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Topic: Bipropellant rocket

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	Bipropellant rocket - Wikipedia, the free encyclopedia
		A bipropellant rocket engine is a rocket engine that uses two fluid propellants stored in separate tanks that are injected into, and undergo a strong exothermic reaction, in a rocket's combustion chamber.
		Bipropellant rocket engines are extremely powerful rockets- they can provide the highest specific impulse of all current Earth launchable rocket engines whilst at the same time as providing thrust to weight ratios of 70-100+, and permitting extraordinarily lightweight tankage and vehicle structure.
		The highest ISP bipropellant rocket engine in existence is the hydrogen/oxgen fuelled SSME which gives very high performance; but in terms of overall performance the dense-fuelled NK-33 is comparable due to better mass ratios; inspite of lower specific impulse.
	en.wikipedia.org /wiki/Bipropellant_rocket (1223 words)

	Rocket engine - Wikipedia, the free encyclopedia
		Rocket engines take their reaction mass from one or more tanks and form it into a hypersonic jet, obtaining thrust in accordance with Newton's third law.
		The speed ratio of a rocket nozzle is mostly determined by its area expansion ratio—the ratio of the area of the throat to the area at the exit, but details of the gas properties are also important.
		Rockets emitting plasma can potentially carry out reactions inside a magnetic bottle and release the plasma via a magnetic nozzle, so that no solid matter need come in contact with the plasma.
	en.wikipedia.org /wiki/Rocket_engine (830 words)

	Rocket - Wikigadugi (Site not responding. Last check: 2007-11-07)
		A rocket is a vehicle, missile or aircraft which obtains thrust by the reaction to the ejection of fast moving exhaust gas from within a rocket engine.
		Rockets must be used when there is no other substance (land, water, or air) or force (gravity, magnetism, light) that a vehicle may employ for propulsion, such as in space.
		Rockets became extremely military important in the form of intercontinental ballistic missiles (ICBMs) when it was realised that nuclear weapons carried on a rocket vehicle were essentially not defensible against once launched, and they became the delivery platform of choice for these weapons.
	www.wikigadugi.com /wiki/Rocket (2809 words)

	Pressure feed for liquid propellant - Patent 5823478
		In use, as the pressurized propellant is fed to the rocket motor, the pressure in the tank drops due to expansion of the gas.
		Rocket performance may thus be improved by arranging the propellant supply system to have a low tank pressure at the termination of the rocket burn (even if for performance reasons pressure was high at the beginning of the bum), and/or by heating the pressurizing gas.
		To reduce the pressure (and thus, the gas density and mass at the end of a rocket burn), pressurant gas may be bled from the top of the tank during liquid propellant withdrawal, and used for a variety of purposes.
	www.freepatentsonline.com /5823478.html (4436 words)

	Rocket (Site not responding. Last check: 2007-11-07)
		Rocket thrust is due to the exhaust gases applying pressure on the inside surfaces of the rocket engine as they accelerate (see Newton's 3rd Law of Motion).
		Rockets are also used for deceleration, to transfer to a lower-energy orbit, for example to enter into a circular orbit from outside, to de-orbit for landing, for the whole landing if there is no atmosphere (e.g.
		Modern rockets were born when, after receiving a grant in 1917 from the Smithsonian Institution, Robert Goddard attached a de Laval nozzle to a rocket engine's combustion chamber, doubling the thrust and enormously raising the efficiency, giving the real possibility of practical space travel.
	rocket.ask.dyndns.dk (2169 words)

	NASA Information on Propulsion Systems (Site not responding. Last check: 2007-11-07)
		In other types of rockets no chemical change takes place within the engines but the working fluid may be converted to a hot gas for ejection by the addition of heat from a nuclear reactor or some other energy source.
		The common liquid rocket is bipropellant; it uses two separate propellants, a liquid fuel and liquid oxidizer.
		For example, the rocket motor, and perhaps also the empty propellant tank, of a liquid rocket booster could be returned to earth intact by means of parachutes, gliding wings, lifting jet-engines, or a combination thereof.
	www.godonthe.net /ezekiel/misc-propulsion_systems.html (3320 words)

