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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 379 records · Page 21

Semitransparent Sb 2 S 3 thin film solar cells by ultrasonic spray pyrolysis for use in solar windows

The integration of photovoltaic (PV) solar energy in zero-energy buildings requires durable and efficient solar windows composed of lightweight and semitransparent thin film solar cells. Inorganic materials with a high optical absorption coefficient, such as Sb 2 S 3 (>10 5 cm -1 at 450 nm), offer semitransparency, appreciable efficiency, and long-term durability at low cost. Oxide-free throughout the Sb 2 S 3 layer thickness, as confirmed by combined studies of energy dispersive X-ray spectroscopy and synchrotron soft X-ray emission spectroscopy, semitransparent Sb 2 S 3 thin films can be rapidly grown in air by the area-scalable ultrasonic spray pyrolysis method. Integrated into a ITO/TiO 2 /Sb 2 S 3 /P3HT/Au solar cell, a power conversion efficiency (PCE) of 5.5% at air mass 1.5 global (AM1.5G) is achieved, which is a record among spray-deposited Sb 2 S 3 solar cells. An average visible transparency (AVT) of 26% of the back-contact-less ITO/TiO 2 /Sb 2 S 3 solar cell stack in the wavelength range of 380–740 nm is attained by tuning the Sb 2 S 3 absorber thickness to 100 nm. In scale-up from mm 2 to cm 2 areas, the Sb 2 S 3 hybrid solar cells show a decrease in efficiency of only 3.2% for an 88 mm 2 Sb 2 S 3 solar cell, which retains 70% relative efficiency after one year of non-encapsulated storage. A cell with a PCE of 3.9% at 1 sun shows a PCE of 7.4% at 0.1 sun, attesting to the applicability of these solar cells for light harvesting under cloud cover.

36 MATERIALS SCIENCE↗

Orbital Launch Operations: Escape Window Analysis

The analysis of the gross aspects of the flight mechanics for lunar trajectories from orbital launch is presented. An attempt is made to define the launch requirements from an earth orbit, the geometrical relationships existing between an Orbital Launch Facility in earth orbit and the moon in its orbit, the departure trajectory sensitivity to energy and time requirements, the launch-on-time problem and the orbital "escape window".

ESCAPE↗

A VARIATIONAL LAUNCH WINDOW STUDY

Obtention of a launch window, as a function of allowable performance loss, for placing a saturn v in a circular orbit in a prespecified space-fixed plane

ORBITAL MECHANICS↗

LAUNCH WINDOWS FOR HIGHLY ECCENTRIC ORBITS

Orbital elements necessary for minimum lifetime of a satellite with highly eccentric orbit are graphically specified by construction of a launch window map

LAUNCH WINDOW↗

A Method of Implementing Cutoff Conditions for Saturn V Lunar Missions Out of Earth Parking Orbit Assuming a Continuous Ground Launch Window

A method of implementing Saturn V lunar missions from an earth parking orbit is presented. The ground launch window is assumed continuous over a four and one-half hour period. The iterative guidance scheme combined with a set of auxiliary equations that define suitable S-IVB cutoff conditions, is the approach taken. The four inputs to the equations that define cutoff conditions are represented as simple third-degree polynomials as a function of ignition time. Errors at lunar arrival caused by the separate and combined effects of the guidance equations, cutoff conditions, hypersurface errors, and input representations are shown. Vehicle performance variations and parking orbit injection errors are included as perturbations. Appendix I explains how aim vectors were computed for the cutoff equations. Appendix II presents all guidance equations and related implementation procedures. Appendix III gives the derivation of the auxiliary cutoff equations. No error at lunar arrival was large enough to require a midcourse correction greater than one meter per second assuming a transfer time of three days and the midcourse correction occurs five hours after injection. Since this result is insignificant when compared to expected hardware errors, the implementation procedures presented are adequate to define cutoff conditions for Saturn V lunar missions.

PARKING ORBIT↗

EGO Launch Window Study

Computer programs for determining EGO launch window to satisfy spacecraft imposed restraints

EGO↗