Panel on Science and Technology, Fourth Meeting: Hearings Before the Committee on Science and Astronautics, U.S. House of Representatives, Eighty-seventh Congress, Second Session, March 21 and 22, 1962U.S. Government Printing Office, 1962 - 110 pages |
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accelerator accuracy American arc-jet Astronautics basic believe bipropellant booster boron fuels BROWN CHAIRMAN chemical rocket engines combustion committee cooperation COSPAR Earth electric rocket engines electrons energy Essential features exhaust jet exhaust nozzle Federal Government field figure FULTON geodesy geodetic satellite geodetic systems going GOLAND Harrison Brown heat high temperature hydrogen important industry ion rocket ionization Jodrell Bank kilowatt Kistiakowsky liquid bipropellant LOVELL Lunik II ment metric system micrometeorites million NASA Noyes nuclear electric powerplant operating orbit oxidizer panel payload percent Petterssen plasma powerplant weight problem propellant rocket engine propulsion system question radar radiation radio astronomy radio telescope ramjet reactor research and development Revelle Russian scientific scientists Sir Bernard solid propellant space exploration space missions space program space vehicle specific impulse TEAGUE telescope Thank thermal thing thrust chamber thrustors United universities velocity WHIPPLE ZUCROW
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Page 27 - I believe that this nation should commit itself to achieving the goal, before this decade is out, of landing a man on the moon and returning him safely to earth.
Page 18 - The committee will recess until 2 o'clock this afternoon. (Whereupon, at 12 : 25 pm, the committee recessed, to reconvene at 2 pm, of the same day.) AFTERNOON SESSION The CHAIRMAN.
Page 19 - Now it is time to take longer strides — time for a great new American enterprise — time for this nation to take a clearly leading role in space achievement, which in many ways may hold the key to our future on earth.
Page 28 - For missions such as satellite sustaining or orientation, or for furnishing the electric power for communications, instruments, and the like, the electric power demands will be relatively small, ranging from a few watts to possibly 30 kw. Estimates indicate that, for unmanned lunar and Mars missions, the power requirements will range from 30 to 300 kw, and that for manned missions they may reach 10,000 to 30,000 kw. For electric power demands exceeding approximately 300 kw the nuclear electric powerplant,...
Page 31 - ... superior payload capability than energy-limite'd (chemical and nuclear) rocket engines. There are useful missions where the long flight times are acceptable [2,3,12]. Table III presents some of the general characteristics of the different types of rocket engines. Of the rocket engines listed in Table III only the chemical types have attained practical realization. To date, no electric rocket engine has been operated in space so that the practicable feasibility of electric rocket engines is an...
Page 29 - Temperatures: The radiator of a nuclear electric powerplant for space application is in any case a large piece of apparatus, and it becomes a dominant factor in the designs of powerplants for power outputs exceeding a few hundred kilowatts. The dimensions of the radiator are important for the following reasons...
Page 21 - ... energy is added to it. As a consequence of the energy addition, the propellant is ejected from the thrustor in the form of a high velocity jet of material, termed the exhaust jet. The ejection speed of the exhaust jet is termed the jet velocity, and is denoted by Vj.
Page 35 - III, the ion rocket engine has the potential capability of achieving larger values of specific impulse than any other type of rocket engine without introducing severe heat transfer problems. Its thrust-to-weight ratios are, however, the smallest. Although the basic operating principle of an ion thrustor is relatively simple, a large number of complicated problems are as yet unsolved. The propellant must be a readily ionized material and is fed to an ionizer wherein electrical power is used...