	Bipropellant rocket: Encyclopedia topic (Site not responding. Last check: 2007-11-07)
		A bipropellant rocket is a rocket (rocket: A jet engine containing its own propellant and driven by reaction propulsion) that uses separate fuel (fuel: A substance that can be consumed to produce energy) and oxidizer (oxidizer: A substance that oxidizes another substance) propellant (propellant: Something that propels) s.
		Bipropellant systems are more efficient than monopropellant systems (monopropellant systems: more facts about this subject), but they tend to be more complicated because of the extra hardware components needed to make sure the right amount of fuel gets mixed with the right amount of oxidizer (this is known as the mixture ratio.)
		Because of this the mixtures of hydrazine (hydrazine: A colorless fuming corrosive liquid; a powerful reducing agent; used chiefly in rocket fuels) and its derivatives in combination with nitrogenoxides are used for these rockets.
	www.absoluteastronomy.com /reference/bipropellant_rocket (1439 words)

	Spacecraft propulsion - ExampleProblems
		All current spacecraft use chemical rocket engines (bipropellant or solid-fuel) for launch, though some (such as the Pegasus rocket and SpaceShipOne) have used air-breathing engines on their first stage.
		Most satellites have simple reliable chemical rockets (often monopropellant rockets) or resistojet rockets to keep their station, although some use momentum wheels for attitude control.
		The speed ratio of a rocket nozzle is mostly determined by its area expansion ratio—the ratio of the area of the throat to the area at the exit.
	exampleproblems.com /wiki/index.php/Spacecraft_propulsion (3205 words)

	Gemini Press Reference Book
		The spent retrograde rockets are jettisoned with the retrograde section of the adapter approximately 45 seconds after rocket firing initiation.
		In the event of an abort before orbital altitude and velocities are achieved, the retrograde rockets may be salvo fired by the flight crew to aid in separation of the spacecraft from the launch vehicle.
		The pyrogenic igniter is a small rocket of short burn duration which fires into the charge of the retrorocket thus igniting it.
	www.apollosaturn.com /geminiNR/sec8.htm (1254 words)

	Dimensionally stable throat insert for rocket thrusters - Patent 5802842
		The rocket thruster of claim 7 wherein the casing of the throat insert means is made of a material selected from the group consisting of silver, gold, and nickel.
		The rocket thruster of claim 7 wherein the shell of the throat insert means is made of a material having nickel, chrome, and cobalt therein.
		In a regeneratively cooled bipropellant rocket motor the thruster is cooled using the latent heat of vaporization of the oxidizer flowing through coolant passages in the wall of the thruster chamber.
	www.freepatentsonline.com /5802842.html (2982 words)

	Project NOVA
		The basic difference between the rocket engine and jet engines is that rocket engines carry not only their fuel, but also their own oxygen or oxidant needed for the burning of the fuel.
		All the rocket engine does through combustion is to provide additional energy to the molecules, increasing the speed at which they move and providing a narrow opening to cause these molecules to escape under pressure.
		In a rocket it is the reaction to the action of the escaping gases that causes the rocket to rise.
	www.uncfsu.edu /msec/nova/timmod9c.htm (785 words)

	Specific impulse - Engineering (Site not responding. Last check: 2007-11-07)
		For a chemical rocket the propellant mass therefore would include both fuel and oxidizer; for air-breathing engines only the mass of the fuel is counted, not the mass of air passing through the engine.
		Nuclear thermal rocket engines differ from conventional rocket engines in that thrust is created strictly through thermodynamic phenomena, with no chemical reaction.
		A rocket must carry all its fuel with it, so the mass of the unburned fuel must be accelerated along with the rocket itself.
	engineering.wikia.com /wiki/Specific_impulse (1900 words)

	Spacecraft propulsion - (Site not responding. Last check: 2007-11-07)
		All current spacecraft use chemical rocket (bipropellant or solid-fuel) for launch, though some (such as the Pegasus rocket and SpaceShipOne) have used air-breathing engines on their first stage.
		The total $\Delta v$ of a vehicle can be calculated using the rocket equation, where M is the mass of fuel (or rather the mass of propellant), P is the mass of the payload (including the rocket structure), $I_{sp}$ is the specific impulse of the rocket, and $g_{o}$ is the gravitational acceleration at sea level.
		Most rocket engines are internal combustion heat engines (although non combusting forms exist).
	psychcentral.com /psypsych/Spacecraft_propulsion (3444 words)

