ROCKET PROPULSION USING UNITARY PASTE-LIKE PROPELLANT. ESSENTIAL DEEP REGULATION AND MULTIPLE ENGAGING
- Paper number
IAC-08.C4.2.10
- Author
Mr. Yulian Protsan, The Laboratory of Advanced Jet Propulsions, Ukraine
- Coauthor
Mr. Anatoliy Ivanchenko, The Laboratory of Advanced Jet Propulsions, Ukraine
- Coauthor
Dr. Sergiy Bondarenko, Dnipropetrovsk National University, Ukraine
- Year
2008
- Abstract
The idea of a Rocket Propulsion (RP) with forced feeding of the unitary paste-like propellant into combustion chamber became as necessity to improve safety of rockets and Launch Vehicles (LV) by way of changing of Liquid Fuel Rocket Engine (LFRE) using toxic high-boiling components of fuel of upper stages of LVs by RPs which are working on the Paste-like Propellant (PlP). The forced feeding of the PlP into combustion chamber from a tank to allow on-the-fly to regulate and have multiple possibility to switch-on its like to LFRE. At the same time, the use of the unitary propellant, that is solid rocket propellant in non-hardened condition, allows to simplify the propulsion design approximating it to Solid Fuel Rocket Engine (SFRE), to reduce cost and to lighten the LV exploitation with Paste-like Propellant Rocket Propulsion (PPRP). Thus, PPRP unites into itself positive kinds of LFRE and SFRE. Moreover, PPRP has possibility to be regulating deeply (up to 80 times) on thrust that is exceeding the kind at other types of the rocket engines. It occurs due to features of the PlP flowability as a non-Newton’s liquid. The experimental PPRPs (with thrusts 20 and 25 kg) were designed and implemented, and also many (around 200) fire tests were conducted what confirmed efficiency of put into them technical solutions. Thanks to the created unique RD margin in the PPRP area a wide spectrum of project investigations of new engines with different functions were conducted. The project investigations of the PPRP for upper stages of LVs and rockets have shown that during of solution of a range of PPRP’s tasks this one surpasses other types of RP on mass-dimension characteristics approximately in 30%. The LV composition density with the PPRP, as with SFRE, is in 1.5…2 times higher than in LVs with LFRE. The use in LVs of on-the-fly controlling PPJP according to Tsiolkovskiy Second Task will increase their power efficiency obviously in comparison to SFRE LVs. Currently some world aerospace companies are working under creation of regulating RPs. As a rule, they are working with regulating RPs using gel-like components of fuel (in fact fuel+oxidizer) which are being gasified into combustion chamber and being mixed like in LFRE. The Ukrainian direction of the works with monopropellant propulsions is another: we use unitary paste-like propellant which is being mixed thoroughly in factory conditions, is burning out into combustion chamber without separation onto components. It allows to build the propulsion of more simple construction with more deep regulation of the thrust in comparison with LFRE, and exclusion of polymerisation (hardening, solidification) of the fuel broadens choice of the fuel components and thereby to allow to increase the specific thrust in comparison with SFRE. It allows to improve characteristics of an LV/rocket in whole and provide delicate and comfortable withdrawal of payloads onto given orbits.
- Abstract document
- Manuscript document
IAC-08.C4.2.10.pdf (🔒 authorized access only).
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