A flexure including a bipod strut pair extending from a base and a titanium-zirconium-niobium alloy, which includes titanium, about 13.5 to about 14.5 wt.% zirconium, and about 18 to about 19 weight% (wt.%) niobium. The titanium-zirconium-niobium alloy has a congruent melting temperature of about 1750 to about 1800° C. (°C).

An electromagnetic radiation collecting and directing apparatus is described herein. The electromagnetic radiation collecting and directing apparatus facilitates directing light from an exterior of a structure to an interior of a structure. The directed light is then distributed as necessary within the structure for heating, illumination, or is stored for use at a later time.

An electromagnetic radiation collecting and directing apparatus is described herein. The electromagnetic radiation collecting and directing apparatus facilitates directing light from an exterior of a structure to an interior of a structure. The directed light is then distributed as necessary within the structure for heating, illumination, or is stored for use at a later time.

A system for fastening a mirror to a support is disclosed including intermediate structures, for example bipod structures. At least some of the intermediate structures are provided with torsion devices making it possible to at least partially compensate for optical aberrations of an instrument that includes the mirror. Each torsion device may comprise an elastic element and a variator. The variator is designed to control a deformation of the elastic element, resulting in a torque which is applied to the mirror.

A system for fastening a mirror to a support is disclosed including intermediate structures, for example bipod structures. At least some of the intermediate structures are provided with torsion devices making it possible to at least partially compensate for optical aberrations of an instrument that includes the mirror. Each torsion device may comprise an elastic element and a variator. The variator is designed to control a deformation of the elastic element, resulting in a torque which is applied to the mirror.

A flexure including a bipod strut pair extending from a base and a titanium-zirconium-niobium alloy, which includes titanium, about 13.5 to about 14.5 wt. % zirconium, and about 18 to about 19 weight % (wt. %) niobium. The titanium-zirconium-niobium alloy has a congruent melting temperature of about 1750 to about 1800° Celsius (° C.).

An aerospace mirror having a reaction bonded (RB) silicon carbide (SiC) mirror substrate, and a SiC cladding on the RB SiC mirror substrate forming an optical surface on a front side of the aerospace mirror. A method for manufacturing an aerospace mirror comprising obtaining a green mirror preform comprising porous carbon, silicon carbide (SiC), or both, the green mirror preform defining a front side of the aerospace mirror and a back side of the aerospace mirror opposite the front side; removing material from the green mirror preform to form support ribs on the back side; infiltrating the green mirror preform with silicon to create a reaction bonded (RB) SiC mirror substrate from the green mirror preform; forming a mounting interface surface on the back side of the aerospace mirror from the RB SiC mirror substrate, and forming a reflector surface of the RB SiC mirror substrate on the front side of the aerospace mirror. Additionally, the method can comprise cladding the reflector surface of the RB SiC mirror substrate with SiC to form an optical surface of the aerospace mirror.

An aerospace mirror having a reaction bonded (RB) silicon carbide (SiC) mirror substrate, and a SiC cladding on the RB SiC mirror substrate forming an optical surface on a front side of the aerospace mirror. A method for manufacturing an aerospace mirror comprising obtaining a green mirror preform comprising porous carbon, silicon carbide (SiC), or both, the green mirror preform defining a front side of the aerospace mirror and a back side of the aerospace mirror opposite the front side; removing material from the green mirror preform to form support ribs on the back side; infiltrating the green mirror preform with silicon to create a reaction bonded (RB) SiC mirror substrate from the green mirror preform; forming a mounting interface surface on the back side of the aerospace mirror from the RB SiC mirror substrate, and forming a reflector surface of the RB SiC mirror substrate on the front side of the aerospace mirror. Additionally, the method can comprise cladding the reflector surface of the RB SiC mirror substrate with SiC to form an optical surface of the aerospace mirror.

An optical device can deal with a relative difference in thermal expansion coefficient between a reflecting mirror and a mirror supporting member, and can also support the reflecting mirror with a simpler structure than the conventional one. The optical device includes: a reflecting mirror including a reflecting surface to reflect light, and a supported portion disposed on a rear surface and having three supported surfaces arranged with rotational symmetry of 120 degrees around an optical axis, the rear surface being a surface of the reflecting mirror existing on the contrary side to the reflecting surface; a structural member provided on a rear side of reflecting mirror; and three supporting members, each of the three supporting members including a mirror supporting portion connected to and supporting each of the three supported surfaces, and having two ends connected to the structural member.

An optical device can deal with a relative difference in thermal expansion coefficient between a reflecting mirror and a mirror supporting member, and can also support the reflecting mirror with a simpler structure than the conventional one. The optical device includes: a reflecting mirror including a reflecting surface to reflect light, and a supported portion disposed on a rear surface and having three supported surfaces arranged with rotational symmetry of 120 degrees around an optical axis, the rear surface being a surface of the reflecting mirror existing on the contrary side to the reflecting surface; a structural member provided on a rear side of reflecting mirror; and three supporting members, each of the three supporting members including a mirror supporting portion connected to and supporting each of the three supported surfaces, and having two ends connected to the structural member.