Aerospace Instrument-Making Annotation << Back THE UNITARU PULPPROPELLAT FOR SPACE V.P. Burdakov P.A. Khromchenko The article reports on the invention, and the advantages of the oxygen unitary pulp- propellant (UPP) for space: phenomenally high theoretical specific impulse in vacuum, reaching 470 s and high density 1140 kg/m3. These high performance provide a basis for the study operational qualities UPP and in the first place – the theoretical and ex-perimental studies of their cooling capacity. Conclusion of the work: the invention of the unitary pulp-propellant for LRE opens rocketry and astronautics innovative new devel-opment prospects, is not only to increase the theoretical specific impulse, but also in simplifying and reducing the cost of construction of the rocket carrier. The use of alu-minum hydride in DCA provides a theoretical specific impulse at the level of the most efficient propellant: oxygen + hydrogen, but not at a density 360 kg/m3 but 1140 kg/m3, which allows for more than three times to reduce volume of vehicle. Its volume is re-duced, even compared with the existing carrier «Soyuz», because its average propellant density is 960 kg/m3. One of the many important issues to be addressed in connection with the transition to a new propellant, is the problem of cooling the LRE. This is the problem of thermal, rheological and hydraulic characteristics of UPP due to the low value of the optimum ratio of fuel components Km=0,8 and 100 times higher viscosity compared with liquid oxygen. It is shown that the flow in the cooling duct of UPP is in transition flow region (between laminar to turbulent). It is most difficult mode to calculate and requires experimental verification. Key words: unitary propellant, rocket propellant, cooling the LRE, specific impulse, propellant density Contacts: E-mail: burdakov-valery@rambler.ru Pp. 33-43.