
	Where results make sense

Topic: Dual mode propulsion rocket

Related Topics

Spacecraft propulsion

Resistojet rocket

Pulsed plasma thruster

Poodle thruster

Field Emission Electric Propulsion

Tripropellant rocket

Ion thruster

Hall effect thruster

In the News (Wed 23 Dec 09)

Northern Trust

Marvin Harrison

Peter Chernin

Gary Locke

Match Play

Penelope Cruz

Mickey Rourke

AR Rahman

Danny Boyle

Hugh Jackman

	Spacecraft propulsion - Engineering - A Wikia wiki
		Spacecraft propulsion is used to change the velocity of spacecraft and artificial satellites, or in short, to provide delta-v.
		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.
		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.
	engineering.wikia.com /wiki/Spacecraft_propulsion (3270 words)

	ipedia.com: Spacecraft propulsion Article (Site not responding. Last check: 2007-10-13)
		can be calculated using the rocket equation, where M is the mass of fuel, P is the mass of the payload (including the rocket structure), and is the specific impulse of the rocket.
		Propulsion methods can be classified based on their means of accelerating the reaction mass.
		Rockets emitting gases are limited by the fact that their exhaust temperature cannot be so high that the nozzle and reaction chamber are damaged; most large rockets have elaborate cooling systems to prevent damage to either component.
	www.ipedia.com /spacecraft_propulsion_1.html (2670 words)

	PowerPedia:Spacecraft propulsion - PESWiki
		A rocket engine is a reaction engine that can be used for spacecraft propulsion as well as terrestrial uses, such as missiles.
		Rocket engines take their reaction mass from one or more tanks and form it into a 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.
	peswiki.com /index.php/PowerPedia:Spacecraft_propulsion (4054 words)

	Rocket Tutorial from ATI Space and Defense Technical Training Courses (Site not responding. Last check: 2007-10-13)
		A satellite is launched into space on a rocket, and once there it is inserted into the operational orbit and is maintained in that orbit by means of thrusters onboard the satellite itself.
		The center of mass of the total system, subsequently consisting of the particles remaining in the rocket and the particles in the exhaust, follows a trajectory determined by the external forces, such as gravity, that is the same as if the original particles remained together as a single entity.
		Although gravity has nothing whatever to do with the rocket propulsion chemistry, it has entered into the definition of specific impulse because in past engineering practice mass was expressed in terms of the corresponding weight on the surface of the earth.
	www.aticourses.com /news/rocket_tutorial.htm (3806 words)

	Scramjets integrate air and space - The Industrial Physicist
		The rocket sent the experimental aircraft soaring to its test altitude of 95,000 ft, where the X-43A separated from its booster, and its scramjet engine fired for a planned 10-s test, achieving an incredible Mach 7, or 5,000 mph.
		The propulsion system consists of five major engine and two vehicle components: the internal inlet, isolator, combustor, internal nozzle, and fuel supply subsystem, and the craft’s forebody, essential for air induction, and aftbody, which is a critical part of the nozzle component.
		Propulsion efficiency decreases with speed as we progress through turbojets to ramjets and scramjets to rockets; hydrogen is more efficient than jet fuel.
	www.aip.org /tip/INPHFA/vol-10/iss-4/p24.html (2173 words)

	Multi-mode pulsed detonation propulsion system - Patent 6857261
		In one embodiment, the propulsion system of the present invention has an ejector-augmented pulsed detonation rocket propulsion mode, a pulsed normal detonation wave engine mode, a steady oblique detonation wave engine mode, and a pure pulsed detonation rocket mode.
		The method of claim 10 wherein the fourth propulsion mode is a pulsed detonation rocket mode.
		The propulsion system is somewhat similar to the conventional scramjet propulsion system, but uses unsteady detonation waves to increase pressure levels beyond that attainable in scramjet engines that employ deflagration burning.
	www.freepatentsonline.com /6857261.html (6721 words)

	Rocket Thrust Equation and Launch Vehicles (Site not responding. Last check: 2007-10-13)
		The configuration of a chemical rocket engine consists of the combustion chamber, where the chemical reaction takes place, and the nozzle, where the gases expand to create the exhaust.
		As the altitude of the rocket increases along its trajectory, the surrounding atmospheric pressure decreases and the thrust increases because of the increase in pressure thrust.
		By the rocket equation, assuming a specific impulse of 300 seconds, the fraction of the separated mass consumed by the propellant for the apogee maneuver is 46 percent from Cape Canaveral, 40 percent from Kourou, and 39 percent from the equator.
	www.aticourses.com /rocket_tutorial.htm (3798 words)

