Download or read book An Analytical Method for Determining the Multi layer Thickness and Regression Rates for a Hybrid Or Tribrid Rocket Motor written by Walter Brooks Drew and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Monthly Catalogue United States Public Documents written by and published by . This book was released on 1970 with total page 1730 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Cumulative Title Index to United States Public Documents 1789 1976 written by Sandra K. Faull and published by Arlington, Va. : United States Historical Documents Institute. This book was released on 1979 with total page 608 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Instantaneous Regression Rate Determination of a Cylindrical X ray Transparent Hybrid Rocket Motor written by Brian Evans and published by . This book was released on 2003 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Enhancement of Regression Rate in Hybrid Rocket Motor Using Various Techniques written by Muhammad Hanafi Azami and published by . This book was released on 2014 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt: A hybrid rocket motor represents a compromise between a solid rocket and a liquid rocket motor. It offers throttling capability, increased safety, moderate cost, in addition to its benign environmental impact. However, low regression rate is a major drawback of hybrid rocket performance. In this work, a design and simulation codes are developed to size the rocket, analyze its performance both in steady state and transience. The codes are based on a legacy interior ballistic model and developed using MATLAB® environment. The codes were also used to analyze the temporal variation of regression rate, specific impulse and thrust with different initial design features; different nozzle expansion ratios, different initial mass fluxes, different number of ports used, different type of propellants used, different ports designs and different metallic doping. These design parameters bring a significant effect on hybrid rocket size and performance especially the regression rate. We also develop a lab scale hybrid rocket motor testing facility to study the effect of doping metallic additives. In the test runs, paraffin wax is used as a fuel and gaseous oxygen as the oxidizer. Experimental results reveal that varying the distribution and concentration of metallic additive concentration can improve the regression rate up to 22%. However, the non-homogeneous fuel does not improve the uniformity of the burning fuel but at least it has 70% improve on the regression rate using aluminum powder and 170% increase using zirconium powder. The code shows reasonable consistency with the experimental results.
Download or read book Comparison of Four Boundary Layer Solutions for Fuel Regression Rate in Classical Hybrid Rocket Motors written by Mark Salita and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analytical study of hybrid rocket combustion written by Wilfred Suen Ying Hung and published by . This book was released on 1972 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Further analytical study of hybrid rocket combustion written by Wilfred Suen Ying Hung and published by . This book was released on 1972 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Fundamental Phenomena on Fuel Decomposition and Boundary Layer Combustion Processes with Applications to Hybrid Rocket Motors written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-03 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: The experimental study on the fundamental processes involved in fuel decomposition and boundary-layer combustion in hybrid rocket motors is continuously being conducted at the High Pressure Combustion Laboratory of The Pennsylvania State University. This research will provide a useful engineering technology base in the development of hybrid rocket motors as well as a fundamental understanding of the complex processes involved in hybrid propulsion. A high-pressure, 2-D slab motor has been designed, manufactured, and utilized for conducting seven test firings using HTPB fuel processed at PSU. A total of 20 fuel slabs have been received from the Mcdonnell Douglas Aerospace Corporation. Ten of these fuel slabs contain an array of fine-wire thermocouples for measuring solid fuel surface and subsurface temperatures. Diagnostic instrumentation used in the test include high-frequency pressure transducers for measuring static and dynamic motor pressures and fine-wire thermocouples for measuring solid fuel surface and subsurface temperatures. The ultrasonic pulse-echo technique as well as a real-time x-ray radiography system have been used to obtain independent measurements of instantaneous solid fuel regression rates. Kuo, Kenneth K. and Lu, Yeu-Cherng and Chiaverini, Martin J. and Harting, George C. and Johnson, David K. and Serin, Nadir Unspecified Center NAS8-39945...
