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Topic: SSTO

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	SSTO: A Spaceship for the Rest of US (1992) (Site not responding. Last check: 2007-11-03)
		This means that the only infrastructure needed to launch a SSTO is a concrete pad and a fuel truck.
		SSTO vehicles are built to be operated like airliners.
		The reliability of SSTO vehicles should be close to that of airliners -- a loss rate of essentially zero -- and far better than the 3% loss rate of existing launchers.
	www.islandone.org /Policy/SSTO-ASpaceShipForTheRestOfUs.html (2351 words)

	Single-stage to orbit - Wikipedia, the free encyclopedia
		No actual SSTO launch vehicles have been constructed - current orbital launches are either performed by multi-stage fully expendable rockets, or like the Space Shuttle which is multi-stage and partially reusable, since it is assisted by a drop tank and solid rocket boosters that are jettisoned during the climb.
		This may not appear to be large amount, but the mass ratio to delta-v curve is very steep to reach orbit in a single stage, and this makes a 10% difference to the mass ratio, on top of the tankage and pump savings.
		SSTO vehicles use the same engine for all altitudes, which is a problem for traditional engines with a bell shaped nozzle.
	en.wikipedia.org /wiki/Single_stage_to_orbit (2066 words)

	Space Future - History of the Phoenix VTOL SSTO and Recent Developments in Single-Stage Launch Systems
		This proved to be necessary due largely to their self-imposed requirement that they land the vehicle on a small pad, while tolerating a guidance error typical of the worst case performance of the Apollo spacecraft.
		SSTOs, since it was generally believed that larger vehicles would be easier to make work than smaller ones.
		SSTOs were performed by the Aerospace Corporation, a civilian analysis arm of the USAF, during the 1980s.
	www.spacefuture.com /archive/history_of_the_phoenix_vtol_ssto_and_recent_developments_in_single_stage_launch_systems.shtml (6439 words)

	Bantam Boosters: The Key to Small RLVs?
		The argument for starting with an SSTO appears to be that if the government subsidizes the development of the vehicle, investment can be ignored, and the vehicle can then be marketed at launch prices corresponding to recurring costs.
		Since both the SSTO and the Space Van require more than $100,000,000 per year of business for even a 10 percent ROI, neither of these vehicles are appropriate if business revenue is only $100,000,000 per year of business.
		Large reusable launch vehicles -- such as the SSTO and reusable two-stage vehicles with large payloads -- are probably incapable of achieving a proper return on investment until the launch market is greatly expanded by a smaller reusable launch vehicle with much lower pre-operational investment costs.
	www.tour2space.com /archives/economic/19973124.htm (4361 words)

	[No title] (Site not responding. Last check: 2007-11-03)
		SSTO is the sum of squares that is used to compute the variance of Y if no model is fit.
		In regression, the total sum of squares (SSTO) is partitioned into SS due to model (SSR) and SS due to error (SSE).
		SSTO = Y'Y - (1/n)Y'JY SSR = b'X'Y - (1/n)Y'JY SSE = (Y-Xb)'(Y-Xb) SSTO = SSR + SSE (1/n)Y'JY is the correction term.
	www.stat.ncsu.edu /~st512_info/lab02/anova.htm (177 words)

	The Millennium Express
		SSTO recurring operational costs might only be about $5 million per flight.
		And these would drop even more at higher traffic levels in accordance with a "learning curve." However, at traffic levels of perhaps 25 flights per year, the ROI part of the price would have to be about $72 million per flight.
		The SSTO is not economically attractive during this transition period.
	www.tour2space.com /archives/millexpr/millexpr.htm (1898 words)

	SPACE-TALK - SSTO (Site not responding. Last check: 2007-11-03)
		SSTO's bear a critical limitation: they must, using the most powerful chemical fuel available, have a fuel fraction of 90% of their weight.
		I was initially going to voice my belief about the SSTO concepts having that lack of capacity, but now that I think about it, the only reason one would need a staged rocket for heavy launches to orbit is because the materials used for the construction of the rocket itself.
		If we wish to use high-grade, fairly cheap (by comparison) steel, we will need a staged rocket, and to tell the truth, it wouldn't be that much harder to have these stages themselves be reusable, and might help in servicing and speed of re-launch.
	www.space-talk.com /ForumE/showthread.php3?threadid=2218 (1114 words)

