Rocket cryogenic upper stage

FIELD: aircraft engineering.

SUBSTANCE: rocket cryogenic upper stage (RCUS) designed according to the tandem layout comprises a fuel tank with an instrument compartment and transitional system for fastening of a spacecraft, an oxidizer tank (OT), intertank spacer, RCUS mid-flight engine (MFE), an intermediate compartment, fire and explosion prevention system, thermal mode maintaining system with the unit of demountable connections of communication with the land equipment and separable inlet pipelines, manifolds for purging of stagnant zones and device for maintaining of the thermal mode of the zone and RCUS equipment, a sealing diaphragm, the detachable head fairing (HF) with windows for detachment of the fire and explosion prevention system and devices for maintaining of the thermal mode of gases for purging of RCUS zone, additional thermal insulation of RCUS zone, a part of separable inlet pipes of manifolds with demountable joints and the unit of demountable connections for communication with the land equipment, an intertank spacer, conjugated with the intertank frame for fastening OT with MFE and conjugated to the top spacer of the separated intermediate compartment with the units of connection and separation with US and HF.

EFFECT: invention allows to improve fire and explosion safety of upper stage.

2 dwg

 

The invention relates to rocket technology, namely relates to cryogenic upper stages of space rockets. From the patent literature known adopted as a prototype, the rocket's cryogenic upper stage containing the fuel tank with dash cover and transition system for attachment of the spacecraft, oxidizer tank, the spacer miraculou, thrust upper stage engine compartment and the intermediate interfacing with the launch vehicle (see patent RU No. 2242405 C2, CL. 64 (G 1/00, 1/16, 1/40).

A disadvantage of the known cryogenic upper stage is the fact that you have applied the layout scheme leads to the loading of the spacer miraculou force arising from the payload mass of the oxidizer tank and the sustainer engine in the preparation and excretion, as well as a decreased level of firefighting and maintenance of a thermal mode: due to the lack of a system of pararosaniline and means of ensuring thermal regime, due to the adopted scheme of the lower placement of the fuel tank relative to the tank oxidizer (possible leak down and oxidizer mixing with fuel vapors) due to the lack of membrane separation, due to the lack of collectors purging of stagnant zones, because of the placement of the main engine inside the fuel tank, made in the form of a torus. The lack of in whom�novotney diagram reset head fairing with extra insulation and a detachable intermediate compartment reduces the effect of conservation of cryogenic propellants during preparation and launching, which leads to the deterioration of the energy-and-mass characteristics due to the need of filling an extra dose of fuel and oxidizer in the calculation of the loss from evaporation of a cryogenic fuel components.

The object of this invention to provide a cryogenic upper stage with the technical result in the form of increased firefighting and optimization for thermal regime of the zone of the upper stage and equipment through the application of the system of pararosaniline and means of ensuring thermal regime, improving energy-and-mass characteristics by storing cryogenic propellants during preparation and launching, by improving the redistribution of loads in the spacer miraculou attachment of the oxidizer tank, by placing a part of the intake pipes to the manifolds and the block plug connector, relative to the system pararosaniline and means for ensuring thermal regime and application of membrane separation and additional insulation discharged at the head fairing cryogenic upper stage and detachable intermediate compartment.

Said technical result is achieved in that in the rocket's cryogenic upper stage block containing the fuel tank with dash cover and transition system for mounting space apt�rata, oxidizer tank, the spacer miraculou, the main engine compartment and the intermediate interfacing with the launch vehicle, in accordance with the invention, a cryogenic upper stage, performed in tandem scheme with top of the fuel tank system contains pararosaniline and means of ensuring thermal regime with Swagelok connection with ground equipment and share of supply lines, manifold purge of stagnant zones and obespecheniya thermal regime of the area and equipment of the booster unit, the membrane separation, contains jettison fairing, curb reset Windows system pararosaniline and means for ensuring thermal regime gas purge zone of the upper stage, additional insulation zone of the upper stage, part of the partial supply lines and manifolds with split joints and Swagelok connection with the surface equipment includes a spacer miraculou involving the farm miraculou for attachment of the oxidizer tank with a mid-flight engine and is paired with the spacer upper intermediate compartment, wherein the nodes of the connection and separation of the booster and the nodes of connection and separation from the rocket nose fairing cryogenic unit. On bottom of the spacers Megaco�Oh made the junction and separation for fastening the upper stage to the launch vehicle using detachable spacer upper and intermediate compartment. At the same time efforts from payload are transmitted through a tapered spacer instrument compartment, then through the outer shell of the fuel tank, through the attachment of the spacers Milakowo, through the upper spacer, through the intermediate compartment to the booster. This farm of the oxidizer tank is not loaded with stress arising from the payload, and the spacer Minakova not loaded force on the mass of the sustainer engine and the weight of the oxidizer tank during removal of booster. On the upper spacer also have nodes of connection and separation for the installation of dropped head fairing, divided into zones of payload and upper stage separation membrane. To reset the head fairing cryogenic upper stage placed the Windows system pararosaniline and means of maintenance of a thermal mode to reset the purge gas mixture, a portion of the inlet pipe collectors purging of stagnant zones of the upper stage and for ensuring thermal regime of the zone of the upper stage and equipment and Swagelok system pararosaniline and means for ensuring thermal regime, for supplying purge gases from ground support equipment, prior to excretion. Windows system pararosaniline and means for ensuring thermal regime made � the opportunity to combine the functions of Windows flight drainage during insertion.

