RU2673439C1 - Method for temperature control of onboard equipment of payload located inside head fairing of space head part of space rocket, and device for its implementation - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: group of inventions relates to the aerospace equipment. Method of temperature control of the onboard equipment of the payload (PL) located inside head fairing (HF) of the space head part (SHP) of space rocket (SR), includes blowing a thermostatic medium into the inner space of HF, its flowing over along HF with subsequent expiration from it. Supply is carried out forcibly from the internal space of HF to the PL compartment through its injection hole with the subsequent outflow of the medium from the PL compartment to the internal space of the HF through the discharge hole. Injection of a thermostatic medium into the PL compartment is carried out only for a given range of medium temperatures in the inner space of HF. Method is implemented by a thermostatic device, which includes a hole for the injection of a thermostatic medium, a hole for its flow into the HF, and a device for the injection of a thermostatic medium into the internal space of the HF. In the maintenance hatch of the onboard equipment of the PL compartment, a removable cover is installed, in which an injection hole is made for the forced flow of a thermostatic medium by means of a fan.EFFECT: technical result of the group of inventions is to increase the efficiency of temperature control.3 cl, 2 dwg

Description

The invention relates to rocket and space technology, and is intended to provide the temperature regime of on-board equipment (BA) of a payload (GH) at the stages of preparation for launch when it is placed inside the head fairing (GO) of the assembly-protective block of the space head part (GH) of the space rocket destination (ILV).

There is a method of thermostating the instrument compartment of the acceleration block of the KGCH launcher and the on-board system for its implementation (patent RU No. 2279377), which includes blowing the thermostatic medium into the PG block and at the same time into the accelerating block, its flow from the PG block to the accelerating block, followed by expiration from at least the booster unit, moreover, the thermostatic medium is injected into the booster unit from the side of its lateral surface in the direction tangential to the lateral surface of the instrument compartment, thermostatically blowing and flowing her environment from the shell of the instrument compartment remove the heat released during operation of the instrument compartment during pre-launch preparation. Injection of the medium is carried out by subsonic diffusers in the form of two or more curved nozzles.

A known method of temperature control of the GHG of the head unit of the launch vehicle and the on-board system for its implementation (patent No. RU 2359878 is a prototype), which includes blowing the thermostatic medium into the head unit, its flowing along the head unit, during which provide thermal operation of the GHG, and spin with the flow of thermostatic medium in the head unit using a subsonic diffuser in the form of a closed container with three outlet openings.

A device is known for providing thermal conditions and cleanliness of the PHC rocket launcher with large-sized payload (patent RU No. 2557092 - prototype), including two mutually opposite injection holes of a thermostatic gas medium on the head fairing, openings for the expiration of a gas medium, a device for blowing in a thermostatic medium.

A disadvantage of the known thermostating method and thermostating device, selected as prototypes, as well as the technical solution described above, is their low thermostating efficiency if it is necessary to continuously remove excess heat from the hermetically insulated compartment with on-board equipment that constantly generates heat, for example, when the spacecraft is in an airtight compartment apparatus of living organisms with their life support systems.

It is difficult to remove heat from a sealed thermally insulated compartment located in the head fairing:

- due to the presence of thermal insulation on the outer shell of the compartment, creating a high value of thermal resistance of the housing of the compartment, which makes it difficult to transfer heat through the wall,

- due to the impossibility of heat removal from the heat-insulated compartment with constantly on-board heat-generating equipment during forced technological interruptions in the supply of thermostatic medium to the assembly-protective unit or in the supply of coolant from the ground means for providing thermal mode, which removes heat from the circuit of the thermal control system of the steam generator.

The objective of the proposed technical solution is to increase the thermostating efficiency due to the continuous removal of excess heat with the BA heat-generating equipment on-board from the payload compartment.

The problem is solved in that in the method of temperature control of the onboard equipment of the payload placed inside the head fairing of the space head part of the space rocket, including blowing the thermostatic medium into the inner space of the head fairing, flowing along it with the subsequent outflow from it, during which they provide thermal operating mode of the payload onboard equipment during the preparation of the payload as part of the space warhead for launch space rockets, according to the invention, force-feed the thermostatic medium from the inner space of the head fairing to the payload compartment through its injection hole, followed by the outflow of thermostatic medium from the payload compartment into the internal space of the head fairing through the exhaust hole, while blowing the thermostatic medium into the payload compartment is carried out only at a given range of medium temperature values in the inner space of the head space Katel.

The method, characterized in that the forced supply of thermostatic medium from the inner space of the head fairing to the payload compartment is carried out at a temperature of the medium in the inner space of the head fairing in the range from (16 ± 2) ° C to (26 ± 2) ° C.

Thermostatting device for the onboard equipment of a payload placed inside the head fairing of the space head part of a space rocket, including a hole for blowing in a thermostatic medium, a hole for its expiration in the head fairing, devices for blowing the thermostatic medium into the inner space of the head fairing, according to the invention, in the maintenance hatch of the onboard equipment of the compartment of the payload, a removable cover is installed in which a blow hole is made under the forced supply of thermo a static medium by means of a fan interacting with its control device, with sensors installed in it that determine the temperature of the thermostatic medium in the inner space of the head fairing, while the control device and the power supply interacting with it are installed on a removable cover in which the outlet of the thermostatic medium flows in interior space of the head fairing.

