RU2271319C2 - Method of support of thermal conditions and purity of space rocket head module and device for realization of this method - Google Patents

Abstract

FIELD: control of parameters of surrounding medium for such launch vehicles as SOYUZ, ZENIT-3 SL (sea launch), PROTON.

SUBSTANCE: proposed method includes cyclic delivery of gas to head module and evacuation of gas from head module. Direction of gas flow is changed in torn. At last cycle after obtaining the required purity of gas, it is fed to upper part of head module and is evacuated from its lower part. Excessive pressure of gas is maintained in head module. Device proposed for realization of this method has filters, units for delivery of gas to head module and thermostatting members. It is also provided with unit for control of direction of gas flow which is connected with thermostatting members and with gas discharge valves; devices for monitoring gas purity are mounted on gas lines. Gas discharge valves are connected to upper and lower gas flow splitters by means of gas lines. End face of head module is provided with cover.

EFFECT: enhanced purity of head module; avoidance of penetration of atmospheric air into head module; enhanced fire safety and moisture proofness.

3 cl, 1 dwg

Description

The invention relates to space rocket technology.

Modern spacecraft (SC), head fairings (GO), booster blocks (RB) and other components of the head blocks (GB) of space rockets (ILV) have high demands on ensuring the cleanliness of the surfaces of these nodes.

This is due to the fact that the composition of the spacecraft uses high-precision electronic devices, optical equipment, solar panels and other elements that are manufactured under high industrial purity requirements and require high reliability in fulfilling the tasks assigned to them.

Therefore, the manufacture, assembly, testing and operation of the components of GB and GB itself are subject to increased requirements for ensuring cleanliness.

There is a method for providing the thermal regime of GB ILV by supplying air to the lower part of the GB using mobile means mounted on a railway or automobile platform, with air leaving the upper part of the GB and returning it to the entrance to the GB, i.e. The system operates in a closed loop. The circulated air is cleaned using filters installed at the inlet of the air supply to the device to ensure the thermal regime of GB.

Devices are also known for ensuring the thermal regime of GB with air supply paths, which include filters, fans, ducts, thermostatic elements of the device, etc. These devices operate both in open and closed cycles. In the first case, the supplied air is released into the atmosphere through one of the GO hatches, in the second it enters the system again.

There is a method for providing the thermal regime of GB ILV by supplying atmospheric air to the lower part of GB using stationary ground-based means and means of the ILV maintenance tower and air emission into the atmosphere in the upper part of GB, i.e. the system operates on an open cycle. The supplied air is cleaned by means of filters installed at the air inlet to the device to ensure the thermal regime of the GB (Cosmodrome, under the general editorship of Prof. A.P. Volsky, Military Publishing House of the Ministry of Defense of the USSR, 1977, pp. 208-213) .

As a prototype of the invention, a method for providing thermal conditions and an open-loop device are adopted.

The disadvantages of the prototype is that:

- air supplied to the lower part of the GB and emitted in the upper part of the GB (consists of RB, adapter KA, GO, and other elements) can transfer pollution from the nodes of GB to KA;

- the air supplied by its directed action on the structure can contribute to blowing particles from the materials used in the GB design, for example, from thermal insulation;

- there is no provision for the creation of excessive pressure inside the GB, which should prevent the penetration of untreated atmospheric air into the internal cavity of the GB through GB leaks (including sea air in the case of launch of the rocket launcher in marine conditions) during the start, when due to the operation of the main engines of the rocket launcher pollution the surrounding atmosphere is the most significant;

- in order to ensure the required purity of the spacecraft, a closed (encapsulated) volume is created for it in GB, which leads to significant mass costs.

The objective of the proposed method is to provide high quality purity GB while ensuring its thermal regime.

