The paper considers possibility of reducing the cost of design, development and launching an ultralight launch vehicle (ULLV) by simplifying its design, including rejection of the use of pump feeding. Key requirements to the ULLV are formulated on the basis of analyzing domestic and world markets of launch vehicles of this class. The paper proposes introduction of low-pressure displacement supply, ablative curtain cooling of the engine combustion chambers, increased thrust-to-weight ratio in stages to compensate for increasing losses due to backpressure, spherical tanks, as well as the final maneuver of the last stage after completing the insertion to compensate for its errors. Based on the Townsend simulation technique to assess the launch vehicle carrying capacity and on the simplified aeroballistic model, effectiveness of the proposed technical solutions is being analyzed and their influence on the possible payload mass is determined. It is shown that a three-stage rocket built on the above principles approximately corresponds in terms of the payload share to the other concepts of a launch vehicle using the same fuel components.