A Thermally-Integrated Spacecraft Design Approach Using Nuclear Dynamic Power Systems | Zendy

B. Raab | Zendy

AI Assistant Blog Pricing

Home ZAIA Blog

Open Access

A Thermally-Integrated Spacecraft Design Approach Using Nuclear Dynamic Power Systems

Author(s) -

B. Raab

Publication year - 1978

Publication title -

osti oai (u.s. department of energy office of scientific and technical information)

Language(s) - English

Resource type - Reports

DOI - 10.2172/1033400

Subject(s) - spacecraft , brayton cycle , eclipse , organic rankine cycle , spacecraft design , degree rankine , power (physics) , electric power system , aerospace engineering , environmental science , dissipation , electricity generation , automotive engineering , computer science , engineering , physics , process engineering , quantum mechanics , turbine , astronomy , thermodynamics

The use of dynamic-cycle heat engines for space electric power systems makes it possible to design a spacecraft which is thermally integrated with the power system. The power system fluid loop is used to cool the spacecraft equipment and structure. This results in a spacecraft which is extremely insensitive to changes in sun-angle, eclipse periods, or power dissipation. Resultant temperature variations of equipment is seen to be a few degrees in the worst-case orbits, without the need for active thermal control. Organic Rankine and Brayton cycle generators are considered. Cycle power losses of less than one-percent are experienced in implementing this concept

The content you want is available to Zendy users.

Already have an account? Click here to sign in.

Having issues? You can contact us here

Accelerating Research