Download or read book Determination of Regression Rate in an Ablating Hybrid Rocket Solid Fuel Using a Physics Based Comprehensive Mathematical Model written by K. M. Akyuzlu and published by . This book was released on 2002 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of a Vortex driven High regression Rate Hybrid Rocket Engine written by William J. Knuth and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hybrid Rocket Motor Scaling Process written by Joseph B. R. Vanherweg and published by . This book was released on 2015 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hybrid rocket propulsion technology shows promise for the next generation of sounding rockets and small launch vehicles. This paper seeks to provide details on the process of developing hybrid propulsion systems to the academic and amateur rocket communities to assist in future research and development. Scaling hybrid rocket motors for use in sounding rockets has been a challenge due to the inadequacies in traditional boundary layer analysis. Similarity scaling is an amendment to traditional boundary layer analysis which is helpful in removing some of the past scaling challenges. Maintaining geometric similarity, oxidizer and fuel similarity and mass flow rate to port diameter similarity are the most important scaling parameters. Advances in composite technologies have also increased the performance through weight reduction of sounding rockets through and launch vehicles. Technologies such as Composite Overwrapped Pressure Vessels (COPV) for use as fuel and oxidizer tanks on rockets promise great advantages in flight performance and manufacturing cost. A small scale COPV, carbon fiber ablative nozzle and a N class hybrid rocket motor were developed, manufactured and tested to support the use of these techniques in future sounding rocket development. The COPV exhibited failure within 5% of the predicted pressure and the scale motor testing was useful in identifying a number of improvements needed for future scaling work. The author learned that small scale testing is an essential step in the process of developing hybrid propulsion systems and that ablative nozzle manufacturing techniques are difficult to develop. This project has primarily provided a framework for others to build upon in the quest for a method to easily develop hybrid propulsion systems sounding rockets and launch vehicles.
Download or read book Fuel Regression Rate Enhancement Studies in HTPB GOX Hybrid Rocket Motors written by Philmon George and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Development and Testing of a Vortex driven High regression Rate Hybrid Rocket Engine written by William H. Knuth and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Characterization of Cryogenic Solid Hybrid Rocket Motors written by Patrick G. Carrick and published by . This book was released on 1995 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: The study of the combustion of cryogenic (77K) solid hydrocarbons in a laboratory scale tube burner that approximates the geometry of the hybrid rocket was extended. This work was carried out to demonstrate the feasibility of cryogenic fuel combustion in the hybrid rocket geometry and to extend knowledge about hybrid rockets to fuels that have very high regression rates as a consequence of their high mass transfer number, or blowing coefficient. Liquid n-pentane was condensed inside a 1-inch diameter tube that was cooled by liquid nitrogen. A mandrel was used to shape a 6-inch long by 1-inch diameter solid fuel grain with a one-half-inch diameter channel along the centerline; the mass of the n-pentane fuel grain was around 35 grams. These fuel samples were ignited with a methane/oxygen microtorch and burned with gaseous oxygen (GOX, up to 25 grams/sec) under conditions of choked flow. Combustion pressure (Pc, up to 250 psia) depends on the throat area of the choke, a converging sonic nozzle. Pc also depends on the fuel, the mass flow rates of fuel and GOX, and the 'oxidation efficiency.' Burn times varied between 1 and 8 seconds. Images of the turbulent reacting boundary layer and burning fuel surface and of the exit plume were recorded with a CCD/video system. Two figures of merit were determined: the instantaneous fuel regression rate (r'(t) cm/sec) and the instantaneous characteristic velocity (c(solid star)(t) cm/sec, the metric of 'combustion efficiency') achieved during combustion. Lower pressure experiments burned with a low oxidizer to fuel mass ratio (O/F around unity) and considerable sooting; these large r' burns were accompanied by low C(solid star) combustion efficiency, as low as 50% of C(solid star)ideal.
Download or read book Progress in Astronautics and Aeronautics written by and published by . This book was released on 1963 with total page 648 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Ignition written by John Drury Clark and published by Rutgers University Press. This book was released on 2018-05-23 with total page 217 pages. Available in PDF, EPUB and Kindle. Book excerpt: This newly reissued debut book in the Rutgers University Press Classics Imprint is the story of the search for a rocket propellant which could be trusted to take man into space. This search was a hazardous enterprise carried out by rival labs who worked against the known laws of nature, with no guarantee of success or safety. Acclaimed scientist and sci-fi author John Drury Clark writes with irreverent and eyewitness immediacy about the development of the explosive fuels strong enough to negate the relentless restraints of gravity. The resulting volume is as much a memoir as a work of history, sharing a behind-the-scenes view of an enterprise which eventually took men to the moon, missiles to the planets, and satellites to outer space. A classic work in the history of science, and described as “a good book on rocket stuff…that’s a really fun one” by SpaceX founder Elon Musk, readers will want to get their hands on this influential classic, available for the first time in decades.
