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"3.2. Main characteristics of MTKS-O

Due to the developed aerodynamic surfaces of an analogue of an orbital aircraft installed in the head part of the RLA-120 launch vehicle (see Fig. 1), the launch vehicle in flight is subject to loads that exceed the loads when launching objects with a fairing . Therefore, the RLA-120 for MTKS-O can only be used with wind limitation at an altitude of 8-12 km to 25-30 m/sec, while additional stabilizers are required to ensure rocket controllability.

Expanding flight conditions to high wind speeds requires strengthening the rocket design, and for wind speeds of more than 45 m/sec it is also necessary to increase the swing angles of the RD-150 and RD-1246 engines.

The use of the RLA-120 launch vehicle during the implementation of MTKS-O is expected to include the following activities:

reducing the permissible wind during launch vehicles at an altitude of 8-12 km from 65 m/sec to 45 m/sec (to maintain the accepted swing angles of the RD-150 and RD-1246 engines);

the introduction of a transition compartment on rocket block B, ensuring the installation of an orbital aircraft on a launch vehicle;

installation of additional stabilizers that provide partial compensation for the influence of the orbital aircraft’s load-bearing surfaces on the moment characteristics of the launch vehicle;

modification of the design of rocket blocks A and B due to increased loads, which is due to the deterioration of the aerodynamic characteristics of the launch vehicle.

In order to increase the mass of the payload, in this case it is advisable to remove the instrument compartment from rocket block B and move the control and computing equipment of the control system, the radio trajectory control system,

SR transmitting devices to the orbital aircraft. The change in the mass of the design of rocket blocks A and B, taking into account these measures, is given in Table. 3"

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