Generalized Vehicle Performance Closure Model For Two-Stage-To-Orbit Launch Vehicles
Min Qu, Peter Gage, Jared Sohn, John Bradford, Brett Starr
January 8, 2004
Abstract
A generalized, fully integrated multidisciplinary performance closure model for analyzing and designing Two-Stage-To-Orbit (TSTO) Launch Vehicles is presented. The model is developed under NASA’s Advanced Engineering Environment (AEE) to allow NASA to perform independent assessments of the emerging architectures and technologies. It covers a large set of architecture concepts such as reusable, expendable, series burn, parallel burn, cross feed, no cross feed, single booster, multiple boosters and common boosters. The model accommodates a broad range of different design assumptions and mission objectives. The analysis disciplines integrated in the model include weights, sizing, CAD based parametric geometry, rocket propulsion, ascent trajectory, highspeed aerodynamics, and structure. Different types of analysis tools running on different platforms are integrated together using Phoenix Integration’s ModelCenter and Analysis Server framework, and the entire closure process can be run in a fully automated fashion.
Introduction
NASA's Advanced Engineering Environment1 (AEE) project is developing a distributed, collaborative engineering environment for designing and analyzing the next generation launch systems under the Integrated System Engineering and Analysis office at Marshall Space Flight Center. The environment provides several important benefits:
- Convenient linking of data between distributed disciplinary analysis tools
- Controlled access for team members across NASA and contractor sites
- Persistent storage of complete analysis details
The three core components of the AEE framework are a customized PTC Windchill2,7 Product Data Management (PDM) system, a set of launch vehicle analysis models integrated in Phoenix Integration’s ModelCenter©3, and an XML-based launch vehicle language4 (LVL). The PDM provides web-accessible database for analysis data storage and process control. ModelCenter provides an integration framework that allows analysis tools to be integrated together in a "model" and run in distributed and automated fashion. The LVL provides a common interface for data transfer between different analysis components.
AEE is supporting NASA’s Next Generation Launch Technologies (NGLT) program to develop architecture and technology roadmaps for the next generation of launch systems. In the area of analysis tool integration, AEE has been developing a series of distributed analysis capabilities for performing independent assessments on architectures and technologies. Available tools include performance analyses such as launch vehicle ascent performance, payload stage sizing, fly-back trajectory, entry/aborts trajectory, and landing trajectory, as well as life cycle analyses such as cost, operations, safety and reliability. One of the most challenging tasks of these developments is to build a generalized, fully integrated, multidisciplinary vehicle performance closure model that can be used for designing the next generation Two-Stage-To-Orbit (TSTO) Launch.
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