RU2557092C1 - Device to control thermal conditions and cleanliness of spacecraft head with large-sized payload - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed device comprises thermostating gas injection holes arranged at head cowl and adapter compartment. Besides, its comprises thermostating gas efflux holes and one-way valves of thermostating gas injection and efflux. Thermostating has injector is composed of a flute with one-way valves as sealing covers arranged at injection hole shaping strips. There are extra thermostating gas injection holes. One-way valves are composed of a flap with counterweight between inlet with protective screen and outlet. There are also heat insulating and heat control coatings.

EFFECT: higher purity and efficiency of thermostating.

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Description

The invention relates to rocket and space technology, and in particular to a device for providing space-launch rocket (ILV) during preparation in the launch site of the thermal regime and cleanliness of the space head part (ILG) of the rocket launcher with a large payload (PN) mounted on the transition compartment (PXO) ) gas-dynamically interconnected with the head fairing (GO), and is intended to provide the necessary parameters of the gaseous medium around the PN.

Known devices (patents RU No. 2359878, No. 2412874) thermostatic control of the payload of the head block of the launch vehicle, located under the fairing of the head block, containing a blow hole of the thermostatic medium, openings of its outflow in the fairing of the head block, single-acting valves of the blow holes and expiration of the thermostatic medium, pivotally mounted outside the fairing of the head unit, a device for blowing the thermostatic medium into the head unit, made in the form of a subsonic diffuser in the form of a closed symmetry egg container with an inlet and three outlet openings.

The closest device to the claimed device is the device according to patent No. 2353556, selected by the authors as a prototype.

The temperature control device for the payload of the head block of the launch vehicle, consisting of a series-connected and gas-dynamically interconnected head fairing and the transition compartment (fairing of the booster block) of the rocket launcher and placed underneath them, while on one side of the head fairing and the transition compartment there are respectively made an injection hole thermostatic medium and its outflow openings with single-acting valves installed in them, which are pivotally mounted outside the head fairing and the transition compartment, in the injection holes on the inner side of the head fairing and the transition compartment are installed subsonic diffusers, made in the form of a closed symmetrical tank, with inlet and three outlet openings.

The known device, as well as the above-described devices, have limited possibilities for their use, since they are not intended for large payloads placed in the assembly-protective block of the KGCh with a minimum space between the surfaces of the PN and the SZB, due to the presence of large diffusers, at which significant heat loss of a thermostatic medium due to high velocities of a gaseous medium flowing around a swirling diffuser around the entire surface of the NWB shell interacting with its external surface airborne atmosphere, and heat-stressed separation zones of the thermostatic flow can occur near the surface of the payload with non-calculated heating temperatures of its individual elements, leading to unnecessary load on the ground means of the air system to ensure the thermal regime and purity of KGCh, which reduces the efficiency of ensuring the thermal regime and quality of space purity the head of a space rocket.

When the lower part of the ST is thermostatically controlled by the gas component supplied to the upper part of the ST, the temperature of the total flow in the lower part of the ST is determined taking into account additional temperature losses during the flow in the upper part of the ST, as well as the contamination of the total flow in the lower part of the ST will be higher than in the upper part parts due to additional contamination of the flow when moving in the upper part of the ST, while the temperature state and purity of the lower part of the ST deteriorate.

The effectiveness of temperature control also depends on the external impact on the assembly-protective block of solar radiation and the surrounding atmosphere with extreme values of temperature and wind on a large payload, which requires significant energy costs and increased costs of thermostatic gas medium injected into the SZB.

The objective of the proposed technical solution is to expand the capabilities of the device with the provision during the preparation and launch of the rocket launcher in the starting structure of the effective thermal regime and cleanliness of the space head of a space rocket with a large payload.