	Propulsion Research Center
		The aim of the experiment is to use the rocket as a pilot/fuel injector in a ramjet mode (Mach 4) and as an additional fuel source in a scramjet mode (Mach 6.5).
		The desirable operating conditions of the rocket for this experiment are oxidizer-to-fuel ratios from 2 to 5 and combustion chamber pressure from 250 to 1250 psia.
		For a specific rocket operating condition, an attempt at controlling heat release will be made by altering the rocket film coolant, the auxiliary fuel injector location, and the combustor inlet pressure. Previous tests at Aerojet were run with 40% of the total fuel flow being film coolant.
	prc.uah.edu /current_projects/strutjet.html (562 words)

	"One Step Back, One Giant Leap Forward," Feature Article, May 2006
		For a dual rendezvous mission, the EDS performs only the Earth departure burn, and capture into lunar orbit is assigned to the lunar lander.
		In the case of rocket propulsion, however, this term lies in the exponent of the all-hallowed rocket equation, so a doubling of Isp yields a large downward change in the mass of propellant.
		Both the LOR Apollo-style mission mode and EOR-LOR dual rendezvous require approximately the same number of new developments, launches, and mission operations, so the life-cycle cost of the two were approximately equal.
	www.memagazine.org /contents/current/features/onestep/onestep.html (2963 words)

	SPACE.com -- Redesigned Heavy-Lift Ariane 5 Rocket Launched
		The Ariane 5 ECA rocket was transported to its launch pad in the jungles of northeastern South America this morning.
		The rocket's main stage and upper stage will be loaded with super-cold liquid hydrogen and liquid oxygen propellants during the final hours of the count.
		The rocket was unable to control its trajectory as it passed the three-minute point in the climb to space.
	www.space.com /missionlaunches/ariane5_xtar_countdown.html (3230 words)

	ScienceDaily: Air-Breathing Rocket Engine Technology Achieves Testing Milestone
		Rocket engine -- A rocket engine is a reaction engine that can be used for spacecraft propulsion as well as terrestrial uses, such as missiles.
		Solid-fuel rocket -- A solid rocket or a solid fuel rocket is a rocket with a motor that uses solid propellants (fuel/oxidizer).
		Rocket -- The traditional definition of a rocket is a vehicle, missile or aircraft which obtains thrust by the reaction to the ejection of fast moving fluid from within a rocket engine.
	www.sciencedaily.com /releases/2000/05/000531174215.htm (1615 words)

	High-Performance, Inexpensive, Clean Spacecraft Electrolysis Propulsion
		A further advantage of the water rocket is its dual-mode potential.
		In a cooperative NASA Lewis Research Center, Hamilton Standard, and Lawrence Livermore National Laboratory effort, an electrolysis propulsion testbed was assembled.
		Parameters recorded during testing were the electrolysis unit supply current and voltage, and temperatures and pressures inside the electrolysis unit, near the storage tanks, and in the 1.1-N thruster.
	www.grc.nasa.gov /WWW/RT1997/5000/5430degroot.htm (561 words)

	Aerospaceweb.org \| Hypersonic Waveriders - Vehicle Applications
		A small rocket system would provide the final push into orbit, but the attractiveness of the concept was using the atmosphere to provide most of the fuel needed to get into space.
		The RBCC engine is a new technology using a rocket engine fed by oxygen from the atmosphere rather than carried aboard the vehicle.
		The missile bears some resemblance to the X-43 since the propulsion system in mounted underneath the body and utilizes the forebody as a compression ramp.
	www.aerospaceweb.org /design/waverider/examples.shtml (1643 words)

	PRATT & WHITNEY THERMAL NUCLEAR ROCKET ENTRY: TRITON
		It uses a dual turbopump arrangement driven by an expander cycle using LH2 and a gas generator add-on to drive the LANTR (LOX Augmented Nuclear Thermal Rocket) When the TRITON is operating in electrical power mode, the reactor operating at less than 1% maximum thermal capability.
		A typical nuclear rocket would have a radioactive inventory that was about at 1 part in 106 of what a standard commercial reactor would have at the end of its life.
		In the propulsion mode is where your statement is applicable for describing running at higher exit temperatures for the higher fuel surface temperatures.
	www.nuclearspace.com /A_PWrussview_FINX.htm (8662 words)

