RU2053937C1 - Space vehicle - Google Patents

Abstract

FIELD: cosmonautics. SUBSTANCE: space vehicle has hermetic casing and solar power plant; space vehicle is provided with nontight containers made in form of parallelepiped at small height and ratio of outer surface of container to area of its base not exceeding 2.0; arranged inside containers are storage batteries. Space vehicle is also provided with control equipment for monitoring the solar power plant as well as with devices ensuring the required thermal conditions of solar power plant. Non-tight containers are articulated on casing of space vehicle and are locked in unfolded position relative to casing of space vehicle with the aid of retainers. Solar-battery panels are articulated on lateral surface of nontight containers for turning them in one plane with containers and oriented for checking and monitoring the solar power plant arranged inside nontight containers are made in nontight to height of nontight container; their bases are linked with bases of nontight container by means of heat-transfer members; heat-transfer member are used as radiators for radiation removal of heat. Thus volume of hermetic casing of space vehicle is reduced, reliability is enhanced and service life of units and devices is increased due to optimal thermal conditions of operation and due to avoidance of shading of photocells of solar power plant by casing of space vehicle. EFFECT: enhanced reliability of functioning and volume-and-mass characteristics of space vehicle. 3 cl, 5 dwg

Description

 The invention relates to the construction of spacecraft (SC), in particular to the design of a spacecraft with a solar power plant, namely, the layout of the spacecraft.

 The closest known apparatus is a spacecraft containing a sealed enclosure and a solar power plant, including a solar panel (SB), a battery, control and monitoring equipment for a solar power plant, and means to ensure its fuel mode [1]. The disadvantages of the known spacecraft are that when operation of a spacecraft of such a design in a near-earth orbit with a spacecraft orientation in the orbital coordinate system, part of the solar panel panels will inevitably be obscured by the spacecraft construction elements (antennas, spacecraft body), which leads to a decrease in the power generated by the solar battery and even to the failure of certain groups of photovoltaic converters. Applied protective measures are not effective enough. By moving the solar panel further away from the spacecraft hull, the effect of partial shading of the panels on the characteristics of the photoelectric converters can be reduced.

 The technical task of this invention is to increase the reliability of operation and improve the space-mass characteristics of the spacecraft.

 This goal is achieved in that the spacecraft containing a sealed enclosure and a solar power plant, including SB panels, batteries, control and monitoring equipment for the solar power plant and means for ensuring its thermal regime, is equipped with leaky containers having a parallelepiped shape with a small height and the ratio of the outer surface area of the container to the area of its bases not more than 2.0, with batteries located inside them, control and monitoring equipment of the solar power installation and redstvami ensure its thermal mode, wherein the leaky containers are hinged on the spacecraft body and provided with retainers deployed position relative to the container body spacecraft.

 In addition, the SB panels are pivotally mounted on the lateral surface of leaky containers with the possibility of turning them in the same plane with the containers and orienting them to the Sun. Also, the batteries and control and monitoring equipment of the solar power plant are equipped with leaky housings made in the form of a parallelepiped with a low height corresponding to the height of the leaky container, the bases of which are connected by heat transfer elements to the bases of the leaky container, made in the form of radiating heat radiation for radiation.

 In FIG. 1 shows a spacecraft with a solar power plant, with complex SB panels; in FIG. 2 the same, with partially opened SB panels; in FIG. 3 the same with open SB panels; in FIG. 4 construction of an unpressurized container; in FIG. 5 a section along AA in FIG. 4.

 The spacecraft contains a housing 1, on which two disclosed units 2 are mounted to the housing 1, located symmetrically on both sides and containing the solar panel 3 panels (Fig. 1 in folded, Fig. 3 in the open position). Batteries, control and monitoring equipment for the solar power installation, and thermal management equipment for the solar power installation are located in two leaky containers 4. The deployment sequence of the leaky containers and the solar battery is shown in FIG. 1, 2, 3. The wings of the solar battery are pivotally mounted on the lateral surface of leaky containers, that is, for a fully deployed design, it is characteristic that the shadows from the spacecraft's body elements at the position of the Sun at an angle to the plane of the spacecraft’s orbit will fall on the leaky containers, and not on the solar panel. In addition, the panels of the solar battery can be oriented to the Sun by changing their position relative to the motionless (after the deployment of the solar power plant) leaky containers.

 Inside the leaky container, batteries 5, control and monitoring equipment for the solar energy battery, consisting of discharge-charging devices 6, excess power regulators 7 control units 8 and means for providing warm mode, consisting of heat pipes 9 thermal contacts 10 and radiators for radiation heat rejection 11 are installed .

 During the operation of the spacecraft, the thermal regime of the batteries and the control and monitoring equipment of the solar power installation is ensured using heat pipes by heat transfer from the heat-generating equipment and batteries through thermal contactors breaking open the thermal bridges when the temperature inside the instrument container drops to a threshold value, after which further heat removal abruptly reduced due to thermal insulation laid between the batteries, control and monitoring equipment with solar power plant and the surface of the leaky container.

 This invention allows for optimal thermal operation of batteries and control equipment and control of a solar power plant, which increases the life of the spacecraft.

Claims (3)

 1. SPACE VEHICLE, comprising a sealed enclosure and a solar power plant, including solar panels, batteries, control and monitoring equipment for a solar power plant and means for providing thermal conditions, characterized in that it is equipped with leaky containers having a parallelepiped shape with a small height and an area ratio the outer surface of the container to the area of its bases is not more than 2.0, with batteries located inside them, control and monitoring equipment for solar power plant, means to ensure its thermal regime, while leaky containers are pivotally mounted on the spacecraft body and equipped with latches for the deployed position of the containers relative to the spacecraft body.  2. The apparatus according to claim 1, characterized in that the solar panel is pivotally mounted on the side surface of leaky containers with the possibility of turning them in the same plane with the containers and orienting them to the Sun.  3. The apparatus according to claim 1, characterized in that the batteries and control and monitoring equipment of the solar power installation are equipped with leaky housings made in the form of a parallelepiped with a low height corresponding to the height of the leaky container, the bases of which are connected by heat transfer elements to the bases of the leaky container, made in the form of emitters for radiation heat dissipation.

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