Rocket

About: Rocket is a research topic. Over the lifetime, 14018 publications have been published within this topic receiving 95852 citations. The topic is also known as: rockets.

Experimental Study of Major Species and Temperature Profiles of Liquid Oxygen/Gaseous Hydrogen Rocket Combustion

Abstract: Understanding thefundamentalsofhigh-pressure, high-temperaturecombustion of practical rocketpropellants is key to improving rocket engine performance and efe ciency. The application of Raman spectroscopy for making detailed species concentration measurements of oxygen, hydrogen, and water vapor in the elevated-pressure, combusting e owe eld downstream of a liquid-oxygen/gaseous-hydrogen swirl-coaxial injector element at fuel-rich conditionsispresented.Detailsregardingmeasurementerroranalysisandrecommendationsforfurtherree nement ofthediagnostictechniquearealsopresented.To theauthors’ knowledge,theseexperimentsrepresentthee rsttime that instantaneous temperature and major species proe les have been successfully made in such an environment. Theseresults,whichincludebothinstantaneousand time-averagedtemperatureand speciesconcentrationproe les, impact both rocket fuel preburner design and computational e uid dynamic code validation activities. Nomenclature f .T/ = temperature dependent function that relates the spectral bandwidth strength to the signal strength = focal length =# = focal length divided by the diameter of the lens K = constant that accounts for the laser pulse energy, species Raman cross section, optical collection efe ciency, and optical solid angle N = measurement uncertainty n = number density S = Raman signal intensity aeB = background shot noise due to e ame luminosity aeD = dark current noise of the intensie er aeR = Readout noise aeS = signal shot noise due to Raman signal

Twenty-Five Years of Ramjet Development

Abstract: T ramjet engine is the youngest of the family of jet propulsion devices that includes the squid, the rocket, the turbojet, and the pulsejet. Because the ramjet depends on its forward motion to achieve compression of the intake air, the engine itself employs no moving parts and is therefore capable of a simplicity and lightness of construction not possible in other air-breathing engines. This, plus the high thermal efficiency it can achieve, makes the ramjet a favored choice for propulsion of aircraft at supersonic speeds. In the present article the history of ramjet development is briefly reviewed. This is followed by a summary of the design principles of ramjet engines. In the final section performance data for ramjets are compared with data for other jet engines.

Aerospace vehicle having multiple propulsion systems on a relatively rotatable flying wing

Abstract: An aerospace vehicle having multiple propulsion systems on a relatively rotatable flying wing capable of takeoff and subsequent landing with intermediate space flight in the manner of a conventional aircraft and rocket, respectively, comprising an elongated wing member having internal passenger and crew, cargo and fuel storage compartments. A plurality of propulsion systems are distributed about the wing member for providing thrust and aerodynamic control. The vehicle also includes rotating means for controlling the direction of the thrust of the propulsion systems relative to the longitudinal axis of the wing whereby to rotate the wing member relative to the direction of flight. The vehicle takes off and lands with the longitudinal wing axis being transverse to the direction of thrust and therefore to the flight direction in a manner similar to that of conventional aircraft. In flight as the vehicle approaches space, the rotating means rotates the longitudinal wing axis into alignment with the direction of thrust of the plurality of propulsion systems and therefore to the direction of flight for suborbital, orbital and space flight in the manner similar to that of conventional rockets.

Generic Magnetic Fusion Rocket Model

Abstract: A generic magnetic fusion rocket model is developed and used to explore the limits of fusion propulsion systems. Two fusion fuels are examined, D-T and D-(He-3), and the D-(He-3) fuel cycle is found to give a higher specific power in almost all parameter regimes. The key findings are that (1) magnetic fusion should ultimately be able to deliver specific powers of about 10 kW/kg and (2) specific powers of 15 kW/kg could be achieved with only modest extrapolations of present technology. 9 refs.