Variable Switching System for Heat Protection and Dissipation of Ultra-LEO Satellites Based on LHP Coupled with TEC DOI Creative Commons
Jin Huang, L. C. Chang,

Baiyang Dong

et al.

Aerospace, Journal Year: 2024, Volume and Issue: 11(7), P. 539 - 539

Published: July 1, 2024

Ultra-low Earth orbit (LEO) satellites are widely used in the military, remote sensing, scientific research, and other fields. The ultra-LEO satellite faces harsh aerothermal environment, complex variable attitude task requires radiator of to not only meet heat dissipation requirements load but also resist flux. In this study, flux 160–110 km was calculated, loop pipe (LHP) coupled with a thermo-electric cooler (TEC) multi-layer insulation (MLI) were applied determine switching fast response protection. An simulation test platform built. After assessment test, even when head temperature as high 350 °C side 160 °C, internal source could be controlled within 22.5 through efficient work thermal switch system. study confirms accuracy feasibility system, which provides an important reference for subsequent actual on-orbit mission.

Language: Английский

A review on automated plant disease detection: motivation, limitations, challenges, and recent advancements for future research DOI Creative Commons
Sajid Ullah Khan, Anas Alsuhaibani, Abdulrahman Alabduljabbar

et al.

Journal of King Saud University - Computer and Information Sciences, Journal Year: 2025, Volume and Issue: 37(3)

Published: May 9, 2025

Language: Английский

Citations

0
Variable Switching System for Heat Protection and Dissipation of Ultra-LEO Satellites Based on LHP Coupled with TEC DOI Creative Commons
Jin Huang, L. C. Chang,

Baiyang Dong

et al.

Aerospace, Journal Year: 2024, Volume and Issue: 11(7), P. 539 - 539

Published: July 1, 2024

Ultra-low Earth orbit (LEO) satellites are widely used in the military, remote sensing, scientific research, and other fields. The ultra-LEO satellite faces harsh aerothermal environment, complex variable attitude task requires radiator of to not only meet heat dissipation requirements load but also resist flux. In this study, flux 160–110 km was calculated, loop pipe (LHP) coupled with a thermo-electric cooler (TEC) multi-layer insulation (MLI) were applied determine switching fast response protection. An simulation test platform built. After assessment test, even when head temperature as high 350 °C side 160 °C, internal source could be controlled within 22.5 through efficient work thermal switch system. study confirms accuracy feasibility system, which provides an important reference for subsequent actual on-orbit mission.

Language: Английский

Citations

2