SPACE STORABLE PROPELLANT MODULE THERMAL CONTROL TECHNOLOGY SUMMARY REPORT VOLUME I OF2/B2 H6 PROPULSION MODULE

摘要

Since the thermal control design requirements are not critical, the propulsion module configuration is dictated by the propulsion and structural subsystems.nA single tank for each propellant provides a design with the best arrangement for thermal control as well as the most reliable propellant supply system. This configu¬ration is, however, heavier than a two-tank arrangement due to increased stage length, but the penalty is less than 1%. The single-tank arrangement also causes the module center of gravity to be shifted laterally approximately seven inches from the spacecraft centerline which is easily compensated for by the proper gimbal angle.nThe design provides the most efficient structural configuration in utilizing a space truss system with a propellant tank support platform. This configuration is also best for thermal control because the fluid tanks have a clear view of space and the RTG. Installation of the spacecraft's electronics package on top (rather than the side) of the module also allows the module an unobstructed view of space.nThe type of tank material is unconstrained by thermal control. The use of non-metallic struts to stabilize the top of the propellant tank is an advantage for structural design (less weight) and for thermal control (heat transfer from the spacecraft to the propulsion module is substantially reduced). A bottom support frame constructed of metal members and an aluminum beam supporting the helium tank is recommended to thermally connect the helium and propellant tanks. The pin joint design at the bottom of the tank is unconstrained by thermal requirements.