Abstract: A space solar concentrator based on deployable reflectors attached to a panel base is described. Each of the reflectors includes sides coated with reflective coating on surfaces facing away from the base. In one embodiment, the sides of the reflector have thicker portion to provide stiffness for deployment absent compressive force, and thinner portion to reduce weight and storage energy. In another embodiment, both reflective sides are unfolded when the reflectors are in stowed position. During deployment, a stop side will limit the deployment of both reflective sides and ensure the proper reflecting position. In addition, these embodiments reduce the storage energy.

Abstract: A space solar concentrator based on deployable reflectors attached to a panel base is described. Each of the reflectors includes sides coated with reflective coating on surfaces facing away from the base. In one embodiment, the sides of the reflector have thicker portion to provide stiffness for deployment absent compressive force, and thinner portion to reduce weight and storage energy. In another embodiment, both reflective sides are unfolded when the reflectors are in stowed position. During deployment, a stop side will limit the deployment of both reflective sides and ensure the proper reflecting position. In addition, these embodiments reduce the storage energy.

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: The invention provides a method of assembling an optical assembly having first and second longitudinal ends and comprising N coaxial shells forming individual mirrors, each of which extends between said first and second ends and presents a first diameter at said first end and a second diameter that is greater than the first at said opposite, second end, the method comprising: 1) putting the first end of the first shell situated outermost in the optical assembly into place on a support; 2) putting the first end of the second shell which is immediately adjacent thereto in the optical assembly into place on the support inside the first shell; . . . ; and N) putting the first end of the Nth shell which is situated innermost in the optical assembly into place on the support.

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