Abstract

AbstractThe effects of electron irradiation on the performance of GaAs solar cells with a range of architectures is studied. Solar cells with shallow and deep junction designs processed on the native wafer as well as into a thin‐film were irradiated by 1‐MeV electrons with fluence up to 1×1015 e−/cm2. The degradation of the cell performance due to irradiation was studied experimentally and theoretically using model simulations, and a coherent set of minority carriers' lifetime damage constants was derived. The solar cell performance degradation primarily depends on the junction depth and the thickness of the active layers, whereas the material damage shows to be insensitive to the cell architecture and fabrication steps. The modeling study has pointed out that besides the reduction of carriers lifetime, the electron irradiation strongly affects the quality of hetero‐interfaces, an effect scarcely addressed in the literature. It is demonstrated that linear increase with the electron fluence of the surface recombination velocity at the front and rear hetero‐interfaces of the solar cell accurately describes the degradation of the spectral response and of the dark current characteristic upon irradiation. A shallow junction solar cell processed into a thin‐film device has the lowest sensitivity to electron radiation, showing an efficiency at the end of life equivalent to 82% of the beginning‐of‐life efficiency.

Highlights

  • A standard space solar cell array consists of triple junction III-V cells on Ge wafer

  • In order to deduce the important cell parameters, five different solar cells architectures were applied, and the environment the cells would face in Geostationary orbit missions (GEO) and low earth orbit (LEO) space missions was simulated by subjecting the devices to electron fluences up to 1 × 1015 e−/cm[2]

  • The GaAs minority carriers' lifetime damage constants reported in the literature, required for a proper prediction of the cells performance in space application, differ significantly

Read more

Summary

Introduction

A standard space solar cell array consists of triple junction III-V cells on Ge wafer These devices provide efficiencies well above 30%,1 but they are rigid devices with relatively large weight. These cells are generally mounted on stabilizing panels consisting of an aluminum honeycomb structure sandwiched by carbon fiber reinforced polymer (CFRP) sheets, and a Ce-doped protective cover glass is applied on top of the system. By removing the growth substrate completely, the resultant solar cells consist of lightweight and flexible thin-film devices These cells no longer require to be mounted on rigid panels for application, and when combined with new technologies for flexible front cover-glasses and mounting and deployment systems have the potential to reach specific mass of 0.6 kg/m2.2,5,6

Methods
Results
Conclusion
Full Text
Published version (Free)

Talk to us

Join us for a 30 min session where you can share your feedback and ask us any queries you have

Schedule a call