The problem is solved due to the fact that in the method of ensuring the thermal regime and cleanliness of the head block of a space rocket, which includes supplying a gas component to the lower part of the head block and ejecting it from the upper part of the head block, the gas component is supplied cyclically, starting to supply the gas component to the upper part of the head unit with its ejection from the bottom of the head unit, the end part of which is plugged with a cover, alternately changing the direction of the gas component flow to the opposite, moreover in the last cycle, after obtaining the specified purity of the gas component, it is fed to the upper part of the head unit, the emission is carried out from the lower part of the head unit, while creating an excess pressure in the head unit of the supplied gas component.

The cycle consists of supplying the gas component to the upper part of the head unit and ejecting it from the lower part of the head unit, then the flow direction of the gas component is reversed using the flow direction control element. The cycles are repeated until the next purity of the gas component is detected by the purity control device at the outlet of the lower part of the head unit during the next cycle, after which they switch to overpressure maintenance in the head unit by supplying the gas component to the upper part of the head unit with emission it from the bottom of the head unit, while on the end of the head unit must be installed cover.

The problem is solved due to the fact that the composition of the device for implementing the method of ensuring the thermal regime and cleanliness of the head block of a space rocket, including a filter that cleans the gas component entering the flow inductor, a flow inducer, which supplies the gas component through the gas ducts to the head block, gas ducts, thermostatic elements of the device, ensuring the maintenance of the thermal regime of the head unit, an additional control element is introduced for the direction of flow of the gas component, which is the gas duct it is connected to thermostatic elements of the device and to the valves for the discharge of the gas component from the head unit, the control devices for the purity of the gas component that are installed on the gas ducts, the valves for the discharge of the gas component connected by gas ducts to the flow dividers of the gas component, the upper and lower flow dividers of the gas component, mounted on the upper and lower parts of the head fairing, and the cover mounted on the end face of the head unit, the upper and lower flow dividers of the gas component introduced of the head assembly.

The drawing schematically shows a device for ensuring thermal conditions and cleanliness of GB.

1 - head unit;

2 - spacecraft;

3 - booster block;

4 - gas ducts;

5 - upper divider;

6 - cleanliness control devices;

7 - filter;

8 - flow stimulator;

9 - flow direction control element;

10 - lower divider;

11 - a cover;

12 - head fairing;

13 - valves;

14 - thermostatic elements of the device.

In the method of ensuring the thermal regime and cleanliness of the head block 1 of a space rocket, including the supply of a gas component to the head unit 1 with its discharge from the head unit 1, the gas component is supplied cyclically, starting to supply the gas component to the upper part of the head unit 1 with its release from the lower part of the head unit 1, the end part of which is plugged by a cover 11, alternately changing the direction of the gas component flow to the opposite, and in the last cycle after obtaining a given purity ha ovogo component thereof is fed into the upper part of the head unit 1, and ejection is performed from a lower portion of the head block 1, thus creating a head unit 1 overpressure feed gas component. The composition of the device for implementing the method of ensuring the thermal regime and cleanliness of the head block 1 of a space rocket, including a filter 7, cleans the gas component coming to the inlet of the flow inductor 8, a flow inducer 8, supplying the gas component through the gas ducts 4 to the head unit 1, gas ducts 4, thermostatic elements of the device 14, ensuring the maintenance of the thermal regime of the head unit 1, additionally introduced a control element for the direction of flow 9 of the gas component, which is connected to the thermos by gas ducts 4 tating elements of the device 14 and with valves 13 for the discharge of the gas component from the head unit 1, purity control devices 6 for the gas component that are installed on the gas ducts 4, valves 13 for the discharge of the gas component connected by gas ducts 4 to the dividers 5 and 10 of the gas component flow, upper and lower dividers 5 and 10 of the gas component stream, mounted respectively on the upper and lower parts of the head fairing 12, and a cover 11 mounted on the end face of the head unit 1, the upper and lower dividers 5 and 10 of the gas stream th component incorporated into the head unit 1.

