Abstract: A solar concentrator module comprising a front lens on its front face, a receiver cell on its rear face and a reflector between the front lens and the receiver cell, said reflector having inclined sidewalls along at least two opposite sides of the receiver cell characterised in that the reflectors are truncated and in that the sidewalls of the reflectors are inclined in such a way that, for a 0[deg] off-pointing, solar rays are reflected on the inclined side walls of the reflectors before impinging on the receiver cell, to produce a relatively uniform illumination on the receiver cell for a range of off pointing acceptance angle superior to zero degree.

Abstract: A solar concentrator module comprising a front lens on its front face, a receiver cell on its rear face and a reflector between the front lens and the receiver cell, said reflector having inclined sidewalls along at least two opposite sides of the receiver cell characterised in that the reflectors are truncated and in that the sidewalls of the reflectors are inclined in such a way that, for a 0 [deg] off-pointing, solar rays are reflected on the inclined side walls of the reflectors before impinging on the receiver cell, to produce a relatively uniform illumination on the receiver cell for a range of off pointing acceptance angle superior to zero degree.

Abstract: A space solar concentrator based on light-weight reflectors (3) attached to a honeycomb panel (1) is described. The integration of the reflectors (3) allows for a high modularity. Solar panel deployment is not perturbed by the reflectors (3) even with two-dimensional deployment concept. Each reflector (3) consists in small saw tooth aligned as rows (2) with solar cell rows in between. Low concentration is achieved with a high level of thermal control and a high optical efficiency. When small off-pointing occurs, the solar flux distribution is still the same on each cells. It guarantees a good electrical control and management on the whole panel. The reflectors (3) are preferably made of a thin film tight on a light-weight rigid frame deployed after launch. In another embodiment, the reflector is not deployable and is part of the panel substrate. A stowed configuration allows for superimposition of the solar panel.

Abstract: A space solar concentrator based on light-weight reflectors (3) attached to a honeycomb panel (1) is described.