	:::► Dictionary of Meaning www.mauspfeil.net ◄:::
		All current spacecraft use chemical rocket engines (bipropellant rocket bipropellant or solid rocket solid-fuel) for launch, though some (such as the Pegasus rocket and SpaceShipOne) have used air-breathing engines on their Multistage rocket first stage.
		Artificial satellites must be Rocket launch launched into orbit, and once there they must accelerate to circularize their orbit.
		In a conventional solid rocket solid fuel rocket, the fuel is burned, providing the energy, and the reaction products are allowed to flow out the back, providing the reaction mass.
	www.mauspfeil.net /Spacecraft_propulsion.html (3509 words)

	Propellant - One Language (Site not responding. Last check: 2007-11-07)
		A propellant is a gas, liquid or plasma used to move an object by applying a motive force.
		Common propellants are gasoline, jet fuel and rocket fuel.
		In ballistics and pyrotechnics, a propellant is a material which burns very rapidly but controllably, to produce thrust by gas pressure and thus accelerate a projectile or rocket.
	www.onelang.com /encyclopedia/index.php/Propellant (337 words)

	Launch Vehicle Propulsion.
		Rocket engine technologies developed at Ottobrunn have contributed to the success of such programmes as the Ariane launch vehicle family and the US space shuttle.
		The Aestus rocket engine was developed at the Ottobrunn Space Propulsion Centre during the period 1988 - 1995.
		The HM-7 rocket engine feature Ottobrunn's unique regenerative cooling technology whereby hydrogen propellant is efficiently used to cool the combustion chamber before being injected for combustion.
	cs.space.eads.net /sp/LauncherPropulsion/LaunchVehiclePropulsion.html (1475 words)

	TA: Article (Site not responding. Last check: 2007-11-07)
		A new gel bipropellant system that offers safety and controllability and enables the use of environmentally friendly propellants is being tested for military and commercial applications.
		This bipropellant system was funded by MDA with an SBIR Phase I for use in the kinetic energy (KE) interceptor and divert and attitude control systems.
		The bipropellant system also enables energy management--via computer feedback, the flow rate and energy release rate of the propellants are controlled as they enter the rocket engine to burn.
	www.mdatechnology.net /printerpage_article.asp?id=4408 (636 words)

	EADS Ottobrunn - Launch Vehicle Propulsion.
		The Ottobrunn Centre specialises in the design, development and manufacture of rocket engines and thrust chambers for launch vehicles and upper stages using bipropellant and cryogenic propellant.
		Expertise is within the fields of rocket engines ranging from 500 N to 1350 kN thrust.
		The Ottobrunn team designed, developed and produced the rocket engines and thrust chambers that have contributed to the reliability and success of the Ariane launch vehicle since its maiden flight on Christmas eve in 1979.
	cs.space.eads.net /sp/Ottobrunn.html (1039 words)

	[No title] (Site not responding. Last check: 2007-11-07)
		A bipropellant rocket has two separate propellants which are mixed inside the combustion chamber.
		Hence, the rocket motor exhaust gases will be overexpanded from sea-level to around the 5 km altitude mark where the ambient pressure is 0.55 times sea- level (55kPa).
		The rocket, as mentioned in previous sections, is pressure fed. There are 2 gases that have been identified as being applicable to this application; Nitrogen and Helium.
	www.sworld.com.au /steven/space/ausroc/ausroc3/a3motor.txt (2992 words)

	Rocket Propulsion
		The thrust force of a rocket motor is the reaction experienced by the motor structure due to ejection of the high velocity matter.
		The rocket and fuel have a total mass M and the combination is moving with velocity v as seen from a particular frame of reference.
		Liquid bipropellant rocket engines can be categorized according to their power cycles, that is, how power is derived to feed propellants to the main combustion chamber.
	www.braeunig.us /space/propuls.htm (4925 words)

