Ares I-X Crew Module and Launch Abort System (CM/LAS)
-
Upload
celeste-aguirre -
Category
Documents
-
view
22 -
download
0
description
Transcript of Ares I-X Crew Module and Launch Abort System (CM/LAS)
January 22, 2009January 22, 2009
www.nasa.gov
Ares I-X Crew Module and
Launch Abort System (CM/LAS)
Ares I-X Crew Module and
Launch Abort System (CM/LAS)
Jonathan CruzDeputy Project Manager
Jonathan CruzDeputy Project Manager
2Ares I-X CMLAS CDR February 12-13, 2008 010 - Mission / Project Overview
Ares I-X Overview
Ares I-X is a Flight Test Vehicle being developed to provide flight control and performance data for the Ares I Crew Launch Vehicle (CLV) design process
Objectives of the test flight: Ascent performance First stage separation and recovery
Ares I-X will provide proof of flight control strategy for CLV and data to validate aerodynamic databases and engineering predictions across multiple discipline tools
J-2x EngineMass Model(not shown)
Interstage
Roll Control System (not shown)
Empty 5th Segment
Crew Module (CM) / Launch Abort System
(LAS) Simulator
4-SegmentMotor
UpperStage
Simulator (USS)
FirstStage
(FS)
Frustum
Primary Avionics and Developmental Flight Instrumentation(not shown)
First Stage Avionics(not shown)
Ballast(not shown)
Forward Skirts
BoosterSeparation
Motors(not shown)
3January 22, 2009
4Ares I-X CMLAS CDR February 12-13, 2008 010 - Mission / Project Overview
Separation +270 secsChute deployment begins
Booster, Parachutes and
Recovery
USS / CM / LASUncontrolled descent
and impact
Separation +15 secsFrustum / Interstageseparation
Pitch over
Launch
Thrust < 40K lb-force, FS separation begins
Flight Profile
Maximum Altitude: 200,000 ft
Peak Velocity: Mach 6.1
5January 22, 2009
Ares I-X CM / LAS Overview
Purpose: Provide the Crew Module (CM) and Launch Abort System (LAS) mass simulator hardware for the Ares I-X mission
Primary requirements are to match the specified outer mold line and mass properties
Primary hardware interfaces: Upper Stage Simulator Avionics Developmental Flight
Instrumentation (DFI)
Deliverables: CM & LAS flight test hardware
with installed DFI CM & LAS Handling Ground
Support Equipment Documentation
53’ Long16’ Diameter
16,000 lb
6January 22, 2009
Instrumentation in CM/LAS
270°
Pressure Transducer
Thermocouple
Accelerometer
Air Vane
Calorimeter
0°
Total Air Temperature
5-Hole Probe
7January 22, 2009
CM—LAS Test Stacking