Integrated System Test Approaches for the NASA Ares I Crew Launch Vehicle
- Paper number
IAC-07-D2.6.04
- Author
Mr. Charles Cockrell, National Aeronautics and Space Administration (NASA)/Langley Research Center, United States
- Year
2007
- Abstract
The U.S. National Aeronautics and Space Administration (NASA) is developing the Ares I Crew Launch Vehicle (CLV). The Ares I will deliver the Orion Crew Exploration Vehicle (CEV) to the International Space Station (ISS) and later to low Earth orbit (LEO) to rendezvous with additional components for lunar exploration missions delivered by the Ares V Cargo Launch Vehicle (CaLV). The Ares I launch vehicle consists of a five-segment solid rocket booster (FSB), derived from the Space Shuttle solid rocket booster (SRB), and an upper stage, powered by a single J-2 liquid-fueled engine. The CEV, including the crew module, service module, and launch abort system (LAS), is integrated with the FSB and upper stage to form the complete launch vehicle stack. The Ares I project has a baseline set of system requirements and is proceeding with preliminary design, analysis, test, and evaluation. The paper will discuss major elements of the Ares I integrated test program, including development, qualification, and acceptance test approaches. Development testing is conducted in the earlier phases of the project and is used to mature requirements, reduce risk, and to define qualification test procedures. Qualification testing will be conducted as the design matures to show that flight or flight-type hardware meets functional, performance, or design requirements with sufficient margin for human rating. Acceptance testing will be conducted prior to delivery to the launch site to show that the hardware meets design requirements under conditions specified for the mission. Major test programs as part of the design, development, and qualification phases, which will be discussed in the paper, include: • Structural loads and dynamics testing, including an integrated full scale ground vibration test to characterize the vehicle dynamic response, and partially verify input parameters for the flight control system (FCS). • Integrated propulsion test articles, including the main propulsion test article (MPTA), designed to qualify the J-2 engines and elements of the main propulsion system for flight certification. • Pathfinder test articles designed to characterize ground processing, including stacking, assembly, interface testing, and cryogenic fuel handling requirements at the launch site. • Developmental and operational flight testing to demonstrate the readiness of the Ares I launch vehicle for human flight. Operational flight tests are intended to validate the final design and operational configurations of the launch vehicle and launch site. • Aerodynamics and aeroelasticity testing to characterize ground winds, buffet response, and aerodynamic performance during ascent and FSB re-entry.
- Abstract document
- Manuscript document
IAC-07-D2.6.04.pdf (🔒 authorized access only).
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