| 摘要 |
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 positioned at the centre of the surface of revolution (40), and said surface of revolution comprises a first portion (411) forming a solar concentrator for concentrating solar radiation in the direction of said heat engine and a second portion (412), coaxial with the first portion (411), and such that the first portion (411) and the second portion (412) form, relative to each other, a Cassegrain solar concentrator, of which a focal point is located at the heat engine. |