A device for ensuring the thermal regime and cleanliness of the space head part of a space rocket with a large payload fixed on the transition compartment gasdynamically interconnected with the head fairing, containing on the head fairing and on the transition compartment the injection holes of the thermostatic gas medium interacting with removable main gas ducts of the launch complex, openings expiration of thermostatic gas medium, articulated single-acting valves The apertures of blowing in and out of a thermostatic gas medium, a device for blowing in a thermostatic gas medium, characterized in that in the head fairing and in the transitional compartment from the opposite sides of the longitudinal plane of the assembly-protective block there are additional blowing openings of thermostatic gas medium, while the blowing device is on the head fairing made in the form of a tray fixed to the edging of the hole, the curved axis of which is directed upward at an angle to the generatrix of the upper part of the head fairing, pr than the single-acting valves of the injection holes are made in the form of sealing covers, and the outflow openings are arranged radially mutually opposite rows in the transverse plane of the lower part of the GO, providing at the same time uniform flow of thermostatic gas medium from the upper and lower parts of the SZB, by means of single-acting valves made in the form of a shutter with a counterweight located between the inlet and outlet, and the inlet of the valve has a protective mesh, and on the shell of the head btekatelya secured heat-insulating and temperature-control coating.

The invention is illustrated by drawings:

in FIG. 1 shows a General view of the device;

in FIG. 2, view A from FIG. 1 shows a device for blowing a thermostatic gas medium into a head fairing;

in FIG. 3 view B from FIG. 2 shows a device for blowing a thermostatic gas medium into a head fairing;

in FIG. 4, view B of FIG. 3 shows the fastening of a thermostatic gas medium blowing device into the head fairing and the separation pipe of the main gas duct;

in FIG. 5, an external element G of FIG. 1 shows a device for blowing a thermostatic gas medium into a transition compartment of an SZB;

in FIG. 6, the remote element D of FIG. 1 shows a valve device for the discharge of a thermostatic gas medium from an SZB;

in FIG. 7 is a view E of FIG. 6 shows a valve device for the discharge of a thermostatic gas medium from an SZB;

in FIG. 8 section FJ with FIG. 1 shows the distribution of the outflow openings of a thermostatic gas medium from the SZB;

in FIG. 9 section II with FIG. 1 shows heat-insulating and thermoregulating coatings of the head fairing of SZB.

The device for ensuring the thermal regime and cleanliness of the space head part of a space rocket 1 with a large payload 2, mounted on the transition compartment 3, is gasdynamically interconnected with the head fairing 4, contains on the head fairing 4 and on the PXO 3 blowing holes 5, 6, on the opposite sides of which there are additional injection holes 7, 8 of the thermostatic gas medium (Fig. 1), interacting with removable main gas ducts 9 of the launch complex.

On the head fairing 4, each blowing device of a thermostatic gas medium is made in the form of a blowing hole 5, 7 of a tray 11 fixed to the edging 10 with an input 12 and output 13 holes (Fig. 2), the curved axis 14 of which is directed in the longitudinal plane at an angle α to the generatrix head fairing 4.

The injection holes 5, 6, 7, 8 of the thermostatic gas environment are interconnected by means of flanges 15 and 16, mounted on the edging 10 and 17 of the holes, with removable dividing pipes 18 and 19 of the main gas duct 9 of the launch complex (see Fig. 1, 2, 3, 4, 5).

In the injection holes 5, 6, 7, 8 from the outer sides of the head fairing 4 and the transition compartment 3, single-acting valves are made in the form of sealing caps 20.

In the outflow openings 21 (FIG. 1), on the inside of the head fairing 4, single-acting valves 22 (hereinafter, the valve) are pivotally mounted in the form of a movable flap 23 with a counterweight 24 located between the inlet and outlet openings 25, 26 of the valve 22 (FIG. 6, 7).

The inlet 25 of the single-acting valve contains a protective mesh 27 (Fig. 7).

After stopping the supply of the thermostatic component to the OGC at the launch of the rocket launcher 1, the design of the valve 22 allows to reduce the levels of gas-dynamic effects through the openings 21 of the atmosphere of the surrounding rocket launcher 1 in the launch facility at the monopole 2 eliminating the entry into the SPB and the formation of polluting PN 2 particles under the SPB.

