A Multipurpose Hardened Spacecraft Multilayer Insulation (MLI) system was developed and implemented to meet diverse survivability and performance requirements. Within the definition and confines of a MLI assembly (blanket), the design: (1) provides environmental protection from natural and induced nuclear, thermal, and electromagnetic radiation; (2) provides adequate electrostatic discharge protection for a geosynchronous satellite; (3) provides adequate shielding to meet radiated emission needs; and (4) will survive ascent differential pressure loads between enclosed volume and space. The MLI design is described which meets these requirements and design evolution and verification is discussed. The application is for MLI blankets which closeout the area between the laser crosslink subsystem (LCS) equipment and the DSP spacecraft cabin. Ancillary needs were implemented to ease installation at launch facility and to survive ascent acoustic and vibration loads. Directional venting accommodations were also incorporated to avoid contamination of LCS telescope, spacecraft sensors, and second surface mirrors (SSMs).
Multipurpose Hardened Spacecraft Insulation
1990
27 pages
Report
Keine Angabe
Englisch
Miscellaneous Materials , Unmanned Spacecraft , Multilayer insulation , Pressure distribution , Spacecraft configurations , Spacecraft contamination , Spacecraft design , Thermal insulation , Differential pressure , Electromagnetic radiation , Environment protection , Hardening (Systems) , Nuclear radiation , Radiation shielding , Space environment simulation , Spacecraft survivability , Thermal radiation , Vibration effects
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