Rocket and spacecraft propulsion: principles, practice and by Martin J. L. Turner PDF

By Martin J. L. Turner

ISBN-10: 3540692029

ISBN-13: 9783540692027

The third variation of this useful, hands-on booklet discusses the diversity of release cars in use this present day through the global, and comprises the very newest information of a few of the complex propulsion structures at the moment being built. the writer covers the basics of the topic, from the elemental ideas of rocket propulsion and motor vehicle dynamics throughout the concept and perform of liquid and good propellant cars, to new and destiny advancements. The didactic worth of the early chapters at the fundamentals of rocket propulsion, by way of re-working the derivations and updating the examples can be enhanced.

The third variation will follow an identical precept of delivering a major exposition of the foundations and perform of rocket propulsion, yet from the perspective of the person and enquirer who's no longer an engineering professional. such a lot chapters will stay considerably almost like the second one version; they are going to be up-to-date the place important and errata corrected. particularly the recent chapters extra for the second one variation, on electrical and Nuclear propulsion will stay considerably the same.

In addition to normal revision, updating and the correction of errata on all chapters, this up to date version will element a few new advancements within the box bankruptcy three on Liquid propellant rocket engines could have new sections on air respiring engines and on new engines and propellants for the human exploration software. bankruptcy eight will now de-emphasize the SSTO recommendations, now not longer obvious as promising, and comprise new sections on variable thrust engines, back for human exploration. different new advancements following the declaration and next improvement of NASA’s new man-rated launcher, the ARES, and its Constellation automobile set. additionally coated should be sub-orbital area vacationer cars and the hot rocket engines, which were constructed for them. a brand new bankruptcy on man-rated launchers and their very important features will element this. New curiosity in Lunar exploration and the necessity to provide Lunar bases exposes the requirement for prime potency engines for Lunar transportation and garage of excessive power propellants like liquid oxygen and liquid hydrogen. New engines designed for in-space transportation and Lunar touchdown and departure should be further to the suitable chapters.

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Extra resources for Rocket and spacecraft propulsion: principles, practice and new developments

Example text

The other de®ning parameter is the minimum distance of the orbit from its focusÐthe centre of the Earth. The way to think of this is to imagine a spacecraft stationary at a certain altitude. The rocket ®res, and gives it a certain velocity V, tangential to the gravitational ®eld (parallel to the surface of the Earth). The kinetic energy of the spacecraft will be 1 2 2 MV ; and its momentum and angular momentum about the centre of the Earth will be MV and MrV respectively. Here r is the distance from the centre of the Earth, not just the height above the surface.

In these terms, a mass ratio of, say, 5 indicates that 80% of the initial mass of the rocket is fuel. 003. So a rocket vehicle is nothing like any other kind of vehicle, because of the requirement to have a mass ratio considerably greater than 1. The most obvious feature about a rocket like the Saturn V, or the Space Shuttle, is its sheer size compared with its payload. The Saturn V carried three men on an eight-day journey, and weighed 3,000 tonnes. Most of this weight was fuel. 6 that the rocket can travel faster than the speed of its exhaust.

So to compare the performance of a single and a two-stage rocket, we have to compare the following: V0 ˆ ve loge R0 V ˆ ve loge R1 ‡ ve loge R2 Any advantage of the two-stage approach will be revealed as V > V0 . For an example calculation, we assume a rocket of total mass 100 tonnes, carrying a spacecraft of 1 tonne. The engines develop a constant exhaust velocity of 2,700 m sÀ1 . The structural mass is assumed to be 10% of the fuel mass. Substituting Sec. 10. Multistaging. 09, which is fairly optimistic.

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Rocket and spacecraft propulsion: principles, practice and new developments by Martin J. L. Turner


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