RU2661270C1 - Device for temperature control of on-board equipment of the payload within the space nose cone - Google Patents

Abstract

FIELD: rocket equipment.

SUBSTANCE: invention relates to prelaunch preparation means for the space nose cone of a rocket with payload (2) comprising on-board equipment (OBE) (1). Device includes screen-vacuum thermal insulation (SVTI) (3) on the surface of payload (2), radiator-cooler (4) in the form of power shell (9) of payload, thermostatic gas injection (6) and discharge (7) holes. OBE (1) is installed on heat-conducting panel (8). Between the surfaces of radiator (4) and panel (8) there is a gap (gas interlayer). Radiator (4) and panel (8) are provided with thermoregulating coatings (5) and (11) with a high degree of blackness. In SVTI (3), cutout (10) for the heat removal by radiation is made under panel (8).

EFFECT: expansion of operational capabilities and increased reliability of temperature control of on-board equipment located in non-hermetic compartments of payload when conducting pre-start electrical switch-ons.

1 cl, 2 dwg

Description

The invention relates to rocket and space technology and is intended to provide the temperature regime of the payload (GH) and its on-board equipment during the prelaunch preparation of the space warhead (KCH) of a space rocket (ILV).

In particular, the launch unit as part of the KGCH, which is put into orbit by a launch vehicle, can be considered a payload.

At present, on modern GHGs, there is a need for thermostating of on-board equipment in GHG compartments located under the head fairing (GO) during the pre-launch preparation (when it is worked out in ground conditions) until the launch of the rocket launcher.

This is dictated by the fact that during pre-launch preparation of products, removal of excess heat is required, for example, when recharging batteries during long-term parking at the start, as well as during electrical checks of devices that remove excess heat through their landing surfaces.

Known on-board thermostat system of the steam generator and control system devices RG PH (patent RU No. 2353556 - analogue), including the injection hole of thermostatic medium (TS) in the RG with diffusers and the outlet of the medium, providing flow over the length of the RG TC and its expiration, during which provide the thermal mode of functioning of the spacecraft and control system instruments during prelaunch preparation of the KSCh ILV.

A disadvantage of the known technical solution is that for effective heat removal by interference flow around the devices, the devices must be in the vehicle flow and the heat sink from the devices must be carried out from the entire surface of the device. If the heat sink surfaces are the instrument seats and the instruments are located inside the SG compartments, the known thermostatic control device is ineffective. For example, for equipment installed in leaking compartments of the steam generator.

The well-known “System for ensuring the thermal regime of the inter-orbit space tugboat“ Frigate ”” (UDC 629.78.06-533.6 “Frigate”, Bulletin of the NPO named after SA Lavochkin, 2014, No. 1 (22), pp. 37-40), including gas-circulating thermal control systems, screen-vacuum thermal insulation (EVTI), radiators, providing the thermal regime of the instrument hermetic compartments. Gas circulation along the circuit of each compartment is carried out by fans. Gas passing along the design of the instrument compartments enters heat exchange with the equipment units inside the compartments. The main part of the heat flux is diverted to the radiator-cooler zone and radiated into space or at the prelaunch stage, at the launch complex (SC) as a part of the rocket launcher, is diverted to the air environment under the civil defense. As a radiator, the surfaces of the covers of each of the instrument compartments are used. This temperature control device is adopted as a prototype.

A disadvantage of the known technical solution is that:

- this system cannot be used in unpressurized GHG compartments during orbital flight due to the lack of a gas medium in the compartments. The use of this system in unpressurized compartments only during prelaunch preparation leads to an increase in the mass of GHG launched into orbit due to the mass of the gas circulation system that is not used during normal operation of GHG in flight;

- the use of fans reduces the reliability of the system due to the possibility of loss of their performance;

- in leaky compartments, where heat fluxes are removed from the on-board equipment to their seats, a known device (the Fregat inter-orbiting space tug thermal supply system) is ineffective due to the small areas of the heat-transfer surfaces.