	The SSX Concept
		SSTO is "Single Stage to Orbit." LOX is Liquid Oxygen, which is a cryogenic fuel.
		However, SSTO will work without aerospike, and while the original SSX concept employed aerospike in the proposed design, it was not considered essential to the SSX concept.
		We believe that SSX is possible; that an SSTO ship could be built and flown in fewer than four years and for less than a billion dollars.
	www.jerrypournelle.com /slowchange/SSX.html (6984 words)

	what's a spaceplane? (Site not responding. Last check: 2007-11-03)
		SSTO’s would take off and land in one piece, unlike current rockets which have been called disintegrating totem poles.
		In an SSTO, a very light structure has to carry a lot of propellant.
		An SSTO is like a plane that could fly once around the world without refuelling.
	www.users.waitrose.com /~spaceplanes/htm/whatsasp.htm (267 words)

	[No title] (Site not responding. Last check: 2007-11-03)
		In order to develop SSTO several technical factors need to be overcome, namely low weight structures and high performance and reliable engines that can be used many times before having to be refurbished.
		Other parts of the SSTO are proportional to m_p, such as the engine mass (since the required lift-off thrust is proportional to the launch mass which is mostly propellant).
		The McDonnell Douglas Delta Clipper SSTO [3] is specified to have a cross-range ability of 2575 km, which is within the required cross-range for a NEO trajectory, indicating that this is possible.
	www.sworld.com.au /steven/space/ssto.txt (3003 words)

	SSTO (Single Stage To Orbit) (Dani Eder; Henry Spencer)
		The big problem with the SSTO designs of the past was that they tended to have rather limited mass margins, and this correctly made people nervous.
		Part of the reason why SSTO is now being taken seriously is a steady stream of studies showing that realistic mass margins are now feasible.
		So an SSTO with a life of 100 flights would have to be designed 20% heavier than a 1 use structure (like the Saturn third stage).
	yarchive.net /space/launchers/ssto.html (8062 words)

	ACCESS TO SPACE
		In fact, we had the very people who produced the arguments against SSTO that kept it in limbo for so very long, and who had figured out what was flawed in their original thinking.
		And Henry Vanderbilt on SSTO and unexamined assumptions:
		Jerry, I can appreciate the irritation you must feel over your anonymous mainstream aerospace correspondent; he is to a considerable extent a prisoner of unexamined assumptions, and he seems to be taking you (us) to task for failing to treat these assumptions as laws of physics.
	www.jerrypournelle.com /topics/gettospace.html (6806 words)

	Mass fraction -- Facts, Info, and Encyclopedia article (Site not responding. Last check: 2007-11-03)
		A lower mass fraction for the rocket means that it uses fuel efficiently, reserving a larger portion of its mass as payload.
		Without the benefit of staging, SSTO designs are typically designed for mass fractions around 0.9.
		Staging increases the mass fraction, which is one of the reasons SSTO's appear difficult to build.
	www.absoluteastronomy.com /encyclopedia/m/ma/mass_fraction.htm (371 words)

	NASM Talk
		Although the SDIO SSTO Program easily fit into the Reagan space policy (technologically like the reusable single-stage-to-orbit NASP and politically as a launcher of SDI payloads), the idea for the program began not within the SDIO nor any other government agency, but within what we might call the space movement.
		With the Phase II Statement of Work, the SSTO Program clearly was disengaging itself from Brilliant Pebbles and the SDI's Cold War programs and was seeking a niche outside missile defense.
		Unfortunately for the SSTO Program, the end of the Cold War was not the only political change it had to deal with.
	www.hq.nasa.gov /office/pao/History/x-33/nasm.htm (5556 words)

	Glossary of Terms - SSTO
		History of the Phoenix VTOL SSTO and recent developments in single-stage-to-orbit launch systems
		The Road from Delta Clipper Experimental to Operational SSTO
		Why SSTO rocket launch vehicles are now feasible and practical
	www.spacefuture.com /cgi/glossary.cgi?gl=term&term=SSTO (472 words)