	Bipropellant rocket: Facts and details from Encyclopedia Topic (Site not responding. Last check: 2007-11-07)
		Bipropellant systems are more efficient than monopropellant systems[follow this hyperlink for a summary of this topic], Exception Handler: No article summary found.
		Saturn V (The saturn v (popularly known as the moon rocket) was a multistage liquid-fuel expendable launch systemexpendable...)
		Tripropellant rocket (A tripropellant rocket is a form of spacecraft propulsion that uses two fuels and one oxidizer....)
	www.absoluteastronomy.com /ref/bipropellant_rocket (3409 words)

	History and Development of the Rocket Engine
		solid fuel rocket, the fuel is burned, providing the energy, and the reaction products are allowed to flow out the back, providing the reaction mass.
		Smart 1 more than a year to reach the Moon, while with a chemical rocket it takes a few days.
		The speed ratio of a rocket nozzle is mostly determined by it's area expansion ratio- this is the ratio of the area of the throat to the area at the exit.
	www.edinformatics.com /inventions_inventors/rocket_engine.htm (3031 words)

	The MIT Rocket Team (Site not responding. Last check: 2007-11-07)
		The MIT Rocket Team formed in an effort to become the first student group to launch a rocket into space.
		These tests will be used to improve the rocket design, with the goal of launching a sub-orbital vehicle to a height of 200 kilometers from Wallops Island in 2002.
		The MIT Rocket Team was originally inspired by the Cheap Access To Space (CATS) Prize (which expired in Nov. 2000).
	web.mit.edu /cats/www (423 words)

	Northrop Grumman > NGST > Capabilities > Space Systems > Propulsion Systems > Technologies > Bipropellant (Site not responding. Last check: 2007-11-07)
		We are the only rocket manufacturer that uses pintle injector technology in liquid and gel bipropellant rocket engines.
		The pintle injector also allows us to build rockets that pulse extremely fast (e.g., 2 millisecond pulse at 100 Hz rate) and that can also lock-up the liquid or gel propellants at the injection point so that none dribble out into the chamber during off times.
		Northrop Grumman's bipropellant engine experience includes scaling over 130,000:1 in thrust and 250:1 in chamber pressure, and operations with 25 different propellant combinations.
	www.st.northropgrumman.com /capabilities/space/propulsion/technologies/Article_print_layout_1_15781_15781.html (224 words)

	Nat' Academies Press, Implications of Emerging Micro and Nanotechnology (2002)
		Burn rates for operational rocket propellants are typically between 0.3 and 0.8 inches per second, which would generate unacceptably long burn times (~40 minutes for the 110-foot-long solid rocket motor units (SRMUs) used on the Titan IV booster if the propellant burned from bottom-to-top—like, for instance, a cigarette).
		Large, solid rocket engines have propellant cores cast with convoluted openings to provide radial burning with larger surface areas; this leads to higher gas generation rates and shorter burn times (about 2 minutes for the Titan IV solid boosters).
		Another example of a smaller, less ambitious bipropellant thruster is the “microjet” developed in the United Kingdom at the Defence Establishment Research Agency.
	www.nap.edu /books/030908623X/html/122.html (646 words)

	Guide for the Design of HRST-Number of Engines...
		An engine is defined as: The number of discrete propulsion sets that are individually delivered or installed or that are individually overhauled.
		Note that a requirement for "engine out" capability possibly increases the number of engines for a vertical take-off rocket whereas with horizontal take-off, imposing the same requirement, it is still possible to reduce engine count.
		The number of engines on a vehicle is strongly related to the ease of integration and the maintainability of the propulsion system.
	science.ksc.nasa.gov /shuttle/nexgen/Guide_HRST_Design/gidedf26.htm (369 words)

	UCLA Rocket News (Volume 2, Number 1) (Site not responding. Last check: 2007-11-07)
		As this rocket is being designed, we will also produce a preliminary design for a liquid propellant upper stage to convert the Spartan ABMs into launch vehicles.
		Jim French, a leader in the space and rocket fields for the last 30 years, has become the director of the USRA effort to convert Spartans into launch vehicles.
		David Crisalli, one of the first amateurs since the early days of rocketry to actually build and fly a liquid bipropellant rocket, has offered his experience and some of his facilities for our use.
	www.seas.ucla.edu /aiaa/spg/news/news2.1.html (2086 words)

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