Time sequence design method of solid carrier rocket stage separation

Abstract

The invention provides a time sequence design method of solid carrier rocket stage separation. The time sequence design method comprises the following steps that after sending an ignition signal, an upper stage engine sends an unlocking signal to a stage connecting structure between the upper stage engine and a lower stage engine at a preset time interval, wherein the preset time is 10 ms-100 ms.According to the time sequence design method of solid carrier rocket stage separation, the function of stage thermal separation in a pressure building up mode is ensured to be realized, the peak values of the pressure, the temperature and the impact force of a stage zone during stage thermal separation in a pressure building up mode can be effectively reduced, the flight safety of a solid carrierrocket is effectively improved, and the carrying capacity is improved.

Description

technical field [0001] The invention relates to the field of interstage separation of solid launch vehicles, and in particular to a timing design method for interstage separation of solid launch vehicles. Background technique [0002] The interstage separation of solid launch vehicles is generally divided into two methods: thermal separation and cold separation. If the flying height of the rocket body is low at the time of separation between stages, the separation process will be greatly affected by aerodynamic interference. In order to ensure the reliability of separation, the thermal separation method is generally selected. [0003] The conventional form of thermal separation between stages of solid launch vehicles is the way of venting vents, but the structural strength coefficient of the venting vents is low, which has a greater negative impact on the rocket body. In terms of the timing arrangement of the thermal separation between the stages of the solid launch vehicle...

AI Technical Summary

Problems solved by technology

However, this separation sequence tends to cause excessive pressure inside the interstage section during separation

In order to avoid damage to the rocket body structure caused by the high pressure of the interstage section and ensure the structural strength, the structural design of the interstage section is often too conservative, resulting in an increase in the structural mass and a decrease in the carrying capacity

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