This paper describes the modification of a three-electron-beam (EB) gun system for vacuum depositing a highly reflective aluminum coating on a 7.01-m (23-ft) -diam nickel-plated aluminum collimating mirror. The mirror is part of the JPL 7.62-m space simulator that was recently modernized with a new high vacuum pumping system, solar lamp power supplies, solar optic lens system, and refurbished collimating mirror. The 7.01-m 12,700-kg (14-ton) spherical collimating mirror was removed from this facility for replating with 381 micron (0.015 in.) of electroless nickel and polished to a specular finish for realuminizing. The space chamber served as the vacuum coating vessel for the realuminizing coating process. The mirror is the primary reflecto...
A 400 kilowatt argon arc lamp for a solar simulator has been designed, operated, and evaluated. The ...
This paper will describe efforts at developing broadband mirror coatings with high performance that ...
Optical characteristics of vapor deposited coating systems for thermal control of spacecraft structu...
Optical, structural, and thermal design criteria and fabrication techniques for collimating mirror i...
A fabrication technique was successfully developed for a metallic aluminum honeycomb, high-accuracy,...
By improving several important components of the well known off-axis solar simulator system, a consi...
A solar simulator utilizing nine 30-kW xenon arc lamps was built to provide radiant power for testin...
This presentation discusses the goal of this project which was to demonstrate that it is possible to...
An existing space simulation test facility was modified by enlarging the solar simulator. Because of...
This simulator is unique in that it is capable of producing intensities up to 16.0 solar constants (...
The JPL 7.62-m space simulator was modified to simulate the solar intensities at the planet Mercury....
Optical properties and stability of vacuum deposited silver and dielectric film coating
A radiation effects experimental program was performed, in which second surface mirror type thermal ...
The design and development of two solar radiation simulators with an intensity variation ranging fro...
Solar simulator mirrors were refurbished. Two different refurbishment methods were employed. In the ...
A 400 kilowatt argon arc lamp for a solar simulator has been designed, operated, and evaluated. The ...
This paper will describe efforts at developing broadband mirror coatings with high performance that ...
Optical characteristics of vapor deposited coating systems for thermal control of spacecraft structu...
Optical, structural, and thermal design criteria and fabrication techniques for collimating mirror i...
A fabrication technique was successfully developed for a metallic aluminum honeycomb, high-accuracy,...
By improving several important components of the well known off-axis solar simulator system, a consi...
A solar simulator utilizing nine 30-kW xenon arc lamps was built to provide radiant power for testin...
This presentation discusses the goal of this project which was to demonstrate that it is possible to...
An existing space simulation test facility was modified by enlarging the solar simulator. Because of...
This simulator is unique in that it is capable of producing intensities up to 16.0 solar constants (...
The JPL 7.62-m space simulator was modified to simulate the solar intensities at the planet Mercury....
Optical properties and stability of vacuum deposited silver and dielectric film coating
A radiation effects experimental program was performed, in which second surface mirror type thermal ...
The design and development of two solar radiation simulators with an intensity variation ranging fro...
Solar simulator mirrors were refurbished. Two different refurbishment methods were employed. In the ...
A 400 kilowatt argon arc lamp for a solar simulator has been designed, operated, and evaluated. The ...
This paper will describe efforts at developing broadband mirror coatings with high performance that ...
Optical characteristics of vapor deposited coating systems for thermal control of spacecraft structu...