1 / 2

C-C/Heat-Pipe-Cooled Leading Edges for Space Shuttle Orbiter

Benefits and Impacts Obsolescence Reduction Risk Reduction Safety Improvement Cost Reduction Process Improvement Other Operations Improvement Performance Enhancement • Significant improvement in impact resistance and damage tolerance.

constance-little
Download Presentation

C-C/Heat-Pipe-Cooled Leading Edges for Space Shuttle Orbiter

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. Benefits and Impacts Obsolescence Reduction Risk Reduction Safety Improvement Cost Reduction Process Improvement Other Operations Improvement Performance Enhancement • Significant improvement in impact resistance and damage tolerance. • Significant increase in structural and thermal margins. • Reduction in Category 1 Failure Rate of 10% Area(s) of Significant Benefit Safety Performance Sustainability Operations Infrastructure C-C/Heat-Pipe-Cooled Leading Edges for Space Shuttle Orbiter • Description • • A Carbon-Carbon Heat-Pipe-Cooled Leading Edge will be designed, analyzed, fabricated, and tested for the Space Shuttle Orbiter. The concept uses refractory-metal/liquid- metal heat pipes embedded inside C-C. • Molybdenum-Rhenium/Lithium heat pipes embedded within a 3-D woven refractory-composite material such as Carbon- Carbon or C/SiC. • • Heat pipes cool the stagnation region by transporting heat to the upper and lower surfaces where it is rejected by radiation. • The design is passive, redundant and fail safe in the event of multiple heat-pipe failures. It significantly increases the margin and performance of the leading edge and enables additional high energy TAL options and trajectory modifications to minimize heating to acreage areas in the event of off nominal tile damage. • Technologies and Capabilities • LaRC has 30 years experience developing heat-pipe-cooled leading edges for Space Transportation Systems. • LaRC successfully tested (Hypersonic wind tunnel and radiant lamp testing) an all metallic heat-pipe leading edge for the Orbiter in the 70’s which reduced maximum temperatures from 2800 deg. F to 1800 deg. F. • Design, analysis, and test experience for leading edges resides at LaRC and JSC. The proposed effort would involve both centers. • Components of a C-C/heat-pipe-cooled leading edge have already been fabricated and successfully tested to heating rates over six times that expected for the Shuttle Orbiter application. • Use of radiant heat lamp facilities and arc jets at JSC and radiant lamps and the 8’ High Temperature Tunnel at LaRC will be used to verify predicted performance & certify readiness for flight test. • POC, Cost, Schedule and Maturity • POC: Charles J. Camarda (JSC - 281-244-8691) • Maturity: Components and elements have been successfully fabricated and tested to verify performance. Estimated TRL 3-4. • Cost: Total of $10M over 4 years to develop. $200M to outfit 10 panels on each wing of all three vehicles plus spares.

  2. C-C/Heat-Pipe-Cooled Leading Edges for Space Shuttle Orbiter • Total Project Costs: $ 210 M ($200 M Implementation) • Design Studies/Trades: $ 0.5 M • Manufacturing Development: $ 2.5 M • Fabrication and Test: $ 5 M • Project Submitted By: Charles J. Camarda NASA JSC, (281) 244-8691

More Related