Spacecraft architecture having torus-shaped solar concentrator
US10450092B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Dec 8, 2014 |
| Grant date | Oct 22, 2019 |
| Priority date | — |
| Expiry date | Sep 5, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02E10/52
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A spacecraft includes: a body a surface of revolution connected with the body, and a heat engine positioned at the center of the surface of revolution. The surface of revolution has a substantially open hollow torus shape with a transverse cross-section of a circle and two diametrically opposite portions each having a curvature extending from the circle. A first portion of the diametrically opposite portions has an opening and forms a solar concentrator for concentrating solar radiation in the direction of the heat engine. The first portion forms a primary solar radiation reflector. A second portion of the diametrically opposite portions is coaxial with the first portion and forms a secondary solar radiation reflector. The opening is configured so that the solar radiation passes in the direction of the center of the surface of revolution after reflection at the primary and secondary reflectors.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.