Artificial satellite

A technology for artificial satellites and battery packs, applied in artificial satellites, space navigation equipment, space navigation equipment, etc., can solve the problems of time-consuming installation, high cost, low thermal conductivity, etc., to reduce power consumption, time and cost Effect

Active Publication Date: 2018-04-03
AIRBUS DEFENCE & SPACE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, it is very time-consuming to install
In addition, the bracket 34 supporting the p

Method used

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Examples

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Embodiment Construction

[0047] This invention relates to the field of artificial satellites, in particular geosynchronous satellites.

[0048] refer to Figure 3B , the artificial satellite 38 according to the first embodiment of the present invention comprises a cubic or parallelepiped box 40 comprising an opposite-earth face 46, a hollow central structure 44 resting on the opposite-earth face 46, an earth face 42, carrying equipment items The east and west faces (not shown) and the north 48 and south 50 faces that host radiators and equipment items.

[0049] The satellite according to the invention also comprises a propulsion system, which may be a chemical propulsion system or a plasma propulsion system (not shown in the figures) or constituted by using a combination of these types of propulsion systems.

[0050] The propulsion system includes a propellant storage and distribution system 52 and two or more nozzles 54 mounted on the opposite-Earth face 46 .

[0051] Propellant storage and distrib...

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PUM

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Abstract

The invention relates to an artificial satellite comprising an accumulator (62) apt to dissipate heat, at least one radiator (64) able to remove to space the heat dissipated by the accumulator (62), and a piece of equipment (52) that is said to be not very dissipative and that possesses an individual power density per unit area lower than 250 watts/m2, characterised in that it INC.ludes a thermally insulating cover (66) bounding, with said radiator (64), an isothermal interior zone (68) in which temperature is controlled by radiation, said accumulator (62) and said piece of not very dissipative equipment (52) being arranged under said thermally insulating cover (66), and in that said accumulator (62) has an operating range comprised between 0DEG Cand 50DEG Cand, preferably, between 10DEG Cand 30DEG C.

Description

technical field [0001] This invention relates to the field of artificial satellites, in particular geosynchronous satellites. [0002] In particular, the invention relates to thermal control of satellites. Background technique [0003] Satellites include equipment such as batteries, payloads, onboard computers, and more. These items of equipment must be thermally controlled to ensure proper operation, and thus ensure that the satellite of interest can successfully complete its mission. Since these items of equipment operate in different temperature ranges, they need to be segregated into compatible temperature zones according to their operating temperature. These areas are surrounded by multiple layers of insulation that are in thermal contact with the heat sink. To simplify the implementation of this isolation, items of equipment operating in similar temperature ranges can be grouped together in the same zone. Isothermal zones that need to be kept at the coldest tempera...

Claims

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Application Information

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IPC IPC(8): B64G1/10B64G1/50B64G1/22
CPCB64G1/10B64G1/22B64G1/50B64G1/226B64G1/425B64G1/58B64G1/503B64G1/283B64G1/402
Inventor 安德鲁·瓦尔克
Owner AIRBUS DEFENCE & SPACE
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