RU2399564C1 - Rocket unit engine plant - Google Patents

Abstract

FIELD: transport. ^ SUBSTANCE: invention relates to aerospace engineering. Proposed engine plant comprises engine fuel and oxidiser tanks to supply sustainer engine, high-pressure cylinder to supply gas for engine plant actuators, pressure reducer communicated via pipeline with high-pressure cylinder to create operating pressure at the inlets of actuators. Additionally, pipeline is added to engine plant, with its inlet communicated with pressure reducer drain union, while its outlet Y-tube added to fuel tank pressurisation pipeline. ^ EFFECT: improved weight dimension characteristics of rocket unit. ^ 1 dwg

Description

The invention relates to space rocket technology.

Known propulsion system of the rocket block according to patent 2286924, containing the oxidizer fuel tank, fuel fuel tank, main engine, high pressure cylinder with helium, executive bodies, which is taken as a prototype.

The executive bodies of the propulsion system of the rocket block include a gearbox that lowers the high cylinder pressure to the working pressure necessary for the operation of other executive bodies (electro-pneumatic valves, pneumatic valves). During the entire operation time of the gearbox, helium is drained from its cavity, as a result of which its loss occurs, which must be taken into account when calculating helium reserves for the operation of the propulsion system of the rocket block. In addition, helium, gasing the internal space of a rocket block, can adversely affect the operation of avionics as a rocket block, and payload.

The objective of the proposed propulsion system of the rocket block is to improve its mass characteristics by using helium from the cavity of the pressure reducer to pressurize the fuel drainage tank of helium.

The problem is solved due to the fact that in the propulsion system of the rocket block, containing the oxidizer fuel tank and the fuel tank, supplying the main engine, a high-pressure cylinder, the gas of which is used for the operation of the executive units of the propulsion system, a pressure reduction gearbox connected by a pipeline to the high-pressure cylinder pressure and providing working pressure at the entrance to the executive bodies, a pipeline has been introduced, the inlet of which is connected to the drainage fitting of the pressure reduction gearbox, and you od - a tee introduced into the fuel tank pressurization conduit.

The drawing schematically shows a propulsion system of a rocket block with a pipeline, with which helium drainage from a pressure reduction gearbox is used to pressurize the fuel tank, where:

1 - oxidizer fuel tank;

2 - fuel fuel tank;

3 - high pressure cylinder;

4 - mid-flight engine;

5 - pipeline;

6 - boost pipe;

7 - pressure reduction gear;

8 - tee;

9 - drainage fitting.

In the propulsion system of the rocket block, containing the oxidizer 1 fuel tank and fuel 2 fuel tank, supplying the main engine 4, the high-pressure cylinder 3, the gas of which is used for the operation of the actuators of the propulsion system, a pressure reduction gear 7 connected by a pipeline to the high-pressure cylinder 3 and providing operating pressure at the inlet to the actuators, a pipe 5 is introduced, the inlet of which is connected to the drainage union 9 of the pressure reducing gear 7, and the outlet - with a pipe tee 8 a fuel tank 6, fuel pressurization rovoda 2.

As a result, helium losses are eliminated, while helium is used to pressurize the fuel tank 2.

During the operation of the propulsion system of the rocket booster block, after the sustainer engine is started, 4 helium is supplied from the high-pressure cylinder 3 to the pressure reduction gear 7, while the helium drained from the pressure reduction gear 7 using the pipeline 5 and tee 8 of the boost pipe 6 is used to pressurize the fuel tank fuel 2.

Using drained helium from a pressure reducing gear 7 to pressurize the fuel tank of a rocket 2 rocket unit allows this quantity of gas to be taken into account when calculating the helium reserves in the high-pressure tank 3 required for the propulsion system to work and, accordingly, to reduce the mass of the rocket block.

In addition, the negative effect of helium on the operation of the avionics of the rocket block and the payload is eliminated.

Claims (1)

A rocket engine propulsion system containing an oxidizer fuel tank and a fuel tank supplying a main engine, a high-pressure cylinder, the gas of which is used for the operation of the propulsion system’s executive bodies, a pressure reduction gearbox connected by a pipeline to a high-pressure cylinder and providing operating pressure at the inlet executive bodies, characterized in that a pipeline is introduced into it, the inlet of which is connected to the drainage fitting of the pressure reduction gearbox, and the outlet - with roynikom introduced into the supercharging pipe of the fuel tank of fuel.