	Inertial Electrostatic Confinement Reactor based Fusion Ash Impact Propulsion System
		The ratio of acceleration of the FAIP rocket to the LSG is 0.2547 and this implies that a spiral propulsion system must be used for the early stages of the trip.
		Although this propulsion technique does not allow direct launching of the spaceship from earth it is suitable for propulsion beyond the earth’s gravitational field.
		This new propulsion technique does not employ magnetic fields and is hence light in weight, as a result of which smaller chemical rockets are required to launch these systems.
	fti.neep.wisc.edu /iec/murali1.htm (4393 words)

	AIM-7 Sparrow
		Propulsion for the missile is provided by a solid propellant rocket motor.
		The rocket motor assembly consists of three major subassemblies: a case with propellant grain, a safe-arm ignition assembly and a nozzle weather seal at the rear.
		These rocket motor assemblies are used with the air-launched missiles (AIM-7M/P) and include a safe-arm ignition assembly with an Arm-Fire Device (AFD) relock assembly.
	www.fas.org /man/dod-101/sys/missile/aim-7.htm (2228 words)

	SEI TECHNICAL CONCEPTS - Nuclear Thermal Propulsion
		The choice of these options results from a balance of various figures of merit, and may result in a sequence of missions in which the first Mars mission could be slower and less risky, with later Mars missions having shorter trip times, building on earlier experience and infrastructure.
		One of the primary innovations is the use of an extendible rocket nozzle skirt, to significantly increase the nozzle expansion ratio.
		The growing interest in dual mode nuclear propulsion concepts (in which the reactor is initially operated for thermal propulsion for injection into and braking from trans-Mars and trans-Earth trajectories, then operates at lower power to produce electrical power following injection and prior to capture) increases the relevance of Sandia's work.
	www.fas.org /nuke/space/c07sei_2.htm (8015 words)

	M85 dual-purpose bomblet
		The fuze should allow for a delay after dispersal from the rocket or projectile to permit operation of the primary function upon target engagement.
		When used in rockets the fuze's primary function mode must have a reliability of at least 96% and the combined primary and self destruct function reliability must result in a hazardous dud rate of less than 1%.
		When used in artillery the primary function mode must have a reliability of at least 97% and the combined primary and self-destruct function reliability must result in a hazardous dud rate of less than 1 dud in 500 or 0.2% Fuzing concepts may be pyrotechnic, mechanical, electrical, etc, or a combination thereof.
	www.globalsecurity.org /military/systems/munitions/m85.htm (821 words)

	All Hands - January 2001 - Naval Weapons
		A service life extension program was initiated in 1992 to extend the life of the MK 46 Mod 5A(S), convert it to the MK 46 Mod 5A(SW), and to provide additional shallow water and bottom avoidance modes.
		The stored chemical energy propulsion system develops full power at all depths and is capable of multi-speed operations required by the tactical situation.
		Also a new longer-lasting, safer and cheaper stored chemical energy propulsion system is currently being introduced.
	www.mediacen.navy.mil /pubs/allhands/jan01/weapons.htm (1650 words)

	Space Dynamics Laboratory / Programs
		A NASA/LaRC sounding rocket program, the main instruments provided by SDL included a 9.6 µm CVF spectrometer, a 2-channel near-IR WIRR, and an atomic oxygen resonance-fluorescence/absorption experiment.
		A tether-based propulsion experiment that dissipates power to the space environment around the Earth, allowing the transfer of spacecraft orbital kinetic energy to heat.
		SAL's mission was to investigate the phenomenon of sporadic sodium layers (NaS), thin (1 km) layers of neutral atomic metal which form in the Earth's mesosphere at altitudes near 95 km.
	www.sdl.usu.edu /programs/past (814 words)

