Abstract: With the development of aerospace technology，the functional integration of spacecraft has been improved，and the complexity of research and development has increasingly high requirements for system heat dissipation.As a two-phase high-efficiency heat transfer component，loop heat pipes（LHPs）have the characteristics of long distance，anti-gravity，and flexible layout，which are often used for directional heat transfer under a single heat source.For complex environments with multiple heat sources，LHP systems have poor stability，which are generally difficult to adapt to.A strong coupling heat management system for LHPs based on brazing technology is designed to meet the heat dissipation requirements of dispersed heat sources under complex spatial heat flux.Sensitivity analysis of key coupling parameters is conducted，and relevant experiments are conducted to verify the feasibility of key technologies such as low thermal resistance and strong coupling at the interface.The platform's heat dissipation capacity is improved by 52%.LHPs，having been applied to payload module of the Land Exploration Satellite-4（LEX-4），which is the first large-scale application in the platform system in the world，improve heat dissipation capacity of the payload module from 4kW to 6kW，providing an on-orbit temperature environment of 0 - 20℃ for the high-power solid-state amplifier.LHP breaks through the restriction of platform application，which provides reference for the design of thermal coupling systems for LHP in the future.

Key words: loop heat pipe, spacecraft, thermal coupling, heat exchange, thermal management, brazing