In preparing ILV 1 in the launch facility and during its flight, valves 22 ensure the presence of optimal overpressure of the gaseous medium in the cavities of the SZB, which determines high levels of structural, mass perfection of the SZB and the quality of the cleanliness of the gaseous medium and the surfaces of the PN 2 in the SZB.

The outflow openings 21 are arranged in radially mutually opposite rows in the transverse plane of the lower part of the GO 4, which simultaneously provide uniform distribution in the cavities and the outflow of thermostatic gas flows from the upper and lower parts of the SZB moving towards each other to the inlet 25 of the valve 22.

The proposed location of the expiration holes 21 allows thermostat the upper and lower parts of the PN 2 separately, for example, a spacecraft above its interface with the upper stage and the upper stage in the lower part of the PN 2.

A heat-insulating coating 28 is fixed on the shell of the head fairing 4, which increases the thermal resistance of GO 4 and, as a result, reduces the heat flux between the thermostatic medium and atmospheric air, which allows to reduce the heat loss of the gas component when moving along PN 2 and at the same time maintain the quality of the cleanliness of the gas medium and surfaces PN 2 (Fig. 8).

The device for blowing in a thermostatic gas medium, made in the form of a tray 11, occupies a minimum zone inside the GO 4, has a minimum hydraulic resistance to the supplied flow of the thermostatic gas medium due to the simplicity of the design with its small mass (see Fig. 1, 2, 3, 4).

Removable separation pipes 18, 19 (Fig. 4) are installed with corresponding seals 29 and 30 (Fig. 2, 5) outside the SZB on the edges 10 and 17 of the openings 5, 6, 7 of the 8 SZB blowing devices for interaction with removable main gas supply ducts 9 in KGCH thermostatic gas component of a high degree of purification from the systems of the launch complex.

The mass characteristics, the displacement values of the CM of the movable damper 23, forming a counterweight 24, are determined taking into account the area of the movable damper 23 and the maximum allowable pressure drop acting on the shell of the SZB, not exceeding which is provided by the valves 22, between the overpressure in the SZB and the ambient pressure on the SK and at flight of ILV 1 atmosphere.

The flap 23 movable on the axis 31 interacts in extreme angular positions with the stops 32 fixed on the valve body 22, as well as in the closed position of the valve 22 along the contour of the movable flap 23 with a profile 33 fixed to the shell of the GO 4 SZB (see Fig. 6) .

During transportation and installation of the rocket launcher 1 to the launch site from the horizontal to the vertical position, the outflow openings 21 are provided with removable openings to the SC before starting the supply of a high-purity thermostatic gas component through the openings of injection 5, 6, 7, 8 with covers 34 and latches 35 of the movable shutters 23 valve 22.

On the outer surface of the shell of GO 4 and on the inner surface of the insulating coating 28, heat-reducing coatings 36 are applied by radiation between PN 2 and GO 4, made, for example, on the outer surface of the shell in white with a low absorption coefficient of solar radiation and a high value degree of blackness, and in the form of aluminum foil 28 fixed over the entire area of the insulating coating 28, providing a low degree of blackness.

The device operates as follows.

In the device for ensuring the thermal regime and cleanliness of the space head part of a space rocket 1 with a large payload 2, a gas thermostatic component of a high degree of purification is supplied via ground gas ducts 9 to GO 4 through removable separation pipes 18, 19 and blow holes 5, 6, 7, 8.

The ratio of the flow rate of the gas component in PHO 3 to the flow rate in GO 4 is from 0.5 to 0.875.

When a gas thermostatic component of a high degree of purification is supplied, an excess pressure of the gaseous medium is formed in the SZB cavity, which prevents the ingress of foreign particles and moisture into the internal cavity of the SZB from the surrounding KGH atmosphere.

Blowing devices made in the form of curved trays 11 located in the upper part of the GO 4 of the SZB direct the flow vectors of the gas thermostatic component through the outlet openings 13 to the upper part of the GO 4 above the payload 2 towards each other.

