Abstract: A method for shaping an optical element includes heating a first surface of an optical element, and allowing the first surface of the optical element to cool, thereby causing residual stress in the first surface which deforms the optical element to a predetermined shape. Heating can include applying a laser to the first surface.

Abstract: A method of forming an optical component includes depositing slurry that includes glass powder material onto a facesheet and fusing the glass powder material to a facesheet to form a first core material layer on the facesheet. The method also includes successively fusing glass powder material in a plurality of additional core material layers to build a core material structure on the facesheet. The method can include selectively depositing slurry including glass powder material over only a portion of at least one of the facesheet, the first core material layer, and/or the one of the additional core material layers. Depositing the slurry can include extruding the slurry from an extruder.

Abstract: A method includes placing a first part proximate a second part, disposing a sintering material in contact with both the first part and the second part, and applying energy to the sintering material to join the first part and the second part. An apparatus includes a first part, a second part, and an additively manufactured joint comprising a sintering material that joins the first part and the second part.

Abstract: A method includes placing a first part proximate a second part, disposing a sintering material in contact with both the first part and the second part, and applying energy to the sintering material to join the first part and the second part. An apparatus includes a first part, a second part, and an additively manufactured joint comprising a sintering material that joins the first part and the second part.

Abstract: A method includes applying a laser directly to a surface of a glass substrate to smooth the surface of the glass substrate. The method can further include applying a reflective coating directly to the smoothed surface of the glass substrate. An apparatus can include a titania-silica glass substrate having a laser polished surface that is not a separate layer from the glass substrate. The apparatus can include a reflective surface applied directly to the laser polished surface.

Abstract: A method of forming an optical component includes fusing glass powder material to a facesheet to form a first core material layer on the facesheet. The method also includes successively fusing glass powder material in a plurality of additional core material layers to build a core material structure on the facesheet. The method can include positioning the facesheet on a mandrel prior to fusing glass powder material to the facesheet. Fusing glass powder material to the facesheet can include fusing the glass powder material to a polishable surface of the facesheet.

Abstract: A method of forming an optical component includes depositing slurry that includes glass powder material onto a facesheet and fusing the glass powder material to a facesheet to form a first core material layer on the facesheet. The method also includes successively fusing glass powder material in a plurality of additional core material layers to build a core material structure on the facesheet. The method can include selectively depositing slurry including glass powder material over only a portion of at least one of the facesheet, the first core material layer, and/or the one of the additional core material layers. Depositing the slurry can include extruding the slurry from an extruder.

Abstract: A telescope, mirror assembly and method of forming an aspheric mirror is disclosed. The telescope includes the mirror assembly which has a substantially spherical surface contour in a relaxed state. A plurality of actuators distributed substantially along an outer edge of the mirror is configured to apply a load to the mirror assembly to deform the mirror to obtain a substantially aspheric surface contour.

Abstract: A telescope, mirror assembly and method of forming an aspheric mirror is disclosed. The telescope includes the mirror assembly which has a substantially spherical surface contour in a relaxed state. A plurality of actuators distributed substantially along an outer edge of the mirror is configured to apply a load to the mirror assembly to deform the mirror to obtain a substantially aspheric surface contour.

Abstract: A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10). One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom ( 11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) is disclosed. One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) is disclosed. One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.