# Presentation: 676817

## Debris Environment Overview

**SPACE SHUTTLE PROGRAM**
**Space Shuttle Systems Engineering and Integration Office**
**NASA Johnson Space Center, Houston, Texas**

**Debris Environment Overview**
**September 16, 2003**

**John Muratore**
**Chief, Systems Engineering and Integration Office**
**Space Shuttle Program**

## Debris Approach

**Debris is an environment generated by the shuttle as it flies and the shuttle must be engineered to successfully fly through that environment**
**Our approach to the debris environment has four levels**
**First - Eliminate sources of debris by design **
**Second -Understand the transport mechanism for any remaining debris that is generated**
**Third -Understand the impact tolerance for any debris that can be generated and can reach the shuttle**
**Fourth – Contingency plans**

## RTF actions map into our strategy

**First - Eliminate sources of debris by design **
**ET Bipod redesign, ET TPS revalidation, SRB Bolt Catcher Redesign**
**Non destructive Evaluation (NDE) of TPS **
**Inflight video and photographic coverage **
**Second - Understand the transport mechanism for any remaining debris that is generated**
**Tests of debris generation **
**Modeling of debris transport**
**Inflight video and photographic coverage **
**Third - Understand the impact tolerance for any debris that can still be generated and can reach the shuttle**
**Coupon and full impact tests as well as analytical models**
**NDE of RCC to verify the effect of age on strength **
**TPS hardening **
**Fourth, Contingency Plans**
**On orbit inspection and repair capability**
**Contingency Shuttle Crew Support (CSCS)**

## Debris Strategy

**Eliminate Debris Generation**

**Eliminate Debris By Transport Mechanism**

**Eliminate Debris by Impact Tolerance**

**Contingency Plans**

## External Tank

**External Tank**

***The application of TPS materials includes computer controlled******automatic spray cells and manual application***

***Intertank Acreage (Machined/Vented)***
***NCFI 24-124***

***LO2 Tank Ogive / Barrel***
***NCFI 24-124***

***LO2 PAL Ramp***
***BX-250***

***LO2 Tank to Intertank Flange Closeout***
***BX-250***

***LO2 Feedline***
***BX-250 with PDL-1034 closeouts***

***Bipod Struts***
***MA 25s***

***LH2 PAL Ramp***
***BX-250 and BX-265***

***LH2 Tank Dome***
***NCFI 24-57***
***Apex Closeout***
***BX-250***
***SLA 561***

***Aft Struts***
***BX-250 or BX-265***

***LO2 Ice/ Frost Ramps***
***PDL-1034***
***SLA 561***

***Bipod Closeouts***
***BX-250***
***SLA 561***

***LH2 Ice/Frost Ramps***
***PDL-1034***

***LO2 Cable Trays & Fairings***
***SLA 561***

***LH2 Tank Barrel***
***NCFI 24-124***

***Nose Cone (internal)***
***MA 25s***
***PDL 1034***

***Aft Interfaces / Cable Tray Covers/Fairings***
***BX-250 with PDL closeouts***
***SLA 561***

***Nose Cone***
***Graphite / Phenolic***

***LO2 Feedline Fairing***
***SLA 561***

***Composite GH2 Pressline Fairing***

***LH2 Tank to Intertank Flange Closeout***
***BX-250 and BX-265***

***Third Hardpoint******(planned for KSC)***
***BX-265***

## Picture of ET Flange Foam Transport Cases

- Example of ET Flange Foam Debris Transport Analysis, Mach 3.5

## Impact Kinetic Energy

| Weight (lbs) | Velocity (fps) | Energy (ft-lbf) |
| --- | --- | --- |
|  |  |  |
|  |  |  |
| 1.5 | 777 | 14,062 |
|  |  |  |
| .2 | 777 | 1874 |
| .1 | 1000 | 1552 |
| .1 | 700 | 760 |
| .02 | 1000 | 310 |

## Purposes of Inflight Imagery

**Verify Design Changes to Eliminate Debris**
**Understand transport mechanisms of any remaining debris**
**Observe integrated performance to find unknown phenomena**