In increasing along the curved axis from the inlet 12 to the outlet 13 of the hole, the cross section of the tray 11, having the outlet 13 opening larger than the inlet 12 hole, at the outlet of the tray 11 the speed of the jet of gas medium supplied to the SZB decreases.

Two jets of the gas component, colliding with each other and the surface of the conical part of the head fairing 4, form a vortex movement limited by the region of the upper cone of GO 4 above the PN 2 zone, the potential stream of jets leaving the blowing device is washed out (divided), and the gas velocity is significantly reduced environment, excluding the direct effect of a stream of a gaseous medium coming from the tray on PN 1 with speeds exceeding the permissible value of the impact on PN 1.

Further, the flow of the gas component enters the cylindrical part in the gap space between the PN 2 and GO 4 with aligned velocities around the circumference around the PN 2.

Two jets of the gas component supplied through blowing devices on the transition compartment 3, colliding with the surface of the PXO 3, form a vortex movement limited by the region of the transition compartment and the lower parts of the PN 2 and GO 4, there is a erosion (splitting) of the potential flows of the jets leaving the openings 6 8 blowing the thermostatic component, and the speed of the gas component is significantly reduced.

Further, the flow of the gas component enters the cylindrical part into the gap space between the PN 2 and the GO 4 shell with aligned velocities around the circumference around the lower part of the PN 2.

The flows of the gas component from the KGCh flowing into the slit space between the PN 2 and the shell of GO 4 through the blowing holes 5, 6, 7, 8 are discharged through valves 22 and openings 21 of the outflow of the gas medium of the protective assembly, which are arranged radially mutually opposite rows in the transverse plane the lower part of GO 4, providing both uniform distribution in the cavities and the outflow of thermostatic gas medium from the upper and lower parts of the SZB.

The separation of the branch pipes 18, 19 with ground gas ducts 9 for supplying a thermostatic medium is carried out automatically after completion of thermostating.

The claimed device allows you to:

- to exclude the possible formation of polluting MO particles in the gaseous medium under the SZB by reducing the speed levels of the direct action of jets of thermostatic component on the MON 2 to acceptable values;

- to ensure the most uniform flow of the thermostatic component along the perimeter in the gap between the surface of GO 4 and PN 2, eliminating the appearance in the KGC cavities of the zones of flow around PN 2 with costs lower than in other zones, which will improve the cleanliness and temperature state of the upper and lower parts of PN 2 .

Thus, the claimed device increases the efficiency of thermostating and provides an increase in the quality of cleanliness of the internal cavity of the SZB, in which a large-sized PN is mounted on the transition compartment during the preparation and launch of the rocket launcher in the launch facility.

Claims (1)

A device for ensuring the thermal regime and cleanliness of the space head part of a space rocket with a large payload fixed on the transition compartment gasdynamically interconnected with the head fairing, containing on the head fairing and on the transition compartment the injection holes of the thermostatic gas medium interacting with removable main gas ducts of the launch complex, openings expiration of thermostatic gas medium, articulated single-acting valves The apertures of blowing in and out of a thermostatic gas medium, a device for blowing in a thermostatic gas medium, characterized in that in the head fairing and in the transitional compartment from the opposite sides of the longitudinal plane of the assembly-protective block there are additional blowing openings of thermostatic gas medium, while the blowing device is on the head fairing made in the form of a tray fixed to the edging of the hole, the curved axis of which is directed upward at an angle to the generatrix of the upper part of the head fairing, pr than the single-acting valves of the injection openings are made in the form of sealing covers, and the outflow openings are arranged radially mutually opposite rows in the transverse plane of the lower part of the fairing, providing at the same time uniform flow of thermostatic gas medium from the upper and lower parts of the assembly-protective block, by means of single-acting valves, made in the form of a damper with a counterweight located between the inlet and outlet openings, and the inlet of the valve has a protective net, and on the shell of the head fairing there are fixed insulating and thermoregulating coatings.

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