (ETU) was completed by Astrium, and will be shipped to the United States later this year for integration testing. For additional information on the ETU, see this article in Space News. Integration testing will allow work to continue while the final NIRSpec instrument is developed. Along with the NIRSpec ETU, a test model of the other European instrument, the Mid-Infrared Instrument (MIRI) will also be delivered.

See also:

The Wikipedia article on JWST.
NASA home page for JWST.
ESA home page for JWST.
CSA home page for JWST.
Make your own Paper Model of the JWST.
YouTube and JWST.

The Augustine Commission – Final Report – Hits and Misses – Part 4

(Part 1. Part 2. Part 3. Part 4. Part 5. Wrap Up.)

In Part 1, we looked at the pieces strewn about our living room floor. In Part 2, we examined the Goals and Destinations in Chapter 3.0. And in Part 3, the three current Human Space Flight programs were reviewed (International Space Station, the Space Shuttle and the Constellation Program).

Chapter 5.0 Launch to Low-Earth Orbit and Beyond

In this section, The Augustine Commission examines launch vehicles. We begin with the opening statement, with which we agree:

Launch to low-Earth orbit is the most energy-intensive and dynamic step in human space exploration. No other single propulsive maneuver, including descent to and ascent from the surfaces of the Moon or Mars, demands higher thrust or more energy or has the high aerodynamic pressure forces than a launch from Earth. Launch is a critical area for spaceflight, and two of the five key questions that guide the future plans for U.S. human spaceflight focus on launch to low-Earth orbit: the delivery of heavy masses to low-Earth orbit and beyond; and the delivery of crew to low-Earth orbit.

5.1 Evaluation methodologies for Launch Vehicles

The Commission used “cost, performance and schedule parameters, as well as safety, operability, maturity, human rating, workforce implications, development of commercial space, the consequences to national security space, and the impact on exploration and science missions”. They note that some of these are quantitative and some are qualitative measures. Evaluations of the claim for each launcher was made and adjusted, and the uncertainty was assessed. Historical bounds were employed where appropriate. Some 70 lower-level metrics were used to construct 13 top level metrics.

5.2 Heavy Lift to Low-Earth Orbit and Beyond

The Commission began by reiterating the Constellation plan to loft about 600 metric tons (mt) per year to low Earth orbit (LEO). By comparison, NASA launched 250 mt per year during Apollo and the International Space Station (ISS) has a mass of about 350 mt.

Figure 5.2-1 listed the five candidates and their lift to LEO (see Launch Vehicles for visuals) and Figure 5.2.1-1 gave Trans Lunar Injection (TLI) with no refueling and with in-space refueling:



Launch Vehicle	LEO	TLI no refueling	TLI in-space refueling
EELV Super Heavy	75 mt	26 mt	55 mt
Directly Shuttle Derived	100-110 mt	35 mt	75 mt
Ares V Lite	140 mt	55 mt	120 mt
Ares V	160 mt	63 mt	130 mt
Ares V plus Ares I	185 mt	71 mt	150 mt

Notice that the Commission has brought the potential of in-space refueling front and center, either as propellant transfer from one spacecraft to another (as in a dual launch Ares V Lite or Jupiter 246), or from a true propellant depot, which would be supplied by commercial contract. However, “the Committee found both of these concepts feasible with current technology, but in need of significant further engineering development and in-space demonstration before they could be included in a baseline design”. Thus, the initial set of evaluations would need to examine the mass that an Earth Departure Stage (EDS) could push through TLI without refueling.

A detailed study of launch reliability of multi-launch missions commissioned by the Committee concluded that at most three critical launches be used. Reasonable chances for success required 90+ days of on-orbit life for an EDS or propellant depots.

Subsequent to Shuttle retirement, the need for NASA to launch 400 to 600 mt to LEO each year would consume much if not all of the existing and planned excess EELV capacity. Further, it would be expensive.

Finally, the Commission notes that heavy lift vehicles “would allow large scientific observatories to be launched, potentially enabling them to have optics larger than the current five-meter fairing sizes will allow. More capable deep-space science missions could be mounted, allowing faster or more extensive exploration of the outer solar system”.

All the foregoing was seen as justification for the development of Heavy Lift vehicles. The Commission then reviewed the choices in the chart above.

