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Analysis of the Laser Propelled Lightcraft Vehicle NASA/TMm2000-210240 AIAA-2000-2348 Analysis of the Laser Propelled Lightcraft Vehicle Douglas Feikema Glenn Research Center, Cleveland, Ohio t June 2000 The NASA STI Program Office... in Profile Since its founding, NASA has been dedicated to CONFERENCE PUBLICATION. Collected the advancement of aeronautics and space papers from scientific and technical science. The NASA Scientific and Technical conferences, symposia, seminars, or other Information (STI) Program Office plays a key part meetings sponsored or cosponsored by in helping NASA maintain this important role. NASA. The NASA STI Program Office is operated by SPECIAL PUBLICATION. Scientific, Langley Research Center, the Lead Center for technical, or historical information from NASA's scientific and technical information. 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NASA Access Help Desk NASA Center for AeroSpace Information 7121 Standard Drive Hanover, MD 21076 ,B- NASA/TMm2000-210240 AIAA-2000-2348 Analysis of the Laser Propelled Lightcraft Vehicle Douglas Feikema Glenn Research Center, Cleveland, Ohio Prepared for the 31st Plasmadynamics and Lasers Conference sponsored by the American Institute of Aeronautics and Astronautics Denver, Colorado, June 19-22, 2000 National Aeronautics and Space Administration Glenn Research Center June 2000 Acknowledgments The author gratefully acknowledges the financial support of NASA MSFC and the American Society of Engineering Education (ASEE) under the 1998 and 1999 summer faculty fellowship program. The author also gratefully acknowledges the assistance of Mr. Kevin Buch and Mr. Sandy Kirchendal during the summer of 1999. This report is a formal draft or working paper, intended to solicit comments and ideas from a technical peer group. Available from NASA Center for Aerospace Information National Technical Information Service 7121 Standard Drive 5285 Port Royal Road Hanover, MD 21076 Springfield, VA 22100 Price Code: A03 Price Code: A03 AIAA-2000-2348 ANALYSIS OF THE LASER PROPELLED LIGHTCRAFT VEHICLE Douglas Feikema National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 reduction in the intensity of the laser ignition site on the cowl. However, because of the caustic effect of ray- Advanced propulsion research and technology tracing optics the laser radiation still forms a well- require launch and space flight technologies, which can defined ignition line on the cowl. The blast wave cal- drastically reduce mission costs. Laser propulsion is a culations show reasonable agreement with previously concept in which energy of a thrust producing reaction published calculations and recent detailed CFD mass is supplied via beamed energy from an off-board computations. power source. A variety of laser/beamed energy concepts were theoretically and experimentally investigated since the early 1970's. During the 1980"s the Strategic NOMENCLATURE Defense Initiative (SDI) research lead to the invention of the Laser Lightcraft concept. Based upon the Laser C average plasma velocity Lightcraft concept, the U.S. Air Force and NASA have D* injector diameter jointly set out to develop technologies required for E laser energy deposited launching small payloads into Low Earth Orbit (LEO) h enthalpy for a cost of $1.0M or $1000/lb to $100/lb. The near I laser intensity term objectives are to demonstrate technologies and I9 specific impulse capabilities essential for a future earth to orbit launch L plasma length capability. Laser propulsion offers the advantages c£ M molecular weight both high thrust and good specific impulse, Isp, in P gas pressure excess of 1000 s. Other advantages are the simplicity q heat addition from laser and reliability of the engine because of few moving r blast wave radius parts, simpler propellant feed system, and high specific Ru universal gas constant impulse. Major limitations of this approach are the laser T gas temperature power available, absorption and distortion of the pulsed t time laser beam through the atmosphere, and coupling laser u* sonic gas injection velocity power into thrust throughout the flight envelope. The V blast wave velocity objective of this paper is to assist efforts towards Z gas compressibility factor optimizing the performance of the laser engine. In order to accomplish this goal (1) defocusing of the primary Greek optic was investigated using optical ray tracing and (2), time dependent calculations were conducted of the gas density optically induced blast wave to predict pressure and percentage of laser energy absorbed temperature in the vicinity of the cowl. Defocusing of ratio of specific heats the primary parabolic reflector causes blurting and Subscripts Copyright © 2000 by the American Institute of Aeronautics and CJ Chapman-Jouget Condition Astronautics, Inc. No copyright is asserted in the United States under LSD laser supported detonation Title 17,U.S. Code. The U.S. Government has a royalty-free license o initial or ambient state to exercise all rights under the copyright claimed herein for p laser pulse Governmental Purposes. All other rights are reserved by the REF reference condition copyright owner. 2D two-dimensional NASA/TM--2000-210240 1 American Institute of Aeronautics and Astronautics INTRODUCTION with a first pulse followed by a second pulse, which forms plasma at the surface, and the formation of a laser Advanced propulsion concepts for the 21 s' century supported detonation (LSD) wave. A second approach include the use of beamed energy such as a ground involves focusing the laser intensity into a gas near a based laser to provide thrust to a vehicle propelled by a solid surface in order to break down the gas and induce laser-induced blast wave} '2 Jointly, the U.S. Air Force a detonation wave transferring momentum to the and NASA have set out to develop technologies and surface. Previous research has shown that ablation and concepts required for launching small payloads into pitting of the surfaces occur which can strongly reduce Low Earth Orbit (LEO) for a total cost of $1.5M or the efficiency of the laser absorption process. Raizer L' $1000/lb to $100/lb. This concept is shown (1977) noted for high temperature air where -_ 2 schematically in Fig. 1. Among the technology, options I= 10_MW/cm _,po= 1.3×10 g/cm, and _t = 1.33 available, one potential high pay off approach is using a that VtSD = 133 km/s and T_quilibri,m = 910,000 K• high power pulsed laser as an offboard energy source. 3 These values were in reasonable agreement with Laser propulsion offers the advantages of both high experiment, VLSD = 110 km/s and T = 700,000 K. thrust and theoretically infinite specific impulse, Lp, at Therefore, future advances in pulsed detonation laser altitudes less 20 km during the first stage and high propulsion will require mitigating the adverse effects of thrust and specific impulse in excess of 1000 s during material degradation in the regions of intense laser the second stage above 20 km. Other advantages are the radiation, which induces high plasma temperatures _-'m" simplicity and reliability of the engine because of few the vicinisty of the surface• moving parts, simpler propellant feed system, and high Pirri et al. (1974) reported on experiments specific impulse. Major limitations of this approach are utilizing a solid and a gas propellant. They concluded the laser power available, 4 absorption and distortion of that the best way to achieve a high specific impulse is the pulsed laser beam through the atmosphere, 5 and to add laser energy directly to gas rather than to first .= coupling 2aser power into thrust throughout the flight __aporize
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