The objective of the proposed technical solution is to expand operational capabilities and increase the reliability of thermostating of heat-generating on-board equipment of the steam generator during electrical switching at the stage of pre-launch preparation at the SC, in the case of placing the on-board equipment in unpressurized compartments of the steam generator.

This problem is achieved by the fact that in the temperature control device of the onboard GHG equipment as part of the KGCH, including screen-vacuum thermal insulation on the outer surface of the GHG, a radiator-cooler, on the surfaces of which are applied thermostatic coatings, injection holes and the expiration of the gas thermostatic component in the KGCh, in place of installing on-board GHG equipment on a heat-conducting panel as a radiator-cooler, the power shell of the GHG is used, with a cutout in the screen-vacuum thermal insulation of the GHG in the location of the heat-conducting panel, the size of which must correspond to the size of the heat-conducting panel, and a heat-regulating coating is applied to the heat-conducting panel from the side of the payload cooler-radiator and it is installed relative to the payload cooler-radiator with a gap forming a gas layer.

In FIG. 1 and FIG. 2 presents the claimed device.

In the thermostatic control device BA 1 PG 2 as a part of KGCh RKN, including screen-vacuum thermal insulation 3 on the outer surface of PG 2, a radiator-cooler 4, on the surfaces of which are applied temperature-controlled coatings 5, blow-in and outlets 6, 7 of the gas thermostatic component in the space the head part, which provides the thermal regime of a functioning BA 1 PG 2, is introduced at the installation site of BA 1 PG 2 on a heat-conducting panel 8 as a radiator-cooler 4, using a power shell 9 PG 2, with a cutout of 10 screen-vacuum thermal insulation 3 GHG 2 in the area of the heat-conducting panel 8, and on the heat-conducting panel 8 from the side of the radiator-cooler 4 PG 2 is coated with a temperature-regulating coating 11 and it is installed relative to the radiator-cooler 4 PG 2 with a gap λ, forming a gas layer.

The thermostatic control unit BA 1 PG 2 as a part of KGCH ILV works as follows.

The heat generated from the operating BA 1 PG 2 is evenly distributed over the heat-conducting panel 8. To reduce the contact thermal resistance between BA 1 and the heat-conducting panel 8 at the contact point, for example, heat-conducting paste is applied (not shown in the drawing).

From the heat-conducting panel 8, heat is transferred to the radiator-cooler 4 of the steam generator 2 by the radiation flux, as well as by free convection and thermal conductivity of the gaseous medium layer. To maximize the radiation flux, a heat-regulating coating 11 with a high degree of blackness, for example, more than 0.85, is applied to the heat-conducting panel 8 from the side of the radiator-cooler 4. Thermoregulatory coatings 5 with a high degree of blackness are applied to the inner and outer surfaces of the radiator-cooler 4 of PG 2, for example, TP-СО-ЦМ with a degree of blackness of more than 0.9.

From the outer surface of the radiator-cooler 4 PG 2 in the place where the cut-out 10 is made in the screen-vacuum thermal insulation 3, heat is transferred by convective heat exchange to the thermostatic medium under the GO and radiant heat exchange to the surface of the multilayer insulation of the GO.

The use of the claimed thermostat BA BA thermostat will expand the operational capabilities and increase the reliability of temperature control of the onboard GHG equipment as part of the KGCH rocket launcher during prelaunch preparation in case of electrical inclusions and checks of the onboard equipment located in the unpressurized compartments of the GHG.

Claims (1)

Thermostatting device for the onboard equipment of the payload as part of the space head part, including screen-vacuum thermal insulation on the outer surface of the payload, a radiator-cooler, on the surfaces of which are applied thermostatic coatings, injection holes and the expiration of the gas thermostatic component in the space head part, characterized in that in the place of installation of the onboard equipment of the payload on the heat-conducting panel, a power shell is used as a radiator-cooler payload with a cutout in the screen-vacuum thermal insulation of the payload in the zone of location of the heat-conducting panel, and the size of the cut-out should correspond to the size of the heat-conducting panel, on which a heat-regulating coating is applied from the side of the heat sink-cooler, while the panel is installed relative to the heat sink-cooler cargo with a gap forming a gas layer.

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