Ares V: This is the most capable of the proposed rockets. Together with the Ares I, it can launch 185 mt to LEO, 71 mt through TLI and land 14 tons of cargo only on the lunar surface, or 2 mt of cargo plus crew. Ares V requires expansion of the External Tank (ET) to 10 meters, the development of new 5.5 segment solid rocket motors (SRM), development of a regenerative version of the RS-68 engine and the development of the J2-X second stage engine (modified from the Saturn J2 engine).

Ares V Lite: Ares V Lite is a derivative of the Ares V, but with an LEO payload of 140 mt. This rocket would require the completion of the 5 segment SRM under development for Ares I. The remaining new Ares V components would still require development. For lunar missions, the Ares V Lite would be human-rated and used in the “dual mode”. In single launch it can place 14 mt of cargo on the lunar surface, and with a larger Lander than Ares V, it can land 5 mt of cargo plus crew.

SDLV Side-Mount: The side-mount and the in-line SDLV both use the existing Space Shuttle ET, the 4 segment SRM and the Space Shuttle Main Engines (SSME). The side-mount replaces the Shuttle with a cargo pod. The Committee combined the side-mount with the in-line variants for purposes of evaluation. They did note, however, that “the side-mount variant is considered an inherently less safe arrangement if crew are to be carried, and is more limited in its growth potential”.

SDLV In-Line The in-line variants are represented by the Jupiter family of rockets, as proposed by the Direct team. The Committee assumed that three Jupiter 241 vehicles would be used for a lunar mission, and that 5 mt of cargo could be landed with crew. No figure was given for a cargo only dual-launch mission, but the report states that more than 20 mt of cargo can be landed by a single Jupiter 241 using in-space refueling. Now, the three launch scenario is peculiar. Perhaps the Commission was trying to replicate the LEO loft mass of a dual Ares V Lite mission (2 x 140 mt). However, that much fuel, lander and crew far exceeds the Constellation Program (CxP) requirements. Furthermore, Ross Tierney, from Direct, has stated that “the right 2-launch Jupiter architecture is actually capable of landing 19mT of useful payload mass on the lunar surface every crew mission…Given that the Ascent Module only consists of about 6.4mT of that, this architecture is actually capable of landing almost the same 14.5mT* cargo modules as CxP are currently planning to land using cargo-only missions”. So we are left with unanswered questions concerning the assumptions and evaluations made by the Commission, not only about SDLV, but the Ares mission architectures.

EELV Super Heavy The Extended Expendable Launch Vehicle (EELV) is represented by the Atlas 5 Phase 2 Heavy, which consists of the core rocket plus two boosters of the same basic design along with an upgraded common upper stage (to be used by both Atlas and Delta). The common upper stage would use four RL-10 rocket engines, which have a long history of successful flights aboard Titan, Delta and Atlas among others. This configuration is capable of lofting a maximum of 75 mt to LEO. A dual launch configuration with in-space refueling is capable of conducting Flexible Path missions.

Summary of Findings

• Heavy Lift capability is beneficial to human exploration as well as national security and the scientific community.
• In-Space refueling represents a significant benefit to space transportation systems beyond low Earth orbit. It requires development and would not be on the critical path. A prudent approach is to develop Heavy Lift capable of early missions and phase in in-space refueling when it becomes available.
• A new emphasis of sustainable operations is needed. “NASA’s design culture emphasizes maximizing performance at minimum development cost, repeatedly resulting in high operational and lifecycle costs. A shift in NASA design culture toward design for minimum discounted life-cycle cost, accompanied by robustness and adequate margins, will allow NASA programs to be more sustainable”.
• In-Space Propulsion for missions beyond LEO that last for weeks or months require stages using efficient engines with high-reliability restart capabilities.

The Lunar Surface Capabilities of the various systems are compared in the following table:



Launch Vehicle	LEO	Cargo Only	Cargo and Crew
EELV Super Heavy	75 mt	NA mt	NA mt
Directly Shuttle Derived	100-110 mt	14 mt*	5 mt*
Ares V Lite	140 mt	14 mt	5 mt
Ares V plus Ares I	185 mt	14 mt	2 mt

5.3 Crew Launch to Low-Earth Orbit

Crew safety is an overriding issue in human space flight. The safe delivery of crew to LEO and their return is critical. This is the fourth key question (see Part 1) that the Committee examined. The assumed that Orion would be the crew vehicle, and that the launch vehicle would either be government provided and operated, or a commercial service.

