High-thrust carrier rocket low-temperature final-stage storage-tank connection support structure design method

Abstract

The invention discloses a high-thrust carrier rocket low-temperature final-stage storage-tank connection support structure design method. The method specifically includes the steps of 1), material selection, namely selecting carbon fiber composite materials having higher strength and lower thermal conductivity in 20K-90K low-temperature zones on the basis of the ratio of the strength to the thermal conductivity; 2), preliminary structure style design, namely performing five kinds of preliminary structure designs by taking structure strength and heat flow restrictions into consideration; 3), strength and weight analysis, namely, performing analysis on tensile stress, compression stress and buckling factors under the condition of bearing big load of tensile and compression; 4), heat analysis, namely selecting a structure style lowest in heat flow rate in structure styles meeting requirements of strength in the step 3). By optimization of the method, the high-strength carbon fiber composite materials are used in V-shaped 20-bar structure design of a low-temperature tank of a carrier rocket, and requirements of the ascent stage the high-thrust carrier rocket on large load are met.

Description

technical field [0001] The invention relates to a design method for a connection support structure of a low-temperature final stage storage tank of a high-thrust carrier rocket, and belongs to the field of aerospace transportation systems. Background technique [0002] The development of a new type of high-thrust liquid carrier rocket is an inevitable road for the development of my country's aerospace carrier technology, and it is also a necessary foundation to support the sustainable development and growth of my country's aerospace application industry. Low-temperature propellants are considered to be the most economical and efficient chemical propulsion for entering space and orbital transfer due to their high specific impulse, non-toxic, non-polluting, and relatively low price. Under the same carrying capacity, they can effectively reduce the overall launch vehicle scale. Low-temperature propellant is widely used in the final stage and upper stage of domestic and foreign ...

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Problems solved by technology

[0003] However, due to the low boiling point of low-temperature propellants (liquid hydrogen is 20K, liquid oxygen is 90K), it is easy to evaporate when heated, so the heat sources such as space solar radiation and earth radiation greatly limit the long-term storage and application of low-temperature propellants in space.

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