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Supplying a spacecraft with heat carrier featuring the parameters required in order to maintain thermal conditions during system preparation for launch involves considerable power consumption and requires bulky ground equipment in fortified structures. The paper establishes the possibility to decrease power consumption by ground equipment considerably. This result is due to circulating heat carrier between the layers of the fairing. This eliminates contact between the heat carrier and the spacecraft and substantially simplifies requirements posed to the heat carrier. It becomes possible to place ground equipment at the service level of the spacecraft upper stage and to reduce significantly the air duct lengths containing the heat carrier and the heat loss within them.

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The paper considers the problem of selecting the optimal weight and size characteristics of an erector frame for advanced super heavy-lift launch vehicle by selecting the suspension points of lifting mechanism ropes to the erector when transferring the rocket to a vertical position at the launch complex. The calculated dependences of frame weight and the force in polyspast system on the distance between the points of erector attachment to the racks of the launch pad and the points of erector suspension with the ropes are presented. The effect of the transverse width of the erector frame guide beams and the angle between the tight ropes and the horizon at the initial moment of lifting the rocket to the vertical position on the weight and dimensions of the erector is analyzed. According to the calculation results there is the possibility of a significant reduction in the weight, size and cost of the erector and the drives of lifting mechanisms in comparison with the case when ropes are attached to the cantilever part of the frame and systems using hydraulic drives as the lifting end organs of the erector beam.