	Fact Sheet #5
		The funding difficulty was the same faced by all defense and space programs that year: a shrinking federal budget forced programs to fight among themselves for a slice of a smaller and smaller budgetary pie.
		In order for the SSTO, or any other launch system, to be funded, it had to have a mission geared to the needs of an existing institution, such as NASA or the Air Force.
		Characterizing the SSTO vehicle as fulfilling military, civil, and commercial missions was not the answer, although it was the truth.
	www.hq.nasa.gov /office/pao/History/x-33/facts_5.htm (3474 words)

	CTIO to Offer Synoptic/Observing on 0.9-m Telescope
		The SSTO observations will be scheduled and performed in service mode by the SSTO scientist and/or by qualified CTIO 0.9-m telescope operators.
		SSTO observations will be made using the normal CTIO 0.9-m telescope CCD camera (see CTIO web page at http://www.ctio.noao.edu for details) and only standard BVRI filters.
		SSTO proposers should be prepared to provide in their proposals specific information in addition to the standard proposal instructions.
	www.noao.edu /noao/noaonews/sep99/node24.html (765 words)

	Hyperion SSTO
		Hyperion would be travelling at 1100km/h as it left the sled at the end of the 3km launch rail.
		Unlike other Douglas SSTO concepts, Hyperion was fully reusable so it would have been ideally suited for flights from inland sites since no fuel tanks would be dropped during flight.
		The booster sled would literally have provided a "flying start" which greatly reduced the SSTO dry mass.
	www.astronautix.com /lvs/hypnssto.htm (551 words)

	Single-Stage-to-Orbit Vehicles
		Since the dry mass of an SSTO vehicle must be kept low, it requires the use of high-tech materials and technologies.
		Using SSME performance, the mass fraction of an SSTO would have to be about 0.87, which means the structure and payload of the vehicle is 13% of the total weight of the fueled vehicle (Bekey 33).
		Once it is seen that SSTOs provide a faster and cheaper method of launch, the government and large aerospace companies may jump on the bandwagon and develop even more SSTO vehicles.
	vorlon.cwru.edu /~jam64/work/ssto.htm (3232 words)

	TWENTY QUESTIONS ABOUT SSTO
		The goal of the SSTO program is to build a new spaceship that will take off straight up, fly to orbit without dropping anything off, & that will then land on its tail on a pillar of fire, not gliding but under power, much like the rocketships of 1950s science fiction movies.
		The total cost of developing the first SSTO orbital demonstration vehicle will be about the same as the development cost of a new commercial airliner such as the Boeing 777.
		In fact, the operational SSTO vehicles that are to be derived from the orbital demonstrator will be certified by the U.S. Department of Transportation's Office of Commercial Space Transportation.
	www.hvcn.org /info/a2s2/20questions.html (1674 words)

	Alternate SSTO Propellants
		The usefulness of alternate propellants for SSTO vehicles is explored.
		The most commonly proposed propellant combination for an SSTO launcher is liquid oxygen and liquid hydrogen, at a mixture ratio of approximately 6.0.
		SSTOs use an Isp of 90% of the theoretical shifting equilibrium Isp (this is a surrogate for the losses induced by less than 100% efficient engines, and for losses for atmospheric operations)
	www.dunnspace.com /alternate_ssto_propellants.htm (1705 words)

	Shuttle II
		The SSTO core configuration was designed to satisfy the baseline space station mission (20 Klb).
		The augmentation approach used in the Shuttle II studies is not unlike the Ariane 4 expendable launch vehicle which can be launched without boosters or, for heavier payloads, can use 2 or 4 solid and/or liquid boosters, thus tailoring the launch system to meet the payload delivery requirements.
		A brief look was made of the "Bimese" configuration, which essentially mated two nearly identical SSTO vehicles with one of the SSTO vehicles acting as a booster for the orbiter stage.
	www.aerospaceguide.net /ShuttleII.html (2012 words)