The essence of the technical solution is illustrated by the drawings:

FIG. 1 - shows a General view of the thermostatic control device BA PG located inside the GO;

FIG. 2 - a remote element A of FIG. 1 (removable, cover on the BA service manhole cover).

The thermostatic control device for the on-board equipment 1, in the payload compartment 2 located inside the head fairing 3, in which the blowing holes 4 are made and the expiration holes 5 contain a blowing device 6 for the thermostatic medium in the inner space of the head fairing 3, while in the service hatch 7 of the on-board equipment 1 payload compartment 2 has a removable cover 8, which has a blowing hole 9 for forced supply of thermostatic medium, carried out by means of a fan 10 installed in the hole and blowing 9. The fan control device 11 and the power supply 12 are mounted on a removable cover 8, in which a thermostatic fluid outlet 13 is made into the interior of the head fairing 3. In the fan control device 11, sensors 14 are installed that determine the temperature of the thermostatic medium in the head space fairing 3.

The removable cover 8 is installed before assembling the KGCH. After the start of the temperature control of steam generator 2 from the systems of the launch complex, the removable cover 8 is removed and a standard sealed cover is installed on the service hatch 7 (not shown in the drawing).

The claimed method of thermostating the onboard equipment of a payload placed inside the head fairing of the space head part of a space rocket is as follows.

The thermostatic medium is fed into the inner space of the head fairing 3 through the holes of the blower 4 by means of the blowing device 6 with its subsequent flowing along the head fairing 3 and out of the space through the openings of the outlet 5, ensuring the thermal operation of the onboard equipment 1 in the payload compartment 2.

By means of a fan 10, a thermostatic medium is forcedly supplied from the internal space of GO 3 to the SG 2 compartment through its injection hole 4, while thermostatic medium is blown into the SG 2 compartment only at a given range of temperature values of the medium in the internal space of GO 3, which is determined by sensors fourteen.

Received thermostatic medium from the space inside the GO 3 forcibly enters the SG 2 compartment, mixes with air heated from the functioning BA 1, thereby cooling it in the SG 2 compartment to the temperature values required by the BA 1 operating conditions. Further, the mixed heated thermostatic medium is discharged into the interior of GO 3 and is discharged from it through the outlet 5 to the environment. In case of termination of the supply of thermostatic medium, the temperature conditions of operation of BA 1 in the SG 2 compartment are provided due to the inertial temperature reserves of the structural elements of the SG 2 compartment.

Blowing the thermostatic medium into the SG 2 compartment is carried out only at a given range of temperature values of the medium in the internal space of GO 3.

For example, to ensure the temperature of the medium in the SG 2 compartment in the range from 17 ° С to 28 ° С, in accordance with the temperature conditions of operation of BA 1, the range of the temperature of the medium in the internal space of GO 3 from (16 ± 2) ° С can be set up to (26 ± 2) ° С, at which the thermostatic medium is forcedly supplied to the SG 2 compartment by means of a fan 10, which is connected to a power supply 12 by the fan control device 11.

When the temperature of the thermostatic medium in the internal space of GO 3 is lower than the minimum value, or if it increases above the maximum value of the boundaries of the specified range, the flow of the thermostatic medium into the SG 2 compartment stops. To prevent cessation of the supply of thermostatic medium to the SG 2 compartment, it is necessary to maintain a predetermined temperature range in the area of the SG 2 compartment by controlling the temperature of the thermostatic medium injected into GO 3 through the holes of the blower 4.

Thus, the claimed technical solution allows for the removal of excess heat from an airtight heat-insulated compartment with a constantly heat-generating BA during the preparation of the GHG as a part of the OGC to launch the ILV, thereby ensuring the efficiency of the method.

Claims (3)

1. The method of temperature control of the onboard equipment of a payload placed inside the head fairing of the space head part of a space rocket, including blowing the thermostatic medium into the inner space of the head fairing, flowing along it with the subsequent outflow from it, during which the thermal mode of functioning of the onboard equipment of the useful cargo during the preparation of the payload as part of the space warhead for launching a space rocket, excellent characterized in that the thermostatic medium is forcedly supplied from the inner space of the head fairing to the payload compartment through its injection hole, followed by the outflow of the thermostatic medium from the payload compartment into the internal space of the fairing through the exhaust hole, while thermostatic medium is blown into the payload compartment only for a given range of temperature values of the medium in the inner space of the head fairing. 2. The method according to p. 1 characterized in that the forced supply of thermostatic medium from the inner space of the head fairing to the payload compartment is carried out at a temperature of the medium in the inner space of the head fairing in the range from (16 ± 2) to (26 ± 2) ° C. 3. Thermostatting device for the onboard equipment of the payload placed inside the head fairing of the space head part of the space rocket, including the hole for blowing in the thermostatic medium, the hole for its expiration in the head fairing, the device for blowing the thermostatic medium into the inner space of the head fairing, characterized in that in the onboard maintenance hatch payload compartment equipment has a removable cover, in which an injection hole is made for forced flow of thermostat of the heating medium by means of a fan interacting with its control device, with sensors installed in it that determine the temperature of the thermostatic medium in the inner space of the head fairing, while the control device and the power supply interacting with it are installed on a removable cover, in which the outlet of the thermostatic medium flows out interior space of the head fairing.

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