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spacecraft structure

A technology of spacecraft and concentrator, applied in the field of spacecraft

Active Publication Date: 2018-04-03
EUROPEAN AERONAUTIC DEFENCE & SPACE CO EADS FRANCE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The number of solar panels, drive means, high-efficiency photovoltaic coatings or also wing orientation means required to operate an orbiting satellite constitutes a far non-negligible cost of the total cost of the satellite and may add up to as much as 20% of the total cost

Method used

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Embodiment Construction

[0056] The invention will now be described in the non-limiting context of satellite 10 . The invention relates more particularly to satellites arranged in geosynchronous orbits, and in particular geostationary orbits, and stabilized such that one particular axis of the satellite remains directed towards the earth.

[0057] The invention can also be applied to all spacecraft, such as space probes or exploration probes.

[0058] figure 1 The general structure of a satellite 10 according to one embodiment is schematically shown in a deployed state when said satellite is in orbit.

[0059] Satellite 10 comprises body 20, in figure 1 In the figure, the body 20 is shown in a non-limiting manner as a solid rectangle, the body 20 having a first face 21 oriented towards the earth 80, and a second face 22 opposite said first face.

[0060] Body 20 generally includes the tank, payload, equipment housing, and onboard electronics.

[0061] Satellite 10 includes at least one antenna 3...

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Abstract

The invention relates to a spacecraft (10) comprising a body (20), a surface of revolution (40) rigidly connected to said body, the spacecraft comprising a heat engine, and the surface of revolution comprises a first part (411) and a second part (412), wherein the first part (411) forms a solar concentrator for concentrating solar radiation in the direction of the heat engine, and the second The part (412) is coaxial with the first part (411), so that the first part (411) and the second part (412) form a Cassegrain type solar concentrator with respect to each other, the Cassegrain type solar concentrator The focal point of the device is located at the heat engine.

Description

technical field [0001] The invention belongs to the field of spacecraft. More specifically, the invention relates to spacecraft having structures for generating electrical power. Background technique [0002] In a manner known per se, today's satellites are provided with a body, an antenna for radio transmission, and "wings" located on both sides of said body in an approximately symmetrical manner, the "wings" comprising the Solar panels that power satellites. [0003] It is also known that each wing is formed into a deployable structure such that the space occupied by each wing is minimal at the time of satellite launch, and once the satellite is in orbit, each wing is Both adopt their working size and position. Each wing thus comprises a set of solar panels supporting photovoltaic cells, said solar panels being hinged together so that they can occupy either a folded launch position or a deployed operating position, wherein in the folded launch position the solar panels ...

Claims

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Application Information

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IPC IPC(8): B64G1/22B64G1/44F24S30/422F24S70/20H01L31/052H01L31/054H01Q1/28H01Q15/16
CPCH02S30/10H02S10/40B64G1/423B64G1/503Y02E10/52B64G1/446B64G1/2227B64G1/2224B64G1/4021B64G1/2226B64G1/222B64G1/402
Inventor 让-弗朗索瓦·热内斯特
Owner EUROPEAN AERONAUTIC DEFENCE & SPACE CO EADS FRANCE
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