The invention is illustrated by drawings, where Fig.1 shows a General view of the space head part of Fig.2 shows a cryogenic rocket upper stage, where:

1 - fuel tank;

2 - the instrument section;

3 - transition system;

4 - oxidizer tank;

5 - spacer Minakova;

6 - thrust engine;

7 farm tank oxidizer;

8 - node connections of separation from the launch vehicle;

9 - upper spacer;

10 - intermediate compartment;

11 - the connection node separation with nose fairing;

12 - reset fairing;

13 - the collector purge;

14 - the shared supply pipe;

15 - Swagelok;

16 - membrane separation;

17 - additional thermal;

18 - vent;

19 - the fixing unit.

Rocket cryogenic upper stage contains the fuel tank 1 with the instrument compartment 2 and transition system 3 for attachment of the spacecraft, oxidizer tank 4, the spacer miraculou 5, thrust engine 6 upper stage and the intermediate compartment 6 of interfacing with the launch vehicle. To a tank of fuel 1 on which is mounted the instrument compartment 2 transition system 3 for attachment of the spacecraft, docked oxidizer tank 4 through a spacer miraculou 5 and the farm of the oxidizer tank 7. Sustainer engine 6 is installed at a depth in a spherical niche �poor oxidizer tank 4. On the spacer miraculou there are 5 nodes join and partition 8 for fastening the upper stage to the launch vehicle through the upper spacer 9 of the intermediate compartment 10. On the upper spacer 9 also have nodes of connection and separation 11 to install the discharged head fairing 12 of the upper stage. Spreader block system is used pararosaniline and means of ensuring thermal regime, consisting of collectors purge stagnant zones 13, share of the inlet pipe 14 with split joints, Swagelok 15, membrane separation 16. Jettison fairing 12, mounted on the upper spacer 9 of the intermediate compartment 10, for protection from aerodynamic and thermal loads cryogenic upper stage and the spacecraft encountered during the preparation and removal of the carrier rocket, made with extra insulation 17, is provided with reset Windows 18 system pararosaniline and means for ensuring thermal regime, membrane separation with 16 nodes fixation 19, Swagelok 15 and shared the inlet conduit 14.

This device operates as follows. Possible leakage in the volume of product vapor cryogenic fuel components arising from external climatic conditions, when preparing cryogen�th upper stage is met at the start by blowing inert gases from surface facilities through a system of pararosaniline and means of ensuring thermal regime, includes collectors purge stagnant zones 13, share of the inlet pipe 14 with split joints, head fairing jettison 12, made with extra insulation 17, is provided with reset Windows 18 system pararosaniline and means for ensuring thermal regime, membrane separation with 16 nodes fixation 19, block plug-in connections 15 connections with ground equipment. This makes it possible in contrast to the prior art to increase the explosion safety and optimize thermal control that allows you to increase the persistence of cryogenic propellants during the preparation and excretion, to improve energy-and-mass characteristics by eliminating the need for refueling an extra dose of fuel and oxidizer in the calculation of the loss from evaporation of a cryogenic fuel components.

The application of the discharged head fairing 12, curb reset Windows 18 system pararosaniline and means for ensuring thermal regime gas purge zone of the upper stage, additional insulation zone 17 of the booster unit, part of the partial supply lines 14 collectors purge 13 with split joints and Swagelok 15 communicating with ground-based equipment enables in contrast to the prior art to reduce the weight of the Accel�tion unit mass and improve performance.

External inertial loads arising from the preparation and removal of the carrier rocket, perceived structure, including intermediate compartment 10 with the upper spacer 9, spacer miraculou 5, through the nodes of connection and separation from the launch vehicle 8, the fuel tank 1, the instrument compartment 2, a transient system 3 mates with the spacecraft. The force from the oxidizer tank 4, the sustainer engine 6 is transmitted through the farm of the oxidizer tank 7, through the upper spacer 9 of the intermediate compartment 10, mated with the launch vehicle. This enables unlike prototype to rationalize the workload with the spacers miraculou 5 detachable in deriving the intermediate compartment 10 together with the upper spacer 9, which allows to reduce the mass of the cryogenic upper stage.

Thanks to this implementation of the layout scheme of the cryogenic upper stage can increase the explosion safety and to optimize thermal control zone of the upper stage and equipment through the application of the system of pararosaniline and means of ensuring thermal regime, to improve energy-and-mass characteristics by storing cryogenic propellants during preparation and launching, by improving the redistribution of loads in the spacer miraculou mount�tion of the oxidizer tank, by placing part of the intake pipes to the manifolds and the block plug connector relative to the system of pararosaniline and means for ensuring thermal regime and application of membrane separation and additional insulation discharged at the head fairing cryogenic upper stage and detachable intermediate compartment, that is, to achieve the technical result.

Rocket cryogenic upper stage containing the fuel tank with dash cover and transition system for attachment of the spacecraft, oxidizer tank, the spacer miraculou, thrust upper stage engine compartment and the intermediate interfacing with the launch vehicle, characterized in that the cryogenic upper stage performed by tandem scheme with top of the fuel tank system contains pararosaniline and means of ensuring thermal regime with Swagelok connection with ground equipment and share of supply lines, manifolds purge of stagnant zones and obespecheniya thermal regime of the area and equipment of the booster unit, the membrane separation, contains jettison fairing, curb reset Windows system pararosaniline and means for ensuring thermal regime gas purge zone acceleration�th block, additional insulation zone of the upper stage, part of the partial inlet pipes manifolds with split joints and Swagelok connection with the surface equipment includes a spacer miraculou involving the farm miraculou for attachment of the oxidizer tank with a mid-flight engine and is paired with the upper spacer detachable intermediate compartment, wherein the nodes of the connection and separation of the booster and the nodes of connection and separation with nose fairing of the rocket's cryogenic upper stage.



 

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