	[No title]
		(SSTO payload fractions are necessarily quite small, making them quite vulnerable to weight growth.) What they should have done, of course, was to start experimenting with SSTO while using a more conservative approach to their "production" system.
		SSTO development is risky -- any serious weight growth and you're in trouble -- but there is nothing terribly envelope-pushing about it.
		SSTO is taking a calculated risk in hopes of producing a far less clumsy final system.
	www.cs.cmu.edu /afs/cs.cmu.edu/usr/mnr/st/std103 (3107 words)

	Hydrogen delta-V (Henry Spencer; Mitchell Burnside Clapp)
		Consider two SSTOs, one LOX/LH2 and one H2O2/kerosene (I like LOX/propane myself, but H2O2/kerosene is Mitch's favorite, and it's his discovery...), with the same GLOM (gross liftoff mass), the same engine thrust (and so same initial acceleration), and no requirement for G-limiting.
		The H2O2/kerosene SSTO is accelerating faster, so it has lower gravity losses, and needs less total delta-V. Moreover, that makes its burn time still shorter, and its mass line still steeper, so the difference in acceleration is even larger than it first seems.
		From: Henry Spencer Newsgroups: sci.space.tech Subject: Re: SSTO delta-V and dense fuels Date: Mon, 13 May 1996 18:49:37 GMT In article <4mdvso$6nl@lll-winken.llnl.gov> Jordin Kare writes: >>The incorrect assumption is that the total delta-V to reach orbit is the >>same for all fuels.
	yarchive.net /space/rocket/fuels/hydrogen_deltav.html (3315 words)

	Document 7 - Gedanken-Experiment
		For SSTO options it can be assumed the one time development and production of one or more vehicles is not accompanied by a constant yearly production of entirely new vehicles.
		Initial SSTO Tripropellant levels can reasonably be assumed to be as high given the combination of uncertainties with a tripropellant approach which is currently a paper engine (high programmatic risk) and the lack of benefit (toward enabling the goal of drastically reducing the cost of access to space) inherent in the design.
		In turn, the sideline development effort is replaced (evolved) into the only major remaining part of the government enterprise, to develop new space vehicles and technologies - not to operate them, but in effect to build another even better version than that which sets off this chain of events.
	science.ksc.nasa.gov /shuttle/nexgen/rlvhp7a.htm (2472 words)

	Air-Breathing Launch Vehicle Technology
		Effect of aeropropulsion efficiency on the SSTO dry weight fraction for a 220-nmi flight from a 28.5° easterly launch into a circular orbit (RBCC, rocket-based combined cycle).
		SSTO rockets such as the VentureStar (ref. 2) concept are limited to the lower I* range and rely on advancements in structural and material technologies that were to be provided by NASA's recently terminated X-33 (ref. 3) program.
		The optimum I* for a reusable SSTO vehicle may be between these two extremes.
	www.lerc.nasa.gov /WWW/RT2002/5000/5880trefny.html (723 words)

	Student Travel (Site not responding. Last check: 2007-11-03)
		Students may also visit the SSTO in person to have their requests input directly into Travel Manager (TM software), if appropriate.
		After completion of travel, a completed Travel Voucher Form, DD1351-2, needs to be filled out and submitted to the SSTO in person, along with copies of lodging receipts and all other receipts of $75 or more.
		After the voucher information has been entered into TM by the student traveler or SSTO personnel, the traveler will be required to electronically sign their voucher.
	www.nps.navy.mil /travel/stravel.htm (284 words)

	Economics of Assist-Stage Concepts
		The prices for both the SSTO and the Assisted SSTO assume a ROI of 26 percent is required; current launch vehicles assume investment is a sunk cost or that any additional investment is already factored into the price.
		Unless and until a larger reusable launch vehicle like an SSTO captures about half of the current dollar market as soon as it is ready to operate, then a 26 percent ROI does not appear to be possible.
		Large reusable launch vehicles -- such as the SSTO must be, and as reusable two-stage launch vehicles planned by the government tend to be -- are probably incapable of achieving a proper return on investment until the launch market is greatly expanded by a smaller reusable launch vehicle with much lower pre-operational investment costs.
	www.tour2space.com /archives/economic/19962773.htm (3163 words)

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