A cold helium pressurization and cooling delivery system for cryogenic launch vehicles

Abstract

The invention discloses a low-temperature carrier rocket cold-helium pressurization cooling and conveying system. The low-temperature carrier rocket cold-helium pressurization cooling and conveying system comprises a helium bottle arranged in a liquid-hydrogen storage tank liquid phase, an outlet of the helium bottle is connected with an inlet of a first bubbling device and an inlet of a second bubbling device through a first throttling device and a second throttling device; the first bubbling device is located in the liquid phase of the liquid-hydrogen storage tank, and the second bubbling device is located in the liquid phase of a liquid-oxygen storage tank; and a liquid phase outlet of the liquid-hydrogen storage tank is connected with a first inlet of an engine, and a liquid phase outlet of the liquid-oxygen storage tank is connected with a second inlet of the engine. According to the low-temperature carrier rocket cold-helium pressurization cooling and conveying system, the heat insulation throttling refrigeration, the bubbling refrigeration, the bubbling pressurization, and the utilization of the cold energy and the pressure energy in the cold helium bottle are organically combined together, and dual effects of the high-efficiency pressurization conveying of the low-temperature carrier rocket and the cooling of propellants are achieved; and the consumption of needed pressurization gases can be greatly reduced, the number of the required helium bottles is reduced, the total take-off mass of the carrier rocket is reduced, the effective load is improved, the launching cost is further reduced, and the advantage of the obtained pressurization cooling effect is more remarkable.

Description

technical field [0001] The invention relates to the technical field of propulsion, pressurization and delivery of low-temperature carrier rockets, in particular to a cold helium gas pressurization and cooling delivery system for low-temperature carrier rockets. Background technique [0002] Cryogenic propellants (such as liquid hydrogen, liquid oxygen, liquid methane, etc.) have become the most widely used group of propellants for large launch vehicles due to their advantages of non-toxicity, pollution-free, low cost, high specific impulse, and high thrust. The specific impulse is 30% to 40% higher than that of normal temperature propellants. However, cryogenic propellants can only meet the pump's net positive suction head requirement if the propellant is delivered to the inlet of the engine turbo pump at the specified pressure and flow rate under a controlled tank pillow pressure. Usually, cryogenic rocket pressurization delivery methods are divided into extrusion type and...

AI Technical Summary

Problems solved by technology

Although helium heating and pressurization technology has been widely used, there are still the following deficiencies: 1) storage tanks are pressure vessels, in order to meet the requirements of pressurized delivery, the wall thickness of the storage tank needs to be increased accordingly, resulting in an increase in the total take-off mass; 2) The cold energy stored in the liquid hydrogen storage tank is wasted after being heated, and is not used better; 3) The pressure energy stored in the high-pressure helium cylinder is lost in vain after passing through the pressure reducing valve; 4) After the high-temperature helium enters the air pillow of the storage tank, it will exchange heat with the propellant, which will intensify the thermal stratification of the propellant, reduce the quality, and increase the remaining amount, resulting in a decrease in the utilization rate of the low-temperature propellant

Especially for the low-temperature upper-stage launch vehicle that starts the propulsion booster system multiple times, if the high-temperature helium pressurized transport method is still used, it will inevitably cause a large amount of propellant to be discharged in order to reduce the temperature and pressure, and take away the extra heat flow. lead to waste of propellant

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