Improving the processes of missile preparation at launch complexes on the basis of system design of interacting elements

Abstract

The results of the research presented in the paper are aimed at reducing the duration of preparing to launch Space and Missile System (SMS) at the launch complex (LC) and costs for it. This is achieved by thermostating the spacehead (SH) with the coolant supplied from the ground-based temperature control system (TCS) to the heat shield (HS) through the cavity between its walls and eliminating the removable heat insulation for the SH even under extreme environmental conditions. The justification of this option required the application of a systematic approach, in which the parameters of two functionally interacting SMS elements - TCS and SH were considered. In the framework of this approach, it is proposed to refine the HS, in which the coolant (gas) does not pass through volumes with a payload (PL) and an upper-stage rocket (USR), as is currently accepted, but through the HS cavities between its two walls. This will significantly reduce the requirements for gas purity, reduce restrictions on its flow rate (or speed), increase the safety of simultaneous thermostating of PL and USR, as well as provide pressure boosting of volumes from PL and USR due to high-speed pressure. To substantiate the proposal, a numerical simulation of the stress-strain state of the HS structure with a cavity was carried out, a numerical simulation of thermal processes taking place in the HS during the gas flow in the cavity between its walls during thermostating in a wide range of mean gas velocities between the HS walls was carried out. Based on the results obtained, a positive conclusion about the prospects for the application of the proposed circuit-constructive solution of HS and the option of supplying the coolant to the SH during thermostating is made.