A device for implementing the method of ensuring the thermal regime and cleanliness of the head block 1 of a space rocket, including a filter 7, which purifies the gas component that enters the inlet of the flow inductor 8, a flow inducer 8, which supplies the gas component through gas ducts 4 to the head unit 1, gas ducts 4, thermostatic elements device 14, ensuring the maintenance of thermal conditions of the head unit 1, operates as follows.

A cover 11 is installed on the open part of the head unit 1 to create a closed volume in the head unit 1, then the head unit 1 is cyclically purged.

The gas component is supplied at a rate that ensures the entrainment of contaminants from the surfaces of the components of the head unit 1.

The purge cycle consists of feeding a flow rate 8 to the upper part of the head unit 1 of the gas component, cleaned by the filter 7 and with the temperature obtained using thermostatic elements of the device 14 (for example, electric heaters and coolers), while the gas component flows through the upper divider 5 into the cavity head unit 1 and is ejected from the bottom of the head unit 1 through the bottom valve 13.

At the exit of the head unit 1, the purity control device 6 monitors the gas component. Upon receipt of a predetermined purity value of the gas component, the flow direction is reversed using the flow direction control element 9 (for example, a controlled damper).

The upper divider 5 and the lower divider 10 of the gas component stream are introduced into the head unit 1 to ensure uniform distribution of the gas component stream inside the head unit, eliminating the directed action of the stream jets on structural elements of the head unit 1 components (thermal insulation, optics, solar panels, etc. ), and gas ducts 4, a purity control device 6 of the gas component, a filter 7, a flow inducer 8, a flow control element 9 of the gas component, valves 13 and cover 11 are used for a while ensure the purity and thermal regime of the head unit 1.

The first and last purge cycles of the head unit 1 provide for the mandatory supply of a gas component to the upper part of the head unit 1 with the release of the gas component from the lower part of the head unit 1 in order to prevent the transfer of contaminants to the spacecraft located in the upper part of the head unit 1 from other components of the head unit 1.

The introduction of a new method and device to ensure thermal conditions and cleanliness of the head unit 1

- allows you to combine the provision of high quality purity of the head unit 1 with the simultaneous provision of thermal conditions;

- allows you to additionally solve the problems of fire and explosion safety, moisture protection and, as a result, the reliability of the removal of SC 2 when using the corresponding inert dry gases;

- prevents the penetration of untreated atmospheric air into the head unit 1;

- allows you to improve the mass characteristics of the head unit 1 due to the rejection of the structures that separate the spacecraft 2 from the rest of the space under GO 12, which leads to an increase in the mass of the payload by about 5%.

Implementation of the invention is possible on existing ILVs of the Soyuz, Zenit-3 SL type (sea launch), Proton and the newly developed ILV.

Claims (2)

1. A method of ensuring the thermal regime and cleanliness of the head block of a space rocket, comprising supplying a gas component to the head block and then ejecting it from the head block, characterized in that the gas component is supplied cyclically, starting to supply the gas component to the upper part of the head block with emission it from the bottom of the head unit, the end part of which is plugged by a lid, alternately changing the direction of the gas component flow to the opposite, and in the last cycle after the floor For a given purity of the gas component, it is supplied to the upper part of the head unit, and the emission is carried out from the lower part of the head unit, while creating an excess pressure in the head unit of the supplied gas component. 2. A device for ensuring the thermal regime and cleanliness of the head block of a space rocket, including a filter that cleans the gas component that enters the inlet of the flow inducer, a flow inducer that feeds the gas component through the gas ducts to the head block, gas ducts, thermostatic elements of the device that maintain the thermal regime of the head block , characterized in that it further introduced a control element for the direction of flow of the gas component, which is connected by gas ducts to thermostatic elements device and with valves for the discharge of the gas component from the head unit, control devices for the purity of the gas component that are installed on the gas ducts, valves for the discharge of the gas component connected by gas ducts to the flow dividers of the gas component, the upper and lower flow dividers of the gas component, mounted on the upper and lower parts the head fairing, and a cover mounted on the end face of the head unit, the upper and lower flow dividers of the gas component being introduced into the head unit.