Space vehicle thermal rejection system

US4830097A · kind A · utility

Assignee

• The United States of America as represented by the Administrator of the National Aeronautics and Space Administration · US

Inventor

• Herbert J. Tanzer · Folsom, US

Key dates

• Filing date: Jul 15, 1987
• Grant date: May 16, 1989
• Expiry date: Jul 15, 2007

Classification

• Technology area (CPC B): Performing Operations; Transporting
• CPC primary: B64G1/506
• WIPO field: Transport
• WIPO sector: Mechanical engineering

Abstract

A space vehicle thermal heat rejection system 10 utilizing separate optimized heat pipe components for the functions of heat acquisition, heat transport, and heat rejection. A honeycomb panel heat pipe evaporator section 20 performs the function of heat acquisition, and forms a closed thermodynamic system with a dual channel heat pipe transport section 30, which performs the function of heat transport. A plurality of truss or channel core heat pipe rejection fins 41 form the condenser section 40, which performs the function of heat rejection. A common wall 32 separates the condenser section 40 from the transport section 30. Using the above heat pipe components and having efficient interfacing between them results in high performance factors for the overall system.