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NEW TECHNICAL SOLUTION The solid fuel
rocket
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Solid reketny motors (SRM) have an advantage over liquid. SRM are simple in design: a balloon filled with solid fuel, while the cylinder has a hole with a nozzle. Combustion of fuel occurs in the cylinder under pressure. It provides steady pressure fuel combustion. In the transition to a high-calorie (energy) for sustainable fuels burning them, as a rule, it takes more pressure. All this leads to the need to do more robust cylinders so heavy that partially reduces the transfer efficiency on a high-calorie fuel.
The pressure of the fuel products of combustion in the cylinder through the nozzle is converted to the speed of their expiration, and creation of jet thrust, which by its magnitude is proportional to the mass of the combustion products and the speed of their expiry. Production of cylinders and nozzles operating at high pressures and temperatures, with complex technology of processing (and settlement), turned into a missile industry - a prestigious and expensive. The development of missile technology, its well-being, one of the conditions for sovereign and national independence (independence) states. A new principle of SRM. It will produce a solid propellant for such a public technology that SRM will be able to buy, really, a mass character. Without special equipment, with gunpowder checkers (rocket fuel) can satisfy any need. This will require the manufacturers of missile technology to move to a fundamentally new principles without reference movement may opt out of wasteful jet propulsion. Otherwise, the mighty technology priority will be lost. Rocket power until today blocked and hindered the development of technology in this area, but now can arise from the conditions under which it will power the rocket pioneers in the development of new transport techniques unsupported.
The proposed fuel burning solid propellant stability is achieved not by increasing the combustion pressure, but due to erosion jet fuel solid surfaces.
The new SRM is shown in Figure 1.
New SRM consists of a powder Checkers 1, covered with a protective layer 2. In the central axis of checkers 1 passes the channel 3, open at one end of checkers 1 indoor and 4 plug at the other end. The intensity and stability of fuel combustion in that engine is proportional to the length and inversely proportional to the engine-sectional area of the channel 3.
During operation, solid propellant, with fuel burnup, the section of the channel 3 is increased and the thrust solid rocket motor decreases as the intensity decreases fuel combustion and reduced exhaust velocity of the combustion products. This is desirable, since the fuel burn-up of the engine weight is reduced and the acceleration of motion for ordering rocket advisable to reduce cravings SRM that comes naturally.
Powder gases moving through the channel 3 test resistance of the channel wall 3. This effect intensifies the process of fuel combustion, and gases (SEO Channel 3) from the continuous fuel combustion to increase its volume and weight. This leads to an acceleration of the flow (jet) of powder gases in the channel 3. Those most exposed fading channel 3 at the end of checkers hole 1. As you use solid propellant block 1 is shortened and the solid propellant thrust is reduced. This eliminates the need for multi-stage rocket principle. A new design of SRM is sufficient for spacewalk.
Given the uneven burning Checkers 1, the latter can be made conical shape on the channel configuration 3 to the end of the work SRM (see. Figure 2).
In some cases, there is no need for a broad and smooth thrust reduction SRM. To do this, instead of the plug 4 is attached to the saber 1 traditional SRM 5 with nozzle 6 directed into the channel 3 (see. Figure 3).
In this case, the jet stream from the nozzle 6 is accelerated in a channel checkers 1 3, wherein the block 1 burns evenly throughout its length. It eliminates the need for a substantial extension Checkers 1.
SRM of FIG. 1 - long, that is, it may be mechanically unstable. This is for the SRM is a limitation. In addition, SRM at work may give rise to "string" vibrations, which should be taken into account. On the proposed SRM application was filed for the invention N 3457317/23 (103 492) of 22 June 1982, by which the decision was rendered VNIIGPE refusal to grant a copyright certificate for the invention of the USSR.
But for some reason, modern rocket science has gone the way of case solid propellant under pressure, and the erosion process for stabilizing combustion of gunpowder nobody, until now, did not pay attention. The fact that in the early days of rocketry black and pyroxylin powders were basic, but they are not sufficiently strong for concealed SRM. Only with the advent of sufficiently durable powder formulations can go to the construction of the new SRM, which has long been there. But came into effect the principle of inertia (habit), the tradition (to this day), and all continue to puzzle over the morally exhausted itself balloon SRM high pressure.
Description of the proposed solid propellant registered in All-Russian Scientific and Technical Information Center of the Ministry of Industry, Science and Technologies of the Russian Federation of December 25, 2000 under number 72200000048, as an intellectual product. Text description of the information stored in the fund VNTIC.
Published in the Bulletin VNTIC "Ideas. Hypotheses. Solutions" number 1, 2001.
Source: http://zhurnal.lib.ru/s/suhanow_w_n/trdru.shtml
print version
Publication date 22.01.2004gg
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