	RIM-161 SM-3 (AEGIS Ballistic Missile Defense)
		SM-3 uses the same booster and dual thrust rocket motor as the Block IV missile for the first and second stages and the same steering control section and midcourse missile guidance for maneuvering in the atmosphere.
		To support the extended range of an exo-atmospheric intercept, additional missile thrust is provided in a new third stage for the SM-3 missile, containing a dual pulse rocket motor for the early exo-atmospheric phase of flight and a Lightweight Exo-Atmospheric Projectile (LEAP) Kinetic Warhead (KW) for the intercept phase.
		On 17 November 2005 a test involved for the first time a "separating" target, meaning that the target warhead separated from its booster rocket requiring the interceptor to distinguish between the body of the missile and the actual warhead.
	www.globalsecurity.org /space/systems/sm3.htm (2532 words)

	ZM-D11S Abigor
		BESPA's first transformable mobile suit/mobile armor, the "dual type" ZM-D11S Abigor was developed and deployed in the early days of the Zanscare War in UC 0153.
		The Abigor also carried a pair of beam blade-generating "beam katarls", as well as a large number of beam net generators, which could be deployed to create an entangling energy web over a large area.
		In mobile armor mode, the Abigor made good use of this three beam cutter weapons, which could be used at high speed to slice through enemy targets; the beam cutter blade on its back could also fire its beam energy at a target like a normal ranged weapon.
	www.mahq.net /mecha/gundam/v/zm-d11s.htm (289 words)

	[No title]
		Since the Delta 2 rocket does not have the power to boost NEAR directly to Eros, NEAR will instead have to follow a looping path to Eros by way of an Earth flyby and gravity assist.
		NEAR also has a dual mode propulsion system with a large fuel capacity that gives the spacecraft a great deal of mobility.
		NEAR is expected to provide a wealth of information on asteroids, including their role in the evolution of the solar system as well as their role in the development of life on Earth.
	www.seds.org /nodes/NODEv5n4-4.html (992 words)

	gizmag Article: Star Wars-style Pod Racing comes to life - the Rocket Racing League blasts off
		The Rocket Racing League has entered into a design and engineering partnership with XCOR Aerospace and Velocity Aircraft to build the first generation of X-Racers.
		Granger Whitelaw, two-time Indianapolis 500 champion team partner, the league's mission is to serve as a technology accelerator in the areas of airframe, propulsion and spacecraft design, and reach for the future to inspire the next generation of spaceflight enthusiasts.
		The league also plans to produce nationwide tours of its rocket planes and pilots to answer the public's demand for high-excitement entertainment.
	www.gizmag.com /go/4783 (892 words)

	ESA - Careers at ESA - Areas of research
		rocket exhaust plume analyses; plume flow-field characteristics; plume impingement effects
		derivation and thermodynamic performance analysis of advanced rocket engine cycles for future launchers: influence of combustion pressure, variable mixture ratio, external expansion nozzles, advanced materials, dual fuel engines, tripropellant engines
		analysis of the installed propulsive performance of air-breathing engines in reusable launchers: force accounting and balance for thrust, drag, lift and vehicle weight
	www.esa.int /SPECIALS/Careers_at_ESA/SEMAOTXO4HD_0.html (928 words)

	AIM-152 AAAM
		The projected AAAM (Advanced Air-to-Air Missile) was to be significantly smaller and lighter than the Phoenix, but was to have a longer range and a speed of at least Mach 3.
		Some key technologies for these goals (like integral rocket/ramjet propulsion and multimode (radar/IR) guidance) had been evaluated by the U.S. Naval Weapons Center (NWC) at China Lake during 1983 in the ACIMD (Advanced Common Intercept Missile Demonstration) program.
		It was designed to use an inertial mid-course guidance with command updates (similar to the AIM-120 AMRAAM), and a dual-mode (active-radar/infrared) seeker for terminal homing.
	www.designation-systems.net /dusrm/m-152.html (410 words)

	[No title]
		Review of advanced propulsion needs, dual mode ramjet/scramjet, pulsed detonation engines, magnetic launch assist, nuclear propulsion, electric and solar driven electric propulsion, rocket and turbine based combined cycles, advanced propellants.
		Presented in conjunction with the 40th AIAA Aerospace Science Meeting & Exhibit, 13 January 2002.
		Journal of Propulsion and Power--Online and Print - Journals and Magazines, Mixed media
	www.aiaa.org /store/storeproductdetail.cfm?ID=1033 (185 words)

Try your search on: Qwika (all wikis)