Evaluation of the use of polyurethane in a solid rocket fuel for a single stage launch vehicle — carrier of an unmanned spacecraft orbiter for orbital and suborbital flights

1Levenko, AS, 2Prysiazhnyi, VI, 3Pauk, OL, 4Drozdenko, AS
1Air-Space Agency Magellan, Kyiv, Ukraine
2National Center of Space Facilities Control And Test, State Space Agency of Ukraine, Kyiv, Ukraine
3The State Enterprise “Production Association Yuzhny Machine-Building Plant named after A. M. Makarov”, Dnipropetrovsk, Ukraine
4Dnipropetrovsk Rocket Space Engineering College, Dnipropetrovsk National University after Oles Honchar, Dnipropetrovsk, Ukraine
Space Sci.&Technol. 2016, 22 ;(1):36-51
Publication Language: Russian
We present the results of theoretical study of an opportunity of creating a single-stage solid-fuel carrier for delivery of an Unmanned SpaceCraft (USC) orbiter on a suborbital trajectory. We investigate the use of polyurethane in the solid rocket fuel and the chosen production technology of a fuel charge of complex shape. We discuss possible dimensions of the launch vehicle and its design features. We calculate flight distance of the spacecraft on a suborbital trajectory (without the inclusion of the onboard engine) by the final carrier velocity in the boost path, with the possible achievement altitude up to 170 km. We analyze the complex combined control system of the launch vehicle and the spacecraft to achieve the required landing coordinates on a parachute system; control system may be applied for landing the spacecraft on mobile marine platforms. 
Keywords: booster, composite solid propellants, on-board control system., polyurethanes, rocket and space complex, solid rocket motor, the return orbiter unmanned orbiter
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