Ares I was selected in 2005 as part of the ESAS study, and was expected to be operational in 2012. The Constellation program now projects initial operational capability (IOC) in 2015, and the Committee thinks this will slip further. Both budgetary and design problems have been encountered.

International Transportation was deemed acceptable by the Committee. However, sustained U. S. leadership in space requires domestic crew launch capability.

A human rated EELV was considered by the Commission. An independent study found that the launch of Orion on the Delta IV Heavy was technically feasible, but the long term development and carrying costs offset any savings versus Ares I.

Commercial Transport of crew to LEO is a hot topic. The Committee asked “can a simple capsule with a launch escape system, operating on a high-reliability liquid booster, be made safer than the Shuttle, and comparably as safe as Ares I plus Orion”? A number of factors were considered:

• A strong role for NASA oversight of the development would be required.
• The cost to NASA of underwriting design, development, test, and evaluation (DDT&E).
• The potential non-NASA uses of LEO crew transport

The Committee made several estimates of total costs, and arrived at a preliminary estimate of $5 Billion dollars. Assuming a “less-constrained” NASA budget, a commercial LEO crew transport service could be available by 2016.

Finally, the Committee assessed the risks to the human space flight program associated with commercial crew transport. Such development could distract from the near-term goal of developing commercial cargo capability. The commercial community might fail to deliver a crew transportation system. The fall-back position for NASA would be human rating the Heavy Lift Vehicle. The Committee assumes that the first stage of the HLV will be developed as quickly as possible. We leave the implications of this statement as an exercise for the reader.

5.4 Additional Issues in Launcher Selection

Launch Vehicle Performance and Costing The factors in this section include:

• Evaluation of the claimed cost, schedule and performance of the various launch vehicles.
• The advantage of shifting to commercial purchase of space transportation systems.
• The loss of the workforce and expertise built up within NASA from shifting to commercial sources.
• The health and viability of the solid rocket motor industry from all-liquid fuel launch vehicles.

Launcher Reliability The Committee reviewed the historical reliability of the Shuttle, Saturn, Titan, Delta and Atlas programs. Launchers derived from existing systems have shown greater reliability in early stages of development than newly developed systems.

(Part 1. Part 2. Part 3. Part 4. Part 5. Wrap Up.)

Ares I-X – Second Launch Attempt

Following yesterday’s scrub, Ares 1-X survived the overnight thunderstorm and is scheduled for launch this morning. And we are watching on NASA – TV. Currently, they are reviewing systems within Ares I-X to verify there has been no damage. The nearest lightening strike was 700 feet (200 meters) away. The countdown is sitting at T minus 4:00 minutes, and launch is tentatively scheduled for around 9:00 AM EDT.

The resumption of the count is expected in about 25 minutes.

Ares I-X. Second Attempt. Early Morning Credit: NASA TV.

Second Attempt. Hold for Rocket Check. Credit: NASA TV.

Currently waiting for completion of the systems checks on Ares I-X and the weather. The main weather problem is “triboelectrification”, which is fully explained in this review of yesterday’s launch attempt. Briefly:

According to the 45th Weather Squadron of the Air Force – the Squadron responsible for monitoring all launch weather rules – Triboelectrification is defined as: “triboelectric charging observed to put aircraft and space vehicles into corona when they fly through clouds containing ice or precipitation in either phase.

“The corona generates radio signals known as P-static (Precipitation static). P-static can degrade the signal to noise ratio of critical communications to the vehicle, especially including the range destruct command link.

The new launch time is 11:00 AM EDT. Weather is expected to have an 80% chance to be acceptable at that time (8:00 AM Phoenix time).

Pad 39B. Credit: NASA TV.

Aerial View of Ares I-X. Credit: NASA TV.

If today’s launch is scrubbed, the next window is late December or early 2010.

With 20 minutes to go until 11:00 AM EDT, the launch director has polled all systems and all systems are ready for launch. Everything is ok except the weather for triboelectrification.

At 11:03, weather is no go and the estimate is for 20 to 25 minutes from now. And now, they plan to pick up the clock at 11:16 AM and launch at 11:20 AM.

At 11:20, we have a ten minute window. Launch Director looking to resume the count at 11:27 EDT.

The count has resumed with launch expected at 11:30 AM.

Launch success.

Ascent. Credit: NASA TV.

More details.